本文首先介绍了无人机飞控系统的设计过程，采用模型飞行试验进行控制律参数设置与确定。
Firstly, the paper introduce the process of design the UAV AFCS, which use the test of model fly to confirm the control principle parameter.
利用飞行试验信号对发动机模型辨识进行了研究。
The engine model identification using flight test signals is introduced.
论文使用了现代参数辨识技术的ARMAX模型递推法和状态子空间辨识法，对飞行颤振试验数据进行处理，辨识飞机的颤振模态参数。
ARMAX model method and subspace-based state space method were used to process the flight flutter test data, and identify the flutter modal parameters of aircraft.
飞行试验表明此模型具有较高的置信度。
Flight test shows that the confidence of this model is higher.
利用旋臂式模型机动飞行试验机进行倾转过渡状态下旋翼瞬态拉力的试验研究，试验与理论计算结果表现出很好的相关性。
The experiment of transient rotor thrust during transition flight has been carried out on whirling beam test facility, and the experimental results show excellent agreement with theory.
对某飞船返回舱的飞行试验数据进行了计算和分析，结果证实了弹道重建数学模型的正确性和算法的可行性。
The flight test data of some a reentry capsule are analyzed. The results validate the developed mathematical model and algorithm of trajectory reconstruction.
本文采用飞行器六自由度运动方程组，建立了飞行试验数据相容性检验的数学模型。
In this paper, the mathematical model of compatibility check of flight test date is set up based on the kinematic equations with six freedom of aircraft.
大振幅试验，非定常空气动力，空气动力模型，洞壁干扰，动导数仿真，数学模型，模糊逻辑，飞行仿真。
Large amplitude test, Unsteady aerodynamic, Wall influence, dynamic derivative simulating, Mathematic model, Fuzzy logic, Aerodynamicmodeling, Flight simulating.
用分析和模型试验方法难以确定可靠的尾翼载荷，所以要求通过飞行试验获取尾翼载荷数据，但因测载技术复杂，精确地测定尾翼载荷亦是困难的。
Airplane tail loads are difficult to determine accurately by means of model tests and theoretical analysis. In order to obtain reliable tail load data, it should be determined by flight tests.
将高速滑体制成相似的机翼模型，进行风洞试验，即可测定滑坡凌空飞行的空气动力学参数，从而计算大型高速滑坡凌空飞行的空气动力升力、飞行速度和飞行距离等。
If we make a wing model which is similar to sliding mass, we can determine aerodynamic parameters by the wind tunnel testing and thus calculate the lift.
通过建立扇翼飞行器的二维数学模型进行模拟分析、设计试验模型并进行了相关实验比较分析，证明垂直升降的可行性。
According to comparative analysis between the 2d mathematical model simulation and the of test model design of fan wing aircraft, the feasibility of VTOL is proven.
虽然模型机在一次模拟风洞飞行试验中取得成功，但这项设计没有被继续下去。
Although good results were obtained with a model in the windtunnel, this design was not followed up.
仿真结果表明，与实际飞行试验数据达到非常好的拟合，说明采用六自由度的制导控制系统的数学模型进行设计的正确性。
Numerical simulation results for sample engagement scenarios are given. It shows that simulation results are very close to the actual flight test results. So …
仿真结果表明，与实际飞行试验数据达到非常好的拟合，说明采用六自由度的制导控制系统的数学模型进行设计的正确性。
Numerical simulation results for sample engagement scenarios are given. It shows that simulation results are very close to the actual flight test results. So …
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