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《中国航空学报》2016,(6):1649-1663
Noises always disturb the control effect of an environment test especially in multi-input multi-output (MIMO) systems. If the frequency response function matrices are ill-conditioned, the noises in the driving forces will be amplified and the response spectral lines may awfully exceed their tolerances. Most of the major biases between the response spectra and the reference spectra are pro-duced by the amplified noises. However, ordinary control algorithms can hardly reduce the level of noises. The influences of the noises on both the auto-and cross-power spectra are analyzed in this paper. As a conventional frequency domain method on the inverse problem, the Tikhonov filter is adopted in the environment test to suppress the exceeding spectral lines. By altering regularization parameters gradually, the auto-power spectra can be improved in a closed control loop. Instead of using the traditional way of selecting regularization parameters, we observe the coherence change to estimate noise eliminations. Incidentally, the requirement of coherence control can be realized. The errors of the phase are then studied and a phase control algorithm is introduced at the end as a sup-plement of cross-power spectra control. The Tikhonov filter and the proposed phase control algo-rithm are tested numerically and experimentally. The results show that the noises in the vicinity of lightly damped resonant peaks are more stubborn. The response spectra are able to be greatly improved by the combination of these two methods. 相似文献
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In order to further study the performance of tightly integrated navigation system of GPS/INS, a semi-physical simulation of tightly coupled system has been done based on the data gathered from the experiment of integrated system of GPS and INS. The closed-loop Kalman Filter and U-D discompose algorithm have been used. The simulation results associated to four integrated models of pseudo-range, delta-range, pseudo-range and delta-range alternation, and pseudo-range and delta-range synthesis have been provided, and the actual effects of variously integrated models have been analyzed. The results show that the pseudo-range and delta-range synthesis coupled model is the most effective to improve the coupled system performance and the individual delta-range coupled model had better be avoided in application. 相似文献
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In safety-critical systems such as transportation aircraft, redundancy of actuators is introduced to improve fault tolerance. How to make the best use of remaining actuators to allow the system to continue achieving a desired operation in the presence of some actuators failures is the main subject of this paper. Considering that many dynamical systems, including flight dynamics of a transportation aircraft, can be expressed as an input affine nonlinear system, a new state representation is adopted here where the output dynamics are related with virtual inputs associated with the intended operation. This representation, as well as the distribution matrix associated with the effectiveness of the remaining operational actuators, allows us to define different levels of fault tolerant governability with respect to actuators’ failures. Then, a two-stage control approach is developed, leading first to the inversion of the output dynamics to get nominal values for the virtual inputs and then to the solution of a linear quadratic(LQ) problem to compute the solicitation of each operational actuator. The proposed approach is applied to the control of a transportation aircraft which performs a stabilized roll maneuver while a partial failure appears. Two fault scenarios are considered and the resulting performance of the proposed approach is displayed and discussed. 相似文献
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Numerical approach of hybrid laminar flow control(HLFC) is investigated for the suction hole with a width between 0.5 mm and 7 mm. The accuracy of Menter and Langtry’s transition model applied for simulating the flow with boundary layer suction is validated. The experiment data are compared with the computational results. The solutions show that this transition model can predict the transition position with suction control accurately. A well designed laminar airfoil is selected in the present research. For suction control with a single hole, the physical mechanism of suction control, including the impact of suction coefficient and the width and position of the suction hole on control results, is analyzed. The single hole simulation results indicate that it is favorable for transition delay and drag reduction to increase the suction coefficient and set the hole position closer to the trailing edge properly. The modified radial basis function(RBF) neural network and the modified differential evolution algorithm are used to optimize the design for suction control with three holes. The design variables are suction coefficient, hole width, hole position and hole spacing. The optimization target is to obtain the minimum drag coefficient. After optimization,the transition delay can be up to 17% and the aerodynamic drag coefficient can decrease by 12.1%. 相似文献
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The paper presents a new three-dimensional (3D) cooperative guidance approach by the receding horizon control (RHC) technique. The objective is to coordinate the impact time of a group of interceptor missiles against the stationary target. The framework of a distributed RHC scheme is developed, in which each interceptor missile is assigned its own finite-horizon optimal control problem (FHOCP) and only shares the information with its neighbors. The solution of the local FHOCP is obtained by the constrained particle swarm optimization (PSO) method that is integrated into the distributed RHC framework with enhanced equality and inequality con-straints. The numerical simulations show that the proposed guidance approach is feasible to imple-ment the cooperative engagement with satisfied accuracy of target capture. Finally, the computation efficiency of the distributed RHC scheme is discussed in consideration of the PSO parameters, con-trol update period and prediction horizon. 相似文献
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Radar equipment of stealth platforms such as aircraft have adopted the newest modern technology to design the signal waveforms. One of the important and effective methods is the hybrid waveform called spread spectrum stretch (S-cubed) which combines linear frequency modulation (LFM) and discrete phase code. In order to investigate the function of enemy’s stealth radar equipment, the interception algorithm of S-cubed is needed. In this paper, a novel detection and parameter estimation approach for the reconnaissance S-cubed radar signal is presented. First, the generalized time-frequency representation of Zhao, Atlas, and Marks (ZAM-GTFR) and Hough transforms (HT) are applied to detecting the signal, and then the initial frequency and modulation slope of LFM are estimated from the ZAM-GTFR. On the basis of LFM information, the reconstructing signal is generated. Finally, the code rate of discrete phase code is extracted from the negative peaks of the ZAM-GTFR. Simulation results show that the proposed algorithm has higher estimation accuracy when the signal to noise ratio (SNR) is above 3 dB. 相似文献
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《中国航空学报》2016,(2):424-440
The state estimation strategy using the smooth variable structure filter(SVSF) is based on the variable structure and sliding mode concepts. As presented in its standard form with a fixed boundary layer limit, the value of the boundary layer width is not precisely known at each step and may be selected based on a priori knowledge. The boundary layer width reflects the level of uncertainty in the model parameters and disturbance characteristics, where large values of the boundary layer width lead to robustness without optimality and small values of the boundary layer width provide optimality with poor robustness. As a solution and to overcome these limitations, an adaptive smoothing boundary layer is required to achieve greater robustness and suitable accuracy.This adapted value of the boundary layer width is obtained by minimizing the trace of the a posteriori covariance matrix. In this paper, the proposed new approach will be considered as another alternative to the extended Kalman filters(EKF), nonlinear H1 and standard SVSF-based data fusion techniques for the autonomous airborne navigation and self-localization problem. This alternative is based on strapdown inertial navigation system(SINS) and GPS data using the nonlinear SVSF with a covariance derivation and adaptive boundary layer width.Furthermore, the full mathematical model of the SINS/GPS navigation system considering the unmanned aerial vehicle(UAV) position, velocity and Euler angle as well as gyro and accelerometer biases will be used in this paper to estimate the airborne position and velocity with better accuracy. 相似文献
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储海燕 《西安航空技术高等专科学校学报》2011,29(5):55-56,60
为了扩大DSP技术应用范围,通过在工业控制、信息安全等领域的DSP应用产品的介绍,结合DSP方案与传统MCU方案的比较,得出DSP具有速度快、功能强、功耗低、价格便宜、软/硬件开发方便、灵活的结论。 相似文献
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从电解电源的高频高效化、绿色化、数字化及智能化的发展方向出发,利用电流增强原理,设计了一种开关管带并联辅助网络的零电压全桥软开关电路拓扑,具有节能增效、可靠性高的优点.采用TMS320LF 2407A为核心控制芯片.得到了全桥移相PWM输出波形,并设计了反馈信号调理电路与后端驱动电路,电路形式简单紧凑,实现了软开关电解电源的全数字化控制. 相似文献
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航空变频交流电源发电机突然短路是一种常见的故障情况,其瞬变过程值得展开深入研究。针对用于航空变频交流发电系统的双定子绕组异步发电机(DWIG),分析了两套绕组同时发生对称突然短路的情况,运用解析法给出了短路电流的衰减规律,最大短路电流计算公式及到达时刻。研究结果表明,DWIG在短路时定子绕组中将产生两个直流衰减分量和一个旋转衰减分量,分别对应两套定子绕组和转子的影响,其瞬态电抗的形式与带阻尼绕组的同步电机直轴超瞬变电抗类似,并与瞬态电流的峰值成反比关系,分析表明DWIG短路电流的峰值小于同步发电机。所得的结果能够有助于深入理解DWIG的瞬态特性,获得的解析公式有助于对发电机突然短路电流进行估算,辅助发电机电磁设计,可以为发电系统保护单元和控制器的设计提供理论参考。 相似文献
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为增强微电网小干扰电压稳定性,针对含双馈感应风力发电机(DFIG)的风光柴微电网,DFIG无功控制采用V-Q下垂控制并引入积分逻辑环节,同时计算变风速情况下DFIG有功功率对应的无功功率极限,对V-Q下垂控制与积分环节进行限幅。通过小干扰分析法找出了一对反映微电网电压响应特性的典型特征值,分析DFIG无功下垂系数取不同值时对典型特征值分布轨迹的影响。为了解决无功下垂系数取较大和较小值时带来的问题,经过参数改进后既促进了DFIG参与微电网调压的效果,又使微电网拥有更好的小干扰电压稳定性。最后在DIgSILENT/Power Factory仿真软件中搭建微电网模型,通过动态时域仿真验证了所提策略和方法对促进微电网调压以及提高微电网小干扰电压稳定性的有效性。 相似文献
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设计了一种基于PC/ DSP ( Personal Computer / Digital Signal Processor) 的ICT ( Industr ial ComputedTomography) 图像重建系统, 论述了整个系统的硬件组成和工作原理, 介绍了系统中PCI 型DSP 信号处理板的设备驱动程序的主要内容, 给出了整个系统的试验结果。结果表明: 该系统能有效缩短ICT 图像重建的时间, 提高ICT 检测的工作效率。 相似文献