弹载捷联惯性制导系统传递对准技术试飞验证

Flight test analysis of an improved transfer alignment for missile strapdown inertial guidance system

介绍了一种弹载捷联式惯性制导系统传递对准改进设计方案,描述了在运输机上进行试飞验证的方法和结果。试飞结果表明,所设计方案的姿态对准精度为1.9′(1σ),航向对准精度为3.4′(1σ),整个传递对准过程可在40秒之内完成,满足了预定的指标要求。该方案采用了一种先进的“速度+姿态”匹配方法,飞机只需做简单的摆翼机动飞行,相比传统设计方案有较大改进。

The paper described an improved transfer alignment scheme for missile Inertial Guidance System, and presented the flight test procedure in a transporter. The following flight test results meet the missile requirement： attitude accuracy 1.9＇（1σ）, heading accuracy 4.5＇（1σ）, alignment time 〈40 s. An advanced ＂velocity ＋ attitude＂ information matching method was used in the scheme, and only a brief wing jink maneuver was required during the alignment procedure.