激光制导武器光斑形状半实物仿真技术研究

在激光制导武器半实物仿真试验中，其中一个要求就是激光目标模拟器为导引头提供的光斑形状应与其在实战环境下“看到”的一致。根据激光制导武器制导原理，建立了实战条件下激光光斑形状模型，并设计了光斑形状半实物仿真系统。依据仿真相似性原理，建立了仿真条件下的光斑形状数学模型及激光目标模拟器发射的激光束散角数学模型，讨论了照射误差对光斑形状的影响。通过仿真分析证明这些模型是正确的。     

“鑫诺一号”卫星真空热试验介绍

“鑫诺一号”卫星在法宇航中心的空间环境模拟器中历时20天完成了真空热试验(包括热平衡试验和热真空试验)。文章对“鑫诺”卫星及空间环境模拟器作了简要说明,分析了试验的目的和要求,介绍了试验的过程和结果,并与我国同类试验进行了比较。     

PC机遥测数据处理系统若干关键技术的设计及实现

详细阐述 PC机遥测数据处理系统中基线调整电路、模拟源、入盘接口和时间码电路及数据处理软件的设计与实现。     

Hardware-In-the-Loop Simulations of spacecraft attitude synchronization using the State-Dependent Riccati Equation technique

A nonlinear control technique pertaining to attitude synchronization problems is presented for formation flying spacecraft by utilizing the State-Dependent Riccati Equation (SDRE) technique. An attitude controller consisting of relative control and absolute control is designed using a reaction wheel assembly for regulator and tracking problems. To achieve effective relative control, the selective state-dependent connectivity is also adopted. The global asymptotic stability of the controller is confirmed using the Lyapunov theorem and is verified by Monte-Carlo simulations. An air-bearing-based Hardware-In-the-Loop Simulator (HILS) is also developed to validate the proposed control laws in real-time environments. The SDRE controller is discretized for implementation of a real-time processor in the HILS. The pointing errors are about 0.2° in the numerical simulations and about 1° in the HILS simulations, and experimental simulations confirm the effectiveness of the control algorithm for attitude synchronization in a spacecraft formation flying mission. Consequently, experiments using the HILS in a real-time environment can appropriately perform spacecraft attitude synchronization algorithms for formation flying spacecraft.     

Single photon laser altimeter simulator and statistical signal processing

Spaceborne altimeters are common instruments onboard the deep space rendezvous spacecrafts. They provide range and topographic measurements critical in spacecraft navigation. Simultaneously, the receiver part may be utilized for Earth-to-satellite link, one way time transfer, and precise optical radiometry. The main advantage of single photon counting approach is the ability of processing signals with very low signal-to-noise ratio eliminating the need of large telescopes and high power laser source. Extremely small, rugged and compact microchip lasers can be employed. The major limiting factor, on the other hand, is the acquisition time needed to gather sufficient volume of data in repetitive measurements in order to process and evaluate the data appropriately. Statistical signal processing is adopted to detect signals with average strength much lower than one photon per measurement. A comprehensive simulator design and range signal processing algorithm are presented to identify a mission specific altimeter configuration. Typical mission scenarios (celestial body surface landing and topographical mapping) are simulated and evaluated. The high interest and promising single photon altimeter applications are low-orbit (∼10 km) and low-radial velocity (several m/s) topographical mapping (asteroids, Phobos and Deimos) and landing altimetry (∼10 km) where range evaluation repetition rates of ∼100 Hz and 0.1 m precision may be achieved. Moon landing and asteroid Itokawa topographical mapping scenario simulations are discussed in more detail.     

可实时重构的国际C站卫星模拟器

我国自行研制的国际标准C频段统一测控系统,配置了功能齐全的卫星模拟器,但其一星一模拟器的方式已不能适应当前多星管理和未来星座管理的需要。本文旨在探讨利用现有的微波宽带器件技术和软件无线电技术,用一套硬件系统,根据需要实时重构成所需卫星的模拟器,达到多星共用一套模拟器,实现小型化、实时性的目的。     

基于导航信号模拟器的采集回放测试方法研究

随着卫星导航产业的迅猛发展,导航终端测试技术越来越得到重视。传统的室内模拟测试和实际信号测试各有优缺点,因而产生了采集回放测试,通过采集存储实际卫星导航信号,并在实验室环境下进行回放,能够有效完成卫星导航终端的实际使用性能测试。基于导航信号模拟器,对采集回放系统做了介绍。选用国产多模接收机为参考标准接收机,以静态场景为例,从终端测试结果角度,分析了终端采集回放定位精度,对基于导航信号模拟器的采集回放测试方法进行了研究。     

液压仿真转台位置伺服系统频宽特性的研究

推导了带有加速度、速度、位置反馈的转台位置伺服系统的截止频率、穿越频宽、 - 1 0°相移频宽、 - 90°相移频宽的解析式 ,并就他们与参数之间的关系作了理论分析和讨论     

舰载飞机起飞和着舰的地面飞行模拟试验

论述了舰载飞机起飞，着舰的地面飞行模拟试验对舰载飞机设计和飞行员训练的重要性。分析了舰载飞机在起飞，着舰环境条件，起飞方式，着舰方式和着舰导引方式等方面的特点，及实现舰载飞机起飞，着舰地面飞行模拟试验对飞行模拟器的运动系统，视景系统，座舱设备和软件系统等方面的特殊要求。并分析了用现有地面飞行模拟器来模拟舰载飞机起飞，着舰需要进行的各项改造工作。     

Adaptive Sliding Control of Six-DOF Flight Simulator Motion Platform

本文使用Newton-Euler法推导了六自由度飞行模拟器运动平台完整的线性化形式的动力学方程,并以此为基础,提出了一种在任务空间中的非线性自适应滑模控制方法。这种控制方法将系统中的不确定性分为定常不确定参数和时变不确定参数,利用非线性自适应控制对定常不确定参数进行辨识,同时结合滑模控制对时变不确定参数和外部扰动进行补偿。通过数值仿真分析表明,该控制策略能准确识别运动平台的载荷、惯量、重心等参数,同时又能有效地提高系统的鲁棒性能。