Air-to-air missile

About: Air-to-air missile is a research topic. Over the lifetime, 445 publications have been published within this topic receiving 3165 citations. The topic is also known as: AAM & air intercept missile.

A pitch autopilot design for blended aero and reaction-jet air-to-air missile via piecewise sliding mode control

Abstract: In this paper, the problem of blended aerodynamic and reaction-jet autopilot design for air-to-air missile with over-the-shoulder (OTS) launch capability is investigated, and a novel sliding mode control (SMC) approach with piecewise smooth sliding surface is applied to solve the problem. Considering the multi-actuator configuration of the agile missile, a four-order dynamical model is established where the reaction-jet control system (RCS) is arranged at the tail of the missile. By introducing piecewise sliding mode control (PSMC), elevator control and lateral force control are designed separately based on the idea of equivalent control and switched control. By the means of Gauss pseudospectral method (GPM), a minimum time optimal pitch command is obtained for numerical simulation. The simulation result verifies the effectiveness of PSMC for the blended control system.

Method of forming error parameters in radio-electronic control system of air-to-air missile at its self-homing to helicopter with various flight type thereof

Abstract: FIELD: physics; rocket equipment.SUBSTANCE: invention relates to radio-electronic control systems (RECS) by aircraft and can be used for homing of air-to-air missile to helicopter at various nature of its flight with corresponding dynamics. Method of mismatch parameters formation in RECS with air-to-air missile at its self-homing to helicopter at various flight character, consists in the fact that in the missile radar homing (MRH) angle meter of the missile the angular velocity of rotation of the sighting line missile-helicopter is evaluated, evaluation of helicopter bearings, there determined are increments of angular rotation speeds of the line of sight missile-helicopter, caused by helicopter maneuver in horizontal and vertical planes respectively, using the accelerometer, the missile's own accelerations in the horizontal and vertical planes are measured. In the MRH auto-speed selector parallel in each optimal Kalman filter of their matrix, the helicopter is tracked along the range and Doppler frequency at various a priori data, received during filtration in each optimum Kalman filter relative to mcharacter of helicopter flight and appropriate for each flight character of jversion of flight dynamics. At that, according to the rows of the matrix of the optimal filters there are filters, in which the a priori information is the dynamic models for various hypotheses regarding the mcharacter of the helicopter flight, and on columns - filters with dynamic models for various hypotheses relative to jversions of flight dynamics of helicopter with its corresponding mnature of flight, by Chi-square Pearson criterion is estimate mcharacter of helicopter flight, and by criterion of minimum of general dispersion of real filtration errors is estimate ĵversion of flight dynamics of helicopter for estimated value mnature of flight.EFFECT: formation of mismatch parameters in the RECS with an air-to-air missile, which enable self-guidance of the missile to the helicopter with different flight characteristics (stationary flight, flight with acceleration, flight with braking and flight in hovering mode).1 cl, 1 dwg

Research on transfer alignment for helicopter-borne air-to-air missile

Abstract: According to the characteristics that helicopter-borne master inertial navigation system is strapdown inertial navigation system, velocity, angular rate and velocity plus angular rate matching transfer alignment plans are discussed in the paper. Furthermore, observability analysis is performed which induces some important conclusions on the relationship between helicopter maneuver and its filtering observability. Digital simulation proves the validity of this method. At last, velocity plus angular rate matching transfer alignment of helicopter-borne missile is pointed out to be an efficient method worth researching.

Operational Effectiveness Evaluation for the Air-to-air Missile Based on Improved Two-step Adjudication Method

Abstract: Aiming at the lack of situation assessment and target assignment in multi-step adjudication, an improved two-step adjudication model based on the aircraft information, situation assessment and target assignment were proposed to evaluate the operational effectiveness of the air to air missile. Firstly, the altitude advantage function was introduced, meanwhile the advantage functions for entrance angle and air to air missile were modelled, which were assembled into an air combat advantage function. Then, the first-shot probability model, damage probability model and comprehensive threat criteria model were established based on the aerial warfare advantage function. Following this, the targets were assigned according to the comprehensive threat criteria model. Finally, simulations were respectively performed in head-on attack, side attack and tail-on attack conditions, and the effectiveness was verified.

The Applicability of ADS to Precision Guided Munitions Testing

Abstract: : The Systems Integration Test (SIT) was executed by the Joint Advanced Distributed Simulation (JADS) Joint Test Force (JTF) and evaluated the utility of using ADS to support cost-effective testing of an integrated missile weapon/launch aircraft system in an operationally realistic scenario. The SIT scenarios simulated a single shooter aircraft launching an air-to-air missile against a single target aircraft. Extensive testing was performed involving two different ADS architectures: (1) the shooter and target were represented by manned flight laboratories and the missile by an AIM-9M Sidewinder hardware-in-the-loop (HWIL) laboratory and (2) the shooter and target were represented by live F-16 fighters and the missile by an AIM-120 Advanced Medium Range Air-to-Air Missile (AMRAAM) HWIL laboratory. Testing was completed in October 1997, and evaluation of the results supports the conclusion that each ADS configuration has utility for T&E of the corresponding air-to-air missile involved. The applicability of ADS for the T&E of precision guided munitions (PGM) in general was assessed by extending the results and lessons learned from the SIT testing. The PGM classes considered were air-to-air missiles (AAMs), surface-to-air missiles (SAMs), air-to-ground munitions (AGM), surface-to-surface munitions, and subsurface munitions. In the ADS applications considered, the PGM could be represented by either a digital simulation model (DSM) or by an HWIL and the shooter and target could be represented by either live platforms, HWIL laboratories, or DSMs. The choice of shooter, target, and PGM representation depends on the test objectives, the details of the scenario, and the performance area and type of PGM being evaluated. This paper describes the various PGM T&E applications for which the JADS JTF believes ADS has utility. Limitations in applying ADS to PGM T&E are identified, along with applications for which ADS is judged to have little or no utility.