attitude maneuver

基本解釋

This paper deals with the large angle attitude maneuver control of spacecrafts.
本文研究空間飛行器大角度姿態(tài)機(jī)動(dòng)的控制問(wèn)題。
Based on near-eigenaxis decomposition theorem of the relative attitude, the control law of relative attitude maneuver based on quaternion is designed and simulated.
根據(jù)相對(duì)姿態(tài)的歐拉軸分解定理，設(shè)計(jì)了基于四元數(shù)反饋的相對(duì)姿態(tài)機(jī)動(dòng)控制律，并對(duì)相對(duì)姿態(tài)控制律進(jìn)行了仿真分析。
This paper deals with the near-minimum-time attitude maneuver control of vertical launching tactical missile, in order to solve fast attitude maneuver of this kind of missile.
針對(duì)戰(zhàn)術(shù)導(dǎo)彈垂直發(fā)射姿態(tài)調(diào)轉(zhuǎn)時(shí)的快速性要求，研究了垂直發(fā)射快速姿態(tài)調(diào)轉(zhuǎn)的次最小時(shí)間控制問(wèn)題。