The result control system is demonstrated using post - stall maneuver simulation , the results show that this control law achieves a high level performance in post - stall maneuver conditions even if the aircraft model has large uncertain items 结果表明，在存在较大模型误差的情况下，所设计的飞控规律完全能在过失速机动条件下控制飞机跟踪指令飞行。
Vb link with fortran language is realized and solved successfully . both program interfaces are friendly and convenient to operate . the post - stall behavior of three specific compression systems is analyzed by the application of the post - stall behavior simulation programs developed in this paper 以三种特定的压缩系统为研究对象，展示了这两种过失速性能模拟技术的实用性和有效性，单级压缩系统的过失速状态的数值模拟结果得到了实验结果的很好支持。
Thrust vectoring is the key technique for the modem fighter with agility and post - stall maneuver ability and good flight quality . and now it is the necessary technique for the fourth generation fighter and hot technique for the performance improvement for the third generation fighter 推力矢量技术是现代战机具有敏捷性、过失速机动能力、良好的飞行品质的关键技术，其已成为第四代战斗机的必备技术和第三代战斗机改型的热门技术，得到了越来越多的重视。
The radial , circumferential and axial distributions of static pressure amplitude under post - stall conditions are measured and compared . the experimental results have proved the feasibility of using one - dimensional model to analyze the post - stall behavior and recoverability of compression systems . at the same time , the results of experiment have provided the first - hand data for analyzing and calculating vibrating response of blades under post - stall conditions 以单级轴流压气机实验器为对象，研制了两种型式的静压动态探针?梳形针和圆盘针，详细测量了过失速状态下流道中压力沿径向、周向和轴向分布，验证了用一维模型分析压气机过失速性能和失速可恢复性的可信度，同时为过失速状态下叶片的振动响应分析计算提供了第一手实验数据。
According to self - study ability of neural network , this paper designed a fuzzy neural network controller to apply in one of the post - stall maneuvers milestone70 degree angle of attack trimmed flight through train the fuzzy logic rules and membership functions of the traditional fuzzy logic controller , then we got satisfied results 利用神经网络具有自学习能力的优势，采用反向传播学习算法，通过对传统模糊逻辑控制器中的模糊逻辑控制规则和隶属函数有关参数进行训练学习，设计了模糊神经网络控制器,应用于飞机的过失速机动“里程碑”之一? ? 70迎角定常飞行仿真计算，获得了令人满意的结果。
The validation of the programs is verified by the good agreement between the simulation results and experimental results in the single - stage compression system . it is also verified that only a qualitative analysis can be obtained using the one - dimensional unsteady lumped model ; but the one - dimensional unsteady stageby - stage model is more suitable for actual compressor operating conditions and can serve as an effective analytic tool for studying the post - stall behavior and improving recoverability of compression systems 判明了一维非定常总体模型只能定性的分析压缩系统的过失速性能，在定量的分析上存在着一定的局限性；而一维非定常单元容积模型更能反映压缩系统实际情况，从而为研究压缩系统的过失速性能和改善压缩系统的失速可恢复性提供了有力的工具。
The mechanism of two possible ways of thrust vectoring control : force and moment control are analyzed . the effects of thrust vectoring on aircraft supersonic performance , take - off and landing performance , low speed and high angle of attack performance are studied . the air combat effectiveness of thrust vectoring control and post - stall maneuvers are also analyzed 5 、分析了推力矢量的两种应用方式：力控制和力矩控制的机理，研究了推力矢量对飞机超音速性能、起降性能、低速大迎角性能的影响，讨论了推力矢量与过失速机动对空战效能的影响。
For researching the flight test techniques of thrust vector controlled aircraft , dynamic models of thrust vector controlled aircraft were established , four post stall maneuver control laws were designed with the dynamic inverse method , tested and investigated according to a standard evaluation maneuver set ( stems ) 摘要为研究推力矢量飞机的试飞技术，建立了推力矢量飞机的动力学模型，用动态逆方法设计了4种过失速机动控制律，并在地面飞行模拟器上参考标准评估机动动作集( stems )进行了飞行模拟试验研究。
3 . the aerodynamic characteristics and mechanism of flight dynamics under the condition of post - stall maneuvers are discussed , and then the inputs of adaptive fuzzy system are determined . using the control law and nonlinear motion equations built above , some typical post - stall maneuvers are simulated and the effects of thrust vectoring on post - stall maneuver are analyzed 3 、讨论了过失速机动条件下的空气动力特性和飞行力学机理，在此基础上对自适应模糊逻辑系统的输入进行了分析，确定了自适应模糊逻辑系统的输入。
Abstract : two computational techniques for inverse fight dynamics , namely derivation - iteration and integration - iteration techniques , are investigated . the application of inverse dynamics to determine control power requirements for post - stall maneuvering is researched , and a maneuvering flight trajectory based algorithm is provided , which lays a numerical foundation for simplifying design criteria for post - stall aircraft . with the model of inverse dynamics employed , a flight control mode for the outermost loop of the control system , named maneuver generator , is designed to follow desired complicated maneuvering flight trajectories . an example of rapid heading - reversal maneuver and other numerical simulations show the feasibility of the algorithm and the design idea 文摘:考察了求解输入类飞行逆动力学问题的微分-迭代与积分-迭代算法;探讨了利用逆动力学确定过失速机动操纵效能要求问题，这构成了进一步提出过失速机动飞机设计简化判据的数值基础;利用逆动力学设计机动发生模块进行飞控系统的最外环控制，以便跟踪期望的复杂机动轨迹.飞机最速反向示例及其它数值仿真结果表明设计思想与算法是可行的
