1、BSI Standards Publication Space systems Best practices for orbit elements at payload LV separation PD ISO/TR 19473:2015National foreword This Published Document is the UK implementation of ISO/TR 19473:2015. The UK participation in its preparation was entrusted to Technical Committee ACE/68, Space s
2、ystems and operations. 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. Users are responsible for its correct application. The British Standards Institution 2015
3、. Published by BSI Standards Limited 2015 ISBN 978 0 580 87922 7 ICS 49.140 Compliance with a British Standard cannot confer immunity from legal obligations. This Published Document was published under the authority of the Standards Policy and Strategy Committee on 30 September 2015. Amendments/corr
4、igenda issued since publication Date Text affected PUBLISHED DOCUMENT PD ISO/TR 19473:2015 ISO 2015 Space systems Best practices for orbit elements at payload LV separation Systmes spatiaux Meilleures pratiques pour les lments en orbite charge utile Sparation LV TECHNICAL REPORT ISO/TR 19473 Referen
5、ce number ISO/TR 19473:2015(E) First edition 2015-09-01 PD ISO/TR 19473:2015 ISO/TR 19473:2015(E)ii ISO 2015 All rights reserved COPYRIGHT PROTECTED DOCUMENT ISO 2015, Published in Switzerland All rights reserved. Unless otherwise specified, no part of this publication may be reproduced or utilized
6、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 the country of the requester. ISO copyright of
7、fice Ch. de Blandonnet 8 CP 401 CH-1214 Vernier, Geneva, Switzerland Tel. +41 22 749 01 11 Fax +41 22 749 09 47 copyrightiso.org www.iso.org PD ISO/TR 19473:2015 ISO/TR 19473:2015(E)Foreword iv Introduction v 1 Scope . 1 2 Symbols and abbreviated terms . 1 2.1 Abbreviated terms . 1 2.2 Symbols . 2 3
8、 Orbit elements and calculation conditions . 3 3.1 Orbit elements . 3 3.2 Data source . 5 3.2.1 General 5 3.2.2 Guideline of correction about the external measurements 5 3.2.3 External measurement data accuracy . 5 3.3 Coordinate systems and time systems . 5 3.3.1 Coordinate systems . 5 3.3.2 Time s
9、ystems 7 4 Calculation method of Keplerian elements 7 4.1 Calculation method of orbit elements . 7 4.2 Transformation of other orbit elements . 9 4.2.1 Parameters of orbit size and shape 9 4.2.2 Parameters of orbit orientation .10 4.2.3 Parameters of satellite location .10 5 Calculation method of or
10、bit elements error .10 Bibliography .12 ISO 2015 All rights reserved iii Contents Page PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) Foreword ISO (the International Organization for Standardization) is a worldwide federation of national standards bodies (ISO member bodies). The work of preparing Interna
11、tional Standards 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
12、ISO, also 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,
13、Part 1. In 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 t
14、he elements 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
15、received (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 IS
16、Os adherence 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 2015 All rights rese
17、rved PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) Introduction This Technical Report will provide a recommendatory method for post-launch assessment of the orbit elements precision at separation, which is conductive to improving international communication effect and reducing the risks from errors resu
18、lting from miscommunication. It can estimate the orbit elements precision at separation, provide the reference for fuel capacity design of launch vehicle and spacecraft, and then help to reduce the manufactory costs of rocket and payload. ISO 2015 All rights reserved v PD ISO/TR 19473:2015 Space sys
19、tems Best practices for orbit elements at payload LV separation 1 Scope This Technical Report provides the best practices for orbit elements at payload-LV separation. It includes orbit elements and calculation conditions, calculation method of orbit elements and their errors at elliptical orbit inse
20、rtion of various payloads. The fit between the actual and expected values of orbit elements can be used as a criterion of commercial launch. There are many different sets of orbit elements. Each is best suited for a particular application. The traditionally used set of orbital elements is called the
21、 set of Keplerian elements. This Technical Report gives the calculation method of Keplerian elements and the transformation method of all the other orbit elements, in order to satisfy different users need. Affected by terrestrial gravitational perturbation, lunisolar gravitation perturbation and oth
22、er factors, orbit elements change slowly after orbit injection. Orbit elements calculation methods after separation are not included in this Technical Report. The technical communication and specific progress for orbit elements is relatively easy to be agreed on by applying this Technical Report, wh
23、ich can contribute to avoiding possible disputes. 2 Symbols and abbreviated terms 2.1 Abbreviated terms BIPM Bureau International des Poids et Mesures CTP Conventional Terrestrial Pole GAST Greenwich Apparent Sidereal Time GMST Greenwich Mean Sidereal Time GCRF Geocentric Celestial Reference Frame G
24、PS Global Positioning System IERS International Earth Rotation and Reference System Service IRM International Reference Meridian ITRF International Terrestrial Reference Frame ITRS International Terrestrial Reference System LGEIF Launch Geocentric Equatorial Inertial Frame LV Launch Vehicle PZ90 Acr
25、onym of Russian Parametry Zemli 1990 SI International System of Units TECHNICAL REPORT ISO/TR 19473:2015(E) ISO 2015 All rights reserved 1 PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) TAI International Atomic Time TCG Geocentric Coordinate Time TDT Terrestrial Dynamical Time THF Topocentric Horizon Fra
26、me UT1 Universal Time UTC Coordinated Universal Time WGS84 World Geodetic System, 1984 2.2 Symbols a semimajor axis a e earth semimajor axis of terrestrial ellipsoid IERS used in ITRS b semiminor axis E eccentric anomaly e eccentricity GM e earth gravitational parameter used in ITRS h a apogee altit
27、ude h p perigee altitude i inclination M mean anomaly n mean motion of satellite p semilatus rectum r a apogee radius r p perigee radius S 0 GAST at the time of payload LV separation T period t p time interval between the launch moment and the perigee passing t SEP time interval between the launch m
28、oment and the payload LV separation u argument of latitude V velocity V x , V y , V z projection of velocity in LGEIF x, y, z projection of position in LGEIF e flattening of the earth2 ISO 2015 All rights reserved PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) true anomaly e0 geocentric latitude at launc
29、h point 0 longitude at launch point N longitude of the ascending node in LGEIF argument of perigee e angular velocity of the earth right ascension of the ascending node 3 Orbit elements and calculation conditions 3.1 Orbit elements Six independent orbit elements describe the orbit of a satellite. Tw
30、o elements describe orbit size and shape, three elements describe orbit orientation, and one element describes orbit location. Orbit size and shape parameters include the following: a) semimajor axis; b) eccentricity; c) semiminor axis; d) semilatus rectum; e) perigee radius; f) apogee radius; g) pe
31、rigee altitude; h) apogee altitude; i) period; j) mean motion. Orbit orientation parameters include the following: a) inclination; b) right ascension of the ascending node; c) argument of perigee; d) longitude of the ascending node. Satellite location parameters include the following: a) true anomal
32、y; b) eccentric anomaly; c) mean anomaly; d) time past perigee; ISO 2015 All rights reserved 3 PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) e) time past ascending node; f) argument of latitude. The orbit elements are shown in Figure 1. Figure 1 Orbit elements The orbit ellipse geometry is shown in Figu
33、re 2. A C P a b p r r ae r Figure 2 Ellipse geometry4 ISO 2015 All rights reserved PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) 3.2 Data source 3.2.1 General Calculation of orbit elements at separation uses velocity vector and position vector. Ground-based or space-based external measurements should be
34、 used. 3.2.2 Guideline of correction about the external measurements a) Correction about lift-off time Unified timer start point about different instruments is suggested to be specified. The timer start point needs to be corrected by lift-off time. b) Correction about tracking point Tracking point o
35、f different measurement instruments at flight region is suggested to be provided. The tracking point is usually transformed into LV navigation system coordinate frame. The data of tracking point correction is usually provided by system engineering department. c) Correction about exception value The
36、measurement data need to pass a reasonable test and exception value needs to be deleted if necessary. d) Correction about measurement data The measurement data correction includes radio measurement and optical measurement. The measurement data based on ship is suggested to include ship drift positio
37、n correction, ship deformation correction, and ship attitude correction. e) Data format Data format is based on decade float point and the bit numbers are determined by measurement accuracy and measurement mission. 3.2.3 External measurement data accuracy a) Considering the need for flight test. b)
38、Considering the need for flight test result and injection accuracy. c) Considering the need for external measurement accuracy. d) Considering the accuracy, economy, and configuration about external measurement instrument in the flight region. 3.3 Coordinate systems and time systems 3.3.1 Coordinate
39、systems a) True Greenwich Frame The origin is located at the Earths centre of mass (including oceans and atmosphere). The Z axis coincides with the instantaneous earths axis of rotation and points northward. The x-axis is directed vertical to the Z axis and make X-Z plane coinciding with the plane o
40、f the true Greenwich meridian. The y-axis completes a right-handed system. ISO 2015 All rights reserved 5 PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) The X-Y plane is the true earths equatorial plane. b) International Terrestrial Reference Frame (ITRF) ITRF is a realization of the ITRS. The ITRS and I
41、TRF solutions are maintained by IERS. The origin is located at the Earths centre of mass (including oceans and atmosphere). As a time scale TCG (Geocentric Coordinate Time) is chosen, x-axis inherits the IRM (International Reference Meridian) plane. The Z axis coincides with CTP (Conventional Terres
42、trial Pole). The y-axis completes Cartesian system up to right-hand system. The coordinate frame definition of WGS-84, PZ90, and ITRF is almost the same, but there is some parameter difference between them. The coordinate difference on the surface of earth between the latest WGS-84 and ITRF is only
43、a few centimetres, and the difference between PZ90 and ITRF is meter class. For the mission of low-level accuracy requirement, it is admissible to neglect the difference between the true Greenwich frame and ITRF. For the mission of high-level accuracy requirement, it is necessary to consider the dif
44、ference. c) Launch Geocentric Equatorial Inertial Frame (LGEIF) LGEIF is a geocentric equatorial inertial reference frame, made up by the true Greenwich frame fixing at the launch moment. Position and velocity at the separation moment, resulted from LGEIF, are used for orbital elements calculation.
45、d) Geocentric Celestial Reference Frame (GCRF) GCRF is an inertial reference frame. Origin is located at the Earths centre of mass (including oceans and atmosphere). The x-axis is directed toward the mean vernal equinox. The Z axis directed toward the mean celestial pole perpendicular to the equator
46、ial plane. The y-axis lies 90 ahead (Eastward) in the equatorial plane, thus completing the right-handed coordinate system. J2000.0 is a kind of GCRF. Transformation between ITRF and GCRF can be found in 5.5.6 of Reference 7. e) Topocentric Horizon Frame (THF) THF is an earth-fixed reference frame.
47、The origin is located at the observation point. The X-Y plane is the local horizon, which is the plane tangent to the ellipsoid at observation point. The X plane is directed eastward. The Z axis is normal to this plane directed outward towards the zenith. The y-axis points north, thus completing a r
48、ight-handed system.6 ISO 2015 All rights reserved PD ISO/TR 19473:2015 ISO/TR 19473:2015(E) 3.3.2 Time systems The time systems may be used by coordinate transformation includes the following. a) Greenwich Apparent Sidereal Time (GAST) The origin of the GAST is the equinox, which has components of m
49、otion along the equator; these are due to the motion of the equator and ecliptic with respect to each other. Thus, the relationship between GAST and UT1 includes terms due to precession and nutation. The earth rotation angle and its relation to UT1 do not depend on combinations of precession and nutat
