这一方法主要应用于自主式机动飞行器。
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.
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.
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.
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.
研究了刚体飞行器大角度机动的姿态控制问题。
In this paper, attitude control problem of a rigid spacecraft with large Angle maneuvers is investigated.
本文运用飞行力学原理和现代控制理论，对攻击地面固定目标的飞行器的再入机动制导方法进行了研究。
In this paper, the method of reentry maneuver guidance applying to attack the ground fixed target is described by using flight dynamics principle and modern control theory.
本文研究空间飞行器大角度姿态机动的控制问题。
This paper deals with the large Angle attitude maneuver control of spacecrafts.
文提出一种关于再入飞行器程序机动飞行的制导方案。
Programming maneuvering flight guidance scheme about reentry vehicle is presented in this paper.
研究了在降弧段进行高空机动的再入飞行器最优制导律。
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
本文主要讨论再入飞行器机动弹道的设计问题。
This paper mainly discusses the design of maneuverable trajectories of re-entry vehicle.
研究空间飞行器大角度姿态机动反馈开关控制的消振参数优化设计问题。
The optimization design problem of controller parameters of optimal on-off times attitude maneuvers with switch moment is investigated.
并应用这两种方法针对视线坐标系的两空间飞行器在目标机动下的追逃进行了理论推导和实验仿真。
Theory analysis and experimental simulations of pursuit-evasion problem with maneuvering target in sight coordinate system are performed using the two methods.
将嵌入大量微致动器元件的智能蒙皮应用于飞行器，以增强或替代传统的控制面来产生控制力矩，使飞行器稳定并能进行机动飞行。
The smart skin which embedded hundreds of micro effectors was used in an advanced aircraft to generate moments for stabilization and maneuver, by augmenting or replacing conventional control surfaces.
航天飞行器在再入大气过程中会受到严重的气动加热。返回式卫星、飞船返回舱及航天飞机等采取高空机动再入，再入时间长，其峰值加热过程一般在60-90千米高空。
Spacevehicles such as spacecraft and space shuttle are subjected to severe aerothermal environment with the peak heating at height of 60~90km while they maneuver to reentry the earth's atmosphere.
实验系统不但能够模拟柔性航天结构的运行环境，还能对由于航天飞行器的机动和折叠结构的展开而引起的振动进行模拟。
This system could emulate not only the work conditions, but also the motion of space structures and deployment of the foldable structures.
该方法利用最优控制理论的思想方法，不仅使飞行器命中目标时满足了终端角度约束的条件，而且保证了再入飞行器机动速度损失最小。
The guidance method satisfies terminal angular constraint as reentry vehicle hitting target, but also ensures minimum loss of maneuvering velocity for reentry vehicle.
可变弯尾飞行器的气动方案是高超声速机动的潜在可行方案。
Variable bend tail concept may be one of the possible approaches for satisfying the maneuvering requirement of hypersonic reentry vehicle.
一种易脱离球形燃料箱利用球类在各向受力均等，具有耐冲击的特点，制成飞行器或机动车辆的燃料箱。
A easily separable ball-shaped fuel tank is based on the the ball can be equally stressed in different direction and has high impact resistance.
一种易脱离球形燃料箱利用球类在各向受力均等，具有耐冲击的特点，制成飞行器或机动车辆的燃料箱。
A easily separable ball-shaped fuel tank is based on the the ball can be equally stressed in different direction and has high impact resistance.
应用推荐