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1、IW Ob95534 O002082 Ob8 Special Copyright Notice I992 by the American Institute of Aeronautics and Astronautics. All rights reserved. COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handling Services COPYRIGHT American Institute of Aeronautics and Astronautics Lic
2、ensed by Information Handling Services A I A A R-004 92 E Ob95534 0000572 949 E ANSIIAI AA R-004-1992 their existence does not in any respect preclude anyone, whether he has approved the standards or not, from manufacturing, marketing, purchasing, or using products, processes, or procedures not conf
3、orming to the standards. The American National Standards Institute does not develop standards and will in no circumstances give an interpretation of any American National Standard. Moreover, no person shall have the right or authority to issue an interpretation of an American National Standard in th
4、e name of the American National Standards Institute. Requests for interpretations should be addressed to the secretariat or sponsor whose name appears on the title page of this standard. CAUTION NOTICE: This American National Standard may be revised or withdrawn at any time. The procedures of the Am
5、erican National Standards Institute require that action be taken to affirm, revise, or withdraw this standard no later than five years from the data of approval. Purchasers of American National Standards may receive current information on all standards by calling or writing the American National Sta
6、ndards Institute. Recommended practice for atmospheric and space flight vehicle coordinate systems / sponsor , American Institute of Aeronautics and Astronautics : approved American National Standards Institute. p. cm. At head of title: American national standard. 1. Aerodynamics-Standards-United St
7、ates. 2. Astrodynamics- “ANSI/AIAA R-004- 1992” ISBN 0-930403-82-7 Standards-United States I. American Institute of Aeronautics and Astronautics. II. American National Standards Institute III. Title: American national standard TL570.R3733 1992 . 629.1323-dc20 92-35 1 CIP Published by American Instit
8、ute of Aeronautics and Astronautics 370 LEnfant Promenade, SW, Washington, DC 20024 Copyright O 1992 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 otherwise, without prior written
9、 permission of the publisher. Printed in the United States of America COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handling Services COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handling Services ANSI/AIAA R-004- 1992 CO
10、NTENTS Foreword v 1 .o 1.1 1.2 1.3 1.3.1 1.3.2 1.3.3 1.3.4 1.3.5 1.3.6 1.4 1.5 1.6 I . 7 1.7.1 1.7.2 1.8 1.8.1 1.8.2 1.9 1.9.1 1.9.2 1.9.3 1.9.4 1.10 1.1 1 Introduction . 1 Axis systems . 1 Positions 3 Angles . 3 Direction of the center of mass of the vehicle with respect to the geocentric inertial
11、and Orientation of the vehicle velocity with respect to the body-axis system . 4 Transition from the vehicle-carried normal Earth axis system to the body-axis system 5 Transition from the vehicle-carried normal Earth axis system to the air-path axis system 5 Flight-path angles 6 Wind direction angle
12、s 6 normal Earth-fixed axes systems . 3 Velocities and angular velocities 7 Flight vehicle inertia. reference quantities. and reduced parameters . 10 Forces. moments. coefficients. and load factors 12 Thrust. resultant moment of propulsive forces. airframe aerodynamic force. airframe aerodynamic mom
13、ent. and their components . 17 Thrust. resultant moment of propulsive forces. and their components 17 Airframe aerodynamic force. airframe aerodynamic moment. and their components . 18 Coefficients for the components of the thrust. of the resultant moment of propulsive forces. of the airframe aerody
14、namic force. and for the airframe aerodynamic moment . 19 Coefficients for the components of the thrust. and of the resultant moment of Coefficients for the components of the airframe aerodynamic force and of the propulsive forces 19 aerodynamic moment 20 Forces and moments involved in the control o
15、f the flight vehicle 22 Control force and control moment . 22 Motivators . 22 Magnitudes of motivator control parameters . 23 Control force coefficients and control moment coefficients . 24 Forces and moments acting on the motivators 25 . . Quantities related to energy 26 . 111 COPYRIGHT American In
16、stitute of Aeronautics and Astronautics Licensed by Information Handling Services COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handling Services A I A A R-004 92 m Ob95534 000057b 594 m ANSUAIAA R-004- 1992 Appendix A Symbols for the components of the airframe
17、 aerodynamic force and the non-dimensional coefficients of these components in use. or coming into use in different countries 37 Appendix B Classification of the main parts of flight mechanics . 39 B.l Flight mechanics 39 B.2 Flight kinematics . 39 B.4 Maneuverability . 40 B.3 Flight dynamics . 39 A
18、ppendix C Terms and symbols for dynamic derivatives of forces. moments. and their coefficients . 43 C . 1 C.2 C.3 C.4 C.5 c.0 Introduction . 43 sideslip. and airspeed 44 Normalized forms of the derivatives. with respect to time. of the angles of attack and Derivatives of the non-dimensional coeffici
19、ents of the components of the resultant force and moment with respect to normalized quantities (first group) . 44 Reference quantities used to form derivatives of the second group . 46 Normalized derivatives of the components of the resultant force and moment with respect to motion variables (second
20、 group) 46 Derivatives of the non-dimensional coefficients of the components of the resultant force and moment with respect to motivator deflections . 48 Appendix D Transformations 51 D . 1 D.2 D.3 D.4 D.5 Introduction . 51 launch-vehicle inertial measurement units 51 Translation from geocentric ine
21、rtial axis system to Earth-fixed axis system . 51 Transformation matrices for axis rotations 52 Transfomation matrices for aerodynamic coefficients 53 Special definition for geocentric inertial axis system used to initialize Appendix E Quaternions 57 Background . 57 E.2 Quaternion relations . 57 E .
22、 1 Figures 1 A 1B 1C 2 3 4 5 6 7 B-1 Orientation of geocentric inertial and orbit-defined axis systems 28 Vehicle position expressed in a geocentric inertial axis . 29 Vehicle position expressed in a normal Earth-fixed axis system 29 Orientation of the vehicle velocity with respect to the body axis
23、system 30 Orientation of the body axis system relative to the vehicle-carried normal Earth axis system 31 Orientation of the air-path axis system relative to the vehicle-carried normal Earth axis system 32 Sign conventions for control-surface deflections 35 Flight-path angles with respect to the Ear
24、th axis system 33 Wind direction angles with respect to the Earth-fixed axis system . 34 Schematic diagram illustrating the classification of the main parts of flight mechanics 41 iv COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handling Services COPYRIGHT Amer
25、ican Institute of Aeronautics and Astronautics Licensed by Information Handling Services FOREWORD IS0 International Standard 115 1 , in its several parts, was prepared to be applicable to “aircraft,” defined as a vehicle intended for atmospheric or space flight. That series of standards has not been
26、 followed with any consistency by designers of missiles, projectiles, or spacecraft. It has been followed generally by designers of piloted and pi- lotless, heavier-than-air aircraft. The purpose of this AIAA Recommended Practice is to provide nomenclature and coordinate systems for designers and an
27、alysts of missiles, projectiles, and aircraft (atmospheric and transatmospheric). This document is based on two parts of IS0 International Standard 1 15 1. It should be noted that analysts in the field of as- trodynamics use different axis systems than those presented here. Further, axis systems use
28、d in navigation on, or with respect to, the surface of the Earth and those used by test ranges also differ from those presented here. This Committee on Standards believes that a unified system that provides a common basis for describing the motions of flight vehicles in all regimes can be prepared,
29、but more concerted experience with common practice will be necessary before such a level of standardization can be realized. At this time, it is hoped that this Recommended Practice will serve as a “bridge” between traditional aircraft practice and the present variety of astrodynamic practices. As c
30、ommunication between aircraft and satellites become more common, a common method for translating between coordinate systems will be needed. This AIAA Recommended Practice is intended to introduce the main concepts, to include the more important terms used in theoretical and experimen- tal studies, a
31、nd, as far as possible, to give corre- sponding symbols. Throughout this AIAA Recommended Practice, the term “flight vehicle” or “vehicle” denotes a missile, projectile, or aircraft intended for atmospheric or transatmospheric flight. It may have one or more planes of symmetry, as determined by the
32、geometric characteristics of the vehicle. Two orthogonal directions are defined: fore-and-aft and transverse. The normal direction follows from these two axes by the right-hand rule. When there is a single plane of symmetry, it is the reference plane of the vehicle. When there is more than one plane
33、 of symmetry, or when there is none, it is necessary to choose a reference plane. In the former case, the reference plane is one of the planes of symmetry. In the latter case, the reference plane is arbitrary. In all cases, it is necessary to specify the choice made. Angles of rotation, angular velo
34、cities, and mo- ments about any axis are positive clockwise when viewed in the positive direction of that axis. All of the axis systems used are three-dimensional, orthogonal and right-handed, which implies that a positive rotation through n/2 radians around the x- axis brings the y-axis into the po
35、sition previously occupied by the z-axis. The center of gravity coincides with the center of mass, if the field of gravity is homogeneous. If this is not the case, the center of gravity can be re- placed by the center of mass in the definitions of this AIAA Recommended Practice; in such a case, this
36、 should be indicated. With the aim of easing the indication of references from a section or clause, a decimal numbering system has been adopted such that the two or three figures correspond to the number of the paragraph or sub-paragraph. The AIAA Astrodynamics Committee on Standards has started pre
37、paring a consensus document based on the several coordinate systems now in use in that field. Likewise the AIAA Guidance, Navigation, and Control Committee on Standards is planning work on coordinate systems from the viewpoint of that technology, including more detail on the use of quaternions. The
38、work of all three com- mittees will be coordinated carefully to achieve the most useful result for users of these standards. V COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handling Services COPYRIGHT American Institute of Aeronautics and Astronautics Licensed
39、by Information Handling Services A I A A R-004 92 H Ob95534 0000578 3b7 H ANSI/AIAA R-004- 1992 AIAA Atmospheric Flight Mechanics Working Group: T. J. Monteodorisio, Chairman (Raytheon Missile Systems Div.) R. C. Brown, Secretary (McDonnell Douglas Missile Systems Co.) W. B. Blake (Wright-Patterson
40、AFB) H. I. Flomenhoft (Consultant) J. E. Jenkins (Wright-Patterson AFB) D. B. Leggett (Wright-Patterson AFB) S. R. Vukelich (McDonnell Douglas Missile Systems Co.) M. F. Zedd (Naval Research Laboratory) This document was approved by the Working Group in August 1990. The AIAA Atmospheric Flight Mecha
41、nics Committee on Standards (Thomas J. Monteodorisio, Chairman) approved the document in January 1991. The AiAA Standards Technical Council (W. W. Vaughan, Chairman) approved the document in November 199 1. vi COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handl
42、ing Services COPYRIGHT American Institute of Aeronautics and Astronautics Licensed by Information Handling Services A I A A R-004 92 W 0695534 0000579 2T3 W ANSI/AIAA R-004- 1992 1.0 Introduction This document ANSVAIAA R-004-1992 gives basic definitions and deals with the motion of flight vehicles r
43、elative to various inertial axis systems or relative to the atmosphere, which may be assumed to be at rest or in translational motion at constant velocity relative to the Earth. The flight vehicle is assumed to be rigid; however, most of the definitions can be applied to the case of a flexible fligh
44、t vehicle. The vehicle may be in orbit or free flight, or may be in contact with the ground, or a carrying vehicle. The carrying vehicle may be a flight vehicle itself or a ground launcher. When account is taken of the variations at the Earths surface in the direction of the vertical (local directio
45、n of acceleration due to gravity), the term given in the sub-clauses and figures in question is qualified by the term “local.” See Appendix D.l for a discussion of the astronomical standards for the definition of inertial axis systems. 1.1 Axis systems No. 1.1.1 1.1.2 1.1.3 1.1.4 1.1.5 1.1.6 Term Ge
46、ocentric inertial axis system (See Appendix D.2 for a modification of this system used for launch vehicles.) Eart h-f xed axis system Geocentric Earth-fixed axis system (typical for orbiting spacecraft translations) Normal Earth-fixed axis system Vehicle-carried orbit-defined axis system Vehicle-car
47、ried normal Earth axis system Definition An inertial reference system of the FK5 mean equator and equinox of J2000.0 has the origin at the center of the Earth, the XI-axis being the continuation of the line from the center of the Earth through the center of the Sun toward the vernal equinox, the zI-
48、axis pointing in the direction of the mean equatorial planes north pole, and the Y I - axis completing the right-hand system. (See Figure 1A ) A right-hand coordinate system, fixed relative to a n d rotating with the Earth, with the origin and axes directions chosen as appropriate. A system with bot
49、h the origin and axes fixed relative to and rotating with the Earth (1.1.2). The origin is at the center of the Earth, the xG-axis being the continuation of the line from the center of the Earth through the intersection of the Greenwich meridian and the equator, the zG-axis being the mean spin axis of the Earth, positive to the north, and the yG-axis completing the right-hand system. (See Appendix D.3) An Earth-fixed axis system (1.1.2) in which the zo-axis is oriented according to the downward vertical passing through the origin (from the origin to the nadir). (See
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