AIAA S-143-2016 Occupant-Imparted Loads for Commercial Suborbital RLVs.pdf

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1、StandardAIAA/CSF S-143-2016 Occupant-Imparted Loads for CommercialSuborbital RLVsAIAA standards are copyrighted by the American Institute of Aeronautics and Astronautics (AIAA), 12700 Sunrise Valley Drive, Reston, VA 20191-5807 USA. All rights reserved. AIAA grants you a license as follows: The righ

2、t 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 electronic file may not be

3、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/CSF S-143-2016 Standard Occupant-Imparted Loads for Commercial Suborbital RLVs Sponsored by American Institute of Aeronautic

4、s and Astronautics Commercial Spaceflight Federation Approved 7 November 2016 Abstract Specifies human engineering design practices and recommendations to assist the designer in determining expected intentional load conditions on commercial space vehicle controls and mobility elements. AIAA/CSF S-14

5、3-2016 ii Published by American Institute of Aeronautics and Astronautics 12700 Sunrise Valley Drive, Reston, VA 20191 Copyright 2016 American Institute of Aeronautics and Astronautics All rights reserved No part of this publication may be reproduced in any form, in an electronic retrieval system or

6、 otherwise, without prior written permission of the publisher. Printed in the United States of America AIAA/CSF S-143-2016 iii Contents Contents iii Foreword iv 1 Scope . 1 2 Purpose 1 3 Tailoring 1 4 Terms and Definitions 1 5 Process Definition . 1 5.1 Occupant Data 2 5.2 Safety Factor . 2 5.3 Fina

7、l Load Limits . 2 6 Strength Data . 2 6.1 Data Set 2 6.2 Element Use 2 6.3 Environmental Conditions . 2 6.4 Population . 2 6.5 Physical Data 2 6.6 Body Mass Data 3 6.7 Anthropometric Data . 3 6.8 Strength Data 3 7 Loads and Criticality . 3 7.1 Load Limits 3 7.2 Load Criticality . 3 8 Document Loads

8、4 Annex A (informative) 5 Example Load Determination 5 Annex B (informative) 7 References 7 AIAA/CSF S-143-2016 iv Foreword This Standard was developed by the Commercial Spaceflight Federation to provide engineering design practices for human suborbital spaceflight. The standard establishes processe

9、s and recommendations for determining the expected load conditions on sub-orbital commercial space vehicle controls and mobility elements. It is the intent of this standard to provide an experienced designer with the information necessary to evaluate a particular system design as appropriate for the

10、ir vehicle, the intended use, and target population in order to minimize safety and performance risks for sub-orbital spaceflight. The requirements, design practices and anthropometric data in this standard is informed by established sources including the FAA, NASA, DoD, and academia. As the commerc

11、ial space flight industry gains experience, this document will continue to be improved. For questions about this standard, please contact the Commercial Spaceflight Federation at: Commercial Spaceflight Federation 500 New Jersey Avenue NW, Suite 400 Washington, DC 20001 http:/mercialspaceflight.org

12、infocommercialspaceflight.org At the time of approval, the members of the AIAA Commercial Space Committee on Standards were: Audrey Powes, Chair Blue Origin Jane Kinney Commercial Spaceflight Federation Jeff Greason XCOR Aerospace Mark Polansky Barrios Technology Mack Reiley Virgin Galactic Laurie W

13、atkins CSSI, Inc. Ken Myers CSSI, Inc. Ed Burns NASA Zig Leszczynski Virginia Commercial Space Flight Authority Ron Kohl R. J. Kohl b) details of the analysis and rationale that led to that data and resulting loads. AIAA/CSF S-143-2016 5 Annex A (informative) Example Load Determination Determine the

14、 loads data for an element located on the cabin floor beside the pilots seat. The element is not be used in a normal mission but is a critical component that needs to be pulled successfully without breaking in an emergency situation. The emergency can happen at any phase of flight operations. In ord

15、er to reach the element and apply load, the seated pilot reaches down and pulls up on the handle to activate it, or pushes down to deactivate it (imagine a car handbrake on the floorboard). Due to its placement, only the trained pilots can access this element during flight. Pilots are not wearing pr

16、essure suits. Knowing the above information we can develop the requisite strength and load data. Population, Physical Data: Trained pilots Dimensions of arms, torso, and seat relevant to achieving grip on element using Measure of Man and Woman as guide. o Account for possible changes in dimensions o

17、r reachability based on reasonable off nominal events. Higher than average strength No untrained Space Flight Participant access, therefore no une xpected load values or directions Population, Body Mass Data: Center of gravity in seated position, accounting for changes i n CG for relevant off-nomina

18、l events Population, Anthropometrics: User strapped into seat Seated, reaching down side of seat to access element Seated arm pull up or push down Other: Adrenaline effects (element u sed in emergency situation) Weightless effects possibly negligible (pilots remain strapped into seat) Strength Data

19、If, after considering population and environmental variables, there is no need to derive strength data specifically for this element, consult the strength data from Appendix F of the MPCV Human-System Integration Requirements, or other reference material using info above to determine possible load c

20、ases for unsuited arm strength arm up and arm down. Highest loads in all possible situations: Limit pull load = Highest pull-up load Limit push load = Highest push-down load AIAA/CSF S-143-2016 6 Choose safety factors based on criticality: This element is criticality 1; failure of this element will

21、likely lead to loss of life. We have no supporting additional data on this specific pilots strength, so we will use the standard recommended safety factor. Therefore, Safety Factor = 2 Apply safety factor to limit loads: Ultimate pull load = Limit p ull load * Safety factor Ultimate push load = Limi

22、t push load * Safety factor AIAA/CSF S-143-2016 7 Annex B (informative) References 1 NASA, NASA SPACE FLIGHT HUMAN-SYSTEM STANDARD, VOLUME 2: HUMAN FACTORS, HABITABILITY, AND ENVIRONMENTAL HEALTH, NASA-STD-3001, January 10, 2011. 2 NASA, ORION MULTI-PURPOSE CREW VEHICLE (MPCV) PROGRAM HUMAN-SYSTEMS

23、INTEGRATION REQUIREMENTS, MPCV 70024, Rev. A, January 22, 2014. Note in particular Appendix F. 3 The Measure of Man and Woman: Human Factors in Design, Alvin R. Tilley (Author), Henry Dreyfuss Associates , December 31, 2001 4 FAA, Recommended Practices for Human Space Flight Occupant Safety, Version 1, August 27, 2014 5 DoD, Design Criteria Standard, MIL-STD-1472G, 11 January 2012 6 Occupational and Biomechanics textbook (Chaffin, D. B., Occupational Biomechanics, Second Edition, John Wiley & Sons, Inc., 1991)