摘要:针对大展弦比滑翔弹大侧滑飞行容易造成滚转控制饱和的问题，提出了一种降低侧滑角的STT驾驶仪设计方案。该驾驶仪与传统STT驾驶仪结构形式相同，包括俯仰、偏航、倾斜3个通道，通过在倾斜回路中引入侧向加速度反馈，以实现倾斜角对侧向加速度的跟随，达到减小侧滑角的效果。六自由度非线性数学仿真结果表明，改进的驾驶仪有效降低了滑翔弹STT转弯过程的侧滑角，可以应用于此类面对称导弹的飞行控制。

The improved STT autopilot was established to decrease the sideslip angle so that the problem of roll control saturation was settled down for a gliding missile with high aspect ratio wings during big sideslip angle flight． The designed STT autopilot，other than longitudinal， yaw，and roll channels with structure similar to the traditional STT autopilot，can realize the tracking of the roll angle to the lateral acceler ation to decrease the sideslip angle by the introduction of the lateral acceleration feedback in the roll loop． The six-DOF nonlinear simula tion was performed and the results indicated that the improved autopilot effectively decreases the sideslip angle of the gliding missile during STT flight and can be used in flight control for the similar plane-symmetrical missile．