机动飞行器

本文提供了改进的空间Euler方程推进方法和稳定方法，可有效地计算再入机动飞行器的流场，然而，这种数值方法计算再入飞行器的气动特性耗机时多，经费昂贵。

A method for solving improved space marching Euler equations and a method for solving time-dependent Euler equations are presented in this paper . They are efficient in calculating flow fields for maneuvering reentry vehicles ( MaRVs ) . However , the cost for the numerical computation is expensive .

可变落点的再入机动飞行器姿控系统设计

Attitude Control System Design of the Maneuverable Reentry Vehicle for Variable Target

机动飞行器再入的变结构导引控制

Re - entry Guidance with Variable structure for Maneuverable Vehicle

这一方法主要应用于自主式机动飞行器。

This method is mainly applied for autonomous mobile vehicles .

再入机动飞行器的控制系统设计

Control System Design of a Maneuverable Reentry Vehicle

基于轨迹线性化的再入机动飞行器控制器设计

Maneuvering re-entry vehicle controller based on trajectory linearization

机动飞行器的混合制导

Hybrid guidance about maneuvering flight vehicle

大迎角风洞试验技术是先进高机动飞行器研制必需的关键技术。

High angle of attack wind tunnel test techniques is necessary for development of high-maneuverability flight vehicles .

因此，进行轨道机动飞行器的自主快速机动控制技术及其工程实现研究，就具有重要的意义。

Hence , the research on autonomous and rapid maneuver and implement of space maneuver vehicle presents significance .

建立在机动飞行器内具有初始弯曲和不对称刚度的单盘转子的动力学模型，研究重力方向与转子轴间夹角变化对等速运行转子幅频特性曲线和等变速运行转子瞬态响应的影响。

A new mathematical model of a rotor with initial bending and stiffness asymmetry in a maneuvering aircraft is presented .

结果表明，过载反馈系统在再入机动飞行器的飞行控制中效果较好。

The results shows that the overload feedback structure is better than the attitude feedback structure on the maneuverable flight control .

研究了轨道机动飞行器对地球同步轨道卫星的抵近飞行过程。分析了不同过捷点距离下的视线角速度和视线角加速度的变化规律。

The law of angular velocity and angular acceleration of line of sight is analyzed under different closest distances between OMV and target .

高速大迎角动态气动特性是衡量新一代高机动飞行器性能的重要参数之一。

Dynamic aerodynamics characteristic is one of very important parameters of modern maneuverable aircraft to be scaled at high angle of attack and high speed .

利用典型状态的风洞试验结果对十字布局与叉字布局再入机动飞行器的气动特性进行了分析与比较。

In this paper aerodynamic characteristics of maneuvering reentry vehicle of cruciform configuration and bifurcate configuration are compared by means of the wind tunnel test results .

对于地球同步轨道卫星的检查，论文提出了一种利用大椭圆轨道机动飞行器对其抵近照相的方法，并研究了相关技术。

According to the problem of examining GEO satellites , the paper has given a method of using orbit maneuver vehicle on highly eccentric orbit to photograph the target and studied related technologies .

论文提出的椭圆远程、近程最优交会策略和末制导导引律可为轨道机动飞行器空间交会方案设计与轨道控制提供技术支撑。

The proposed optimal rendezvous strategies both for long-distance elliptical rendezvous trajectory and near-distance elliptical rendezvous trajectory and terminal guidance laws will provide technique support for the space rendezvous scheme design and orbit control of OMV .

它们是。空间机动飞行器的导引法，弹体的滚动姿态控制方案，纵平面内机动突防弹道的设计以及摄动制导方程的编排。

They are the guiding scheme for space maneuvering vehicle , the roll control program of attitude for the body , the design of maneuvering penetrating trajectory in longitudinal plane and the mechanization of perturbed guidance equation .

为满足一种新型大机动飞行器飞行姿态半物理仿真的要求，采用变增益液压伺服机构和变系数前馈补偿器等技术，对某三轴液压飞行仿真转台进行了改型研制。

The techniques on variable-gain hydraulic servomechanisms and variable-coefficient feedforward compensators have been used for an operational development of a certain three-axis hydraulic flight simulation table to satisfy demands of semi-physical simulation of flight attitudes of a new aircraft with high maneuverability .

本文建立了位于机动飞行飞行器内且同时具有初始弯曲、不对称刚度和质量不平衡的单盘Jeffcott转子的动力学模型。

A mathematical model of an unbalanced rotor system located in aircraft with asymmetric rigidity and initial bending is given in this paper .

机动飞行飞行器内具有初始弯曲和刚度不对称的转子运动模型

Mathematical Modeling of a Maneuvering Asymmetric Rigidity Rotor with Initial Bending

机动再入飞行器自适应自动驾驶仪设计

Designing for a new adaptive autopilot of maneuvering entry vehicles

具有终端角度约束的机动再入飞行器的最优制导律

An Optimal Guidance Law of Maneuvering Reentry Vehicles with Terminal Angular Constraint

弯体机动再入飞行器气动特性研究

A Study for Aerodynamic Characteristics of Bented Maneuvering Reentry Vehicle

本文计算和分析了弯体机动再入飞行器的高超声速纵横向气动特性。

Hypersonic characteristics of bented maneuvering reentry vehicle were calculated and analysed .

机动再入飞行器自适应飞行控制系统设计

The Design for a New Adaptive Flight Control System of Maneuvering Entry Aerospacecraft

机动再入飞行器主动段再入点约束闭路制导研究

Study of the closed-loop guidance law for boost phase with reentry constraints of maneuvering reentry vehicles

解决了机动再入飞行器在气动系数变化范围大和气动耦合严重等恶劣条件下的姿态和过载控制问题。

The control of attitude and acceleration for maneuvering entry vehicles is obtained in the case that the aerodynamic parameters changing in the large-range and the pneumatic coupling is very strong , in which the control of attitude and acceleration is rather difficult .

本文分析了机动再入飞行器因非定常空气动力流动引起的物面脉动压力环境，并根据高超声速无粘流计算的表面压力分布，给出了一套预测各种脉动压力环境统计特性的工程计算公式。

The surface fluctuating pressure environments of a maneuvering reentry vehicle resulting from unsteady aerodynamic flows have been investigated . According to surface pressure distribution calculated by hypersonic inviscid flow a set of prediction formulate of the statistical properties for the various fluctuating pressure environments have been given .

机动车辆或飞行器中向发动机提供燃料的装置。

Equipment in a motor vehicle or aircraft that delivers fuel to the engine .

在进行快速机动时，飞行器将遭受较大的非定常气动力和显著的气动力迟滞效应，从而对飞行性能和控制都产生很大的影响。

When there is a rapid maneuver , the vehicles will encounter a big unsteady aerodynamic force and sluggish aerodynamic force , which may bring prodigious influence on flight performance and the control of the vehicles .