A340机载导航系统分析

介绍了A340导航系统：大气数据惯性基准系统、电子飞行仪表系统、ATC／S模式应答机及机载防撞系统等。分析了机载导航系统的现状及发展方向，为同类飞机的雏护和培训提供参考。     

运载火箭复杂容错控制系统可靠性分析

在典型可靠性分析模型及理论基础上,建立了运载火箭复杂容错控制系统可靠性分析模型,提出了行之有效的可靠性建模方法,并进行了算例分析.结果表明,该方法能够为复杂容错控制系统可靠性评估、确定合理的系统组成以及方案优化提供良好的支撑,可在控制系统工程设计中推广应用.     

惯性/偏振光组合定姿技术研究

惯性导航系统是一种全参数、全天候的自主导航系统,但其姿态误差随时间发散。太阳光在大气中传播时在天空具有稳定的偏振模式,惯性/偏振光组合定姿系统就是利用偏振光中的方位信息实现惯性导航系统姿态角误差的估计。研究了惯性/偏振光组合定姿系统模型,利用跑车试验数据对所设计的组合定姿系统进行了仿真。结果表明:惯性导航系统引入偏振光导航信息后,可以有效地抑制惯性导航姿态角误差发散的趋势,提高姿态精度,满足中等精度姿态参考系统的需求。     

Nonlinear filtering methods for spacecraft navigation based on differential algebra

The paper investigates the problem of nonlinear filtering applied to spacecraft navigation. Differential algebraic (DA) techniques are proposed as a valuable tool to implement the higher-order numerical and analytic extended Kalman filters. Working in the DA framework allows us to consistently reduce the required computational effort without losing accuracy. The performance of the proposed filters is assessed on different orbit determination problems with realistic orbit uncertainties. The case of nonlinear measurements is also considered. Numerical simulations show the good performance of the filter in case of both complex dynamics and highly nonlinear measurement problems.     

Analysis and experiments for delay compensation in attitude control of flexible spacecraft

Space vehicles are often characterized by highly flexible appendages, with low natural frequencies which can generate coupling phenomena during orbital maneuvering. The stability and delay margins of the controlled system are deeply affected by the presence of bodies with different elastic properties, assembled to form a complex multibody system. As a consequence, unstable behavior can arise. In this paper the problem is first faced from a numerical point of view, developing accurate multibody mathematical models, as well as relevant navigation and control algorithms. One of the main causes of instability is identified with the unavoidable presence of time delays in the GNC loop. A strategy to compensate for these delays is elaborated and tested using the simulation tool, and finally validated by means of a free floating platform, replicating the flexible spacecraft attitude dynamics (single axis rotation). The platform is equipped with thrusters commanded according to the on–off modulation of the Linear Quadratic Regulator (LQR) control law. The LQR is based on the estimate of the full state vector, i.e. including both rigid – attitude – and elastic variables, that is possible thanks to the on line measurement of the flexible displacements, realized by processing the images acquired by a dedicated camera. The accurate mathematical model of the system and the rigid and elastic measurements enable a prediction of the state, so that the control is evaluated taking the predicted state relevant to a delayed time into account. Both the simulations and the experimental campaign demonstrate that by compensating in this way the time delay, the instability is eliminated, and the maneuver is performed accurately.     

发展单兵星敏导航装备的必要性及技术特点

星光导航不受电磁干扰、能提供绝对姿态信息，具有重大战略意义。目前的星敏主要是为空天基导航而发展的，将其应用于单兵导航是否必要、需克服哪些技术难点、能达到怎样的效果等，都是值得探索的问题。为此，首先论述了发展单兵星敏导航装备的必要性，包括：不受电磁干扰破坏，是其他单兵导航装备失效时的保底装备；定向精度高，能弥补单兵卫星导航装备无法定向的缺陷；已突破部分气象因素限制，具备了全天时导航条件等。然后探讨了单兵星敏导航与空天基星敏导航、卫星导航、天文大地测量等比较所具有的不同技术特点。提出了发展单兵星敏导航装备需解决的关键技术问题，包括：气象因素影响的消减、时间基准和电源的长期维持、系统探测性能与系统小型化的平衡等。研究结果可为发展单兵星敏导航技术、设计研制单兵星敏导航系统提供参考。     

卡尔曼滤波在弹道组合导航仿真中的应用

根据捷联惯性导航(INS)和GPS导航两个系统不同的特点,通过卡尔曼滤波方法实现了INS/GPS组合导航,以速度差和位置差作为卡尔曼滤波的量测量信息,建立了组合导航的简化滤波方程.在实际陀螺器件含有零偏的情况下,通过在角速度上引入定量的零位偏置来进行弹体模拟投放过程.将仿真导航结果和弹道参数比较,引入的陀螺偏置引起姿态角误差,而速度误差和位置误差比较小,导航计算参数误差在允许范围之内.     

航天器控制若干技术问题的新进展

航天器姿态和轨道控制技术是航天器研制中的关键技术,对实现复杂航天器的控制以及未来复杂的飞行任务都具有非常重要的作用。文中通过一些飞行实例概述国内外航天器控制技术的发展,论述了航天器控制技术在编队飞行、自主交会与对接和复杂对象控制中的进展。文章通过揭示航天器控制技术领域的研究和发展趋势,为我国航天器制导、导航与控制技术的发展提出建议。     

微型飞行器高度估计的最小二乘法

对微型飞行器高度估计问题,提出了基于针孔成像的最小二乘法。利用惯性器件测量的姿态角,建立了目标在2帧图像的4个投影方程,得到目标相对高度的最小二乘解。对该方法进行了仿真验证,结果表明当飞行器横滚角变化不大时,高度估计对姿态角误差具有较好的鲁棒性,误差在2 m以内,优于传统方法。该方法计算量小,适合微型飞行器平稳飞行时应用。     

加速度计横向误差对无陀螺捷联惯导的影响

现在,国内外越来越重视对无陀螺捷联惯导系统的研究,然而在解算惯性组合基本分量时把加速度计理想化了,忽视了加速度计横向输出对解算结果的影响,从而影响了无陀螺捷联惯导系统的制导准确度。将加速度计的横向输出带人了解算过程,与传统解算过程所得的结果比较,系统基本分量更加精确,对提高无陀螺捷联惯导系统的制导准确度有重大意义。