Ideal proportional navigation （IPN） is a natural choice for exoatmospheric interception for its mighty capture capability and ease of implementation. The closed-form solution of two- dimensional ideal proportional n...Ideal proportional navigation （IPN） is a natural choice for exoatmospheric interception for its mighty capture capability and ease of implementation. The closed-form solution of two- dimensional ideal proportional navigation was conducted in previous public literature, whereas the practical interception happens in the three-dimensional space. A novel set of relative dynamic equations is adopted in this paper, which is with the advantage of decoupling relative motion in the instantaneous rotation plane of the line of sight from the rotation of this plane. The dimension-reduced IPN is constructed in this instantaneous plane, which functions as a three-dimensional guidance law. The trajectory features of dimension-reduced IPN are explored, and the capture regions of dimension-reduced IPN with limited acceleration against nonmaneuvering and maneuvering targets are analyzed by using phase plane method. It is proved that the capture capability of IPN is much stronger than true proportional navigation （TPN）, no matter the target maneuvers or not. Finally, simulation results indicate that IPN is more effective than TPN in exoatmospheric interception scenarios.展开更多
A novel control algorithm with fixed pulse thrust, based on true proportional navigation（TPN）, is proposed for exoatmospheric intercept.According to the TPN guidance law and pulse thrust characteristics, the princip...A novel control algorithm with fixed pulse thrust, based on true proportional navigation（TPN）, is proposed for exoatmospheric intercept.According to the TPN guidance law and pulse thrust characteristics, the principle of control command is presented, the control stability and precision are analyzed.With the help of the TPN guidance law, the algorithm can automatically modulate the turn-on time and duration of the thrust, which could effectively limit the impact of measure noise of the line-of-sight（LOS） angle and rate on the interception miss-distance.At last, the number-theoretic method（NTM） is introduced to acquire the relation between control algorithm and miss-distance, even as it simulates the intercept process with initial state noise.And the reliability of the algorithm is demonstrated with the simulation result.展开更多
True proportional navigation(TPN) guidance law is widely used for exoatmospheric interception, for its robustness and ease of implementation. The performance of TPN against nonmaneuvering target or the maneuvering tar...True proportional navigation(TPN) guidance law is widely used for exoatmospheric interception, for its robustness and ease of implementation. The performance of TPN against nonmaneuvering target or the maneuvering target with a specific acceleration had been analyzed before. However, the obtained results are not suitable for the realistic exoatmospheric interception scenario,since the target may maneuver along an arbitrary direction with an arbitrary but upper-bounded acceleration in the threedimensional(3 D) space, which is the so-called "true-arbitrarily maneuvering target" in this paper. With the help of the line-ofsight(LOS) rotation coordinate system, the performance of 3 D TPN against the true-arbitrarily maneuvering target is thoroughly analyzed using the Lyapunov-like approach. The upper-bound of the 3 D LOS rate is obtained, and so is that of the commanded acceleration of 3 D TPN. After that, the capture region of 3 D TPN is presented on the initial relative velocity plane. The nonlinear3 D relative kinematics between the interceptor and the target is taken into full account. Finally, the new theoretical findings are demonstrated by numerical simulations.展开更多
In this study, two optimal terminal guidance (OTG) laws, one of which takes into account the final velocity vector constraint, are developed for exoatmospheric interception using optimal control theory. In exoatmosphe...In this study, two optimal terminal guidance (OTG) laws, one of which takes into account the final velocity vector constraint, are developed for exoatmospheric interception using optimal control theory. In exoatmospheric interception, because the proposed guidance laws give full consideration to the effect of gravity, they consume much less fuel than the traditional guidance laws while requiring a light computational load. In the development of the guidance laws, a unified optimal guidance problem is put forward, where the final velocity vector constraint can be considered or neglected by properly adjusting a parameter in the cost function. To make this problem analytically solvable, a linear model is used to approximate the gravity difference, the difference of the gravitational accelerations of the target and interceptor. Additionally, an example is provided to show that some achievements of this study can be used to significantly improve the fuel efficiency of the pulsed guidance employed by the interceptor whose divert thrust level is fixed. (C) 2016 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license.展开更多
外大气层杀伤拦截器（exoatompropheric kill vehicle,EKV）是地基拦截导弹（ground based interceptor,GBI）上的拦截设备,是地基中段防御系统中的重要组成部分,是以直接碰撞杀伤的方式对弹道导弹弹头进行中段拦截的飞行设备.对EKV上...外大气层杀伤拦截器（exoatompropheric kill vehicle,EKV）是地基拦截导弹（ground based interceptor,GBI）上的拦截设备,是地基中段防御系统中的重要组成部分,是以直接碰撞杀伤的方式对弹道导弹弹头进行中段拦截的飞行设备.对EKV上红外导引头的各项探测性能参数进行了分析,分别推导了空间冷背景下和大气背景下红外导引头对点目标的作用距离方程,并对相应方程中的各项参数和影响因素进行了分析,估算了在空间冷背景下和大气背景下EKV的探测距离数据.展开更多
目前,我国大部分遥感传感器的大气层外波段平均太阳光谱辐照度(Mean solar exoatmospheric irradiances over band b,简称ESUNb)尚未公布,这给遥感图像表观反射率的计算带来了不便,在一定程度上影响了数据资料的应用和推广。本文基于已...目前,我国大部分遥感传感器的大气层外波段平均太阳光谱辐照度(Mean solar exoatmospheric irradiances over band b,简称ESUNb)尚未公布,这给遥感图像表观反射率的计算带来了不便,在一定程度上影响了数据资料的应用和推广。本文基于已有官方ESUNb值的EO1/ALI、Terra/ASTER、QuickBird等多种中、高空间分辨率传感器,对9条常见的太阳光谱曲线进行比较分析。结果表明,WRC太阳光谱曲线最合适计算中分辨率传感器的ESUNb,而Wehrli太阳光谱曲线最合适计算高分辨率传感器的ESUNb。基于WRC太阳光谱曲线和Wehrli太阳光谱曲线计算,得到了ZY-1 02C/PMS相机、ZY-3/TLC相机和MUX相机,以及GF-1/WFV相机和PMS相机各波段ESUNb值,并对ESUNb值的不确定性进行了分析。结果显示,太阳光谱选取的不同,对ESUNb的取值会产生-1.94%至1.48%的偏差。本文使用多种卫星传感器交叉比较的方式确定了最佳的太阳光谱,给出了ZY-1 02C、ZY-3和GF-1等卫星搭载的遥感传感器各波段的ESUNb值,为这些国产卫星遥感数据的广泛应用提供便利。此外,本文所用方法简便易行,在其他新的遥感传感器上具有推广应用价值。展开更多
基金co-supported by the National Science Foundation of China(No.11222215)the National Basic Research Program of China(No.2013CB733100)
文摘Ideal proportional navigation （IPN） is a natural choice for exoatmospheric interception for its mighty capture capability and ease of implementation. The closed-form solution of two- dimensional ideal proportional navigation was conducted in previous public literature, whereas the practical interception happens in the three-dimensional space. A novel set of relative dynamic equations is adopted in this paper, which is with the advantage of decoupling relative motion in the instantaneous rotation plane of the line of sight from the rotation of this plane. The dimension-reduced IPN is constructed in this instantaneous plane, which functions as a three-dimensional guidance law. The trajectory features of dimension-reduced IPN are explored, and the capture regions of dimension-reduced IPN with limited acceleration against nonmaneuvering and maneuvering targets are analyzed by using phase plane method. It is proved that the capture capability of IPN is much stronger than true proportional navigation （TPN）, no matter the target maneuvers or not. Finally, simulation results indicate that IPN is more effective than TPN in exoatmospheric interception scenarios.
文摘A novel control algorithm with fixed pulse thrust, based on true proportional navigation（TPN）, is proposed for exoatmospheric intercept.According to the TPN guidance law and pulse thrust characteristics, the principle of control command is presented, the control stability and precision are analyzed.With the help of the TPN guidance law, the algorithm can automatically modulate the turn-on time and duration of the thrust, which could effectively limit the impact of measure noise of the line-of-sight（LOS） angle and rate on the interception miss-distance.At last, the number-theoretic method（NTM） is introduced to acquire the relation between control algorithm and miss-distance, even as it simulates the intercept process with initial state noise.And the reliability of the algorithm is demonstrated with the simulation result.
基金supported by the National Natural Science Foundation of China(Grant Nos.61690210 and 61690213)
文摘True proportional navigation(TPN) guidance law is widely used for exoatmospheric interception, for its robustness and ease of implementation. The performance of TPN against nonmaneuvering target or the maneuvering target with a specific acceleration had been analyzed before. However, the obtained results are not suitable for the realistic exoatmospheric interception scenario,since the target may maneuver along an arbitrary direction with an arbitrary but upper-bounded acceleration in the threedimensional(3 D) space, which is the so-called "true-arbitrarily maneuvering target" in this paper. With the help of the line-ofsight(LOS) rotation coordinate system, the performance of 3 D TPN against the true-arbitrarily maneuvering target is thoroughly analyzed using the Lyapunov-like approach. The upper-bound of the 3 D LOS rate is obtained, and so is that of the commanded acceleration of 3 D TPN. After that, the capture region of 3 D TPN is presented on the initial relative velocity plane. The nonlinear3 D relative kinematics between the interceptor and the target is taken into full account. Finally, the new theoretical findings are demonstrated by numerical simulations.
文摘In this study, two optimal terminal guidance (OTG) laws, one of which takes into account the final velocity vector constraint, are developed for exoatmospheric interception using optimal control theory. In exoatmospheric interception, because the proposed guidance laws give full consideration to the effect of gravity, they consume much less fuel than the traditional guidance laws while requiring a light computational load. In the development of the guidance laws, a unified optimal guidance problem is put forward, where the final velocity vector constraint can be considered or neglected by properly adjusting a parameter in the cost function. To make this problem analytically solvable, a linear model is used to approximate the gravity difference, the difference of the gravitational accelerations of the target and interceptor. Additionally, an example is provided to show that some achievements of this study can be used to significantly improve the fuel efficiency of the pulsed guidance employed by the interceptor whose divert thrust level is fixed. (C) 2016 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license.
文摘外大气层杀伤拦截器（exoatompropheric kill vehicle,EKV）是地基拦截导弹（ground based interceptor,GBI）上的拦截设备,是地基中段防御系统中的重要组成部分,是以直接碰撞杀伤的方式对弹道导弹弹头进行中段拦截的飞行设备.对EKV上红外导引头的各项探测性能参数进行了分析,分别推导了空间冷背景下和大气背景下红外导引头对点目标的作用距离方程,并对相应方程中的各项参数和影响因素进行了分析,估算了在空间冷背景下和大气背景下EKV的探测距离数据.
文摘目前,我国大部分遥感传感器的大气层外波段平均太阳光谱辐照度(Mean solar exoatmospheric irradiances over band b,简称ESUNb)尚未公布,这给遥感图像表观反射率的计算带来了不便,在一定程度上影响了数据资料的应用和推广。本文基于已有官方ESUNb值的EO1/ALI、Terra/ASTER、QuickBird等多种中、高空间分辨率传感器,对9条常见的太阳光谱曲线进行比较分析。结果表明,WRC太阳光谱曲线最合适计算中分辨率传感器的ESUNb,而Wehrli太阳光谱曲线最合适计算高分辨率传感器的ESUNb。基于WRC太阳光谱曲线和Wehrli太阳光谱曲线计算,得到了ZY-1 02C/PMS相机、ZY-3/TLC相机和MUX相机,以及GF-1/WFV相机和PMS相机各波段ESUNb值,并对ESUNb值的不确定性进行了分析。结果显示,太阳光谱选取的不同,对ESUNb的取值会产生-1.94%至1.48%的偏差。本文使用多种卫星传感器交叉比较的方式确定了最佳的太阳光谱,给出了ZY-1 02C、ZY-3和GF-1等卫星搭载的遥感传感器各波段的ESUNb值,为这些国产卫星遥感数据的广泛应用提供便利。此外,本文所用方法简便易行,在其他新的遥感传感器上具有推广应用价值。
