Interceptor Line-of-Sight Rate Steering: Necessary Conditions for a Direct Hit

Lawrence, Richard V.

doi:10.2514/2.4260

Cited by 25 publications

(17 citation statements)

References 3 publications

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“…Under the assumption that State Estimation accuracy is insensitive to state perturbations [2], the mean of system state vector could be got. The zero-effort miss (ZEM) of an interceptor is a vector that measures the closest pass to the target that will occur on its current trajectory if no corrective control is applied [5] In this section, a representative intercepting scene is conducted in three-dimension. The propagation of LOS rotate rate and the variety of ZEM are analyzed by the method raised in this paper.…”

Section: Sampling Analysis and Analytical Resultsmentioning

confidence: 99%

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A rapid endgame performance analysis method for exoatmosphere interceptor based on CADET

Zhang

Yang

2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

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The relative equations between interceptor and target are conducted in rotation coordinate of Line of Sight. An error propagate model of LOS rate is established which is based on CADET (Covariance Analysis Describing Function Technique). This model takes several factors into consideration, such as estimate error of LOS rate, acceleration saturation of interceptor, sampling rate. A set of analytical solution is acquired. The uncertainty of Zero Effort Miss distance can be got conveniently according to the variety of LOS rotate rate. Finally, a contrast simulation with Mont-Carlo is taken to demonstrate the preciseness and efficiency of the method proposed in this paper. 978-1-4799-4699-0/14/$31.

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Section: Sampling Analysis and Analytical Resultsmentioning

confidence: 99%

“…They analysis some uncertainty factors which may have impact on miss distance. Moreover, Lawrence R V [5], Martin Weiss [6] etc. do many analysis works in missile guidance performance.…”

Section: Introductionmentioning

confidence: 99%

A rapid endgame performance analysis method for exoatmosphere interceptor based on CADET

Zhang

Yang

2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

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“…The regions of uncovered evader FRS lie in the unreachable regions of the pursuer. Following the necessary conditions given by Lawrence (1998), if the evader's FRS cannot be contained in the pursuer's FRS during the FRS time interval, a trajectory exists for the evader to escape by attempting to drive its state outside the pursuer's FRS. Once the evader exits the pursuer's FRS, the pursuer is unable to reach the evader no matter what control action it takes because of its control bounds.…”

Section: Problem Of Reachabilitymentioning

confidence: 99%

“…The reachability-based framework first represents the reachable state space of both sides over a certain time horizon as reachable sets (RSs) and uses these RSs in the control of the pursuer. In studies by Salmon and Heine (1973) and Lawrence (1998), it was shown that the drawbacks of the PT framework would be overcome because as long as the evader's RS could be covered entirely by the pursuer's RS, a solution exists for the evader to be captured within that time horizon. Despite the advantage of this condition, few pursuit strategies have been developed to exploit the use of RSs in PE games (Zanardi et al 1995, Patsko andTurova 1998), although there are some applications with regard to collision avoidance problems (Mitchell 2002, Frew and Sengupta 2004, Mitchell et al 2005.…”

Section: Introductionmentioning

confidence: 97%

“…Given the definition of the RS, the FRS is simply the reachable state space of a system at a lookahead time horizon. The concept of FRS coverage is introduced as a quantitative measure of the degree of overlap that a pursuer's FRS has over the evader's FRS with respect to the result obtained by Lawrence (1998). In addition, FRS coverage can also be used to pre-determine the number of pursuers required in the case where a single pursuer is not sufficient to capture a more manoeuvrable evader, which, to the best of the author's knowledge has not previously been done.…”

Section: Introductionmentioning

confidence: 99%

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A reachability-based strategy for the time-optimal control of autonomous pursuers

Chung

Furukawa

2008

Engineering Optimization

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A control strategy for an autonomous pursuer is proposed in the reachability-based framework by using forward reachable sets (FRSs) to capture an evader vehicle time optimally. The FRS, which is a geometric representation of a vehicle's dynamic capability, allows the pursuers to determine if a single pursuer can capture the evader time optimally as well as to coordinate and maximize the chance of capturing the evader through the FRS coverage of multiple pursuers. The proposed strategy is then tested against the generic point-tracking (PT) algorithm in three different examples: (1) a single pursuer with sufficient manoeuvrability to capture an evader, (2) a single pursuer with significantly lower lateral manoeuvrability than the evader, and (3) multiple pursuers of the same manoeuvrability as in the second example. The numerical results demonstrate the superior performance of the proposed strategy over the PT algorithm when the pursuer has lower lateral manoeuvrability.

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Design of nonlinear terminal guidance/autopilot controller for missiles with pulse type input devices

Yeh¹

2010

Asian Journal of Control

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This investigation addresses a nonlinear terminal guidance/autopilot controller with pulse-type control inputs for intercepting a theater ballistic missile in the exoatmospheric region. Appropriate initial conditions on the terminal phase are assumed to apply after the end of the midcourse operation. Accordingly, the terminal controller seeks to minimize the distance between the commanded missile and the target missile to ensure a hit-to-kill interception. In particular, a 3D terminal guidance law is initially developed to eliminate the so-called "sliding velocity," thus, constraining the relative motion between the missile and the target along the line of sight. Sliding mode control is adopted to design stable pulse-type control systems. Then, a quaternion-based attitude controller is used to orient appropriately the commanded missile, taking into account the fact that the missile is a rigid body, to realize interceptability. The stability of the overall integrated terminal guidance/autopilot system is then analyzed thoroughly, based on Lyapunov stability theory. Finally, extensive simulations are conducted to verify the validity and effectiveness of the integrated controller with the pulse type inputs developed herein.

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Interceptor Line-of-Sight Rate Steering: Necessary Conditions for a Direct Hit

Cited by 25 publications

References 3 publications

A rapid endgame performance analysis method for exoatmosphere interceptor based on CADET

A rapid endgame performance analysis method for exoatmosphere interceptor based on CADET

A reachability-based strategy for the time-optimal control of autonomous pursuers

Design of nonlinear terminal guidance/autopilot controller for missiles with pulse type input devices

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