载人航天
載人航天
재인항천
MANNED SPACEFLIGHT
2012年
3期
31-35
,共5页
在线估计%在线补偿%姿态角偏差反馈%舵偏角反馈
在線估計%在線補償%姿態角偏差反饋%舵偏角反饋
재선고계%재선보상%자태각편차반궤%타편각반궤
Real-time Estimation%Real-time Compensation%Attitude Angle Error Feedback%Rudder Feedback
由于干扰引起大推力运载火箭入轨前箭体姿态与最佳推力方向产生偏离，致使降低了入轨精度。为实现精确入轨，需对未知干扰进行在线估计和补偿。提出了姿态角偏差反馈和舵偏角反馈两种补偿方案，论述了两种方案的可行性。然后以姿态角偏差反馈为例给出具体实现步骤和三种姿态角偏差的在线估值方式。最后，给出仿真结论。结果表明，采用姿态角偏差反馈方式实现干扰在线补偿能够显著提高火箭的入轨精度。
由于榦擾引起大推力運載火箭入軌前箭體姿態與最佳推力方嚮產生偏離，緻使降低瞭入軌精度。為實現精確入軌，需對未知榦擾進行在線估計和補償。提齣瞭姿態角偏差反饋和舵偏角反饋兩種補償方案，論述瞭兩種方案的可行性。然後以姿態角偏差反饋為例給齣具體實現步驟和三種姿態角偏差的在線估值方式。最後，給齣倣真結論。結果錶明，採用姿態角偏差反饋方式實現榦擾在線補償能夠顯著提高火箭的入軌精度。
유우간우인기대추력운재화전입궤전전체자태여최가추력방향산생편리，치사강저료입궤정도。위실현정학입궤，수대미지간우진행재선고계화보상。제출료자태각편차반궤화타편각반궤량충보상방안，논술료량충방안적가행성。연후이자태각편차반궤위례급출구체실현보취화삼충자태각편차적재선고치방식。최후，급출방진결론。결과표명，채용자태각편차반궤방식실현간우재선보상능구현저제고화전적입궤정도。
The deflection of attitude and direction of the manned launch vehicle caused by disturbance before it goes into orbit may lead to a loss of precision. Two compensation methods, namely the attitude angle error feedback method and rudder feedback method, are proposed to improve the precise attitude control of the launch vehicle. Taking the former one as an example, the realizing approach and three means of real-time compensation are presented. Simulation result shows that the attitude angle error feedback method can compensate the uncertain disturbance effectively, and improve the precision of launch vehicle.
