ID 原文 译文
9834 为得到高可靠性再入轨迹,在倾斜角搜索过程中,除了使再入参考轨迹满足路径约束与终端约束外,同时将QEGC的应用前提"飞行路径角及其变化率为小量"作为倾斜角搜索的一项约束。 ‭To obtain high reliability reentry trajectory, in the process of gradient search, in addition to satisfy reentry reference trajectory path constraint and terminal constraints, at the same time will be the application premise of QEGC "flight path Angle and its rate of change for a small" as a constraint of gradient search. ‭
9835 计算结果表明所提方法能够保证再入轨迹的可靠性,同时基于QEGC规划方法的适应性得到保留。 The calculation results show that the proposed method can ensure the reliability of the reentry trajectory, QEGC planning method based adaptive preserved at the same time. ‭
9836 在高动态链路中存在大多普勒频偏,直接序列扩频(direct-sequence spread spectrum,DSSS)接收机必须具有大捕获带宽。 In high dynamic link mostly doppler frequency offset, direct sequence spread spectrum (direct - sequence spread spectrum, DSSS) receiver must have a big capture bandwidth.
9837 现今广泛使用的部分匹配滤波加快速傅里叶变换运算(partial matching filter-fast Fourier transform,PMF-FFT)方法的捕获带宽受限于其FFT运算点数,难以适应高动态场景。 Nowadays widely used part of the matched filtering and fast Fourier transform arithmetic (partial matching filter - fast Fourier transform, PMF - FFT) method to capture bandwidth is limited by the FFT operation points, difficult to adapt to the high dynamic scenes.
9838 因此,提出一种低复杂度大带宽的折叠PMF-FFT捕获方法。 Therefore, put forward a kind of low complexity, large bandwidth folding PMF - FFT capturing method.
9839 该方法首先对接收信号和本地伪码分别作折叠,即分段求和,然后再按照PMF-FFT方法处理。 This method first to receive signal and the local pseudo-code for folding respectively, namely the subsection summation, then according to the PMF - FFT method.
9840 理论分析和仿真结果表明,在更低计算复杂度下,折叠长度为F的折叠PMF-FFT方法的捕获带宽能够达到PMF-FFT方法的F倍。 Theoretical analysis and simulation results show that under the lower computational complexity, folding length is F folding PMF PMF can be achieved - FFT method to capture bandwidth - F times the FFT method.
9841 使用微机械电子(micro electro mechanical systems,MEMS)惯导系统(inertial navigation system,INS)的飞行器由于其MEMS惯性器件测量精度低,致使导航误差快速发散。 Using the micro mechanical electronics (micro company mechanical systems, MEMS) inertial navigation system (inertial navigation system, INS) aircraft because of its low MEMS inertial device measuring precision and the navigation error spread quickly.
9842 针对该问题,提出了一种利用飞行器动力学(aircraft dynamics,AD)信息辅助MEMS惯导解算的方法。 ‭Aiming at the problem, put forward a way to use aircraft dynamics (aircraft dynamics, AD) the method for calculating auxiliary MEMS inertial navigation information.
9843 它基于AD建立的飞行器运动模型和运动误差模型,利用实时解算的飞行器运动状态构建卡尔曼滤波器对MEMS惯导误差进行估计和修正。 ‭It is based on the AD aircraft motion model is established and the motion error model, using real-time decoding of aircraft motion state kalman filter for MEMS inertial navigation error estimation and correction.