{"id":420532,"date":"2024-10-20T06:31:38","date_gmt":"2024-10-20T06:31:38","guid":{"rendered":"https:\/\/pdfstandards.shop\/product\/uncategorized\/bsi-pd-iso-tr-194732015-2\/"},"modified":"2024-10-26T12:12:44","modified_gmt":"2024-10-26T12:12:44","slug":"bsi-pd-iso-tr-194732015-2","status":"publish","type":"product","link":"https:\/\/pdfstandards.shop\/product\/publishers\/bsi\/bsi-pd-iso-tr-194732015-2\/","title":{"rendered":"BSI PD ISO\/TR 19473:2015"},"content":{"rendered":"
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 insertion of various payloads. The fit between the actual and expected values of orbit elements can be used as a criterion of commercial launch.<\/p>\n
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 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 user\u2019s need.<\/p>\n
Affected by terrestrial gravitational perturbation, lunisolar gravitation perturbation and other factors, orbit elements change slowly after orbit injection. Orbit elements calculation methods after separation are not included in this Technical Report.<\/p>\n
The technical communication and specific progress for orbit elements is relatively easy to be agreed on by applying this Technical Report, which can contribute to avoiding possible disputes.<\/p>\n
PDF Pages<\/th>\n | PDF Title<\/th>\n<\/tr>\n | ||||||
---|---|---|---|---|---|---|---|
6<\/td>\n | Foreword <\/td>\n<\/tr>\n | ||||||
7<\/td>\n | Introduction <\/td>\n<\/tr>\n | ||||||
8<\/td>\n | 1\tScope 2\tSymbols and abbreviated terms 2.1\tAbbreviated terms <\/td>\n<\/tr>\n | ||||||
9<\/td>\n | 2.2\tSymbols <\/td>\n<\/tr>\n | ||||||
10<\/td>\n | 3\tOrbit elements and calculation conditions 3.1\tOrbit elements <\/td>\n<\/tr>\n | ||||||
12<\/td>\n | 3.2\tData source 3.2.1\tGeneral 3.2.2\tGuideline of correction about the external measurements 3.2.3\tExternal measurement data accuracy 3.3\tCoordinate systems and time systems 3.3.1\tCoordinate systems <\/td>\n<\/tr>\n | ||||||
14<\/td>\n | 3.3.2\tTime systems 4\tCalculation method of Keplerian elements 4.1\tCalculation method of orbit elements <\/td>\n<\/tr>\n | ||||||
16<\/td>\n | 4.2\tTransformation of other orbit elements 4.2.1\tParameters of orbit size and shape <\/td>\n<\/tr>\n | ||||||
17<\/td>\n | 4.2.2\tParameters of orbit orientation 4.2.3\tParameters of satellite location 5\tCalculation method of orbit elements error <\/td>\n<\/tr>\n | ||||||
19<\/td>\n | Bibliography <\/td>\n<\/tr>\n<\/table>\n","protected":false},"excerpt":{"rendered":" Space systems. Best practices for orbit elements at payload. LV separation<\/b><\/p>\n |