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Bhimashankar Gurav, John Economou, Alistair Saddington and Kevin Knowles
Linear first/second order fin direct current (DC) actuator model approximations for missile applications are currently limited to angular position and angular velocity state variables. Furthermore, existing literature with detailed DC motor models is dec...
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Bhimashankar Gurav, John Economou, Alistair Saddington and Kevin Knowles
Linear first/second order fin direct current (DC) actuator model approximations for missile applications are currently limited to angular position and angular velocity state variables. Furthermore, existing literature with detailed DC motor models is dec...
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Yi Gao and Juanmian Lei
At present, there is no publicly published research on the unsteady interference effect in the start-up process of the lateral jet control of the spinning missile. The variation of aerodynamic characteristics during the jet start-up process of the spinni...
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Xiaoguang Wang, Jun Yang, Jian Guo and Jun Guo
In the demonstration phase of a missile scheme, to obtain the optimum proposal, designers need to modify the parameters of the overall structure frequently and significantly, and perform the structural analysis repeatedly. In order to reduce the manual w...
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Wenwen Wang, Mingyu Wu, Zhihua Chen and Xiaoli Liu
This study applies deep-reinforcement-learning algorithms to integrated guidance and control for three-dimensional, high-maneuverability missile-target interception. Dynamic environment, reward functions concerning multi-factors, agents based on the deep...
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Erdem Dikbas and Özgür Ugras Baran
In this study, we present our improved RANS results of the missile aerodynamic flow computation involving leading edge vortex separation. We have used our in-house tailored version of the open source finite volume solver FlowPsi. An ongoing study in the ...
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Zheng Gong, Zan Zhou, Zian Wang, Quanhui Lv, Jinfa Xu and Yunpeng Jiang
This paper presents a classic missile-type parallel-approach guidance law for fixed-wing UAVs in coordinated formation flight. The key idea of the proposed guidance law is to drive each follower to follow the virtual target point. Considering the turning...
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Yang Li, Wanchun Chen and Liang Yang
In this paper, a linear Chebyshev pseudospectral method (LCPM) is proposed to solve the nonlinear optimal control problems (OCPs) with hard terminal constraints and unspecified final time, which uses Chebyshev collocation scheme and quasi-linearization. ...
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Chendi Li, Jiang Wang and Peng Huang
This correspondence proposes an optimal cooperative guidance law for protecting a target from a guided missile. The linearized three-body kinematics using the line-of-sight (LOS) triangle concept is formulated, and a new concept called error distance is ...
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Christian Franzmann, Friedrich Leopold and Christian Mundt
An experimental method for the determination of the pitch damping moment coefficient sum ??????+???????
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in a wind tunnel at transonic and low supersonic Mach numbers is developed. With support interference being a major issue for dynamic...
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Jiaxun Li, Xi Chen, Kang Niu and Jianqiao Yu
A novel finite-time tracking control algorithm with disturbances observer is investigated for agile missiles in the presence of mismatched and matched disturbances. A finite-time disturbance observer with the continuous super-twisting algorithm is design...
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Xu Liu, Keyong Zhu, Yijie Wei, Ziwei Chen, Mingming Ge and Yong Huang
In this paper, the thermal management of missile-borne components in a flight state is studied. Avoiding excessive component temperatures under the high-temperature circumstances brought by aerodynamic heat is a requirement to guarantee the equipment?s s...
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Kelin Lu, Bingyu Jin and Ning Zhang
The radome refraction problem gives rise to guidance performance deterioration for homing missiles. Aiming to eliminate the effect of radome refraction on the radar seeker, a novel method is proposed for correcting the radome-induced measurement error by...
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Guang Zhan, Zheng Gong, Quanhui Lv, Zan Zhou, Zian Wang, Zhen Yang and Deyun Zhou
This paper reports on the formation and transformation of multiple fixed-wing unmanned aerial vehicles (UAVs) in three-dimensional space. A cooperative guidance law based on the classic missile-type parallel-approach method is designed for the multi-UAV ...
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Witold Buzantowicz
A description is given of an application of a linear-quadratic regulator (LQR) for stabilizing the characteristics of an anti-aircraft missile, and an analytical method of selecting the weighting elements of the gain matrix in feedback loop is proposed. ...
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Robert Glebocki and Mariusz Jacewicz
In vertical cold launch the missile starts without the function of the main engine. Over the launcher, the attitude of the missile is controlled by a set of lateral thrusters. However, a quick turn might be disturbed by various uncertainties. This study ...
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Daseon Hong, Minjeong Kim and Sungsu Park
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Dariusz Horla
The paper presents the application of variational calculus to achieve the optimal design of the open-loop control law in the process of anti-ballistic missile interception task. It presents the analytical results in the form of appropriate Euler?Lagrange...
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Christian Falaster
Pág. 136 - 137
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