ISO 16454:2024
Space systems

Standard No.

ISO 16454:2024

Release Date

2024

Published By

International Organization for Standardization (ISO)  IX  /  ISO

Latest

ISO 16454:2024

Introduction

Analysis of the core content of the standard

As the basic standard for aerospace structure design, ISO 16454:2024 specifies the complete stress analysis process from material properties to failure determination. Compared with the 2007 version, the new version mainly updates:

• Expansion and precision of term definitions
• Refinition of material property determination rules
• Improvement of mathematical model verification procedures

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Comparison of key technical requirements

Technical elements	Requirements of the 2007 version	Improvements of the 2024 version
Material allowable values	A/B benchmark values are given priority	Application conditions of new supplier guaranteed values
Mathematical model verification	Requirements in principle only	Add 12 specific inspection items (see Appendix A)
Failure mode	5 basic modes	Refine the local buckling judgment conditions

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Key Terms

Safety Margin (MS)

Calculation formula: MS = (L_A/(f×L_L))-1, where:

• L_A: Allowable load considering material performance degradation
• L_L: Ultimate load
• f: Design safety factor (usually ≥1.25)

Note: Special consideration is required when residual stresses are significant

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Implementation recommendations

1. Material data management: Establish an A/B benchmark database, with special attention to the anisotropy of composite materials
2. Model verification: It is recommended to check each item according to Appendix A, and the quality deviation should be controlled within 1%
3. Load combination: Pay attention to distinguishing the combined effects of stabilizing loads (safety factor of 1.0) and destabilizing loads
4. Local buckling: Non-destructive buckling needs to be clearly accepted at the system level

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Standard application case

Satellite bearing cylinder design verification

When a geosynchronous orbit satellite was verified using this standard:

• It was found that the MS=-0.15 was found at the aluminum alloy joint
• The model was remodeled by adjusting the grid density (from 50mm to 20mm)
• The final MS=0.08 met the requirements

It was proved that model refinement had a significant impact on the results

ISO 16454:2024 Referenced Document

• ISO 14622 Space systems - Structural design - Loads and induced environment*， 2025-04-01 Update
• ISO 14623 Space systems - Pressure vessels and pressurized structures - Design and operation

ISO 16454:2024 history

• 2024 ISO 16454:2024 Space systems
• 2007 ISO 16454:2007 Space systems - Structural design - Stress analysis requirements

Standard and Specification