In order to reduce the heat stress of fighter plane pilots in hot environment before planes take off , a cooling vest with frozen gel as refrigerant is developed , and the capability of heat preservation of its correlated thermal insulation instruments is analyzed 摘要为了减轻歼击机飞行员飞行前热暴露阶段的热应激，研制了1种以冰胶为制冷介质的降温背心，分析了与其相配套的保温装具的保温性能。
Aim to plan optimal routes for a type of cruise missiles ( cms ) which can avoid the firepower units as surface - to - air missiles , antiaircraft guns , fighter planes , electromagnetism impulse and terrain obstacles and have the shortest length as well as consume the least oil 摘要目的设计优化一类巡航导弹航迹，且航迹满足避开地空导弹、高炮、歼击机群、电磁脉冲等火力单元和地形地物障碍，并且满足航迹路径长度短、耗油量少等约束条件。
On the basis of designing robust flight control system of the new generation fighter , this dissertation is devoted to the design of the integrated fire / flight control system and the integrated flight / propulsion control system and the integrated fire / flight / propulsion control system 以研究新一代歼击机的鲁棒飞行控制系统为前提，进一步研究其综合火力飞行控制系统、综合飞行推进控制系统以及综合火力飞行推进控制系统的鲁棒控制问题。
It is one of the most common illusions in flight among the pilots of fighter planes . american researchers investigated 105 pilots of fighter planes , according to the survey , 50 per cent pilots had experienced ci in flight . our survey in 1999 is analogous to theirs 据美国1998年进行的一项105名飞行员的调查显示：有50的飞行员在飞行中体验过这种错觉，我们在1999年调查了91名我军歼击机飞行员，也发现有42的飞行员在以往飞行中产生过科里奥利错觉。
First of all , it is devoted to discuss the open - loop characteristics and the nonlinear bifurcation analysis and the maneuver ability for the super - maneuverable flight nonlinear model of the new generation fighter . then a flight control system is designed in analytical dynamical inversion method based on the time - scale separation principle 首先，对新一代歼击机超机动飞行的非线性模型的开环特性、分叉特性及机动能力进行分析，并以此模型为基础，采用基于时标分离原则的动态逆控制方法设计了新一代歼击机的飞行控制系统。
Utilizing the force identification approaches above mentioned , experiments on the model of a supersonic fighter and on a wheel - rail coupled system are performed respectively , in order to verify the validity of the proposed theories in this dissertation 利用上述动载荷识别模型，本文分别对超音速歼击机模型和高速铁路轮轨耦合系统作了动载荷识别实验验证。结果表明，本文提出的方法能有效地进行未知激励下的动态载荷识别及作用位置识别，从而验证了本文理论的有效性。
Secondly , a discussion is devoted to a robust adaptive h control method based on wavelet neural network for a class of mimo nonlinear uncertain systems and applied this method to design the robust adaptive flight control system . this designed method is valid to the flight control system with unknown model 其次，本文提出了基于小波神经网络的一类多输入多输出不确定非线性系统鲁棒自适应h _控制方法并用于解决歼击机模型不完全已知时的鲁棒自适应h _飞行控制系统的设计。
Abstract : this paper presents a new model of rain - flow real - time counting method . it has the advanges such as counting easily , not needing the whole loading - time course . and it is also not necessary to readjust or modify the loading - time course . the field loading - time course of the model can be counted directly . the model surmounts the limitation of the previous counting model . it doesn " t need the second stage counting . the above research results have been applied to the data treatment of loading - spectra for the plane engine , the fighter plane and the war tank 文摘:介绍了一种新的雨流法实时计数模型.它的优点是计数简单，计数时不需要得到完整的载荷时间历程，也不需要对载荷时间历程作任何调整和修正，直接对载荷时间历程进行计数，克服了以往计数模型的局限性.该项研究已用于航空发动机，歼击机，主战坦克等载荷谱数据处理之中
Nonlinear dynamic inversion control law can better solved the control problem of super - maneuver flight . consider the engineering implement and the idiographic request of air force equipment department , this thesis used c + + programming language to describe dynamic inversion control law and model of the fourth generation fighter . for the convenience of user interface and maintenance , we encapsulated the software as a dll 考虑到工程实现和空军装备部的具体要求，本文采用c + +语言来对动态逆控制律以及第四代歼击机模型进行描述，为了用户接口和维护的方便，在此基础上使用dll动态链接库的形式对软件进行了封装。
To accomplish the complicated missions safely and effectively , it must have an advanced integrated fire / flight / propulsion system for the new generation fighter . synchronously , the integrated fire / flight / propulsion system is a complicated , uncertain and multi - variable nonlinear large - scale system . so its control problem is an active subject in the modern control area 而新一代歼击机的综合火力飞行推进系统是其能够安全、有效地完成复杂战术战略使命的基本前提，同时新一代歼击机的综合火力飞行推进系统是一个复杂的、具有不确定性的、多变量非线性大系统，因此它的设计与控制问题是现代控制领域所面临的一大挑战。
