气动布局

临近空间浮升一体化飞行器气动布局研究

Study of Aerodynamic Configuration Design for Buoyancy-lifting Vehicle in Near-space

单旋翼式直升机气动布局的几个问题

Some Problems on Aerodynamic Configuration for the Single Rotor Helicopter

基于三维直角网格Euler方程并行计算的气动布局优化研究

Aerodynamic Optimization of Aerodynamic Configuration Using Parallel Euler Solver and Cartesian Grid

针对某无人战斗机所采用的V形尾翼布局，通过求解N-S方程的数值计算方法，得到了上反与下反V形尾翼气动布局的纵向力矩值。

Aimed at the vee tail of an UCAV , the longitudinal moments of up vee tail and down vee tail are calculated by the method of solving N-S equations .

采用以N-S方程为主控方程的数值模拟方法，进行固定尾翼鸭式气动布局导弹的气动特性和流场数值模拟。

To investigate the rolling control characteristics of canard-controlled missile with fixed-tail , a numerical simulation method based on N-S formulation was conducted .

使用该数值算法，对某常规气动布局的MAV进行流场模拟和分析，并比较了其流场与常规尺寸飞行器的不同。

The difference of flows , around MAV and around a large one , was studied by using such numerical solution .

本文采用多目标遗传算法来确定再入飞行器气动布局优化问题的Pareto最优解集，并和传统的多目标优化方法（加权和方法、约束法）进行比较。

The Pareto genetic algorithm is modified to solve the engineering problems of the aerodynamic shape optimization of reentry body . The comparison of the traditional multi objective optimization methods with the Pareto genetic algorithm is also shown .

根据气动布局的基本原理，结合低RCS要求，设计了一种鸭式布局、带边条的翼身融合无人飞行器外形。

A " canard " configuration with blended fuselage and fringe of unmanned aerial vehicle ( UAV ) is designed according to the basic theory of aerodynamic layout and the low RCS demand and its aerodynamic characteristics test has been carried out .

浅析俄罗斯战斗机CY-37金雕前掠翼三翼面气动布局的先进性

Simple Analysis the Advantage of Russia 's CY-37 " Jin Diao " Forward-Swept Wing and Triplanar Aircraft on Aero Configuration

新气动布局飞机的过失速控制律设计

Post-Stall Maneuver Control Law for Aircrafts with New Control Configuration

同时分析了无尾飞翼气动布局的主要问题及其解决途径，设计思想符合航空飞行器设计规律。

This design thought conforms to the design rule of aviation craft .

轴流压气机叶栅新型气动布局结构的研究

A Study of New Type Configuration of Blade Cascade in Axial Compressors

巡航导弹气动布局的发展和分析

Development and analysis in aerodynamic configuration of cruise missile

单级入轨运载器气动布局研究

Computational Study on an Aerodynamic Configuration for SSTO Vehicles

分析了制导兵器的新型气动布局及特点；

Some new aerodynamic configurations of guided weapons and corresponding characteristics are analyzed .

重点分析前掠翼三翼面气动布局的先进性。

The analysis is focused the advantage of forward-swept wing and triplanar aircraft .

由结果可见，建立的气动布局可满足总体方案设想中飞行任务要求。

The results show that the aerodynamic layout can meet the aerodynamic requirements .

基于蚁群算法的高超声速飞行器气动布局优化设计

Optimization design of aerodynamic configuration for hypersonic cruise vehicle based on ant colony algorithm

两种气动布局飞机的着陆特性分析

Analysis of Landing Characteristics for Two Aircraft Configurations

制导兵器气动布局发展趋势及有关气动力技术

Trends in the Development of Aerodynamic Configuration of Guided Weapons and Relevant Aerodynamic Techniques

本文介绍了某型飞机前掠翼气动布局的低速风洞实验结果。

This paper gives a brief account of the subsonic experimental investigations of FSW models .

一种小展弦比高升力飞机的气动布局研究

A Research on the Aerodynamic Characteristics of a Small Aspect Ratio , High Lift Fighter Configuration

前掠翼气动布局中鸭翼高度影响的实验

Experimental investigation on the effects of the height of distant canard wing of a forward-swept configuration

本文对联接翼气动布局的直接升力控制特性进行了初步的探索。

This paper presents an approach to the direct lift control characteristics on the joined wing configuration .

单纯依靠结构设计、气动布局已难实现高品质的要求。

It is very difficult to implement high quality only depending upon the stucture design or aerodynamic configuration .

提出了一种多操纵面新气动布局飞机的过失速控制律设计方法。

A post stall maneuver control law for aircraft with new control surfaces and trust vectoring control is proposed .

提出了一种以动量轮为执行机构的具有中性静稳定气动布局的再入弹头姿态控制新方案。

A novel set of moment wheel actuators is proposed to control a reentry warhead with indifferently static stability .

结果表明，气动布局优化设计使再入飞行器的气动性能得到了明显的改善，从而证实了本文方法的有效性和实用性。

The optimization results verify the effectiveness , the validity and the practicability of the algorithms presented in the paper .

根据任务需求，对导弹的气动布局、动力系统、弹道方案、控制系统进行了设计研究。

The aerodynamic layout , propulsion system , trajectory system and guidance system are discussed according to the technical requirements .

在复杂外形的气动布局设计和气动特性预估中，发挥了积极的作用。

This procedure has played an active role in aerodynamic configuration design and characteristics calculation for aircraft B , C , D.