Finally , the adaptive inverse controller based on neural networks is applied to keep longitudinal incidence . and the adaptive parameter controller is applied to missile autopilot , which controls the overload of missile 针对导弹自动驾驶仪这样复杂的非线性系统，采用bp网络逆控制方法和bp网络混合调参控制方法设计了姿态保持和机动跟踪自动驾驶仪。
The simulation results show that the btt missile ' s robust autopilot designed on a standard state point can make the btt missile fly stably along the whole trajectory , and has the ability of intercepting maneuvering targets 仿真结果表明：本文按给定空域内一个特征点设计的btt导弹鲁棒自动驾驶仪能控制btt导弹在该空域内沿全弹道稳定飞行，并具有拦截机动目标的性能。
If we wish the btt missile fly stably and accurately along the whole trajectory with the autopilot designed on a special state point , we need to apply the multiple - variable robust design method to design the btt missile ' s autopilot 因此，如希望按一个特征点设计的自动驾驶仪能够控制btt导弹沿全弹道稳定、准确地飞行，就要利用多变量鲁棒设计方法设计btt导弹的自动驾驶仪。
Abstract : a type of pilotless target aircraft flight control system is introduced . the function and basic compose and autopilot control regular and engine control principle and recovery control scheme of the flight control system are discussed 文摘:介绍了无人驾驶靶机的飞行控制系统，详细讨论了系统的功能、基本组成、自动驾驶仪控制规律、发动机控制原理、回收控制方案及系统软件设计等。
This design method overcomes the traditional autopilot ' s disadvantage that should shift the autopilot ' s gain according to flight phase ; it also can make the btt missile fly stably along the whole trajectory , and can intercept a maneuvering target accurately 该设计方法克服了传统自动驾驶仪在控制导弹飞行中需逐段切换增益的不足，能控制btt导弹在大空域内沿全弹道稳定飞行，并能精确拦截机动目标。
To avoid high frequency oscillation in the course of autopilot design , damping coefficient value was treated as a constraint , the rise time was taken as objective , and the other performance criteria were taken as constraints , then the robustness design problem was solved by multi - objective optimization method 摘要在导弹控制系统设计过程中，考虑了自动驾驶仪的高频振荡问题，将其转化为系统的一个约束条件，同时把上升时间转化为目标函数，其他设计指标视为约束条件，采用有约束多目标优化的方法解决了系统鲁棒性设计问题。
By simulation of this autopilot on standard state point and special state points , this robust control system ' s high - speed response ability and good robust stability is validated . under this autopilot ' s control , the btt missile can fly stably along many trajectories in a large airspace . 3 通过对所设计的自动驾驶仪在标称点和给定特征点进行仿真试验，验证了所设计的鲁棒控制系统能快速跟踪指令信号，并具有较好的鲁棒稳定性，能控制btt导弹在大空域内沿多条弹道稳定飞行。
The characters of bank - to - turn control technology determine that the btt missile ' s mathematical model having kinematical coupling , aero dynamical coupling , inertial coupling and control coupling . so the widely used stt missile ' s autopilot , which is designed to be three - channel independent ca n ' t meet the btt missile ' s control need Btt控制技术的控制特点决定了btt导弹的数学模型存在运动学耦合、气动耦合、惯性耦合和控制耦合等多种耦合因素，因此目前侧滑转弯( stt )导弹广泛采用的自动驾驶仪三通道独立设计方法已不能满足btt导弹控制系统的设计要求。
Consequently , computational models of all subsystems are constructed , such as the strapdown inertial navigation system ( sins ) , the control loop applied in self - control period , the guidance system by applying the technology of television ( tv ) guidance and the guidance law of proportion navigation , the autopilot by applying the technology of overload control in terminal control period , and so on 建立导弹各个子系统的计算模型，主要有捷联惯性导航系统、弹体、导弹自控段的控制稳定回路、采用电视制导和比例导引制导律的导引系统，以及采用过载控制的自动驾驶仪，然后在此基础上建立导弹各系统仿真模型。
