过失速机动

最佳过失速机动研究

Research on optimal post stall maneuvers

介绍了X-31A飞机的有关飞行试验情况，特别是循序渐近的四种过失速机动动作以及空战效能评估结果。

In air combat . The flight test program is then outlined , especially on the four step - by - step post stall maneuvers and the inflight tactical evaluation results .

结果表明，战斗机F2比F1更具有空中格斗优势，空战中发动机推力、迎角变化率、操纵规律和离轴发射角（μ0）等因素对战斗机过失速机动敏捷性有一定影响。

The results show that PST fighter F2 is superior in the combat , and the facts such as engine thrust , angle of attack rates , control laws and missile off boresight angle have some influence on fighter agility in poststall air combat .

利用建立的非线性飞机模型和大迎角控制律，对两种典型的过失速机动&眼镜蛇机动和Herbst机动进行了仿真研究，进一步揭示了飞机过失速机动的飞行力学机理。

Basing on the fighter nonlinear model and the high-attack-angle control law , the dynamic characteristics of post-stall maneuver are studied , with the successful simulations of two typical post-stall maneuver - " Cobra " and " Herbst " maneuver .

推力矢量飞机过失速机动仿真研究及大迎角非线性控制律设计

Research on Flight and Control of the TV Fighter 's Post-Stall Maneuvers

过失速机动飞机的鲁棒非线性控制律设计

Robust , nonlinear control design for a poststall maneuver aircraft

模糊神经网络在过失速机动飞行中的应用

Fuzzy neural network control with application to post-stall maneuvers

现代战机的非常规机动&过失速机动技术分析

Analysis of Deep-Stall Maneuverability Technology of the Modern Battleplane

推力矢量控制与飞机过失速机动仿真研究

A Study on the Thrust Vectoring Control and Aircraft 's Post Stall Maneuver

基于过失速机动动力学的控制方法

A control method based on dynamics for post-stall maneuvering

过失速机动战斗机的控制

The Control of Post - Stall Maneuverable Aircraft

过失速机动与快速机头瞄准能力

Post-Stall Maneuverability and Rapid Nose Pointing Capability

敏捷性和过失速机动

Agility and post - stall maneuver

过失速机动的优化这、那的指示研究

Research on Optimal Post-stall Maneuvers

从飞机设计的角度分析了过失速机动飞行的操纵要求问题。

From the viewpoint of aircraft design , a topic on control design requirements for post stall maneuvering is tackled .

大迎角过失速机动是下一代高性能战斗机必须具备的特性之一。

Post-stall maneuverability at high angles of attack is one of the main features for the next-generation air superiority fighters .

应用非线性动态逆的目的就是对过失速机动飞行条件下高度非线性的飞机动力学进行线化；

The purpose of the nonlinear dynamic inversion control is to linearize the highly nonlinear vehicle response at poststall maneuver conditions .

推力矢量控制技术和过失速机动使战斗机的空战效能大大增加，引起了世界各国的关注。

The thrust vectoring control technology and post-stall maneuverability enhance the aircraft 's combat effectiveness greatly , and cause the worldwide interest .

过失速机动飞机具有快速机头瞄准能力。

Post - stall technology ( PST ) aircraft has the rapid nose pointing capability and the advantage of attacking the adversary .

所设计的飞控系统将达到期望的飞行品质，确保系统对过失速机动飞行过程中因非定常气动力效应引起的系统参数摄动鲁棒性良好。

The resulting flight control system achieves desired flying qualities and guarantees good robustness to uncertainties induced by unsteady aerodynamics effects in poststall maneuvering .

为飞机敏捷性、直接力控制和过失速机动问题提供了一种理论研究方法。

The study will provide a new theoretical approach to investigate aircraft agility , the direct force control and post-stall maneuver of modern combat aircraft .

建立起一种具有推力矢量技术和过失速机动能力的现代飞机模型，并给出了控制律的解算方法。

A modern aircraft model with Thrust Vectoring ( TV ) technique and the post stall ( PST ) capacity and the control law are given .

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。

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 .

对典型过失速机动的运动特性进行了分析，根据其运动特点将过失速机动的运动过程分解为定直飞行、快速俯仰和绕速度矢量旋转三种基本运动的组合。

Based on the analysis of typical post-stall maneuvers , steady linear flight , rapid pitching and rolling about velocity vector are presented as three typical basic movements .

虽然关于过失速机动飞行中非定常气动力的研究已进行多年，但是过去的研究，主要集中在飞行姿态快速变化产生的非定常气动力上。

The unsteady aerodynamics about the post-stall maneuvering aircrafts has been studied for many years , but the most investigations mainly focus on the unsteady aerodynamics caused by the attitude angle changes of the aircrafts .

采用定常气动模型进行传统的飞行动力学分析，其结果与实际情况有较大差别。大迎角非定常气动建模是大迎角过失速机动飞行动力学分析的基础。

The traditional flight dynamic analysis based on steady linear aerodynamic model is inadequate at high angles of attack . Therefore , the appropriate unsteady aerodynamic modelling is the foundational research for the analysis of post-stall maneuvers .

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；

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 .

初步设计实例证明，这种方法适应于过失速机动动力学特点，能够获得发挥飞机操纵潜能、较好地控制飞机实现过失速机动、具有满意飞行品质的控制解，并且控制结构易于工程实现。

Preliminary design examples have shown that the design method presented here is suited to post stall maneuvering dynamics and can take full advantage of aircraft control potential . Furthermore , a control solution with satisfactory flying qualities can be conveniently achieved .

针对在过失速机动中气动/推力矢量控制面协调问题，分析了最小控制能量和链式递增两种典型控制面融合方式的特点。

This paper analyzed the characteristic of two typical methods of combination of control surfaces , the least energy control combination method and the chain combination method , according to the harmonization problem of aero / thrust vector control surfaces in post-stall maneuver .

研究大迎角飞行以及大迎角控制律，是提高新一代超音速战斗机过失速超机动格斗能力的重要方面。

It is very important to study high angle of attack flight and control laws that can enhance grapple ability of new supersonic fighter under the condition of post-stall supermaneuver .