Missile

About: Missile is a research topic. Over the lifetime, 12829 publications have been published within this topic receiving 94307 citations. The topic is also known as: guided missile & missiles.

Guidance performance analysis with in-flight radome error calibration

Abstract: ^Cornford, B.A. and Bain, M.A., "The Kinematics of Proportional Navigation Courses for a Missile with a Time Lag," Royal Aircraft Establishment, England, Tech. Note GW85, Oct. 1950. Paarman, L.O., Farone, J.M., and Smoots, G.W., "Guidance Law Handback for Classical Proportional Navigation," IIT Research Institute, Chicago, 111, Rept. GACIAC HB-78-01, June 1978. Pastrick, H.L., Seltzer, S.M., and Warren, M.E., "Guidance Laws for Snort-Range Tactical Missiles," Journal of Guidance and Control, March-April 1981, pp. 98-108. 1 ^Arbenz, K., "Proportional Navigation of Nonstationary Targets," IEEE Transactions on Aerospace and Electronic Systems, July 1970, pp. 455-457. , Nesline, F.W. and Zarchan, P., "A New Look at Classical ys Modern Homing Missile Guidance," Journal of Guidance and Control, Jani-Feb. 1981, pp. 78-85. Smith, W.M., "Preliminary Trajectory Shaping Policy for SM2 Block 11 ER/HAW," General Dynamics, Pomona, Calif., TM 6-331-119.30.1, Jan. 1979. Chadwiek, W.R., "A Theoretical Analysis of Collision Course Navigation with Command Guidance," Weapons Research Establishment, South Australia, 1%ch. Note SAD 141, Dec. 1964.

Adaptive multiple sliding surface control for integrated missile guidance and autopilot with terminal angular constraint

Abstract: Integrated guidance and control for homing missiles with terminal angular constraint is considered. A time-varying integrated guidance and control model with unmatched uncertainties is formulated. In order to solve the multiple states regulation problem of such a system, an adaptive multiple sliding surface control algorithm is developed. It is proved that the proposed feedback controller can drive the missile to intercept the target accurately with a desired terminal attitude angle, and ensure the stability of the missile dynamics simultaneously. The 6DOF nonlinear missile simulation results demonstrate the feasibility of the proposed integrated guidance and control design scheme.

Precision-guided hypersonic projectile weapon system

Abstract: A precision-guided hypersonic projectile weapon system. The inventive system includes a first subsystem for determining a target location and providing data with respect thereto. A second subsystem calculates trajectory to the target based on the data. The projectile is then launched and guided in flight along the trajectory to the target. In the Illustrative application, the projectile is a tungsten rod and the first subsystem includes a forward-looking infrared imaging system and a laser range finder. The second subsystem includes a fire control system. The fire control system includes an optional inertial measurement unit and predicts target location. The projectile is mounted in a missile launched from a platform such as a vehicle. After an initial burn, the missile launches the projectile while in flight to the target. The missile is implemented with a rocket with a guidance system and a propulsion system. In accordance with the present teachings, the guidance system includes a transceiver system mounted on the projectile. The transceiver system includes a low-power continuous wave, millimeter wavelength wave emitter. A system is included at the launch platform for communicating with the projectile. The platform system sends a blinking command to the projectile and measures the round trip delay thereof to ascertain the range of the projectile. Velocity is determined by conventional Doppler techniques or differentiation. Azimuth and elevation are then determined by a monopulse antenna on the launch platform. As a consequence, the platform ascertains the location of the projectile and the impact point thereof. The platform generates a command to the projectile which is received by the projectile and used to actuate control surfaces to adjust the trajectory and impact point thereof as necessary.