耦合位置误差的机载惯性/星光组合算法研究

针对星敏测量输出的是惯性系下姿态信息,无法直接应用于实际的机载地理系下姿态组合导航,提出了地理系下耦合位置误差的机载惯性/星光组合滤波算法。该算法分析了
惯性姿态到地理系姿态之间的相互转换关系,在建立的地理系下姿态线性化量测方程基础上,通过引入导航位置误差转换矩阵,建立了星敏测量的惯性姿态到惯性导航计算输出的地理系姿态之间的耦合误差模型;同时针对姿态观测时高度通道不可观的特点,增加了气压高度输出为系统的观测量;实现了基于星敏测量的惯性系下姿态对地理系下惯性导航误差的直接修正。姿态耦合误差仿真结果表明该组合导航算法设计成功可行,为星敏在机载环境下的组合导航应用提供了新的思路。
     

美国深空测控通信技术动向分析

文章详细介绍了美国深空测控通信技术的发展动向,并对其未来规划进行了较为详细的综述和分析。     

MCAV/IMU integrated navigation for the powered descent phase of Mars EDL

Pin-point landing is considered as a key technology for future manned Mars landing and Mars base missions. The traditional inertial navigation system (INS) based guidance, navigation and control (GNC) mode used in the Mars entry, descent and landing (EDL) phase has no ability to achieve the precise and safe Mars landing, so novel EDL GNC methodologies should be investigated to meet this goal. This paper proposes the MCAV/IMU integrated navigation scheme for the powered descent phase of Mars EDL. The Miniature Coherent Altimeter and Velocimeter (MCAV) is adopted to correct the inertial bias and drift and improve the performance of integrated navigation. Altitude and velocity information derived from MCAV and the lander’s state information sensed by inertial measurement unit (IMU) are integrated in extended Kalman filter algorithm. The validity of the proposed navigation scheme is confirmed by computer simulation.     

一种拦截机动目标的多导弹协同制导律

针对多导弹协同拦截一个机动目标问题,基于有限时间一致性理论提出了一种带有攻击角约束的多导弹协同制导律。首先建立了带有攻击角约束的多导弹协同制导模型。其次,把协同制导律的设计过程分离为两个部分：一是基于有限时间一致性,同时结合积分滑模和自适应控制设计沿着视线方向上的加速度指令,保证所有的导弹能够在有限时间内同时拦截机动目标;二是利用非齐次干扰观测器并运用滑模控制设计视线法向上的加速度指令来保证每枚导弹与目标间的视线角速率收敛到零和视线角收敛到期望的视线角。最后,对三枚导弹同时打击同一机动目标的情况进行仿真,仿真结果表明该设计的带有攻击角约束的协同制导律的有效性和正确性。     

DOA estimation for attitude determination on communication satellites

In order to determine an appropriate attitude of three-axis stabilized communication satellites, this paper describes a novel attitude determination method using direction of arrival （DOA） estimation of a ground signal source. It differs from optical measurement, magnetic field measurement, inertial measurement, and global positioning system （GPS） attitude determination. The proposed method is characterized by taking the ground signal source as the attitude reference and acquiring attitude information from DOA estimation. Firstly, an attitude measurement equation with DOA estimation is derived in detail. Then, the error of the measurement equation is analyzed. Finally, an attitude determination algorithm is presented using a dynamic model, the attitude measurement equation, and measurement errors. A developing low Earth orbit （LEO） satellite which tests mobile communication technology with smart antennas can be stabilized in three axes by corporately using a magnetometer, reaction wheels, and three-axis magnetorquer rods. Based on the communication satellite, simulation results demonstrate the effectiveness of the method. The method could be a backup of attitude determination to prevent a system failure on the satellite. Its precision depends on the number of snapshots and the input signal-to-noise ratio （SNR） with DOA estimation.     

一种基于频域控制的组合导航系统设计方法

随着科学技术的发展,可资利用的导航信息源越来越多,导航系统的种类也越来越多,其中典型的是惯性导航系统和GPS/北斗卫星导航系统这两种系统在性能上正好形成互补,所以采用该两种系统作为组合导航设计中的子系统是最佳方案。SINS能够输出多种导航信息,但导航结果随着时间发散,GPS/北斗导航系统能够提高较高精度的位置速度信息,但不能提供姿态信息,且在遮挡等情况下会出现丢帧现象。为了能够利用SINS和GPS/北斗导航系统两种导航测量结果,使得两者的测量数据互补,且提高导航系统的精度,本文提出了一种基于频域控制的组合导航系统设计方法。通过实验验证,这种方法不仅充分利用了SINS和GPS/北斗导航系统的信息,还增加了定位精度和可靠性,且能在丢帧情况下还能满足导航要求。     

Integrated guidance and control design of a flight vehicle with side-window detection

This paper considers the guidance and control problem of a flight vehicle with side-window detection. In order to guarantee the target remaining in the seeker's sight of view, the line of sight and the attitude of the flight vehicle should be under some constraints caused by the side-window, which leads to coupling between the guidance and the attitude dynamics model. To deal with the side-window constraints and the coupling, a novel Integrated Guidance and Control (IGC) design approach is proposed. Firstly, the relative motion equations are derived in the body-Line of Sight (LOS) coordinate system. And the guidance and control problem of the flight vehicle is formulated into an IGC problem with state constraints. Then, based on the singular perturbation method, the IGC problem is decomposed into the control design of the quasi-steady-state subsystem and the boundary-layer subsystem which can be designed separately. Finally, the receding horizon control is applied to the control design for the two subsystems. Simulation results show the effectiveness of the proposed approach.     

Understanding the mineralogy of a compositional anomaly north of the Korolev basin using Moon mineralogy mapper

The work attempts to understand the mineralogy of the reported geochemical anomaly located in the north – northeast region of the Korolev basin using Moon Mineralogy Mapper (M³) onboard Chandrayaan ?1 and other lunar datasets. To understand the mineralogy, colour composite images using integrated band depth parameters and mineral indices were prepared, and the M³ spectral signatures corresponding to the unique colours of these colours composites were investigated. Further, Modified Gaussian Model (MGM) deconvolution was applied to these spectra. The results of spectra studies reveal that the area is made up of heterogeneous lithologies, predominantly composed of anorthosite along with minor occurrences of pyroxene-bearing (both low-calcium and high-calcium variety) and spinel-bearing lithologies. Correlation of spectral studies with the morphology revealed that pyroxene was typically associated with fresh craters and their ejecta. Spinel was found to be ubiquitous and is well-dispersed, possibly distributed along with the ejecta blanket of large impact craters. This association hints that the pyroxene-hosted layer most likely occurs beneath the spinel-bearing layer. Such observed assemblages may have resulted from physical mixing during the impact cratering events. This mixed lithology could arise due to the mafic mineral-bearing ejecta of the South-Pole Aitken (SPA) basin and spinel-bearing Orientale ejecta. Korolev most likely impacted on a thick layer of SPA ejecta, and impact basins such as Hertzsprung and Orientale have occurred post-Korolev formation. Orientale being the youngest of the large impact basins, its ejecta carrying the light plain material would have overprinted the older SPA ejecta. Smaller impact craters would have churned the ejecta so that presently we observe a composite lithology with a variable abundance of pyroxene and spinel.     

基于速度积分匹配的旋转调制惯导系统动基座对准方法

卫星导航信息辅助动基座对准过程中,速度噪声会影响对准精度和快速性,制约了旋转调制惯导角秒级高精度快速对准的实现.针对这一问题,提出了一种基于旋转调制惯导速度积分匹配的快速动基座对准方法,通过建立旋转调制惯导动基座对准误差方程和卡尔曼滤波观测模型,以消除动基座对准对载机特殊运动的要求.最后,在实验室静态环境和车载环境下,分别开展了速度积分匹配和速度十位置组合导航动基座对准仿真实验.仿真结果表明,提出的速度积分匹配方法具有误差估计量收敛速度快的特点,在对准精度不降低的情况下相对组合导航匹配方式能有效缩短动基座对准时间,并能基于旋转调制惯导取消动基座对准对载机的机动需求.     

基于5G的通导融合位置认证系统性能分析

随着无人化智能移动装备在工业、交通等安全敏感领域的普及应用，民用导航定位系统中的定位安全问题日益突出。位置认证是对终端的物理位置声明进行认证的过程，是导航定位安全技术的重要组成部分。基于第五代(5G)移动通信网络的通导融合位置认证系统具有覆盖范围广、认证精度高、用户容量大、建设运维成本低等多重优势。本文首先介绍了多基站位置认证系统的检测判决原理，提出了漏检平均距离的定义作为位置认证系统精度的量化评价指标。在此基础上，通过数值仿真分析了信号带宽、基站同步误差、信噪比对位置认证系统精度的影响，并利用5G信道模型评估了典型场景下的位置认证系统的性能。结果表明，在具备3个以上的视距基站时，基于5G的通导融合位置认证系统可以实现米级的位置认证精度。