launch vehicle flight system

基本解釋

Based on the separation point error calculation, the error variation of missile flight is the premise for system analysis and error distribution of launch vehicle.
依據(jù)分離點(diǎn)誤差推算彈道飛行的誤差變化規(guī)律，是進(jìn)行運(yùn)載器制導(dǎo)控制系統(tǒng)分析與誤差分配的前提條件。
Satellite remote sensing and control system should include flight telemetry and control of launch vehicle, operation telemetry and control of satellite, and telemetry and control of payload equipment.
衛(wèi)星遙感測(cè)控系統(tǒng)包括運(yùn)載火箭飛行測(cè)控、衛(wèi)星運(yùn)行測(cè)控、有效載荷設(shè)備測(cè)控以及它本身應(yīng)完成的遙感測(cè)量。