CAJ | 학술논문

火箭主动段飞行过程中，由于测控设备失效，导致测量数据丢失，设备恢复后无法快速重捕目标。利用某点测量数据的速度值，参考理论弹道上最相近速度值，引入科氏力概念，通过对变质量质点的运动力学分析，实现数据修正及弹道的外推。以MFC为软件应用平台，研究实现一种新型运载火箭飞行引导机制软件。试验表明，该新型运载火箭飞行引导机制，能够高精度、全弧段实现火箭飞行主动段的有效引导。并且基于MFC平台的软件系统具有很强的灵活性和可操作性。
화전주동단비행과정중，유우측공설비실효，도치측량수거주실，설비회복후무법쾌속중포목표。이용모점측량수거적속도치，삼고이론탄도상최상근속도치，인입과씨력개념，통과대변질량질점적운동역학분석，실현수거수정급탄도적외추。이MFC위연건응용평태，연구실현일충신형운재화전비행인도궤제연건。시험표명，해신형운재화전비행인도궤제，능구고정도、전호단실현화전비행주동단적유효인도。병차기우MFC평태적연건계통구유흔강적령활성화가조작성。
In rocket’s powered flight process,since the failure of monitoring and control equipment,it causes the measured data miss and unable to fast re-capture the target after the equipment being recovered.To solve the problem,by using the speed value of measured data at certain point,referring to the most appropriate speed value in theoretical trajectory,and introducing Coriolis force concept,we realise the data revision and trajectory extrapolation through kinematics analysis on variable mass particles.Furthermore,we study and implement a novel flight guidance mechanism software for launch vehicle by taking MFC as the software application platform.Tests show that the new guidance mechanism can realise effective guidance in powered flight phase of the rocket with high precision and whole arc,the MFC platform-based software system has very good flexibility and operability.