1、BSI Standards Publication PD ISO/TR 11233:2014 Space systems Orbit determination and estimation Process for describing techniquesPD ISO/TR 11233:2014 PUBLISHED DOCUMENT National foreword This Published Document is the UK implementation of ISO/TR 11233:2014. The UK participation in its preparation wa
2、s entrusted to Technical Committee ACE/68/-/3, Space systems and operations - Operations and Ground Support. A list of organizations represented on this committee can be obtained on request to its secretary. This publication does not purport to include all the necessary provisions of a contract. Use
3、rs are responsible for its correct application. The British Standards Institution 2014. Published by BSI Standards Limited 2014 ISBN 978 0 580 65882 2 ICS 49.140 Compliance with a British Standard cannot confer immunity from legal obligations. This Published Document was published under the authorit
4、y of the Standards Policy and Strategy Committee on 31 August 2014. Amendments issued since publication Date Text affectedPD ISO/TR 11233:2014 ISO 2013 Space systems Orbit determination and estimation Process for describing techniques Systmes spatiaux Dtermination et estimation de lorbite Processus
5、pour la description des techniques TECHNICAL REPORT ISO/TR 11233 First edition 2013-11-15 Reference number ISO/TR 11233:2013(E)PD ISO/TR 11233:2014ISO/TR 11233:2013(E)ii ISO 2013 All rights reserved COPYRIGHT PROTECTED DOCUMENT ISO 2013 All rights reserved. Unless otherwise specified, no part of thi
6、s publication may be reproduced or utilized otherwise in any form or by any means, electronic or mechanical, including photocopying, or posting on the internet or an intranet, without prior written permission. Permission can be requested from either ISO at the address below or ISOs member body in th
7、e country of the requester. ISO copyright office Case postale 56 CH-1211 Geneva 20 Tel. + 41 22 749 01 11 Fax + 41 22 749 09 47 E-mail copyrightiso.org Web www.iso.org Published in SwitzerlandPD ISO/TR 11233:2014ISO/TR 11233:2013(E) ISO 2013 All rights reserved iii Contents Page Foreword iv Introduc
8、tion v 1 Scope . 1 2 Symbols and abbreviated terms . 1 3 Background 1 3.1 General . 1 3.2 Initial orbit determination 2 3.3 Subsequent orbit determination . 2 3.4 Required information for orbit determination . 3 3.5 Orbit elements . 7 3.6 Coordinate systems . 9 3.7 Reference frames 13 3.8 State vari
9、ables, mean orbits, and covariance .13 3.9 Orbit propagators 14 4 Documentary requirements 14 Annex A (informative) Representative widely used orbit determination and estimation tool sets 15 Annex B (informative) Representative reference frames 16 Annex C (informative) Representative numerical integ
10、ration schemes 17 Annex D (informative) Sample data sheet .18 Bibliography .19PD ISO/TR 11233:2014ISO/TR 11233:2013(E) Foreword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing International Sta
11、ndards is normally carried out through ISO technical committees. Each member body interested in a subject for which a technical committee has been established has the right to be represented on that committee. International organizations, governmental and non-governmental, in liaison with ISO, also
12、take part in the work. ISO collaborates closely with the International Electrotechnical Commission (IEC) on all matters of electrotechnical standardization. The procedures used to develop this document and those intended for its further maintenance are described in the ISO/IEC Directives, Part 1. In
13、 particular the different approval criteria needed for the different types of ISO documents should be noted. This document was drafted in accordance with the editorial rules of the ISO/IEC Directives, Part 2 (see www.iso.org/directives). Attention is drawn to the possibility that some of the element
14、s of this document may be the subject of patent rights. ISO shall not be held responsible for identifying any or all such patent rights. Details of any patent rights identified during the development of the document will be in the Introduction and/or on the ISO list of patent declarations received (
15、see www.iso.org/patents). Any trade name used in this document is information given for the convenience of users and does not constitute an endorsement. For an explanation on the meaning of ISO specific terms and expressions related to conformity assessment, as well as information about ISOs adheren
16、ce to the WTO principles in the Technical Barriers to Trade (TBT) see the following URL: Foreword - Supplementary information The committee responsible for this document is ISO/TC 20, Aircraft and space vehicles, Subcommittee SC 14, Space systems and operations.iv ISO 2013 All rights reservedPD ISO/
17、TR 11233:2014ISO/TR 11233:2013(E) Introduction This Technical Report prescribes the manner in which satellite owners/operators describe techniques used to determine orbits from active and passive observations and the manner in which they estimate satellite orbit evolution. The same data inputs lead
18、to different predictions when they are used in different models. Satellite owners/operators shall often accept orbit descriptions developed with physical models that others employ. The differences in orbit propagation as a result of using different physical models and numerical techniques can be sig
19、nificant. Safe and cooperative operations among those who operate satellites demand that each satellite owner/operator understand the differences among their approaches to orbit determination and propagation. ISO 2013 All rights reserved vPD ISO/TR 11233:2014PD ISO/TR 11233:2014Space systems Orbit d
20、etermination and estimation Process for describing techniques 1 Scope This Technical Report prescribes the manner in which orbit determination and estimation techniques are to be described so that parties can plan operations with sufficient margin to accommodate different individual approaches to or
21、bit determination and estimation. This Technical Report does not require the exchange of orbit data nor does it prescribe a method of performing orbit determination. It only prescribes the information that shall accompany such data so that collaborating satellite owners/operators understand the simi
22、larities and differences between their independent orbit determination processes. All satellite owners/operators are entitled to a preferred approach to physical approximations, numerical implementation, and computational execution of orbit determination and estimation of future states of their sate
23、llites. Mission demands should determine the architecture (speed of execution, required precision, etc.). This Technical Report will enable stakeholders to describe their techniques in a manner that is uniformly understood. Implementation details that can have proprietary or competitive advantage ne
24、ed not be revealed. 2 Symbols and abbreviated terms BDRF Bidirectional Reflectance Function FPA Flight Path Angle GPS Global Positioning System HEO High Earth Orbit IOD Initial Orbital Determination LEO Low Earth Orbit LS Least Squares OD Orbital Determination RAAN Right Ascension of the Ascending N
25、ode RMS Root Mean Square SP Sequential Processing TLE Two-line Elements UTC Coordinated Universal Time 3 Background 3.1 General Satellite orbit determination (OD) estimates the position and velocity of an orbiting object from discrete observations. The set of observations includes external measureme
26、nts from terrestrial or space-based sensors and measurements from instruments on the satellite itself. Satellite orbit propagation estimates the future state of motion of a satellite whose orbit has been determined from past observations. Though TECHNICAL REPORT ISO/TR 11233:2013(E) ISO 2013 All rig
27、hts reserved 1PD ISO/TR 11233:2014ISO/TR 11233:2013(E) a satellites motion is described by a set of ideal equations of motion representing physical hypotheses, the observations used in OD are subject to systematic and random uncertainties. Therefore, OD and propagation are probabilistic and can only
28、 approximately describe the satellites motion. The degree of approximation that can be tolerated depends on the intended use of the orbital information. A spacecraft is influenced by a variety of external forces, including terrestrial gravity, atmospheric drag, multibody gravitation, solar radiation
29、 pressure, tides, and spacecraft thrusters. Selection of forces for modelling depends on the accuracy and precision required from the OD process and the amount of available data. The complex modelling of these forces results in a highly nonlinear set of dynamical equations. Many physical and computa
30、tional uncertainties limit the accuracy and precision of the spacecraft state that can be determined. Similarly, the observational data are inherently nonlinear with respect to the state of motion of the spacecraft and some influences might not have been included in models of the observation of the
31、state of motion. Satellite OD and propagation are stochastic estimation problems because observations are inherently noisy and uncertain and because not all of the phenomena that influence satellite motion are clearly discernable. Estimation is the process of extracting a desired time-varying signal
32、 from statistically noisy observations accumulated over time. Estimation encompasses data smoothing, which is statistical inference from past observations; filtering, which infers the signal from past observations and current observations; and prediction or propagation, which employs past and curren
33、t observations to infer the future of the signal. This Technical Report and related ISO documents employ the term “orbit data.” Orbit data encompasses all forms of data that contribute to determining the orbits of satellites and that report the outcomes of orbit determination in order to estimate th
34、e future trajectory of a satellite. This includes observations of satellite states of motion either through active illumination, as with radars, or through passive observation of electromagnetic energy emitted or reflected from satellites, as with telescopes. It is desirable to keep each space orbit
35、 standard as simple as possible, treating the form and content of orbit data exchange, description of the modelling approach, and other relevant but independent aspects individually. It is hoped that this will develop a sufficient body of standards incrementally, not complicating matters for which t
36、here is consensus with matters that might be contentious. Most in the space community employ a variation of only a few major architectures. These architectures are cited in many texts and references that need not be enumerated in this document. OD begins with observations from specified locations an
37、d produces spacecraft position and velocity, all quantities subject to quantifiable uncertainty. 3.2 Initial orbit determination Initial OD (IOD) methods input tracking measurements with tracking platform locations, and output spacecraft position and velocity estimates. No a priori orbit estimate is
38、 required. Associated solution error magnitudes can be very large. IOD methods are sometimes nonlinear methods and are often trivial to implement. Measurement editing is typically not performed during IOD calculations because there are insufficient observations. Operationally, the OD process is freq
39、uently begun, or restarted, with IOD. IOD methods were derived by various authors: LaPlace, Poincar, Gauss, Lagrange, Lambert, Gibbs, Herrick, Williams, Stumpp, Lancaster, Blanchard, Gooding, and Smith. Restarting techniques are most easily accomplished by using a solution from another technique. 3.
40、3 Subsequent orbit determination 3.3.1 Least squares differential corrections Least squares (LS) methods input tracking measurements with tracking platform locations and an a priori orbit estimate, and output a refined orbit estimate. Associated solution error magnitudes are by definition small when
41、 compared to IOD outputs. LS methods consist of an iterative sequence of corrections where sequence convergence is defined as a function of tracking measurement residual root mean square 2 ISO 2013 All rights reservedPD ISO/TR 11233:2014ISO/TR 11233:2013(E) (RMS). Each correction is characterized by
42、 a minimization of the sum of squares of tracking measurement residuals. The LS method was derived first by Gauss in 1795 and then independently by Legendre. 3.3.2 Sequential processing Sequential processing (SP) methods are distinguished from LS processing methods in that batches of data are consid
43、ered sequentially, collecting a set of observations over a specified time interval and batch-processing one interval after the next. SP can be thought of as a moving time window whose contents are captured and processed at intervals, independent of previously processed batches of data. The analysis
44、does not include process noise inputs and calculations. It is in no way equivalent to filter processing, in which each new observation is added to past observations, improving estimates in a rigorous, traceable manner. 3.3.3 Filter processing Filter methods output refined state estimates sequentiall
45、y at each observation time. Filter methods are forward-time recursive sequential methods consisting of a repeating pattern of time updates of the state of motion estimate and measurement updates of the state of motion estimate. The filter time update propagates the state estimate forward, and the fi
46、lter measurement update incorporates the next measurement. The recursive pattern includes an important interval of filter initialization. Filter- smoother methods are backward-time recursive sequential methods consisting of a repeating pattern of state estimate refinement using filter outputs and ba
47、ckwards transition. Time transitions for both filter and smoother are dominated most significantly by numerical orbit propagators. The search for sequential processing was begun by Wiener, Kalman, Bucy, and others. 3.4 Required information for orbit determination 3.4.1 Observations When observation
48、data are communicated for collaborative or independent determination of satellite orbits, the observation types upon which that information is based shall be included. Several types of ground-based, airborne, and space-based sensor observations are routinely used in orbit determination. Table 1 desc
49、ribes the various observation types and sources. Table 1 Space surveillance observation product description Content Source two angles and slant range Radars two angles Baker-Nunn cameras, telescopes, binocu- lars, visual sightings Azimuth Direction finders Time of closest approach Radars, radio receivers for transmitting (Doppler) satellites Range, angles, and rates Radars Pseudorange and carrier phase, as well as single, double, and triple dif- ferences of these basic measurement types GPS or onboard inertial
