CLAIMBOUND / SOURCE-PUBLICATION EVIDENCE
Satellites
Every card identifies what it proves, what it does not prove, its exact quote, locator, source hash, and local rerun command.
1. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 9
Narrow public claim
1.1.1 This document serves as a companion to NPR 8715.6 and provides specific technical requirements for limiting orbital debris and methods to comply with the NASA requirements for limiting orbital debris generation.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 9- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
1.1.1 This document serves as a companion to NPR 8715.6 and provides specific technical requirements for limiting orbital debris and methods to comply with the NASA requirements for limiting orbital debris generation.
2. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 9
Narrow public claim
1.1.2 This standard is primarily designed to limit the creation of new orbital debris and, therefore, to limit the risk to other current and future space missions.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 9- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
1.1.2 This standard is primarily designed to limit the creation of new orbital debris and, therefore, to limit the risk to other current and future space missions.
3. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 10
Narrow public claim
1.2.6 NPR 7120.5 and NPR 8715.6 require the use of this document for development of Orbital Debris Assessments (ODA), Orbital Debris Assessment Reports (ODAR), and End of Mission Plans (EOMP).
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 10- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
1.2.6 NPR 7120.5 and NPR 8715.6 require the use of this document for development of Orbital Debris Assessments (ODA), Orbital Debris Assessment Reports (ODAR), and End of Mission Plans (EOMP).
4. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 13
Narrow public claim
A failure mode identified by failure mode and effects analyses or equivalent analyses, for which a quantitative failure probability is available and exceeds 0.000001 (1:1,000,000).
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 13- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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A failure mode identified by failure mode and effects analyses or equivalent analyses, for which a quantitative failure probability is available and exceeds 0.000001 (1:1,000,000).
5. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 14
Narrow public claim
As defined in the 2019 ODMSP, a constellation consisting of 100 or more operational spacecraft cumulative is considered a large constellation.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 14- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
As defined in the 2019 ODMSP, a constellation consisting of 100 or more operational spacecraft cumulative is considered a large constellation.
6. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 15
Narrow public claim
A medical condition received as a result of the falling debris which requires (or should have required) professional medical attention within 48 hours of the impact.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 15- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
A medical condition received as a result of the falling debris which requires (or should have required) professional medical attention within 48 hours of the impact.
7. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 16
Narrow public claim
NPR 8715.6 requires that each program or project conduct a formal assessment of the potential to generate orbital debris.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 16- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
NPR 8715.6 requires that each program or project conduct a formal assessment of the potential to generate orbital debris.
8. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 16
Narrow public claim
4.1.3 Section 4.2 of this standard requires that programs and projects use the orbital debris modeling tools provided (or agreed to) by the NASA ODPO in assessing orbital debris generation and risk in Earth orbit.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 16- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
4.1.3 Section 4.2 of this standard requires that programs and projects use the orbital debris modeling tools provided (or agreed to) by the NASA ODPO in assessing orbital debris generation and risk in Earth orbit.
9. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 22
Narrow public claim
Any non-compliance with the requirements for ODAR and EOMPs stated in this standard requires NASA management approval of a waiver per NPR 8715.6.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 22- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Any non-compliance with the requirements for ODAR and EOMPs stated in this standard requires NASA management approval of a waiver per NPR 8715.6.
10. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 22
Narrow public claim
4.3.1.2 The goal is that in all operational orbits, space systems are designed not to release debris during normal operations.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 22- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t01_primary_claims.json --source-file <local-raw-pdf>Exact source quote
4.3.1.2 The goal is that in all operational orbits, space systems are designed not to release debris during normal operations.
11. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 23
Narrow public claim
Requirement 4.3-1b: The total object-time product shall be less than 100 object-years per launch vehicle upper stage or per spacecraft.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 23- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Requirement 4.3-1b: The total object-time product shall be less than 100 object-years per launch vehicle upper stage or per spacecraft.
12. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 23
Narrow public claim
This requirement will have the greatest impact on programs and projects with perigee altitudes above 700 km, where objects may remain in orbit naturally for hundreds of years.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 23- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
This requirement will have the greatest impact on programs and projects with perigee altitudes above 700 km, where objects may remain in orbit naturally for hundreds of years.
13. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 24
Narrow public claim
In both cases the debris were left in orbits of less than 630 km and decayed from orbit well within the 25-year requirement.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 24- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
In both cases the debris were left in orbits of less than 630 km and decayed from orbit well within the 25-year requirement.
14. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 24
Narrow public claim
Therefore, Requirement 4.3-2 limits the accumulation of debris at GEO altitudes and will help mitigate the development of a significant debris environment, as currently exists in LEO.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 24- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Therefore, Requirement 4.3-2 limits the accumulation of debris at GEO altitudes and will help mitigate the development of a significant debris environment, as currently exists in LEO.
15. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 25
Narrow public claim
For debris released with significant ∆v (typically greater than 10 meters per second), the initial debris orbit may be significantly different from that of the object releasing the debris.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 25- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
For debris released with significant ∆v (typically greater than 10 meters per second), the initial debris orbit may be significantly different from that of the object releasing the debris.
16. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 25
Narrow public claim
“LEO dwell time” is defined as the total time spent by an orbiting object below an altitude of 2000 km during its orbital lifetime.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 25- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
“LEO dwell time” is defined as the total time spent by an orbiting object below an altitude of 2000 km during its orbital lifetime.
17. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 26
Narrow public claim
To ensure that the debris is compliant with Requirement 4.3-2, the spacecraft must be sufficiently above or below GEO at the time of debris release to assure that within 25 years, and for 100 years thereafter, the debris is outside of the GEO +/- 200 km and GEO +/- 15 band.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 26- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
To ensure that the debris is compliant with Requirement 4.3-2, the spacecraft must be sufficiently above or below GEO at the time of debris release to assure that within 25 years, and for 100 years thereafter, the debris is outside of the GEO +/- 200 km and GEO +/- 15 band.
18. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 26
Narrow public claim
The orbit propagator within DAS can determine the minimum altitude above GEO or the maximum altitude below GEO to ensure that the debris is not perturbed into GEO +/- 200 km and GEO +/- 15 within 100 years.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 26- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
The orbit propagator within DAS can determine the minimum altitude above GEO or the maximum altitude below GEO to ensure that the debris is not perturbed into GEO +/- 200 km and GEO +/- 15 within 100 years.
19. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 27
Narrow public claim
The limiting conditions of allowable apogee and perigee in constant solar flux conditions for a variety of area/mass ratios, under which requirement (4.3-1a) is met (25-year decay after EOM).
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 27- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
The limiting conditions of allowable apogee and perigee in constant solar flux conditions for a variety of area/mass ratios, under which requirement (4.3-1a) is met (25-year decay after EOM).
20. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 27
Narrow public claim
Geosynchronous Transfer Orbit (GTO) with perigees near LEO or at higher altitudes and with apogees near GEO, but must be consistent with requirement 4.6-2 or 4.6-3.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 27- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t02_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Geosynchronous Transfer Orbit (GTO) with perigees near LEO or at higher altitudes and with apogees near GEO, but must be consistent with requirement 4.6-2 or 4.6-3.
21. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 28
Narrow public claim
Debris can be left in an eccentric orbit traversing GEO, if orbital perturbations will cause the object to leave GEO within 25 years.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 28- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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Debris can be left in an eccentric orbit traversing GEO, if orbital perturbations will cause the object to leave GEO within 25 years.
22. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 28
Narrow public claim
The orbit propagator within DAS can be used to determine the long-term orbital perturbation effects for specific initial orbital conditions and, hence, to determine compliance with Requirement 4.3-2 by ensuring the debris will not reenter the GEO protection zone within 100 years.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 28- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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The orbit propagator within DAS can be used to determine the long-term orbital perturbation effects for specific initial orbital conditions and, hence, to determine compliance with Requirement 4.3-2 by ensuring the debris will not reenter the GEO protection zone within 100 years.
23. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 29
Narrow public claim
4.4.1.2 In order to limit the risk to other space systems from accidental breakups after the completion of mission operations, all onboard sources of stored energy of a space system, such as residual propellants, batteries, high-pressure vessels, self-destructive devices, flywheels, and momentum wheels are depleted or safed when they are no longer required for mission operations or postmission disposal.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 29- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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4.4.1.2 In order to limit the risk to other space systems from accidental breakups after the completion of mission operations, all onboard sources of stored energy of a space system, such as residual propellants, batteries, high-pressure vessels, self-destructive devices, flywheels, and momentum wheels are depleted or safed when they are no longer required for mission operations or postmission disposal.
24. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 29
Narrow public claim
The explosion of a 2-year-old Pegasus orbital stage in 1996 produced the greatest number of cataloged fragmentation debris to that date and was probably caused by the failure of a pressure regulation valve connecting a high pressure nitrogen supply with a lower pressure propellant tank.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 29- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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The explosion of a 2-year-old Pegasus orbital stage in 1996 produced the greatest number of cataloged fragmentation debris to that date and was probably caused by the failure of a pressure regulation valve connecting a high pressure nitrogen supply with a lower pressure propellant tank.
25. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 31
Narrow public claim
4.4.2.2.2 Requirement 4.4-3: Limiting the long-term risk to other space systems from planned breakups for Earth and lunar missions: Planned explosions or intentional collisions shall: a.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 31- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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4.4.2.2.2 Requirement 4.4-3: Limiting the long-term risk to other space systems from planned breakups for Earth and lunar missions: Planned explosions or intentional collisions shall: a.
26. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 31
Narrow public claim
Be conducted at an altitude such that for orbital debris fragments larger than 10 cm the object-time product is less than 100 object-years.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 31- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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Be conducted at an altitude such that for orbital debris fragments larger than 10 cm the object-time product is less than 100 object-years.
27. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 34
Narrow public claim
For example, an orbital stage main propulsion system depletion burn may be scheduled 15 minutes after separation of the payload, followed by a sequenced venting of the propellant and pressurant tanks thereafter.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 34- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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For example, an orbital stage main propulsion system depletion burn may be scheduled 15 minutes after separation of the payload, followed by a sequenced venting of the propellant and pressurant tanks thereafter.
28. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 34
Narrow public claim
Requirement 4.4-3 for long-term planning conducted during program development and uses Requirement 4.4-4 for near-term planning conducted shortly before the test.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 34- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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Requirement 4.4-3 for long-term planning conducted during program development and uses Requirement 4.4-4 for near-term planning conducted shortly before the test.
29. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 35
Narrow public claim
DAS may be used to approximate the object-time product for objects > 10 cm and the count of > 1 mm objects with lifetime > 1 year.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 35- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t03_primary_claims.json --source-file <local-raw-pdf>Exact source quote
DAS may be used to approximate the object-time product for objects > 10 cm and the count of > 1 mm objects with lifetime > 1 year.
30. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 35
Narrow public claim
Space Force, to verify that immediately after the breakup no operating spacecraft will have a probability of collision greater than 10-6 with debris larger than mm.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 35- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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Space Force, to verify that immediately after the breakup no operating spacecraft will have a probability of collision greater than 10-6 with debris larger than mm.
31. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 36
Narrow public claim
For purposes of evaluation, debris with a diameter of 10 cm and larger will be assumed to cause a catastrophic collision.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 36- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
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For purposes of evaluation, debris with a diameter of 10 cm and larger will be assumed to cause a catastrophic collision.
32. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 36
Narrow public claim
The probability of such an event occurring as a result of a prior damaging impact with small debris is addressed by Requirement 4.5-2.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 36- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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The probability of such an event occurring as a result of a prior damaging impact with small debris is addressed by Requirement 4.5-2.
33. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 37
Narrow public claim
ODPO analysis has shown that the 10-6 goal is met for a 0.001 probability of catastrophic destruction of a 50 kg, 0.25m2 spacecraft at 1000 km circular altitude.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 37- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t04_primary_claims.json --source-file <local-raw-pdf>Exact source quote
ODPO analysis has shown that the 10-6 goal is met for a 0.001 probability of catastrophic destruction of a 50 kg, 0.25m2 spacecraft at 1000 km circular altitude.
34. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 37
Narrow public claim
The calculation of probability is limited to 100 years for objects left in long-term disposal orbits, because in principle an infinite lifetime will always equate to a mathematical collision probability of one.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 37- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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The calculation of probability is limited to 100 years for objects left in long-term disposal orbits, because in principle an infinite lifetime will always equate to a mathematical collision probability of one.
35. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 38
Narrow public claim
The objective of the following evaluation process is to help the user determine (1) if there may be a significant vulnerability to meteoroid or orbital debris impact, (2) which components are likely to be the most vulnerable, and (3) what simple design changes may be made to reduce vulnerability.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 38- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t04_primary_claims.json --source-file <local-raw-pdf>Exact source quote
The objective of the following evaluation process is to help the user determine (1) if there may be a significant vulnerability to meteoroid or orbital debris impact, (2) which components are likely to be the most vulnerable, and (3) what simple design changes may be made to reduce vulnerability.
36. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 38
Narrow public claim
4.5.4.3.5 For operations in Earth orbit, paragraph 1.1.3 requires that DAS is to be used to determine whether damaging impacts by small particles could reasonably prevent successful postmission disposal operations.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 38- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t04_primary_claims.json --source-file <local-raw-pdf>Exact source quote
4.5.4.3.5 For operations in Earth orbit, paragraph 1.1.3 requires that DAS is to be used to determine whether damaging impacts by small particles could reasonably prevent successful postmission disposal operations.
37. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 41
Narrow public claim
Disposal can be accomplished by one of the following methods: (1) Earth atmospheric natural reentry, (2) direct reentry, (3) maneuvering to a storage orbit, (4) direct retrieval, (5) long-term reentry, or (6) Earth escape.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 41- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t04_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Disposal can be accomplished by one of the following methods: (1) Earth atmospheric natural reentry, (2) direct reentry, (3) maneuvering to a storage orbit, (4) direct retrieval, (5) long-term reentry, or (6) Earth escape.
38. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 43
Narrow public claim
Reliability of postmission disposal maneuver operations in Earth orbit: NASA space programs and projects shall ensure that all postmission disposal operations to meet Requirements 4.6-1, 4.6-2, and 4.6-3 are designed for a probability of success as follows: a.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 43- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t04_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Reliability of postmission disposal maneuver operations in Earth orbit: NASA space programs and projects shall ensure that all postmission disposal operations to meet Requirements 4.6-1, 4.6-2, and 4.6-3 are designed for a probability of success as follows: a.
39. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 43
Narrow public claim
For controlled reentry, the probability of success at the time of reentry burn must be sufficiently high so as not to cause a violation of Requirement 4.7-1 pertaining to limiting the risk of human casualty.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 43- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t04_primary_claims.json --source-file <local-raw-pdf>Exact source quote
For controlled reentry, the probability of success at the time of reentry burn must be sufficiently high so as not to cause a violation of Requirement 4.7-1 pertaining to limiting the risk of human casualty.
40. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 44
Narrow public claim
In accordance with Requirement 4.4-2, all propellants remaining after achieving the proper disposal orbit need to be vented or burned in a way that does not upset the disposal orbit.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 44- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t04_primary_claims.json --source-file <local-raw-pdf>Exact source quote
In accordance with Requirement 4.4-2, all propellants remaining after achieving the proper disposal orbit need to be vented or burned in a way that does not upset the disposal orbit.
41. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 44
Narrow public claim
If a collision does occur, then very little debris from that collision would come low enough to pose a significant threat to operational spacecraft in LEO since the region from 1500 km to 2000 km is little used.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 44- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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If a collision does occur, then very little debris from that collision would come low enough to pose a significant threat to operational spacecraft in LEO since the region from 1500 km to 2000 km is little used.
42. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 45
Narrow public claim
However for most space structures in LEO to GEO orbits (such as GTO) the use of a perigee-lowering maneuver or of natural perturbations to ensure an orbital lifetime of less than 25 years is more cost-effective than reshaping the orbit to avoid crossing heavily-populated operational bands as mandated by requirement 4.6-2a.
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The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 45- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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However for most space structures in LEO to GEO orbits (such as GTO) the use of a perigee-lowering maneuver or of natural perturbations to ensure an orbital lifetime of less than 25 years is more cost-effective than reshaping the orbit to avoid crossing heavily-populated operational bands as mandated by requirement 4.6-2a.
43. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 45
Narrow public claim
Any 25-year disposal orbits should minimize and preferably avoid potential interference with major satellite constellations, such as the Global Navigation Satellite Systems.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 45- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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Any 25-year disposal orbits should minimize and preferably avoid potential interference with major satellite constellations, such as the Global Navigation Satellite Systems.
44. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 46
Narrow public claim
For an orbit with apogee altitude above 5,000 km, the orbital lifetime will also be affected by lunar and solar gravitational perturbations.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 46- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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For an orbit with apogee altitude above 5,000 km, the orbital lifetime will also be affected by lunar and solar gravitational perturbations.
45. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 46
Narrow public claim
Coordination with the 18 SPCS to avoid collisions with other tracked objects prior to executing these maneuvers at EOM is operationally expected of all NASA spacecraft per section 4.6.1.9 and by NPR 8715.6, but is not a condition of ODAR/EOMP approval.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 46- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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Coordination with the 18 SPCS to avoid collisions with other tracked objects prior to executing these maneuvers at EOM is operationally expected of all NASA spacecraft per section 4.6.1.9 and by NPR 8715.6, but is not a condition of ODAR/EOMP approval.
46. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 47
Narrow public claim
Note that the minimum required inherent system reliability for postmission disposal operations is 0.90, while the probability of postmission disposal failure due only to small object impacts is 0.01 (Requirement 4.5-2).
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 47- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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Note that the minimum required inherent system reliability for postmission disposal operations is 0.90, while the probability of postmission disposal failure due only to small object impacts is 0.01 (Requirement 4.5-2).
47. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 47
Narrow public claim
The probability of failure due to small object impacts need not be included in the 0.90 inherent system reliability determination.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 47- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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The probability of failure due to small object impacts need not be included in the 0.90 inherent system reliability determination.
48. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 48
Narrow public claim
For example, if a space structure is in a Sun Synchronous Orbit (SSO) of 800 km, less energy is required to ensure an orbital lifetime of less than 25 years if the space structure is left in an elliptical rather than a circular orbit.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 48- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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For example, if a space structure is in a Sun Synchronous Orbit (SSO) of 800 km, less energy is required to ensure an orbital lifetime of less than 25 years if the space structure is left in an elliptical rather than a circular orbit.
49. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 48
Narrow public claim
4.6.5.9 If disposal by controlled reentry into the atmosphere is chosen, the trajectory is to be designed to ensure that the space structure does not skip in the upper regions of the atmosphere.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 48- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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4.6.5.9 If disposal by controlled reentry into the atmosphere is chosen, the trajectory is to be designed to ensure that the space structure does not skip in the upper regions of the atmosphere.
50. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 49
Narrow public claim
4.7.1.1 The use of atmospheric reentry to limit the orbital lifetime of space structures in compliance with Requirement 4.6-1 results in the transfer of an orbital environment risk to a potential human casualty risk.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 49- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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4.7.1.1 The use of atmospheric reentry to limit the orbital lifetime of space structures in compliance with Requirement 4.6-1 results in the transfer of an orbital environment risk to a potential human casualty risk.
51. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 49
Narrow public claim
Range Commanders Council Standard 321-20 Supplement (Section 6.2, May 2020), 15 joules is the minimum threshold for such impact injuries.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 49- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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Range Commanders Council Standard 321-20 Supplement (Section 6.2, May 2020), 15 joules is the minimum threshold for such impact injuries.
52. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 50
Narrow public claim
For long-term reentry of space structures in MEO, Tundra orbits, highly inclined GEO, and other orbits: Surviving debris shall have less than 7 m2 total debris casualty area or 0.0001 (1 in 10,000) risk of human casualty.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 50- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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For long-term reentry of space structures in MEO, Tundra orbits, highly inclined GEO, and other orbits: Surviving debris shall have less than 7 m2 total debris casualty area or 0.0001 (1 in 10,000) risk of human casualty.
53. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 50
Narrow public claim
A kinetic energy threshold criterion of 15 joules is widely accepted as the minimum level for potential injury to an unprotected person (e.g., the U.S.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 50- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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A kinetic energy threshold criterion of 15 joules is widely accepted as the minimum level for potential injury to an unprotected person (e.g., the U.S.
54. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 51
Narrow public claim
The total debris casualty area for a reentry event is the sum of the individual debris casualty areas for all debris pieces of greater than 15-joule terminal energy that survive atmospheric reentry.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 51- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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The total debris casualty area for a reentry event is the sum of the individual debris casualty areas for all debris pieces of greater than 15-joule terminal energy that survive atmospheric reentry.
55. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 52
Narrow public claim
In generating the DCA formulae, the average cross-sectional area of an individual, viewed from above, is taken as the linear average of three distinct projected areas (standing, seated, prone) of an average human per the US Range Commanders Council Standard 321-00 Supplement: Common Risk Criteria for National Test Ranges (April 2000).
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 52- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t06_primary_claims.json --source-file <local-raw-pdf>Exact source quote
In generating the DCA formulae, the average cross-sectional area of an individual, viewed from above, is taken as the linear average of three distinct projected areas (standing, seated, prone) of an average human per the US Range Commanders Council Standard 321-00 Supplement: Common Risk Criteria for National Test Ranges (April 2000).
56. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 52
Narrow public claim
If the DAS result indicates a risk greater than 0.0001, the vehicle may still be compliant, but an ORSAT assessment will be needed to determine a more accurate estimate of the risk.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
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It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 52- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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If the DAS result indicates a risk greater than 0.0001, the vehicle may still be compliant, but an ORSAT assessment will be needed to determine a more accurate estimate of the risk.
57. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 53
Narrow public claim
4.7.4.8 For this technical area, it is suggested that illustrations and scenarios be used in the documentation of the analyses to assist in understanding the operations occurring.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 53- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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4.7.4.8 For this technical area, it is suggested that illustrations and scenarios be used in the documentation of the analyses to assist in understanding the operations occurring.
58. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 53
Narrow public claim
4.7.5.1 If the amount of debris surviving reentry exceeds the requirement, then either the ground impact point is modified by a postmission disposal maneuver or measures are taken to reduce the amount of debris surviving reentry.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 53- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t06_primary_claims.json --source-file <local-raw-pdf>Exact source quote
4.7.5.1 If the amount of debris surviving reentry exceeds the requirement, then either the ground impact point is modified by a postmission disposal maneuver or measures are taken to reduce the amount of debris surviving reentry.
59. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 54
Narrow public claim
The 2019 ODMSP includes a new section on certain special classes of space missions and establishes additional measures to mitigate the risk of debris generation from such missions.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 54- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t06_primary_claims.json --source-file <local-raw-pdf>Exact source quote
The 2019 ODMSP includes a new section on certain special classes of space missions and establishes additional measures to mitigate the risk of debris generation from such missions.
60. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 54
Narrow public claim
Those missions include (1) large constellations, (2) small satellites, including CubeSats, (3) rendezvous, proximity operations, and satellite servicing, (4) safety of active debris removal operations, and (5) tether systems.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 54- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t06_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Those missions include (1) large constellations, (2) small satellites, including CubeSats, (3) rendezvous, proximity operations, and satellite servicing, (4) safety of active debris removal operations, and (5) tether systems.
61. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 55
Narrow public claim
Small satellites, including CubeSats: For spacecraft smaller than 10 cm × 10 cm × 10 cm when fully deployed: (1) Any spacecraft in LEO shall be limited to an orbital lifetime as short as practicable but no more than 25 years after completion of mission.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 55- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Small satellites, including CubeSats: For spacecraft smaller than 10 cm × 10 cm × 10 cm when fully deployed: (1) Any spacecraft in LEO shall be limited to an orbital lifetime as short as practicable but no more than 25 years after completion of mission.
62. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 55
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Depending on the specifics of the mission parameters, a 0.99 reliability may be necessary for some large constellations.
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The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 55- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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Depending on the specifics of the mission parameters, a 0.99 reliability may be necessary for some large constellations.
63. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 57
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Any orbital debris mitigation compliance issues should be addressed and resolved no later than the Key Decision Point (KDP) B as defined in NPR 7120.5.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 57- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Any orbital debris mitigation compliance issues should be addressed and resolved no later than the Key Decision Point (KDP) B as defined in NPR 7120.5.
64. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 57
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A.1.5 Lunar, Mars, Sun-Earth, and Earth-Moon Lagrange point missions must assess the mission compliance in the near-Earth space, up to GEO, and the applicable requirements at the mission destinations.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 57- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
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A.1.5 Lunar, Mars, Sun-Earth, and Earth-Moon Lagrange point missions must assess the mission compliance in the near-Earth space, up to GEO, and the applicable requirements at the mission destinations.
65. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 61
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Detailed description and assessment of the efficacy of any planned debris avoidance capability intended to help in meeting requirement 4.5-1, including any plans to move to less congested altitudes, as well as any tracking enhancements (e.g., GPS, laser retroreflector) that may assist in reducing the covariance of collision estimates.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 61- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Detailed description and assessment of the efficacy of any planned debris avoidance capability intended to help in meeting requirement 4.5-1, including any plans to move to less congested altitudes, as well as any tracking enhancements (e.g., GPS, laser retroreflector) that may assist in reducing the covariance of collision estimates.
66. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 67
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A.3 Abbreviated ODARs A.3.1 For portions of spacecraft and missions where an abbreviated ODAR is required per NPR 8715.6, Table A.3-1 lists the sections of the ODAR defined in Section A.1 to be included.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 67- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
A.3 Abbreviated ODARs A.3.1 For portions of spacecraft and missions where an abbreviated ODAR is required per NPR 8715.6, Table A.3-1 lists the sections of the ODAR defined in Section A.1 to be included.
67. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 69
Narrow public claim
Description of operational orbital maintenance requirements (e.g., Sun-sync, ground track, altitude, formation flying) Initial ODAR Section 2: Orbital Debris Limitation Summary The following 10 questions should be answered to convey the intended plan for the spacecraft and launch vehicle being presented at the ASM.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 69- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
Download the PDF to a local file, then run the committed verifier. A changed PDF is reported as drift rather than silently accepted.
python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
Description of operational orbital maintenance requirements (e.g., Sun-sync, ground track, altitude, formation flying) Initial ODAR Section 2: Orbital Debris Limitation Summary The following 10 questions should be answered to convey the intended plan for the spacecraft and launch vehicle being presented at the ASM.
68. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 70
Narrow public claim
(If applicable, minimize the number of objects that can survive and strike the Earth with greater than 15 Joules of energy; list all objects that may survive when assessed in DAS– paragraph 4.7 & 4.7.2) j.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 70- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
(If applicable, minimize the number of objects that can survive and strike the Earth with greater than 15 Joules of energy; list all objects that may survive when assessed in DAS– paragraph 4.7 & 4.7.2) j.
69. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 71
Narrow public claim
(If applicable, minimize the number of objects that can survive and strike the Earth with greater than 15 Joules of energy; list all objects that may survive when assessed in DAS– paragraph 4.7 & 4.7.2) e.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
- Section locator
PDF page 71- Captured
- 2026-09-07
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67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
(If applicable, minimize the number of objects that can survive and strike the Earth with greater than 15 Joules of energy; list all objects that may survive when assessed in DAS– paragraph 4.7 & 4.7.2) e.
70. NASA-STD-8719.14C Process for Limiting Orbital Debris · PDF page 72
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B.1 Format for EOMPs B.1.1 Delivery of the EOMPs is governed by the requirements specified in NPR 8715.6 and NPR 7120.5, NASA Program Management.
What this card proves
The exact quoted statement occurred in the named official PDF fetched on 2026-09-07, and the complete PDF matched the recorded SHA-256.
What this card does not prove
It does not independently establish the underlying model capability, safety, comparison, or real-world truth. This is a retrospective single-maintainer source-publication audit.
- Primary source
- NASA-STD-8719.14C Process for Limiting Orbital Debris
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PDF page 72- Captured
- 2026-09-07
- Source SHA-256
67b26fc7af75ceeec66f9b205c92af7d6dda6e8e212fb77d61885ec1442194c9- Reproduction
- Maintainer run only; no independent operator rerun is registered.
Repeat this exact check locally
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python scripts/verify_primary_public_claim_group.py artifacts/cb7k_dom082_t07_primary_claims.json --source-file <local-raw-pdf>Exact source quote
B.1 Format for EOMPs B.1.1 Delivery of the EOMPs is governed by the requirements specified in NPR 8715.6 and NPR 7120.5, NASA Program Management.