Showing papers on "Air-to-air missile published in 2016"

Using agent-based modeling and a designed experiment to simulate and analyze a new air-to-air missile

Abstract: New weapons system analysis is a field with much interest and study due to the enduring requirement for militaries to improve their set of tactical capabilities. Moreover, as development, testing, ...

Flush air data sensing system design for air breathing air-to-air missile

Abstract: The key technical difficulties and design flow of flush air data sensing (FADS) system design for air breathing air-to-air missile are analyzed. The aspirated air-to-air missile large slenderness than layout, high maneuverability, high angle of attack and low cost control characteristics proposed a high precision, multi-points of fault diagnosis and fault-tolerant and anti overload of fads system design method. Mainly includes the algorithm design based on strategy of pressure model, hierarchical diagnosis and multi-models of re-configurable fault-tolerant, the error source of the system control model design, high precision and anti overload pressure measurement module design and solution machine module design. According to the shape of a typical air breathing air-to-air missile, the FADS system principle prototype is designed, which is based on 9 pressure measuring points layout and flight Mach number 1.5–4.0. Prototype real-time solution test is done in 1.2 m×1.2 m supersonic wind tunnel. Test results show that: relative error of static pressure measurement is no more than 6.9%, measurement error of Mach number is no more than 0.10, the measurement errors of the angle of attack and side slip angle are no more than 1°. The measurement error of the reconstructed model is close to the baseline model error; algorithm fault diagnosis points is less than or equal to 3, the scope of fault diagnosis of P1 deviation is less than or equal to −20% or greater than or equal to 40%, P2–P9 deviation is less than or equal to −30% or greater than or equal to 30%. The algorithm has less than or equal to 2 fault tolerant ability. The measurement error level, fault diagnosis and tolerance ability of the system can meet the engineering requirements.

Semi-strapdown air-to-air missile guidance method based on sliding mode variable structural theory

Abstract: The invention discloses a semi-strapdown air-to-air missile guidance method based on a sliding mode variable structural theory. The semi-strapdown air-to-air missile guidance method comprises the following steps of 1, acquiring a missile-target line-of-sight turn rate differential model under a line-of-sight coordinate system; 2, acquiring a motion tracking sliding mode guidance rule; and 3, acquiring an expected line-of-sight turn rate xd. According to the method, a sigmoid function is applied to the sliding mode surface design of the motion tracking sliding mode guidance rule, the missile-target line-of-sight angular rate is improved at the initial guidance stage, the estimation to the target motion state is improved, the missile-target line-of-sight angular rate is made to be zero at the last guidance stage, the miss distance is lowered, and the missile hit precision is improved.

Tracking Air-to-Air Missile Using Proportional Navigation Model with Genetic Algorithm Particle Filter

Abstract: The purpose of this paper is to track the air-to-air missile. Here we put forward the PN-GAPF (Proportional Navigation motion model and Genetic Algorithm Particle Filter) method to solve the problem. The main jobs we have done can be listed as follows: firstly, we establish the missile state space model named as the Proportional Navigation (PN) motion model to simulate the real motion of the air-to-air missile; secondly, the PN-EKF and PN-PF methods are proposed to track the missile, through combining PN motion model with EKF and PF; thirdly, in order to solve the particle degeneracy and diversity loss, we introduce the intercross and variation in GA to the particles resampling step and then the PN-GAPF method is put forward. The simulation results show that the PN motion model is better than the CV and CA motion models for tracking the air-to-air missile and that the PN-GAPF method is more efficient than the PN-EKF and PN-PF.

Terminal Velocity Maximization of Air-to-Air Missiles in Agile Turn Phase

Abstract: Terminal velocity maximization of air-to-air agile missiles during agile turn phase is studied. It is important to make sure that agile missiles have enough velocity after agile turn stage in order to impact the target. The agile turn is operated during the boost phase. Thus, the agile turn problem is formulated as terminal velocity maximization with given final time. Optimal solutions are obtained by two different methods, pseudospectral method and parameterized costate optimization method. The parameterized costate optimization method is a part of shooting method of indirect method which is proposed to verify the solutions obtained by pseudospectral method. At first, the basic missile model with constant axial acceleration is treated in the two dimensional yaw plane. After looking into the basic missile model, missile model with aerodynamic forces and thrust is analyzed.

Velocity maximizing suboptimal control law for agile turn of air-to-air missile

Abstract: In this paper, optimal control problems considering agile turn of missile as maximizing terminal velocity at boost phase are dealt. The missile in the phase experiences dramatic variation in velocity, mass and angle of attack within finite duration. This research at first, classifies the missile models into two different cases; longitudinal motion and lateral motion, but all of the models neglect aerodynamic forces. Each model has an optimal solution known as Bang-Singular Control, and the corresponding optimal control as well as switching condition for Bang to Singular is analytically derived. After the derivation of optimal solutions, two different suboptimal control laws which are based on the optimal solutions and capable of aerodynamic forces are proposed. The first law uses the optimal solution directly while the other incorporates theoretical aerodynamic equations. A comparison between results from the proposed control laws, results from PD type control law and optimal results from a commercial optimization tool are presented and usefulness of proposed method is validated through the comparison.

The expectation of applying IR guidance in medium range air-to-air missiles

Abstract: IR guidance has been widely used in near range dogfight air-to-air missiles while radar guidance is dominant in medium and long range air-to-air missiles With the development of stealth airplanes and advanced electronic countermeasures, radar missiles have met with great challenges In this article, the advantages and potential problems of applying IR guidance in medium range air-to-air missiles are analyzed Approaches are put forward to solve the key technologies including depressing aerodynamic heating, increasing missiles’ sensitivity and acquiring target after launch IR medium range air-to-air missiles are predicted to play important role in modern battle field

Kinetic air defense

Abstract: A missile defense system on an aircraft for destroying threats to the aircraft. The defense system includes at least one miniature guided missile mounted in a launch tube on the aircraft, where the guided missile includes a target acquisition and seeker system. The system also includes at least one sensor on the aircraft for acquiring a target threat, and a controller on the aircraft receiving signals from the at least one sensor. The controller generates a fire control solution that is provided to the at least one guided missile that directs the guided missile once it is fired from the launch tube towards the target threat, and the seeker system on the guided missile acquires the target once it is launched from the aircraft so as to destroy the target.

Allowable missile launch zone calculation for multi-fighter coordination attack under network targeting environment

Abstract: Network targeting is a new technology which is developed to adapt to the network centric warfare. Based on the operational characteristics of the complex attack, the air-to-air missile launching mode is analyzed, and the calculation method of the missile launching area is given. On the basis of the model of missile and target kinematics, the fast simulation method is used to calculate the missile launching area. Two typical fighter formations under network targeting are picked to compare to platform targeting. Finally the change trend of the missile launching area is summarized under network targeting environment.

Agile turn autopilot design of over-the-shoulder launched air-to-air missile based on sliding mode control theory

Abstract: Aiming at the agile turn of over-the-shoulder launched air-to-air missile based on aerodynamic/direct force, this paper establishes the mathematical model of attitude control, designs the agile turn attitude control law based on second-order sliding mode control in the pitching plane and uses Matlab software for simulation. Compared with the conventional sliding mode control law, results show that the agile turn control law designed in this paper can effectively undermine the system buffeting and reduce the direct force consumption.

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.