In order to settle the requirement of target location and line-of-sight(LOS) rate estimation with multi-angle measurement in terminal guidance process,the state estimation algorithm based on Kalman filter is proposed ...
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In order to settle the requirement of target location and line-of-sight(LOS) rate estimation with multi-angle measurement in terminal guidance process,the state estimation algorithm based on Kalman filter is proposed in this *** linearized system model is established,and the extended Kalman filter is used to estimate the position and LOS rate of the *** simulation results show that this method exhibits high accuracy for position estimation,and it can precisely track the change of LOS angular rate in real *** algorithm is simple in principle,easy to implement and of high value in practice.
A kind of terminal guidance law based on Gauss pseudo spectral method (GPM) is provided for the target slowing moving property. Owing to high accuracy and fast convergence, GPM was adopted to solve the optimal reentry...
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ISBN:
(纸本)9781450365307
A kind of terminal guidance law based on Gauss pseudo spectral method (GPM) is provided for the target slowing moving property. Owing to high accuracy and fast convergence, GPM was adopted to solve the optimal reentry trajectory satisfied some performance index and constraints, and the waypoints were set as corrected points. Predictor-correction guidance method was adopted to revise the location error at waypoints. Simulations prove that the guidance method has higher accuracy and can be used to guidance online.
This paper derives a new terminal homing guidance law for missiles to intercept noncooperative maneuvering targets subject to the constraint of terminal line-of-sight angle. The new guidance law avoids abrupt and larg...
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This paper derives a new terminal homing guidance law for missiles to intercept noncooperative maneuvering targets subject to the constraint of terminal line-of-sight angle. The new guidance law avoids abrupt and large changes in guidance commands, while allows the control gains to be determined analytically or chosed loosely to ease the design of guidance law. This is achieved by combining the advantages of sliding mode, prescribed performance, and inertial delay controllers. The prescribed performance controller is designed by a new two-phased prescribed performance function with an improved continuous dynamic property, which drives the predefined state error-based sliding mode variable to a small residual set around zero. The inertial delay controller is adopted to suppress the system uncertainty. Thus, the new guidance law yields continuous guidance commands over the entire terminal homing phase while eliminating abrupt and large changes in the initial phase, resulting from the initial state errors in the prescribed performance function. The newly proposed guidance law improves the prescribed performance control that dominates the gains of the proposed guidance law. Theoretical analyses and numerical simulations are conducted to verify the robustness and preciseness of the proposed guidance law.
A terminal guidance control method based on strapdown image is proposed and implemented on a SUAV(Small Unmanned Aerial Vehicle) equipped with a strapdown image processing module and a redeveloped commercial *** compa...
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ISBN:
(纸本)9781538631089;9781538631072
A terminal guidance control method based on strapdown image is proposed and implemented on a SUAV(Small Unmanned Aerial Vehicle) equipped with a strapdown image processing module and a redeveloped commercial *** compared to image stabilization platform,strapdown image module which includes a highly integrated image processing board and a micro electro-optic camera is significantly smaller,lighter and less *** measure the vertical line-of-sight angle c and the horizontal line-of-sight angle c as angles of deviation and actually do an angle ***,Median-Flow tracking algorithm which is good at tracking a stationary target with obvious features and a designed terminal guidance controller on the basis of STT are *** method is tested and verified repeatedly by using a commercial foam aircraft on spot landing and SUAV *** performance is beyond expectation with a relatively high precision.
NASA Technical Reports Server (Ntrs) 19990063983: an Investigation of terminal guidance and Control Techniques for a Robotic Mars Lander by NASA Technical Reports Server (Ntrs); published by
NASA Technical Reports Server (Ntrs) 19990063983: an Investigation of terminal guidance and Control Techniques for a Robotic Mars Lander by NASA Technical Reports Server (Ntrs); published by
NASA Technical Reports Server (Ntrs) 20000085950: an Investigation of terminal guidance and Control Techniques for a Robotic Mars Lander by NASA Technical Reports Server (Ntrs); published by
NASA Technical Reports Server (Ntrs) 20000085950: an Investigation of terminal guidance and Control Techniques for a Robotic Mars Lander by NASA Technical Reports Server (Ntrs); published by
In a practical terminal guidance process, missile acceleration may be saturated and the saturation can lead to degraded interception performance. This paper presents an anti-saturation guidance law with finite-time co...
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ISBN:
(纸本)9781509045839
In a practical terminal guidance process, missile acceleration may be saturated and the saturation can lead to degraded interception performance. This paper presents an anti-saturation guidance law with finite-time convergence for a three-dimensional maneuvering interception, using the theories of finite-time boundedness (FTB) and input-output finite-time stability (IO-FTS). With this law, the line-of-sight (LOS) angular rates converge in finite time while guaranteeing the missile accelerations do not exceed their physical limits. A sufficient condition for FTB and IO-FTS of a class of nonlinear systems is given, and is used to design the guidance law. Quasi-one-sided Lipschitz condition is employed to address the nonlinear term, and transforms the problem of ensuring the system FTB and IO-FTS simultaneously to that of solving a differential linear matrix inequality (DLMI). Simulation results verify the effectiveness of the new guidance law design.
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