Ballistic missile trajectory prediction using a state transition matrix

Harlin, W. J.; Cicci, David A.

doi:10.1016/j.amc.2006.11.048

Cited by 22 publications

(8 citation statements)

References 3 publications

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“…Calculation method for the impact point (area) of a ballistic missile has been developed [17], here we will not discuss s ij furthermore. Figure 4 is a process of solving IRP problem.…”

Section: Target-interceptor Assignment Modelmentioning

confidence: 99%

Modified particle swarm optimization for BMDS interceptor resource planning

Fu-xian

Long

et al. 2015

Appl Intell

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One important mission of the strategic defense is to develop an integrated, layered Ballistic Missile Defense System (BMDS). We consider the problem of assigning interceptors to multiple waves of incoming ballistic missiles. This work addresses the issue of shot time constraints and directly allocates multiple targets to interceptors in the single engagement problem. A mathematical model and method for BMDS Interceptor resource planning (IRP) is presented. In addition to mathematical model, a modified particle swarm optimization RPPSO algorithm has been developed for solving complex IRP problem. This algorithm adapted a basic PSO algorithm to make it compatible with reasonable engineering problems. RPPSO was developed by embedding a reverse predictor within the basic algorithm to avoid premature convergence without significantly reducing convergence speed, and adding a repulsive force to keep the diversity of both local and global optima.

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“…Calculation method for the impact point (area) of a ballistic missile has been developed [17], here we will not discuss s ij furthermore. Figure 4 is a process of solving IRP problem.…”

Section: Target-interceptor Assignment Modelmentioning

confidence: 99%

Modified particle swarm optimization for BMDS interceptor resource planning

Fu-xian

Long

et al. 2015

Appl Intell

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“…The target is assigned a mathematical value of zero. References which adequately explain this algorithm as it pertains to missiles can be found in Brassard et al (1997), Cloutier et al (1992), Harlin and Cicci (2007), and Liang and Green (1993). Establishing the need to measure the head motion of aviators while observing and flying flight maneuvers in the flight simulator, the authors reversed the aforecited collision algorithm and placed the test subjects in a fixed position utilizing a horizontal and vertical laser system and assigning the test subject a value of zero.…”

Section: Infrared Tracking Utilizing Guidance Technologymentioning

confidence: 99%

Head‐tilt and pilot fatigue measured by flight simulation

Zallen

Cochran²,

Bailey³

2012

Aircraft Engineering and Aerospace Technology

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Purpose -The purpose of this paper is to define and determine quantifiable measurements for head-tilt and pilot fatigue by detecting and measuring the six degrees of freedom (6DOF) head motion of test subjects performing flight simulation operations. Design/methodology/approach -First, a flight simulator that met the needs of the research project was designed and fabricated. Second, the tracking system was tested and deemed operable through a series of shakedown runs. Then, the head motion of test subjects was detected and measured using infrared technology. Finally, the data collected were used to establish definitions for head-tilt and pilot fatigue. Findings -Head-tilt and pilot fatigue were defined and evidence of their presence was observed in the head motion data. Practical implications -The goal of this research is to reduce aircraft accidents upon landing and take-off for general, commercial, and military aviation to include unmanned aerial vehicles. Originality/value -Literature which covers the definition and measurement of a pilot's head motion in flight is unclear. By defining the optokinetic phenomena of head-tilt and precisely measuring pilot head motion and developing and using tests of pilots based on the results to screen for head-tilt, the number of land aircraft veering off runways during both landing and takeoff can be reduced. Also, the number of aircraft overshooting the flight deck on an aircraft carrier can be reduced, as well as fewer crashes upon landing of unmanned aerial vehicles.

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“…Most rockets use rocket engines with solid fuel, but some long-range missiles use engines with liquid fuel which gives them fuel storage capacity to execute certain final maneuvers before striking down the target or to position itself on the best path for striking down the target, this are energy and fuel consuming maneuvers. Instead there are missiles with solid fuel which execute maneuvers during evolution, but these uses a second missile engine which starts during the execution maneuvers (Gansler, 2010). Steering and control system of the missile have an servocontrol electro-mechanic which takes commands from the guidance system and control the control surfaces of the missile, consisting of directional fins, to position the missile to the target or facilitate tracking maneuvers (Fleeman & Schetz, 2012).…”

Section: Introductionmentioning

confidence: 99%

“…The main research studies regarding to ballistic missiles can be divided in some domains: design and construction of the missiles (Luo, Yang, & Chen, 2006), aerodynamic flight performance calculations of the missiles (Zhang, Wang, & Liu, 2013), studies on detecting ballistic missiles (Liu, Mclernon, Ghogho, Hu, & Huang, 2012), research on control of the ballistic missiles (Wael & Quan, 2011), aspects of missile trajectory prediction (Harlin & Cicci, 2007 This used structure is an idea which was applied for eliminate the force which appear on the missile skin. The model is designed for a better maneuverability to a range of speeds up to Mach 7.…”

Section: Introductionmentioning

confidence: 99%