为确保某探空火箭载荷释放点的飞行参数落入指定释放包络内,提出了一种能同时适应4种飞行工况的多约束载荷释放条件判定方法。该方法将释放包络左边界线平移得到的直线和备份时序触发条件作为载荷释放判定条件,并对相关参数进行了合理设计。蒙特卡洛仿真及4发火箭飞行试验结果表明,文中提出的载荷释放条件判定方法可保证每个试验工况下,载荷释放点的飞行参数落入要求的包络框内,简单可靠、包容性好、有较高的工程应用价值。

A multi-constraint payload releasing criterion approach to four flight conditions is proposed to ensure that the flight parameters of a sounding rocket enter the specified release envelope. The straight line shifted by the left boundary of payload release envelope and backup time is used as the determination condition of load releasing, and the relevant parameters are reasonably designed. The criterion approach was verified by numerical simulation of Monte-Carlo and four flight tests of sounding rocket. The results show that the criterion approach can make the flight parameters at the load release point fall into the specified envelope in each flight test, which is simple, reliable, inclusive and of important engineering value.