AIAA S-110-2005 Space Systems Structures Structural Components and Structural Assemblies《航天系统.结构部件和结构程序集》.pdf

1、 Standard AIAA S-110-2005 Space Systems Structures, Structural Components, and Structural Assemblies AIAA standards are copyrighted by the American Institute of Aeronautics and Astronautics (AIAA), 1801 Alexander Bell Drive, Reston, VA 20191-4344 USA. All rights reserved. AIAA grants you a license a

2、s follows: The right to download an electronic file of this AIAA standard for storage on one computer for purposes of viewing, and/or printing one copy of the AIAA standard for individual use. Neither the electronic file nor the hard copy print may be reproduced in any way. In addition, the electron

3、ic file may not be distributed elsewhere over computer networks or otherwise. The hard copy print may only be distributed to other employees for their internal use within your organization. AIAA S-110-2005 Standard Space Systems Structures, Structural Components, and Structural Assemblies Sponsored

4、by American Institute of Aeronautics and Astronautics Approved 12 July 2005 Abstract This document establishes a standard for the design, analysis, material selection and characterization, fabrication, test, and inspection of structural items in space systems, including payloads, spacecraft, upper-s

5、tages, and expendable and reusable launch vehicles. This standard, when implemented on a particular space system, will assure high confidence in achieving safe, reliable operation in all phases of the mission. This document applies specifically to all structural items including fracture-critical har

6、dware used in space systems during all phases of the missionwith the following exceptions: adaptive structures, engines, solid rocket nozzles, and thermal protection systems. AIAA S-110-2005 ii Library of Congress Cataloging-in-Publication Data Standard space systems : structures, structural compone

7、nts, and structural assemblies / sponsored by American Institute of Aeronautics and Astronautics. p. cm. “AIAA S-110-2005.“ Includes bibliographical references and index. ISBN 1-56347-770-X (hardcopy : alk. paper) - ISBN 1-56347-771-8 (electronic : alk. paper) 1. Space vehicles-Standards. 2. Aerospa

8、ce industries-Materials-Standards. I. American Institute of Aeronautics and Astronautics. TL795.S73 2005 629.47021873-dc22 2005012640 Published by American Institute of Aeronautics and Astronautics 1801 Alexander Bell Drive, Reston, VA 20191 Copyright 2005 American Institute of Aeronautics and Astro

9、nautics All rights reserved No part of this publication may be reproduced in any form, in an electronic retrieval system or otherwise, without prior written permission of the publisher. Printed in the United States of America AIAA S-110-2005 iii Contents Foreword . vi 1 Scope 1 2 Tailoring.1 3 Appli

10、cable Documents1 4 Vocabulary 2 4.1 Acronyms and Abbreviated Terms 2 4.2 Terms and Definitions.3 5 General Requirements .7 5.1 Mission Requirements 7 5.1.1 Loads and Pressure7 5.1.2 Environments 8 5.1.3 Life .9 5.2 Design Requirements .9 5.2.1 Static Strength.9 5.2.2 Margin of Safety9 5.2.3 Buckling

11、 Strength10 5.2.4 Static Stiffness 10 5.2.5 Dynamic Behavior.11 5.2.6 Dimensional Stability 11 5.2.7 Fatigue Life11 5.2.8 Damage Tolerance (Safe Life).11 5.2.9 Impact Damage Tolerance.12 5.2.10 Stress-Rupture Life.12 5.2.11 Corrosion and Stress-Corrosion Cracking Control12 5.2.12 Outgassing 12 5.2.1

12、3 Meteoroid and Orbital Debris Protection .12 5.3 Material Requirements .13 5.3.1 Metallic Materials 13 5.3.2 Composite Materials .13 5.3.3 Glass and Ceramic Materials .14 5.3.4 Polymeric Materials 15 5.4 Fabrication and Process Control16 5.5 Quality Assurance.16 5.5.1 Inspection16 AIAA S-110-2005 i

13、v 5.5.2 Acceptance Proof Test .17 5.5.3 Traceability17 5.6 Repair and Refurbishment .17 5.7 Storage18 5.8 Transportation.18 6 General Requirements Verification18 6.1 Design Requirements Verification18 6.1.1 Static Strength Verification .19 6.1.2 Margin of Safety (MS) Determination 20 6.1.3 Buckling

14、Verification .20 6.1.4 Static Stiffness Verification.21 6.1.5 Dynamic Behavior Verification .21 6.1.6 Dimensional Stability Verification.22 6.1.7 Fatigue-Life Verification22 6.1.8 Damage Tolerance (Safe Life) Verification .22 6.1.9 Impact Damage Tolerance Verification .23 6.1.10 Stress-Rupture Life

15、Verification .23 6.1.11 Corrosion and Stress-Corrosion Cracking Control Verification 23 6.1.12 Outgassing Verification.23 6.1.13 Meteoroid and Orbital Debris Shielding Verification .23 6.2 Acceptance Tests .24 6.2.1 Nondestructive Inspection (NDI) 24 6.2.2 Proof Load and Pressure Tests .24 6.2.3 Vib

16、ration and Shock Tests .24 6.3 Qualification Program .24 6.3.1 Proof Load and Pressure Tests .25 6.3.2 Vibration and Shock Tests .25 6.3.3 Inspection25 6.3.4 Qualification Load and Pressure Tests25 7 Special Structural Items26 7.1 Special Structural Items with Published Standards 26 7.2 Special Stru

17、ctural Items without Published Standards .28 7.2.1 Beryllium Structural Items 28 7.2.2 Cryo Structures and Hot Structures .28 7.2.3 Sandwich Structures.28 8 Documentation Requirements29 AIAA S-110-2005 v 8.1 Interface Control Documents .29 8.2 Applicable (Contractual) Documents .29 8.3 Analysis Repo

18、rts.29 8.3.1 Stress Analysis Report .29 8.3.2 Fatigue or Damage Tolerance (Safe Life) Analysis Reports 30 8.3.3 Fracture/Impact Damage Control Plan/Report30 8.3.4 Inspection Reports30 8.3.5 Dynamic Analysis .30 9 Bibliography 30 Tables Table 1 Minimum Design Factors of Safety.11 Table 2 Design Requi

19、rements Verification Matrix .19 Table 3 Minimum Qualification Test Factors .25 Table 4 Published Specific Requirements for Special Structural Items .27 AIAA S-110-2005 vi Foreword This standard was prepared by the AIAA Structures Committee of Standards (CoS) based on an Aerospace Technical Operating

20、 Report, TOR-2003 (8583)-2894, Space Systems-Structures Design and Test Requirements, 2 August 2004. The AIAA Structures CoS was formed in 2004 with an emphasis on inclusion of experts in aerospace industry, academia, and interested government agencies. Deliberations focused heavily on adapting this

21、 standard to new space systems not only developed for the United States Air Force/Space and Missile Systems Center (USAF/SMC) but also for civil and commercial applications. At the time of approval, the members of the AIAA Structures CoS were: Pravin Aggarwal NASA Marshall Space Flight Center Basem

22、Alzahabi Kettering University Steve Brodeur, Chair Swales Aerospace Meredith Cawley, Liaison AIAA Jim Chang, Co-Chair The Aerospace Corporation Sean Coghlan Air Force Research Laboratory Vinay Dayal Iowa State University Bob Farahmand The Boeing Company Anindya Ghoshal United Technologies Research C

23、enter Hector Gomez Northrop Grumman Norman Knight General Dynamics Advanced Information Systems Larry Loh Lockheed Martin Corporation Nat Patel, Co-Chair The Aerospace Corporation William Schonberg University of Missouri-Rolla Larry Trilling Ball Aerospace or (2) contains gas or liquid that will cre

24、ate a mishap (accident) if released; or (3) will experience a MEOP greater than 100 psi (700 kPa) NOTE Pressurized structures, pressure components, and special pressurized equipment including batteries, heat pipes, sealed containers, and cryo-coolers are excluded. Pressurized Structure a structure d

25、esigned to carry both internal pressure and vehicle structural loads EXAMPLES Launch vehicle main propellant tanks, solid rocket motors, and crew cabins of manned modules. AIAA S-110-2005 6 Proof Factor a multiplying factor applied to the limit load or MEOP to obtain proof load or proof pressure for

26、 use in the acceptance test program Protoqualification Test a test of the flight production unit to a higher load level and duration than acceptance, but less than qualification NOTE 1 The testing consists of the same types and sequences as are used in qualification testing. NOTE 2 The protoqualific

27、ation test is conducted on a flight unit. Qualification Tests the required formal contractual tests conducted at load levels and durations sufficient to demonstrate that the design, manufacturing, and assembly of flight-quality structures have resulted in hardware that conforms to specification requ

28、irements Residual Strength the maximum value of load and/or pressure that a flawed or damaged structural item is capable of sustaining without further damage or collapse S-Basis Allowable the mechanical strength value which represents the specification minimum value specified by the governing indust

29、ry specification or federal or military standards for the material, or a specified contractor quality-control requirement Safe Life the required period during which a structural item, even containing the largest undetected flaw, is shown by analysis or testing not to fail catastrophically under the

30、expected service loads and environments Service Life the period of time (or cycles) beginning with the manufacturing of the structural item and continuing through all acceptance testing, handling, storage, transportation, launch operations, orbital operations, refurbishment, retesting, reentry or re

31、covery from orbit, and reuse that may be required or specified for the item Stress-Corrosion Cracking a mechanical and environmentally induced failure process in which sustained tensile stress and chemical attack combine to initiate and propagate a crack or a crack-like flaw in a metal part Stress-R

32、upture Life the minimum time during which a nonmetallic structural item maintains structural integrity, considering the combined effects of stress level(s), time at stress level(s), and associated environments Structural Component mechanical part(s) in a functional hardware item designed to sustain

33、load and/or pressure or maintain alignment EXAMPLES Antenna support structure, instrument housing, pressure vessel, and solid rocket motor case. Structural Item a structure, a structural subsystem (assembly), or a structural component Structural Mathematical Model an analytical or numerical represen

34、tation of a structure AIAA S-110-2005 7 Structural Subsystem (Assembly) a mechanical subsystem or assembly that is designed to carry primary vehicle external loads EXAMPLES Satellite buses and interstages Structure mechanical part(s) designed to carry internal and/or external loads or pressures, mai

35、ntain stiffness, alignment, and/or stability, and provide support or containment for other systems or subsystems NOTE The space vehicle structure is usually categorized into primary and secondary structure. Primary structure is defined as the part that carries the main flight loads and defines the n

36、atural frequencies and mode shapes. The secondary structure supports hardware items with negligible participation in the main vehicle load transfer, and the stiffness of secondary structure does not significantly influence the dynamic behavior of the vehicle. System Threat Analysis Energy Level the

37、maximum energy level due to an impact resulting from a credible threat event determined in a system threat analysis Ultimate Load the maximum design load (force, stress, and/or strain) that the structure must withstand without rupture or collapse Vibroacoustic an environment induced by high-intensit

38、y acoustic noise associated with various segments of the flight profile. It manifests itself throughout the structure in the form of transmitted acoustic excitation and as structure-borne random vibration Visual Damage Threshold (VDT) an impact energy level shown by test(s) to create an indication t

39、hat is barely detectable by a trained inspector using an unaided visual inspection technique Yield Load the maximum design load (force, stress, and/or strain) the structure must withstand without detrimental deformation 5 General Requirements This section contains the mission requirements and genera

40、l requirements for the design, material selection and characterization, fabrication and process control, quality assurance, repair and refurbishment, storage, and transportation for all structural items. 5.1 Mission Requirements 5.1.1 Loads and Pressure Anticipated loads and pressures throughout the

41、 service life of a structural item shall be used to define the load/pressure spectra for design, analysis, and testing. Updates to the design spectra shall be evaluated to verify positive margins prior to flight. 5.1.1.1 Loads All relevant structural load events experienced throughout the service li

42、fe of a structural item shall be identified and considered. Load definitions shall include the load levels and durations during service life. Typical loading conditions relevant to the pre-launch, launch, and ascent phases include transportation, ground operations, operational pressures, engine igni

43、tion, thrust, aerodynamic loads, heat flux, pyrotechnic shock, maneuvering, and separation. Loading conditions for the on-orbit phase shall include operational loads and pressures, thrust, pyrotechnic and deployment shock, temperature, vibration, and micrometeoroid and debris impact. Loading relevan

44、t to reentry, descent, and landing shall include AIAA S-110-2005 8 aerodynamic loads, temperatures, deployment, landing (including contingency), and post-landing heat soak. 5.1.1.1.1 Ground Handling, Transportation, and Post Landing Loads As appropriate, the structural item shall be instrumented dur

45、ing ground handling and transportation to ensure that critical design loads and thermal and humidity levels are not exceeded. Loading conditions for all logistic, ground handling, and post-landing operations shall be developed and considered in designing the structural item. 5.1.1.1.2 Flight and Orb

46、ital Loads The principal source of design loads for the structural item is the loads generated by the quasi-static and transient phenomena occurring during the various operational phases of launch, flight, and orbit (such as docking and EVA-related loads, where applicable). All loads shall be consid

47、ered in the combinations that yield the specified statistical basis. Loads in the low frequency regime shall be determined by analysis utilizing simulations and coupled system flexible body structural dynamic models, as appropriate for the event and the nature of the applied external environment. Ot

48、her significant low frequency loads may occur due to on-orbit operations, such as appendage deployment, vehicle slewing, and mechanism operation. The frequency range for loads analyses, typically up to 70 Hz, shall be supplied by the launch vehicle organization as determined by the resolution and fi

49、delity of the launch vehicle models and forcing functions. The payload dynamic model shall have sufficient fidelity to capture the dynamic behavior of the payload in this frequency range. 5.1.1.2 Pressure All pressure vessels, pressurized structures, and other pressure components shall withstand limit pressure applied simultaneously with other limit loads without experiencing detrimental deformation. They shall withstand ultimate pressure applied simultaneously with relevant ultimate loads without failure in the critical environment. Pressure vessels and pressuriz