• Applying the micro-diagnosis method, the measurement of main-board of flight parameter is realized. The covering rate of fault is high.

    本文应用微诊断法,实现了对飞参主控计算机主机板的测试,故障覆盖率高。

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  • The functions and purposes of flight parameter controller are described. Design of the hardware and programming of the software and application are presented.

    介绍了飞参控制器的功能用途,其硬件电路设计、软件编程及实际应用情况。

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  • How the variation of take-off suspension weights affects the structural fatigue life is investigated through surveying actual flight parameter recorder (FPR) data.

    主要通过飞行参数记录仪(FPR)记录的数据研究战斗机起飞外挂重量对飞机结构疲劳寿命的影响。

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  • Through calculating service temperature by flight parameter and based on the flight training program, infield and outfield test-fly program, and compares the result with actual-measurement.

    包括用飞行训练大纲和内厂、外场试飞大纲作为飞行剖面编制的依据; 以飞参数据作为温度载荷的原始输入; 采用大气状态下的实测结果进行温度校正计算等。

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  • This paper mainly studies how to accurately fit the air dynamics parameter by the ballistic data of projectiles' free flight.

    论文主要研究从弹丸自由飞行数据中如何准确地拟合空气动力系数。

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  • We designed the flight program for solid launch vehicles, resolved the control parameter of ascent trajectory with modified Newton iterative method, and deduced the iterative formula.

    设计了固体运载火箭上升段飞行程序,应用修正牛顿迭代法求解上升段弹道控制参数,推导了迭代算法公式。

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  • This paper presents mainly parameter selection characteristic of autopilot and effect to flight quality of aircraft, after a basic configuration of fixed gain control augmentation system is shown.

    文中在给出了固定增益的控制增稳系统的基本组成之后,着重介绍自动驾驶仪的参数选择特点及其对飞机飞行品质的影响。

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  • Atmosphere parameter collection and process is important for the safety of the flight of small aircraft.

    大气数据参数的采集和处理是保证小型飞行器飞行安全的重要因素。

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  • A mathematical model is established solely according to two kinds of warhead fuze modes considering that atmosphere parameter error works on the flight of warhead explosion spot of ballistic missile.

    以等高程和等过载引信两种弹头引信方式建立了大气参数偏差对弹道式导弹弹头引爆点射程影响的数学模型;

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  • A method based on the set-membership identification theory for the parameter identification of a helicopter fully coupled flight dynamics model is presented.

    提出了一种基于集员辨识理论的直升机全耦合飞行动力学模型参数辨识方法。

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  • Taking the lateral flight control system of an aircraft as an example, simulation was carried out for the cases with perturbing parameter and interference.

    以某型飞机侧向飞行控制系统为例,针对系统参数摄动和承受有界干扰情况,对所提出的方法进行了仿真分析与验证。

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  • This paper introduces the parameter estimation research for the turbine inlet temperature and compressor exit pressure by using the engine variables measured under the different flight conditions.

    本文研究利用不同飞行状态下测量的发动机变量估计涡轮进口温度和压气机出口压力。

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  • These equations are very important for engine parameter calculation in missile flight test, The empirical calculation equations of main engine parameter and error are derived.

    就发动机主要参数及误差的经验计算公式进行了推导和确定。

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  • The precision of time fuze rests with many factors, but the muzzle velocity of a projectile is a key parameter which decides on flight characteristic of a projectile.

    时间引信的精度取决于多种因素,但弹丸初速是决定弹丸飞行特性的主要参数。

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  • When the current flight management computer system(FMCS)optimizes flight, it assumes the flight line is an invariable parameter.

    目前的机载飞行管理计算机系统(FMCS)在进行飞行优化时,视航路为固定常量。

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  • When the current flight management computer system(FMCS)optimizes flight, it assumes the flight line is an invariable parameter.

    目前的机载飞行管理计算机系统(FMCS)在进行飞行优化时,视航路为固定常量。

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