scholarly journals Terminal Guidance with Attack Time and Impact Angle Constraints for Hypersonic Vehicle in Dive Phase

2018 ◽  
Vol 2018 ◽  
pp. 1-9
Author(s):  
Zhao-ting Li ◽  
Hong-bo Zhang
Keyword(s):  
Real Time ◽  
Three Dimensional ◽  
Vertical Plane ◽  
Impact Angle ◽  
Multiple Constraints ◽  
Flight Path Angle ◽  
Terminal Guidance ◽  
Guidance Problem ◽  
Front Section ◽  
Attack Time

The terminal guidance problem of hypersonic gliding missiles under multiple constraints was considered regarding a coordinated attack in time and space. In this paper, a three-dimensional terminal guidance method based on the real-time updating of parameters is proposed with consideration to the attack time and terminal angle. By this method, the three-dimensional motion was decomposed into the horizontal and vertical plane. In each plane, a real-time solution of the optimal trajectory yielded angle commands that satisfied the terminal angle constraints. Additionally, the time was controlled by changing the flight path angle in the front section of the vertical plane. The results obtained by numerical simulation indicated the good applicability and robustness of this method.

scholarly journals Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP

2019 ◽  
Vol 2019 ◽  
pp. 1-16 ◽  
Author(s):  
Yang Li ◽  
Hao Zhou ◽  
Wanchun Chen
Keyword(s):  
Initial Conditions ◽  
Three Dimensional ◽  
Impact Angle ◽  
Guidance Law ◽  
Flight Path Angle ◽  
Saturation Constraints ◽  
Control Saturation ◽  
Heading Angle ◽  
Saturation Constraint ◽  
Impact Angles

A new nonlinear guidance law for air-to-ground missile cooperation attacks is proposed in this paper. This guidance law enables missiles with different initial conditions to attack targets simultaneously, and it can also precisely satisfy the terminal impact angle conditions in both flight-path angle and heading angle. The guidance law is devised using the model predictive static programming (MPSP) method, and the control saturation constraint is incorporated in the MPSP algorithm. The first-order-lag acceleration of the missile is taken as the state variable to realize the convergence of the terminal acceleration to zero. Moreover, a collision avoidance strategy for three-dimensional missile cooperative flight is proposed. The simulation results show that the guidance law can make the missiles hit the target accurately at the same time with the ideal impact angles and can realize the control saturation constraints of the missiles. This can increase the attack effects and is significant for collaborative attacks.

scholarly journals Studies on Multi-Constraints Cooperative Guidance Method Based on Distributed MPC for Multi-Missiles

2021 ◽  
Vol 11 (22) ◽  
pp. 10857
Author(s):  
Mingyu Cong ◽  
Xianghong Cheng ◽  
Zhiquan Zhao ◽  
Zhijun Li
Keyword(s):  
Three Dimensional ◽  
Impact Angle ◽  
Distributed Model ◽  
Guidance Law ◽  
Multiple Missiles ◽  
Virtual Leader ◽  
Prediction Control ◽  
The Impact ◽  
Terminal Guidance ◽  
Impact Angle Constraint

Cooperative terminal guidance with impact angle constraint is a key technology to achieve a saturation attack and improve combat effectiveness. The present study envisaged cooperative terminal guidance with impact angle constraint for multiple missiles. In this pursuit, initially, the three-dimensional cooperative terminal guidance law with multiple constraints was studied. The impact time cooperative strategy of virtual leader missile and follower missiles was designed by introducing virtual leader missiles. Subsequently, based on the distributed model prediction control combined with the particle swarm optimization algorithm, a cooperative terminal guidance algorithm was designed for multiple missiles with impact angle constraint that met the guidance accuracy. Finally, the effectiveness of the algorithm was verified using simulation experiments.

scholarly journals Cooperative Intercepting Guidance Law for Large Maneuvering Target with Impact Angle Constraint

2020 ◽  
Vol 38 (6) ◽  
pp. 1257-1265
Author(s):  
Zhengyu Guo ◽  
Chaolei Wang ◽  
Hang Qian ◽  
Zhiguo Han ◽  
Jingxian Zhang
Keyword(s):  
Finite Time ◽  
Sliding Mode ◽  
Three Dimensional ◽  
Impact Angle ◽  
Attack Angle ◽  
Lateral Acceleration ◽  
Terminal Sliding Mode ◽  
Maneuvering Target ◽  
Guidance Law ◽  
Terminal Guidance

A distributed multi-missile cooperative guidance law based on the finite time theory is proposed to solve the terminal guidance problem of three-dimensional multi-missiles cooperative interception of large maneuvering target. According to the finite time consistency theory, an adaptive guidance law based on the integral sliding mode is designed to ensure that all missiles can reach the target at the same time in the terminal guidance process. The longitudinal and lateral acceleration of the line of sight are based on the guidance law of the fast terminal sliding mode surface. The terminal attack angle is constrained, so that the terminal attack Angle can reach the expected value in finite time. The simulation results show that the designed guidance law can achieve the cooperative attack on the maneuvering targets.

Novel guidance model and its application for optimal re-entry guidance

2018 ◽  
Vol 122 (1257) ◽  
pp. 1811-1825
Author(s):  
C.W. Jiang ◽  
G.F. Zhou ◽  
B. Yang ◽  
C.S. Gao ◽  
W.X. Jing
Keyword(s):  
Three Dimensional ◽  
Impact Angle ◽  
Guidance Law ◽  
Optimal Guidance ◽  
Entry Guidance ◽  
Independent Variable ◽  
Guidance Laws ◽  
Terminal Guidance ◽  
Impact Angle Constraint ◽  
Guidance Model

ABSTRACTAiming at three-dimensional (3D) terminal guidance problem, a novel guidance model is established in this paper, in which line-of-sight (LOS) range is treated as an independent variable, describing the relative motion between the vehicle and the target. The guidance model includes two differential equations that describe LOS’s pitch and yaw motions in which the pitch motion is separately decoupled. This model avoids the inaccuracy of simplified two-dimensional (2D) guidance model and the complexity of 3D coupled guidance model, which not only maintains the accuracy but also simplifies the guidance law design. The application of this guidance model is studied for optimal re-entry guidance law with impact angle constraint, which is presented in the form of normal overload. Compared with optimal guidance laws based on traditional guidance model, the proposed one based on novel guidance model is implemented with the LOS range instead of time-to-go, which avoids the problem of the time-to-go estimation of traditional optimal guidance laws. Finally, the correctness and validity of the guidance model and guidance law are verified by numerical simulation. The guidance model and guidance law proposed in this paper provide a new way for the design of terminal guidance.

scholarly journals Intercepting Higher-Speed Targets Using Generalized Relative Biased Proportional Navigation

2019 ◽  
Vol 37 (4) ◽  
pp. 682-690
Author(s):  
Ronggang Wang ◽  
Shuo Tang
Keyword(s):  
High Speed ◽  
Impact Angle ◽  
Time Varying ◽  
Proportional Navigation ◽  
Guidance Law ◽  
Maneuvering Targets ◽  
Flight Path Angle ◽  
Proportional Navigation Law ◽  
The Impact ◽  
Terminal Guidance

To intercept a higher-speed target in the terminal guidance phase, this paper proposes a generalized relative biased proportional navigation (BPN) law. In order to enlarge the capture domain of the classical proportional navigation (PN) law and make full use of the maneuverability of a missile, the paper designs time-varying navigation coefficients; thus the modified PN guidance law integrates the advantages of the PN guidance law with those of the retro-PN guidance law. In order to intercept high-speed targets with impact angle constraints, the relative BPN law is introduced, and the impact angle is achieved by controlling the relative flight-path angle. In order to improve the performance of the guidance law for intercepting higher-speed maneuvering targets, some compensation measures are designed for guidance commands. Extensive simulations are conducted to verify the design features of the proportional navigation law.

Evaluation of the mitral valve by transthoracic real-time three-dimensional echocardiography

2010 ◽  
Vol 151 (21) ◽  
pp. 854-863 ◽  
Author(s):  
Attila Nemes ◽  
Marcel L. Geleijnse ◽  
Osama I. I. Soliman ◽  
Wim B. Vletter ◽  
Jackie S. McGhie ◽  
...  
Keyword(s):  
Mitral Valve ◽  
Real Time ◽  
Three Dimensional ◽  
Dimensional Echocardiography ◽  
Three Dimensional Echocardiography

Jelenleg az echokardiográfia a legszéleskörűbben alkalmazott rutin noninvazív diagnosztikus eljárás, amelynek segítségével a mitralis billentyű morfológiája és funkciója jellemezhető. Ennek az összefoglaló jellegű közleménynek a célja az egyik legújabb echokardiográfiás fejlesztés, a transthoracalis real-time háromdimenziós echokardiográfia szerepének bemutatása a mitralis billentyű vizsgálatában.

Sign in / Sign up

Export Citation Format

Share Document