【摘要】 针对某一具体的飞艇,在缺少风洞吹风数据的情况下,利用现有气动力手册中的工程估算公式,对飞艇作了气动力估算;采用飞艇的小扰动线化方程,进行本体特性分析.飞艇的小扰动线化方程从低速飞机的线化小扰动方程获得.在Matlab软件中的simulink工具箱中,进行了PID控制律的数字仿真;通过反复迭代循环,观察系统的时域响应,根据最后的响应结果,设计了其定高飞行的控制律;最后进行了真实的飞行试验.试验完成了飞艇自主远距离往返飞行,共飞行时间达2 0min ,指令飞行高度为30 0m .将试验和理论结果进行比较,吻合较好,表明高度控制律设计合理,气动估算可行,有实用价值.更多还原

【Abstract】 The longitudinal aerodynamic parameters of an airship were estimated in defect of the data from wind tunnel test, using the form in compilers group of aerodynamic handbooks. The characteristic of the airship was analyzed, using the linear small-disturbance equations, which was acquired from the linear small-disturbance equations of the low-velocity airplane. The PID (proportion, integration and differentiation) control-law was designed and it’s simulation was done in the Simulink toolbox of the Matlab software, which was used in the design. The height-holding flight control law was presented, observing the time-response. The auto-long-flight was realized in the actual test. The time of flight was 20min and the ideal fight-altitude was 300 m. The approximation was found, through comparing the actual flight test with the ideal result. It shows that the control law is valid and the aerodynamic estimation method is valuable.更多还原