Model Predictive Lateral Pulse Jet Control of an Atmospheric Rocket

Bradley Burchett; Mark Costello

doi:10.2514/2.4979

A Comparison of Different Guidance Schemes for a Direct Fire Rocket with a Pulse Jet Control Mechanism

10.21236/ada401519 ◽

2002 ◽

Cited By ~ 4

Author(s):

Thanat Jitpraphai ◽

Bradley Burchett ◽

Mark Costello

Keyword(s):

Control Mechanism ◽

Jet Control ◽

Pulse Jet

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Design of Missile Autopilot with Aerodynamic Lift and Reaction Jets Based on Auto Disturbance Rejection Controller

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.472-475.1036 ◽

2012 ◽

Vol 472-475 ◽

pp. 1036-1039

Author(s):

Chong Yang ◽

Ke Zhang ◽

Mei Bai Lu

Keyword(s):

Disturbance Rejection ◽

Response Speed ◽

Fast Response ◽

Urgent Problem ◽

Robust Performance ◽

Active Disturbance Rejection ◽

Disturbance Rejection Control ◽

Lateral Pulse Jet ◽

Aerodynamic Lift ◽

Pulse Jet

First a new autopilot design model is presented for the interceptor missile with the blended aerodynamic lift and reaction jet. The reaction jet can improve the response speed, but the structure of control system becomes more complex. Therefore how to design control strategy properly is an urgent problem. Second, considering the discrete property of the lateral pulse jet thrusters and the continuous property of the aerodynamic fins, a kind of ADRC (active disturbance rejection control) autopilot system was designed for the aerodynamic lift/reaction jet missile. Finally, through a testing in the simulation of MATLAB, it is shown that, due to the sufficient utilization of the reaction jet, there is a significant improvement in the fast response and robust performance of the proposed controller. It is applicable to design the autopilot of aerodynamic lift and reaction jet blended missile.

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Short wide angle diffuser with pulse jet control

10.2514/6.1999-280 ◽

1999 ◽

Cited By ~ 5

Author(s):

S. Raghunathan ◽

J. Watterson ◽

R. Cooper ◽

S. Lee

Keyword(s):

Wide Angle ◽

Jet Control ◽

Pulse Jet

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Pulse-frequency modulated guidance laws for a mortar missile with a pulse jet control mechanism

The Aeronautical Journal ◽

10.1017/s0001924000010526 ◽

2015 ◽

Vol 119 (1213) ◽

pp. 389-405 ◽

Cited By ~ 1

Author(s):

M. Pavic ◽

B. Pavkovic ◽

S. Mandic ◽

S. Zivkovic ◽

D. Cuk

Keyword(s):

Sliding Mode ◽

Design Parameters ◽

Proportional Navigation ◽

Adaptive Sliding Mode ◽

Jet Control ◽

Control Authority ◽

The Individual ◽

Miss Distance ◽

Guidance Laws ◽

Pulse Jet

AbstractThe impact point dispersion of mortar missiles can be drastically reduced with a control ring of lateral pulse jets located around the centre of gravity and a homing head to measure or to derive estimates of appropriate missile-target states, e.g. the line-of-sight rates. A simulation model including a missile as a six-degree-of-freedom vehicle, a jet pulse flight control system, and a relative missile-to-target motion was used for the comparison of four guidance laws i.e. proportional navigation guidance, augmented proportional navigation, augmented proportional navigation with rendezvous, and adaptive sliding-mode guidance. This paper focuses on the efficiency of pulse jet control on miss distance, and thus makes the assumption that sensor measurements and the guidance states required to apply each of the guidance laws are perfectly known. Proportional navigation and the adaptive sliding mode guidance exhibit a large miss distance due to limited control authority. Augmented proportional navigation is slightly better than augmented proportional navigation with rendezvous for the same design parameters and they both give small miss distances with limited control authority, but they both require a free gyro. A proper selection of the design parameters — the number of pulse jets and the magnitude of the individual pulse jet thrust for a particular dispersion of flight parameters and the instant of the guidance start — is required to achieve optimum dispersion reduction. The minimum intensity of the individual pulse jet impulse required for the ‘pin point’ accuracy (the circular error probable smaller than 1m) of the mortar missile was determined for all presented guidance laws considering dispersion from the nominal trajectory.

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