Showing papers on "Air-to-air missile published in 2000"

Integrated Guidance-Control Systems for Fixed-Aim Warhead Missiles

Abstract: Integrated guidance-control systems have the potential to improve missile system performance by taking advantage of the synergism existing between subsystems. These systems allow the designer to impose unusual performance requirements on the missile. Such requirements may arise out of the new sensor and warhead technologies that may require complex maneuvers at target interception. Integrated guidance-control techniques of missiles incorporating fixed-aim warheads are discussed in this paper. The fixed-aim warhead technology seeks to reduce the weapon system weight by using a highly directional warhead, together with enhancements to the guidance-control systems. The fixed-aim warhead projects the blast fragments in a direction normal to the missile longitudinal axis. In order to be effective, this warhead requires the missile to achieve a specific roll orientation with respect to the target at interception. Moreover, it is desirable to achieve a near-zero relative lateral velocity vector orientation with respect to the target at interception to minimize the sensitivity of the system to fuze delay. These specifications require the missile to perform a combination of conventional lateral acceleration maneuvers and terminal attitude maneuvers during its operation. Recently developed nonlinear control system design software is used to synthesize three different integrated guidance-control strategies. These design approaches use a nonlinear, six-degrees-of-freedom air-to-air missile model. Simulation results for sample engagement scenarios are given.

MEMS Actuated Deployable Flow Effectors System for Missile Control. AIAA Missile Sciences Conference Held in Monterey, CA on 7-9 November 2000

Abstract: : This paper presents an innovative active flow control strategy to enhance missile launch capability and increase maneuverability of missiles at high Angle of Attack ALPHA thereby allowing rear hemisphere engagement maneuvers. This flow control technique utilizes Deployable Flow Effectors DFE's, which can be actuated using miniature pneumatic valves or micropumps that are fabricated using MicroElectroMechanical Systems MEMS technology. Low power pressure sensors are integrated with the DFE's in a common fixture called a Co-Located Actuator and Sensor CLAS unit. Additionally, the CLAS unit is integrated into a 3:1 tangent ogive nosecone of a 57% scale model of a typical Air-to-Air Missile. This CLAS configuration enables high sensor spatial resolution and optimal placement of flow effectors and sensors on the missile forebody.

A method of increasing the kinematic boundary of air-to-air missiles using an optimal control approach

Abstract: : Current missile guidance laws are generally based on one of several forms of proportional navigation (PN). While PN laws are robust, analytically tractable, and computationally simple, they are only optimal in a narrow operating regime. Consequently, they may not optimize engagement range, time to intercept, or endgame kinetic energy. The advent of miniaturized high speed computers has made it possible to compute optimal trajectories for missiles using command mid-course guidance as well as autonomous onboard guidance. This thesis employs a simplified six degree of freedom (6DOF) flight model and a full aerodynamic 6DOF flight model to analyze the performance of both PN and optimal guidance laws in a realistic simulation environment which accounts for the effects of drag and control system time constants on the missile's performance. Analysis of the missile's kinematic boundary is used as the basis of comparison. A missile's kinematic boundary can be described as the maximum theoretical range at which it can intercept a target assuming no noise in its sensors. This analysis is immediately recognizable to the warfighter as an engagement envelope. The guidance laws are tested against non-maneuvering and maneuvering aircraft targets and against a simulation of a cruise missile threat. An application of the 6DOF model for a theater ballistic missile interceptor is presented.

Feasibility of Third World Advanced Ballistic and Cruise Missile Threat. Volume 2: Emerging Cruise Missile Threat

Abstract: : "The Emerging Cruise Missile Threat", study recently released by the National Defense industrial Association (NDIA) Strike, Land Attack & Air Defense Committee shows how the possibility of long range cruise missile attack by Third World countries is developing rapidly into a serious threat for U.S. interests. Current technology enables the Third World to field a large number of low-cost land-attack cruise missiles that can overwhelm capable defenses. Sophisticated land-attack cruise missiles can be constructed or modified from technologies or components currently available worldwide. The study Is Volume 2 of an industry series on the Feasibility of Third World Advanced Ballistic and Cruise Missile Threat. Volume 1, "The Long-Range Ballistic Missile Threat", was presented at the 67th MORSS at West Point In June 1999. Technologies exploited in cruise missilery include GPS/INS (Global Positioning System/Inertial Navigation System), compact avionics, flight programming software, stealth and powerful, lightweight jet propulsion systems. "The Emerging Cruise Missile Threat" focuses on the technical feasibility of production methods likely to be used by Third World countries to improve their cruise missile capability. Working exclusively from unclassified sources, the study reviews the lessons learned from historical cruise missile development programs. It assesses potential cruise missile improvements available to Third World countries. It evaluates possible alternatives to land-attack cruise missiles. It analyzes recent trends in Third World asymmetric threats. And it provides a comprehensive global cruise missile inventory, Identifying more than 80,000 cruise missiles worldwide.

Variable-structure adaptive control for air-to-air missiles with thrust vectoring

Abstract: A variable structure adaptive control system for air to air missiles with thrust vectoring control is designed. Thrust vectoring actuators are used for the missiles to get supermaneuver flight ability. The designed control law includes two control parts, i.e. the continuous control part and the discontinuous control part, which are implemented by aerodynamics and reaction jet actuators respectively. Moreover, with consideration that while the missiles are supermaneuvering, the system dynamic parameters are poorly known and rapidly changing, an adaptive estimation algorithm for the system parameter variations is proposed to simplify the control system design. Numerical simulation results are given to illustrate its effectiveness.

A Study on Optimal Design of IR MRAAM Seeker

Abstract: The basic principles , methods and problems in the optimal design of IR Medium Range Air to Air Missile (AAM) seeker parameters were discussed. Results obtained by two main programs were proved to be valuable for IR AAM optimum design .

Target for air-to-air missile attacking

Abstract: The utility model relates to a target for air-to-air missile attacking, which is characterized in that the target for air-to-air missile attacking comprises a target body which is composed of a missile head, a missile body, a missile tail and a missile wing, wherein, the missile wing comprises a canard wing which is arranged on the missile head and provided with an attack angle, a tail wing and a vertical wing which are arranged on the tail of the missile body. The missile tail is a cavity and is provided with an electromagnetic reinforcement containing wave ball. The target body is provided with an infrared source. The utility model does not need power, and has the advantages of simple structure, low cost and convenient operation and maintenance. The utility model can effectively simulate the attacked target of an actual combat, and can be used for the target attacking of the air-to-air missile for air force military training.