Showing papers on "Air-to-air missile published in 1997"

A guidance system for air-to-air missiles

Abstract: A method and system for providing navigational data required to guide an air-to-air missile to a target. The missile is equipped either with an infrared seeking sensor or a radar system. The trajectory of the target is predicted on the basis of a series of location measurements. A flight path of the missile is predicted such that the missile will intercept the target. Based on the predicted missile flight path, signals corresponding to the required rotational angle of the missile's sensor or radar antenna are generated and supplied to the sensor or radar's rotation control unit to cause the missile to move along the predicted flight path.

Robustness of a Variable Structure Control System for Maneuverable Flight Vehicles

Abstract: One of the key issues related to design of supermaneuverable missiles is precise control during rapid maneuvers. An autopilot synthesis for a marginally stable air-to-air missile with the inclusion of on/off reaction jets to supplement pitch control provided by the elevators is presented. The proposed control method is an extension of variable structure control theory to include simultaneous use of continuous and discontinuous actuators. Stability and robustness issues are addressed, and autopilot synthesis is then carried out. A blending of aerodynamic and propulsive controls is also introduced, based on linear programming that optimizes continuous and discontinuous control, into a single input at low angles of attack. Results from digital simulation of a controlled 180-deg maneuver of a hypothetical next-generation air-to-air missile model show that the proposed method provides stable and robust control over a wide range of e ight conditions.

Assessment of Store Control Surface Effectiveness in a Non-Uniform Aircraft Flow Field

Abstract: : Comparisons of the control effectiveness for two stores in free stream and in the flow field of a parent aircraft have been performed using computational fluid dynamics (CFD). The computations were performed to assess the changes in control surface effectiveness of the store due to the highly nonlinear flow field of the parent aircraft at transonic speeds. The Navier-Stokes equations were solved using an algebraic turbulence model for an extended range air-to-ground missile (AGM-130A) mounted on the wing pylon of an F-15E aircraft and for an air-to-air missile mounted on the forward station of the inboard pylon of an F-15E aircraft. Free-stream calculations showed good agreement with wind tunnel control surface effectiveness results for both stores. Calculations of control surface effectiveness in the aircraft flow field indicate significant changes occur for the AGM-130A missile while the air-to-air missile showed very little effect. This is attributed to the fact that a large region of separated flow occurs on the lee side of the deflected flap of the AGM-130A while the flow over the air-to-air missile deflected elevator is attached.

Air-to-air missile launching method and small-sized unmanned platform machine

Abstract: PROBLEM TO BE SOLVED: To improve a probability of remaining live of a mating team and also improve a probability of live by a method wherein an enemy airplane can be attacked in unmanned state during an air-born battle using a missile. SOLUTION: A small-sized unmanned platform air-plane 4 having a missile 3 installed therein is separated from a mother plane 1, thereafter it is automatically turned along a flying course programmed in advance. Then, during turning operation, an enemy plane is automatically caught by a target retrieving device 12 and then either active or passive hosing guidance type missile is automatically launched. The mother plane 1 performs an avoiding action after separating the small-sized unmanned platform plane 4. The small-sized unmanned platform plane 4 automatically returns to the ground under an automatic navigation control either after launching of the missile 3 or after a turning of a specified period of time.

H/sub /spl infin// controller design of a missile guidance and control system

Abstract: Presents a case study of H/sub /spl infin// robust controller design of the guidance and control system of an air-to-air missile. Simulations of a simplified linear time-invariant model and a nonlinear time-varying six degree-of-freedom model indicate that the guidance and control system with an H/sub /spl infin// controller can achieve better performance and robustness than that with a proportional navigation amplifier without changing of any other components in the system.

Recent Events in Guidance, Navigation, and Control

Abstract: This article summarizes recent events in Guidance, Navigation, and Control (GN&C) in space, weapons and missiles, and aircraft. The section on space includes recent developments with the following NASA spacecraft and space vehicles: Near Earth Asteroid Rendezvous, Deep Space 1, Microwave Anisotropy Probe, Earth Observer-1, Compton Gamma Ray Observatory, the International Space Station, X-38, and X-40A. The section on weapons and missiles includes recent developments with the following missiles: Joint Air-to-Surface Standoff Missile, Storm Shadow/Scalp EG precision standoff missile, Hellfire missile, AIM-120C Advanced medium-range air-to-air missile, Derby missile, Arrow 2, and the Standard Missile SM-3. The section on aircraft includes recent developments with the following aircraft: Joint Strike Fighter, X-31, V-22, Couger/SUDer Puma Mk. 2, Predator B 001, and the Unmanned Combat Air Vehicle.

Structural testing of the bonded body for an insensitive munitions air-to-air missile

Abstract: This paper describes the structural testing programme carried out to demonstrate the structural integrity of the adhesively bonded rocket motor body, known as Steel Strip Laminate or SSL, for a short range air-to-air missile. The Steel Strip Laminate form of body construction has been found to reduce vulnerability in Insensitive Munition and safety trials to a significant extent in extensive trials carried out over many years at Royal Ordnance Rocket Motors. Trials on the current motor, now completing development and qualification, and entering production, have further demonstrated low vulnerability. In addition, the use of very high strength steel results in an efficient, lightweight motor body structure. The motor successfully completed its structural proving programme in October 1996.