Modified attitude pursuit guidance law for low-cost missiles using strap-down seekers

Attitude pursuit guidance law is suitable for low cost missiles.A strap-down seeker is used to achieve this guidance law.The additional angles of attack or sideslip caused by wind and by control system are considered as two disturbing factors which make attitude pursuit law impossible.Therefore,general attitude pursuit guidance law did not account for this two disturbing factors,because with those disturbing factors,it is difficult to apply.To solve the problem,the principle of strap-down seeker detecting target is investigated,the mathematical control model is established,then a modified attitude pursuit guidance law which employs the angular correction for those two disturbing factors is presented.It is proved that the modified attitude pursuit guidance law is appropriated to both in the presence of the additional angle of attack or sideslip via the simulations with the mathematical control model and Monte-Carlo method.

Design and application of single-antenna GPS/accelerometers attitude determination system

In view of the problem that the current single-antenna GPS attitude determination system can only determine the body attitude when the sideslip angle is zero and the multiantenna GPS/SINS integrated navigation system is of large volume, high cost, and complex structure, this approach is presented to determine the attitude based on vector space with single-antenna GPS and accelerometers in the micro inertial measurement unit （MIMU）. It can provide real-time and accurate attitude information. Subsequently, the single-antenna GPS/SINS integrated navigation system is designed based on the combination of position, velocity, and attitude. Finally the semi- physical simulations of single-antenna GPS attitude determination system and single-antenna GPS/SINS integrated navigation system are carried out. The simulation results, based on measured data, show that the single-antenna GPS/SINS system can provide more accurate navigation information compared to the GPS/SINS system, based on the combination of position and velocity. Furthermore, the single-antenna GPS/SINS system is characteristic of lower cost and simpler structure. It provides the basis for the application of a single-antenna GPS/SINS integrated navigation system in a micro aerial vehicle （MAV）.

A Quaternion Scaled Unscented Kalman Estimator for Inertial Navigation States Determination Using INS/GPS/Magnetometer Fusion

This Inertial Navigation System (INS), Global Positioning System (GPS) and fluxgate magnetometer technologies have been widely used in a variety of positioning and navigation applications. In this paper, a low cost solid state INS/GPS/Magnetometer integrated navigation system has been developed that incorporates measurements from an Inertial Navigation System (INS), Global Positioning System (GPS) and fluxgate magnetometer (Mag.) to provide a reliable complete navigation solution at a high output rate. The body attitude estimates, especially the heading angle, are fundamental challenges in a navigation system. Therefore targeting accurate attitude estimation is considered a significant contribution to the overall navigation error. A better estimation of the body attitude estimates leads to more accurate position and velocity estimation. For that end, the aim of this research is to exploit the magnetometer and accelerometer data in the attitude estimation technique. In this paper, a Scaled Unscented Kalman Filter (SUKF) based on the quaternion concept is designed for the INS/GPS/Mag integrated navigation system under large attitude error conditions. Simulation and experimental results indicate a satisfactory performance of the newly developed model.

Unscented Kalman Filter for Autonomous Warship Attitude Determination

To address a problem of autonomous attitude determination algorithm using gravitational field and geomagnetic field observation, a new recursive optimization autonomous attitude estimation algorithm is proposed. The algorithm is based on unscented Kalman filter(UKF), and can synchronously provide the attitude rate information. The simulated results show that the measurement precision of the method could be increased by 2 times compared to that of the common methods.

Attitude Control Algorithm for Reusable Launch Vehicle in Reentry Flight Phase

An attitude control algorithm for reusable launch vehicle(RLV) in reentry phase is proposed based on sliding mode variable structure control technique.The aerodynamic characteristics of RLV vary rapidly,and the serious uncertainties and nonlinearities exist in the reentry flight phase.As an example,American X-34 technology demonstrator is investigated.The chattering brought by the variable structure control technique is eliminated efficiently by choosing a suitable reaching law and a sign function.A control mode of reaction control system is presented based on the RCS scheme of X-34 vehicle.As two different attitude control effectors,aerosurfaces and RCS,are employed in the reentry flight phase,a composite control strategy based on the dynamic pressure variety is presented.Also,an actuator model and a RCS thruster model are built.Analysis and nonlinear simulation results show that the sliding mode variable structure controller achieves better performance,the overshoot and steady-state error are only 0.7% and 0.04° respectively.

Adaptive Sliding Mode Control for Re-entry Attitude of Near Space Hypersonic Vehicle Based on Backstepping Design

Combining sliding mode control method with radial basis function neural network(RBFNN), this paper proposes a robust adaptive control scheme based on backstepping design for re-entry attitude tracking control of near space hypersonic vehicle(NSHV) in the presence of parameter variations and external disturbances. In the attitude angle loop, a robust adaptive virtual control law is designed by using the adaptive method to estimate the unknown upper bound of the compound uncertainties. In the angular velocity loop, an adaptive sliding mode control law is designed to suppress the effect of parameter variations and external disturbances. The main benefit of the sliding mode control is robustness to parameter variations and external disturbances. To further improve the control performance, RBFNNs are introduced to approximate the compound uncertainties in the attitude angle loop and angular velocity loop, respectively. Based on Lyapunov stability theory, the tracking errors are shown to be asymptotically stable. Simulation results show that the proposed control system attains a satisfied control performance and is robust against parameter variations and external disturbances.

Adaptive filter for a miniature MEMS based attitude and heading reference system

An extended Kalman filter with adaptive gain was used to build a miniature attitude and heading reference system based on a stochastic model. The adaptive filter has six states with a time variable transition matrix. When the system is in the non-acceleration mode, the accelerometer measurements of the gravity and the compass measurements of the heading have observability and yield good estimates of the states. When the system is in the high dynamic mode and the bias has converged to an accurate estimate, the attitude calculation will be maintained for a long interval of time. The adaptive filter tunes its gain automatically based on the system dynamics sensed by the accelerometers to yield optimal performance.

Re-entry Attitude Double-loop SMC of the Spacecraft and Its Logic Selection

A spacecraft re-entry attitude control method using sliding mode control (SMC) theory is developed. The controller utilizes double-loop SMC scheme and provides the robust, de-coupled tracking of both the angular velocity and the shuttle orientation angles. In accordance with the hybrid-controlling characteristics of the aerodynamic surfaces and reaction control system of the spacecraft, the control torque commands are allocated into the actuators such as the aerodynamic surfaces and reaction control system by using the optimal control selection allocation algorithm. The simulation of the spacecraft re-entry attitude controlling demonstrates the robust, de-coupled tracking performance of the proposed method and its validity.

两种双矢量SINS粗对准方法大俯仰角适应性研究

大俯仰角下捷联惯导粗对准双矢量定姿中,不同矢量组合下,姿态角尤其是方位角对准精确度相差很大,必须慎重选择。对此,给出了2种最常用的粗对准矢量组合模式误差方程,对其主要误差影响因素进行分析。综合传感器误差,利用蒙特卡洛随机打靶方法对全姿态角下粗对准精确度进行仿真,并开展了80°俯仰角转台静态粗对准试验。转台试验中,在惯导陀螺误差约1°/h,加速度计误差约0.1mg情况下,第1种、第2种组合模式方位角粗对准最大误差值分别为20°、7.5°,第2种组合模式约为第1种的1/3;仿真测试中,在惯导陀螺误差约0.1°/h,加速度计误差约1mg,80°俯仰角下,第1种、第2种组合模式下方位角粗对准最大误差值分别为11°与2.2°,前者约为后者的5倍。仿真与试验结果表明,大俯仰角下矢量组合模式是影响惯导姿态角与姿态矩阵粗对准精确度的最主要因素。

多矢量姿态测量算法研究综述

将矢量测量转化为姿态测量,该问题在姿态估计中被称为Wahba问题。介绍了最小化Wahba问题的损失函数的不同算法,包括最优四元数估计器(ESOQ)、四元数估计器(QUEST)、快速最优姿态矩阵(FOAM)、矩阵的奇异值分解(SVD)等广泛使用的算法,以及基于快速线性四元数姿态估计器(FLAE)、黎曼流形等近年来提出的算法。给出了简单的计算原理与推导过程,并通过计算机仿真对照,归纳各类算法在计算旋转矩阵时的计算精度、鲁棒性。针对姿态测量算法应对当前应用场景的性能需求,简要介绍其在惯性测量单元(IMU)动态对准、协同集群视觉定姿、图像拼接等方面的适用可能和工作原理,并在此基础上简述了姿态测量算法当前的缺陷与未来的发展趋势。

丘陵地区柑橘园采收搬运机器人系统的研制

针对丘陵地区柑橘园地形多为坡地,柑橘采收搬运困难、劳动强度大,严重制约丘区现代柑橘园发展的问题,通过计算机三维设计、电路搭建和软件控制等方法,研制了丘区柑橘园采收搬运机器人系统,并通过性能测试.试验结果表明,该机器人能够满足丘陵地区柑橘园采摘搬运检测准确率和跟随运输精度要求,检测准确率高于97%,跟随运输精度超过90%.

巡飞弹航迹规划与飞行控制方法发展

巡飞弹是无人机技术与弹药技术结合的产物,可实现战场态势感知、精确打击、信息支援等功能,是未来信息化作战的重要武器之一。介绍巡飞弹的定义组成、分类方法、作战功能、型号发展、战场应用等情况;阐述巡飞弹航迹规划方法的发展现状和未来趋势,包括传统规划方法、智能规划算法和集群规划算法等;对巡飞弹飞行控制的关键技术,包括制导、姿控和导航技术的发展现状和未来趋势进行了介绍,其中的制导技术包括巡飞段跟踪制导、俯冲段末制导和多弹协同制导等;展望了巡飞弹未来的发展方向。

斯里兰卡海域某难船打捞测绘技术的融合应用

详细介绍了新加坡籍集装箱船“X-PRESS PEARL”难船打捞施工过程中的融合测绘技术,包括难船前期位置与姿态调查,难船周边障碍物调查,海风、波浪与海流的海洋环境监测,水上水下综合导航定位,难船起浮姿态监测,难船自浮姿态监测以及最终的残骸打捞工作。通过融合应用一系列测绘设备以及技术创新,为难船的顺利打捞提供了大力支持,为海洋环境保护提供了有效的保障,为相关国际难船打捞工程提供了可靠的参考依据。

低成本惯性多冗余导航控制一体机设计

为了智能体的精确定位和定姿,实现其稳定运动控制,设计了一种低成本多惯性冗余导航控制一体机,给出了设计方法。稳压电路的开关电源MP2482DN和线性电源JW29300U-3.3V为一体机提供稳定5 V和3.3 V的较大功率电源;控制器STM32H7的SPI采用星形拓扑总线与3片六轴惯性芯片BMI088通信,2路TTL串口与差分卫星定位板双向通信,实现智能体定位和定姿;控制器STM32F4的CAN总线接口与智能体底盘双向通信,实现其运动控制,1路TTL串口实现与控制器STM32H7的双向通信;两控制器的网络接口与上位机组成无线局域网,实现数据交换和状态监控。整个系统具有功耗低、体积小、成本低、接口丰富的特点。

基于GNSS双天线测姿的水位监测方法

水位监测是雨水情监测预报“第三道防线”中的重要内容,精确、实时的水位监测在洪涝灾害防御中至关重要。水位计是最常见的水位测量工具,其能有效测量特定区域的相对水位信息,但往往存在成本较高、空间分辨率较低等问题。由于全球导航卫星系统反射测量(Global Navigation Satellite System-Reflectometry,GNSS-R)技术具有低成本、高时空分辨率的优势,因此提出了一种基于全球导航卫星系统(Global Navigation Satellite System,GNSS)双天线测姿的实时水位监测新方法。该方法通过双差观测组合,消除了卫星钟差、接收机钟差、电离层延迟、对流层延迟等误差。为了验证该方法的稳定性和可靠性,在北京市东沙河站开展现场试验。2023年6月5日至7月10日的实验结果表明该方法可以实现1 Hz的水位监测,与现场水尺数据相比,均方根误差为2.88 cm。

GNSS不同区域站网分布对极移精度的影响分析

针对利用中国区域全球卫星导航系统(GNSS)站网求解极移参数存在Y分量精度显著低于X分量的问题,提出利用姿态测量几何分析方法分析GNSS不同区域站网分布对极移精度的影响:利用9个不同区域站网求解极移参数探究站网区域分布的影响;并以国际地球自转服务组织(IERS)产品为基准评估精度。结果表明,当区域站网的平均子午面与0°子午面的夹角小于45°时,X分量差异的标准差通常大于Y分量;夹角大于45°时,Y分量差异标准差通常大于X分量。为最小代价地进一步提升Y分量精度,通过在中国区域站网基础上引入全球不同位置的单个测站,评估精度提升比例。结果表明,在非洲东南部和澳大利亚地区引入单个测站将Y分量均值平均减小了80%,标准差减小了50%,较全球其他地区测站的提升效果更明显;新增美洲地区测站时存在测量奇点,易造成法方程的矩阵奇异,这是由于美洲测站、国内测站地心矢量及地球自转轴共面,从而削弱了方程结构。

基于SINS/OD失准角观测的垂线偏差测量方法

组合导航系统的姿态失准角与垂线偏差(deviation of vertical,DOV)存在对应关系,通过对姿态失准角的观测是实现DOV测量的一种有效手段。本文基于车载捷联惯性导航系统/里程计(strapdown inertial navigation system/odometer,SINS/OD)组合导航姿态失准角观测及失准角误差的递推提出一种DOV测量方法。首先,从组合导航速度误差方程出发,推导出DOV与姿态失准角之间存在复杂的耦合关系。然后,通过沿路径迭代递推的分步计算方法,由导航过程中的姿态失准角直接获取沿线的DOV。最后,仿真结果验证了该算法的有效性,且表明测量精度与行驶路径的长度有关。实验表明,行驶里程35 km的机动路径上DOV误差均值小于0.3″,终点处单点测量误差小于0.7″。

考虑多约束条件的舰船航行姿态自适应控制算法

舰船的航行姿态受到复杂的非线性动力学因素影响,例如水动力、风力、波浪力等。这些因素导致了船舶运动的非线性和不确定性,使得对其航行姿态控制的精度较低。为此,提出考虑多约束条件的舰船航行姿态自适应控制算法。分析舰船在海上航行,构建船舶的低频和高频运动模型;根据舰船航行时的特点建立船舶航行的避障约束、转弯最小半径约束以及控制输入饱和约束,建立以调节能耗最少的舰船航行姿态控制目标函数,并通过径向基函数(Radial Basis Function,RBF)神经网络逼近目标函数,得到无限接近目标函数的船舶航行姿态控制律,完成姿态自适应控制。实验结果表明,该方法能够准确控制舰船航行姿态,控制量输出接近理想状态,在进行姿态控制时最大静态误差仅为0.15°,控制时间以及超调量均较小。

复杂环境下GPS+BDS-3 PPP/INS紧组合算法性能分析

针对城市复杂环境下精密单点定位(PPP)连续高精度定位受限的问题,本文基于北斗三号全球卫星导航系统(BDS-3)与全球定位系统(GPS)双系统,利用PPP与惯性导航系统(INS)紧组合算法来改善城市复杂环境下定位性能。通过构建GPS+BDS-3双系统PPP/INS紧组合滤波模型,分别对GPS PPP、GPS+BDS-3 PPP、GPS PPP/INS紧组合、GPS+BDS-3PPP/INS紧组合4种方案在城区开阔、复杂环境下的定位、测速、定姿性能进行了分析和评估。实验结果表明,开阔环境下PPP/INS紧组合相比PPP定位精度略有提升;而在复杂环境下PPP/INS紧组合可显著解决PPP定位结果连续性和有效性较差的问题;引入BDS-3后,PPP/INS紧组合导航性能进一步提升,GPS+BDS-3 PPP/INS紧组合相比GPS PPP/INS紧组合,在东、北、天方向上,开阔环境下定位精度分别提升18.5%、32.7%、43.2%,复杂环境下定位精度分别提升35.9%、49.1%、56.5%。

惯导系统传递对准模型的研究进展综述

初始对准是惯导系统开启工作后必须经历的阶段,而传递对准则是一种特殊的动基座初始对准技术,可有效提高武器装备的快速反应和精准打击能力。对惯导系统传递对准模型的研究进展进行了综合评述。首先,从姿态误差的定义出发,系统归纳了ϕ_(n)角误差模型、ϕ_(m) 角误差模型和相对姿态对准模型,对比分析了三类误差模型的特点。其次,给出了导航速度、相对速度和惯性速度的定义,理论推导了三种导航速度误差方程。然后,介绍了传递对准的量测模型,并重点归纳了基于相对姿态理论的文献所采用的量测模型。最后,讨论了传递对准有待解决的技术问题和未来研究方向。综述表明,误差的数学定义和参考坐标系以及匹配参数决定了传递对准模型的丰富性,在实际使用时,可以根据应用背景以及使用条件选择相应的传递对准模型,而在误差建模、误差激励、性能评估等方面,传递对准技术都有待进一步研究。