Nonorthodox Guidance Law Development Approach for Intercepting Maneuvering Targets

Shinar, J.; Shima, Tal

doi:10.2514/2.4960

Cited by 98 publications

(34 citation statements)

References 10 publications

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“…Therefore, the case selected for investigation is the one where the interceptor does not have an agility advantage over the target but has a maneuverability advantage using aerodynamic control only. 8) The maximum operation time of the RCS, Át, satisfies:…”

Section: Game Space Structurementioning

confidence: 99%

“…6) Based on realistic TBM flight conditions, the scenario was then extended to include time-varying velocities 7) and inherent estimation delay. 8) In all the above scenarios only a single actuator is considered, so guidance laws cannot be applied by interceptors with dual control systems. Recently, an end-game guidance strategy tailored for an air-to-air missile with forward and aft control system was presented.…”

Section: Introductionmentioning

confidence: 99%

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Bounded Differential Game Guidance Law for Interceptor Missiles with Aero Fins and Reaction Jets

Zhang

et al. 2011

Trans. Japan Soc. Aero. S Sci.

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A differential game guidance law for an endoatmospheric interceptor missile steered by aero fins and reaction jets is developed in this paper with bounded controls. For a low-altitude endoatmospheric interceptor, the propellant of the reaction-jet control system (RCS) is restricted by the missile configuration. Considering propellant limits, the effect of the RCS thrust on homing performance is investigated through game space structures. Also, to use the RCS at an appropriate timing, game space decomposition is used to determine the initiating time of the RCS. Finally, the effectiveness of the guidance law is demonstrated by a realistic ballistic missile defense scenario. It is shown that the proposed guidance law provides a significant improvement in homing accuracy compared to the conditional one. Furthermore, under propellant limits, a bigger RCS thrust cannot guarantee a higher homing accuracy.

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Section: Game Space Structurementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Bounded Differential Game Guidance Law for Interceptor Missiles with Aero Fins and Reaction Jets

Zhang

et al. 2011

Trans. Japan Soc. Aero. S Sci.

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Section: Introductionmentioning

confidence: 99%

“…Several specific two pursuers one evader differential games have been already studied ([4], [7]). Nevertheless, we propose to compute 2x1 NEZ from 1x1 DGL/1 NEZ because DGL models are games with well defined analytical solutions [12].We consider head on scenarios with two pursuers (P1 and P2) and one evader (E). First we summarize results about one on one pursuit evasion game using DGL/1 models.…”

mentioning

confidence: 99%

Linear Differential Game with Two Pursuers and One Evader

Ménec

2010

Annals of the International Society of Dynamic Games

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The purpose of this paper is to compute two on one differential game No Escape Zones (NEZ) [8]. The main objective (over the scope of this paper) consists in designing suboptimal strategies in many on many engagements. 1x1 NEZ and 2x1 NEZ are components involved in suboptimal approaches we propose (i.e. "Moving Horizon Hierarchical Decomposition Algorithm" [6]). Several specific two pursuers one evader differential games have been already studied ([4], [7]). Nevertheless, we propose to compute 2x1 NEZ from 1x1 DGL/1 NEZ because DGL models are games with well defined analytical solutions [12].We consider head on scenarios with two pursuers (P1 and P2) and one evader (E). First we summarize results about one on one pursuit evasion game using DGL/1 models. DGL/1 differential games are co planar interceptions with constant velocities, bounded controls assuming small motion variations around the collision course triangle. Under this assumption the kinematics are linear. Each player is represented as a first order system (time lag constant). The criterion is the terminal miss distance (terminal cost only, absolute value of the terminal miss perpendicular to the initial Line Of Sight, LOS). DGL/1 are fixed time duration differential games, with final time defined by the closing velocity (assumed constant) and the initial pursuer evader range. The terminal projection procedure [3] allows to reduce the initial four dimension state vector representation to a scalar representation and to represent the optimal trajectories in the ZEM (Zero Effort Miss), Tgo (Time to Go) coordinate frame. The (ZEM, Tgo) frame is divided into two regions, the regular area and the singular one. For some appropriated differential game parameters (pursuer to evader maximum acceleration ratio μ and evader to pursuer time lag ratio ε), the singular area plays the role of capture zone so called also NEZ (leading to zero terminal miss), whilst the regular area corresponds to the non capture zone. The NEZ can be bounded (closed) or unbounded (open). The natural optimal strategies are bang-bang controls corresponding to the sign of ZEM (some refinements exist when defining optimal controls inside the NEZ). We start the 2x1 DGL/1 analysis with unbounded 1x1 NEZ as pictured in Figure 1 (NEZ delimited by the two plain red lines, non capture zone corresponding to the state space filled with optimal trajectories in dot blue lines). Moreover, we first assume same Tgo in each DGL/1 game (same initial range, same velocity for each pursuer).

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“…8,11,[14][15][16] Such formulation of a scenario with the assumption of ideal dynamics of two players 17) was investigated and later extended to include first-order pursuer dynamics 18) and evader dynamics. 19) Two formulations 20) are studied for the linear-quadratic differential game associated with a trajectory-shaped interception phase of the interceptor.…”

Section: Introductionmentioning

confidence: 99%

Bounded Linear-Quadratic Differential Game Guidance Law for Dual-Thruster Controlled Missiles

Liu

Lü

et al. 2012

Trans. Japan Soc. Aero. S Sci.

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A guidance law tailored for an interceptor missile steered by aerodynamic lift and divert-thruster and with its attitude oriented by forward attitude-thruster (dual-thruster control) is proposed. The bang-bang strategy has the maximal capture zone. However, it leads to control chattering, resulting in excessive control effort. The continuous strategies have smaller capture zones, but can require a smaller control effort. The combination of bang-bang and continuous strategies may lead to a cooperative effect of the capture zone and control effort. In this paper, the guidance law is derived using a linearquadratic differential game formulation and then modified for bounded controls. For the derivation, the interceptor closed-loop dynamics is represented by a first-order biproper transfer function for the attitude-thruster control system and a strictly proper one for the divert-thruster control system, respectively. Analysis based on the proposed guidance law shows that the divert-thruster control system has higher efficiency due to its small time constant and the direct forces that mainly affect the short-term behavior of the missiles. The parameters' effects and the control command distribution are also studied.

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Nonorthodox Guidance Law Development Approach for Intercepting Maneuvering Targets

Cited by 98 publications

References 10 publications

Bounded Differential Game Guidance Law for Interceptor Missiles with Aero Fins and Reaction Jets

Bounded Differential Game Guidance Law for Interceptor Missiles with Aero Fins and Reaction Jets

Linear Differential Game with Two Pursuers and One Evader

Bounded Linear-Quadratic Differential Game Guidance Law for Dual-Thruster Controlled Missiles

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