针对过失速机动飞机探讨了非线性动态逆方法在飞行控制系统设计中的应用。
This paper discussed the application of this method in the design of flight control system for the post stall maneuver.
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.
这些芯片能将飞行员的脑电波直接发送到飞行控制系统，这样就极大地改善了机动战士的反应能力和操纵性能。
These chips transmit the pilot's brainwaves directly into the flight control system, vastly improving the response and handling characteristics of the mobile suit.
仿真计算结果表明，采用脉冲控制模式，本文提出的安全轨迹制导策略能够实现小卫星临近作业的安全机动飞行。
The results of the simulation indicate that the safety trajectory guidance strategy can achieve safety maneuver flying of the small satellite proximity operation when using thrust control method.
这些高机动性，电脑控制的小飞机，撕裂敌军的飞行编队，强大的等离子电荷无情的扫射地面目标，使其行动缓慢。
These maneuverable computer-guided craft tear through enemy flight formations and relentlessly strafe slower ground targets with potent plasma charges.
根据飞行控制要求，考虑了影响较大的气动力和气动力矩因素，建立了一个完全表征大机动情况下弹头运动的非线性动力学模型。
According to the demand of flight control system, a nonlinear dynamics model with considerable aerodynamic forces and moments for a large maneuver re entry missile head is built.
本文就武装直升机大机动、高敏捷性神经网络鲁棒自适应飞行控制系统的设计问题展开研究。
The robust adaptive flight control system design with neural network of attack helicopter is studied in this dissertation and super maneuver nimble of attack helicopter is realized.
两根外伸支架上有四个小型方向控制片，为飞行摩托提供机动性。
A quartet of small directional steering vanes on twin outriggings afford the speeder its maneuverability.
研究了超机动飞行推进系统稳定性控制。
A study of propulsion system stability control for super maneuvering flight was carried out.
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.
阐明了针对大空域机动反舰导弹飞行空域大、速度变换范围大的特点，采用增益调度的方法设计其控制系统。
For Large aerospace maneuvering anti-ship missiles(LAMASM), which fly in large aerospace with velocity varies in large range, a gain schedule autopilot is designed.
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.
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.
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.
快速控制菜单最适宜玩家在战场上空实行机动飞行操控，随便你看什么，选控系统都能够反映出来。
The quick-command menu is great for reacting to the battle field on the fly, the available options changing to reflect whatever you're looking at.
通过侧杆的高气压转变成电信号，并最终转化成飞行控制面如副翼和舵面的实际机动。
Hand pressure on the side stick controller sends electrical signals to actuators of flight control surfaces such as ailerons and rudder.
针对12维非线性飞机动力学模型，利用非线性逆系统理论和现代最优控制理论设计了一组非线性飞行控制规律。
Based on 12-state nonlinear aircraft dynamic model, a nonlinear flight control law is designed by using nonlinear inverse dynamics and modern optimal control theory.
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.
讨论了一种基于神经网络动态逆的直接自适应控制方法，并应用于超机动飞机的飞行控制中。
An adaptive controller with a neural network compensator is designed and applied in the control of a super-maneuvering aircraft.
直升机飞行动力学逆问题是研究已知运动的控制规律，对直升机机动飞行和现代飞行控制律设计有重要意义。
Inverse problem of helicopter flight dynamics, to solve control laws from given motion, is important to the study for the maneuvering flight and the design for the advanced flight control system.
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.
带传统线性控制器飞机在大迎角高机动飞行时敏捷性明显地减小，运动状态严重耦合更加重这一趋势，而此时操纵能力往往仍有剩余而却未能被利用。
The agility of aircraft with conventional linear flight controllers tends to drop rapidly under high angles of attack, and kinematic coupling of motions furtherly promotes the tendency.
计算仿真表明，该控制器能够较好地发挥飞机的操纵潜力，可使飞机在获得较好的过失速机动能力的同时具有较为满意的飞行品质。
The simulation results have been shown that this controller can take full advantage of aircraft control potential and improve the post stall maneuverability with satisfactory fl...
根据相对轨道要素的变轨机动控制，进行编队飞行卫星群构型的初始化。
The configuration initialization of satellite formations is carried out based on orbit maneuver control...
直升机自转进入和退出是直升机机动飞行经常遇到的状态，它的特性是由直升机旋翼和发动机的安装特性共同决定的，该状态的发动机控制是典型的直升机与发动机的综合控制。
It is a characteristic of the helicopter rotor and its engine installation, and the engine control in this condition is a typical integration control of the helicopter and the engine.
计算仿真表明，该控制器能够较好地发挥飞机的操纵潜力，可使飞机在获得较好的过失速机动能力的同时具有较为满意的飞行品质。
The simulation results have been shown that this controller can take full advantage of aircraft control potential and improve the post stall maneuverability wi…
计算仿真表明，该控制器能够较好地发挥飞机的操纵潜力，可使飞机在获得较好的过失速机动能力的同时具有较为满意的飞行品质。
The simulation results have been shown that this controller can take full advantage of aircraft control potential and improve the post stall maneuverabil…
计算仿真表明，该控制器能够较好地发挥飞机的操纵潜力，可使飞机在获得较好的过失速机动能力的同时具有较为满意的飞行品质。
The simulation results have been shown that this controller can take full advantage of aircraft control potential and improve the post stall maneuverabil…
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