Description

BS PD ISO/TR 19473:2015 provides the best practices for orbit elements at payload-LV separation. Itincludes orbit elements and calculation conditions, calculation method of orbit elements and theirerrors at elliptical orbit insertion of various payloads. The fit between the actual and expected values oforbit 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. Thetraditionally used set of orbital elements is called the set of Keplerian elements. This Technical Reportgives the calculation method of Keplerian elements and the transformation method of all the other orbitelements, in order to satisfy different user’s need.

Affected by terrestrial gravitational perturbation, lunisolar gravitation perturbation and other factors,orbit elements change slowly after orbit injection. Orbit elements calculation methods after separationare not included in this Technical Report.

The technical communication and specific progress for orbit elements is relatively easy to be agreed onby applying this Technical Report, which can contribute to avoiding possible disputes.

Cross References:
ISO/TR 11233
ISO 14303
CCSDS 500.0-G-3
CCSDS 502.0-B-2
CCSDS 503.0-B-1
CCSDS 504.0-B-1
ANSI/AIAA S-131-2010
ISO 15863

All current amendments available at time of purchase are included with the purchase of this document.

Product Details

Published:

09/30/2015

ISBN(s):

9780580879227

Number of Pages:

22

File Size:

1 file , 1.3 MB

Same As:

ISO/TR 19473:2015

Product Code(s):

30312458, 30312458, 30312458

Note:

This product is unavailable in United Kingdom