然而，通过自由落体测试，研究者可以量化的测量翅果的飞行动力并且用得到的信息数据来控制翅果的自旋和飞行轨迹。
However, through free-fall testing, the researchers could quantitatively measure the samara's flight dynamics and use this information to control the samara's autorotation and flight path.
战神一号X型将上升到约40公里(约25英里)的高空，在其动力飞行阶段，将不间断地对其运载空气动力学指标、火箭的第一阶段的控制和表现进行测量。
The 1-x will climb about 40km (25 miles) into the sky during the powered phase of its flight, continuously measuring vehicle aerodynamics, controls and performance of the rocket's first stage.
针对无人机近距离编队飞行问题，采用极值搜索算法，解决其中僚机所需动力最小化的控制问题。
An approach based on extremum seeking algorithms for the minimum power demand of the wingman in formation flight of an UAV is presented.
为了优化无人驾驶航空飞行器在整个飞行过程中的空气动力特性而使机身、推进系统和升力控制面一体化的设计技术。
Design technology for integration of air vehicle fuselage, propulsion system and lifting control surfaces to optimize aerodynamic performance throughout the flight regime of an unmanned air vehicle.
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.
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.
例如在现代飞行器中，动力助推控制系统将飞行员的力放大以推动受到很大的气流作用的机翼表面。
In a modern aircraft, for example, the power boost controls amplify the force applied by the pilot to move the control surface against large aerodynamic forces.
介绍了将DMC - PID串级控制技术应用到无人机无动力飞行时的自动着陆阶段迎角自动控制系统。
DMC-PID bunches control technology in the Angle of attack automatic control system during unpowered flying automatic landing period is introduced.
它是处于空气动力学、飞行力学、弹性力学和现代控制论之间的应用性研究课题。
So, IAAP is an interdisciplinary-science, which bridges the flight mechanics, aerodynamics, elasticity and cybernetics.
但早期飞行，美国宇航局表示，“表明，在X - 3是严重动力不足，难以控制。”
But early flights, NASA said, "showed that the X-3 was severely underpowered and difficult to control."
本文提出飞机中性稳定技术应用于综合火力 /飞行控制系统 ，给出了中性稳定飞机结构图和动力学模型。
In this paper, the authors try to apply neutral stability mode of the aircraft direct force Control technology to the air-to-air gunnery mode of the integrated flight/fire control system.
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.
本发明的优点是显而易见的，推动这种飞行器所需要的动力很小的，很容易控制飞行速度。
The aircraft has the obvious advantages that the aircraft requires very small power to be driven and flying speed can be easily controlled.
分析认为PPT是一种先进的小推力动力装置，特别适合于微小卫星的轨道转移、姿态控制、位置保持以及星座编队飞行。
It was showed that PPT was a kind of advanced propeller with small thrust, which was suitable to orbit transfer, attitude control, station keeping and formation flying for small and micro satellite.
简要介绍了卫星编队飞行的动力学与控制研究的最新进展，对今 后研究工作的重点提出了建议。
The paper briefly reviews the new research progress of satellite formation flying dynamics and control, and presents some key points for future research.
飞机液压系统作为飞机飞行控制系统和起落架等负载的动力源，对飞机的安全飞行起着关键的作用。
As the power source of the aircraft flight control system and landing gear loads, aircraft hydraulic system plays a key role for the safety of aircraft flying.
对慢变量进行非线性逆控制器的设计可使飞行员控制飞机慢动力学，即迎角、侧滑角和速度矢量滚转角。
Another nonlinear inversion controller was designed for the slow variables. It allows the pilot to control the slow dynamics, the Angle of attack, side-slip Angle and the velocity bank Angle.
航天工程专业也涉及到空气动力学，发射，飞行控制和发动机等。
They also study such topics as aerodynamics, launch, flight controls, and engines.
首次推导了基于质量控制和推力矢量控制的一类无尾无舵翼碟形飞行器的空间六自由度运动动力学方程。
The six degrees of freedom dynamic equation of a kind of mass-controlled and thrust vectoring-controlled saucer-like air vehicles without tailes, wings and rudders was derived for the first time.
本文研究了自由飞行空间机器人 （FFSR）关节驱动力矩的求解算法及在其基础上的捕捉目标控制算法 。
This paper studies the computation algorithm of joint driven torque and the control algorithm to capture target for Free Flying Space Robots(FFSR).
针对无人机近距离编队飞行问题，采用极值搜索算法，解决其中僚机所需动力最小化的控制问题。
To solve the problem of unmanned aerial vehicle (UAV) formation flight, an approach of modeling close formation flight of UAV is presented.
针对无人机近距离编队飞行问题，采用极值搜索算法，解决其中僚机所需动力最小化的控制问题。
To solve the problem of unmanned aerial vehicle (UAV) formation flight, an approach of modeling close formation flight of UAV is presented.
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