Showing papers on "Air-to-air missile published in 2003"

Army hypersonic compact kinetic-energy missile laser window design

Abstract: The U.S. Army Aviation and Missile Command, Aviation and Missile Research, Engineering, and Development Center (AMRDEC) is currently developing the Compact Kinetic Energy Missile (CKEM) which achieves hypersonic velocities at sea level. The system incorporates guidance to the target and requires active guidance technology. CKEM's kinetic energy warhead requires an accurate guidance sub-system in order to achieve high probability of kills at long range. Due to the severity of the aerothermal environments, minimized reaction time for small time to target conditions, and the communication degrading effects of the missile's energetic boost motor, a state of the art guidance technique is being developed by the AMRDEC Missile Guidance Directorate called Side-Scatter Laser Beam Rider. This technology incorporates a 1.06 micron laser to receive an off-axis laser guidance link to communicate guidance information from the launch site to the missile. This concept requires the use of optical windows on board the missile for the missile-borne laser energy signal receivers. The current concept utilizes four rectangular windows at 90° increments around the missile. The peak velocity during flight can reach approximately 6300 ft/sec inducing severe aerothermal heating and highly transient thermal gradients. The Propulsion and Structures Directorate was tasked to design and experimentally validate the laser window. Additionally, flight tests were conducted to demonstrate the laser guidance technology. This paper will present the laser window design development process as well as aerothermal testing to induce flight like environments and assess worst case thermostructural conditions.

A solving method of optimal initiating delay time and initiating direction for aimed warhead

Abstract: The technology of the initiation control has been one of the chief technologies of the air to air missile equipped with the aimed warhead.To determine the optimal initiating delay time and initiating direction of the aimed warhead by using synthetically the guidance information and the fuze information is the developing direction of the missile technology.The calculation models of the optimal initiating delay time and initiating direction of the aimed warhead at an arbitrary encounter conditions in missile coordinate are set up in this paper.The encounter feature of missile and target is analyzed by using simulation calculations.The study shows that the initiating direction has nothing to do with the relative velocity of the missile and the target;the direction of the target may change a quadrant in the period of the optimal initiating delay time.In order to destroy the target,the aimed fuze and warhead system must adjust the initiating direction according to the change of the initiating direction.

Control Design Research on Initial Guidance Phase of Vertical Launching Anti-Missile Missile

Abstract: This paper that bases on one type of foreign advanced anti missile missile whose atmosphere dynamical helm responds quickly and initial velocity is high, is in order to study the academic and engineering method of a vertical launching anti missile missile which must be turn and aim quickly in its initial guidance phase. In this paper, an optimization method based on orbit control force is produced. A function of flight program angle transformation which can be used in a practical project is introduced. A new way which can make the missile turn stably liking 'S' in the transonic region is also introduced.

Agile Missile 6-DOF Dynamics Modeling and Simulation

Abstract: The 6 DOF model of an agile missile with high angle of attack and high attitude maneuverability with impulse control or reaction jets control system(RJC) is described in this paper First the total force and moment of the jets are presented for simulation and control of the missile with zero and some constant rolling rate Then the equations of the 6 DOF model are represented with disturbance including wind At last a simulation of an air to air missile for the over the shoulder mission is carried out with the model described above and some results are given This model can be applied to general missile dynamics simulation; it is especially applicable for the simulation of an agile turn of an advanced air to air missile or the maneuvering of a highly maneuverable ballistic missile interceptor

Fast Simulation of Air-to-Air Missile Launch Area

Abstract: We present a new mathematical model to shape the air-to-air missile launch envelopes,which is to simplify the dynamic equations thus to make it prone to real-time computing.This method called Fast Simulation.Through the model,we can form the launch area of all kinds of attack conditions.Moreover,the model fits to launch on all aspects.Results of simulation illustrate that this method has high speed and the envelopes shaped have similar capability to actual ones.

The Characteristics Analysis and Simulation for an Agile Missile's Turn Motion with Stabled Attitude

Abstract: The turn motion characteristics is analyzed by Lyapunov method with the assumption of stabled attitude for an agile missile to get high turn rates for the agile turn of an advanced air-to-air missile,the effect of gravity and local wind is also considered here.The result shows that the velocity vector of the missile will turn to the orientation the missile nose points to with the effect of the gravity and the local wind ignored.High angle of attack generates high turn rate,and low angle of attack generates low turn rate correspondingly.The result also shows the effect of the gravity and the local wind can be neglected.The attitude maneuver simulation of an advanced air-to-air missile shows that large angle attitude maneuver generates high turn rates,and the agile turn is carried out.

Influence of downwash turbulence from armedhelicopter rotor to launching of air-to-air missile

Abstract: In the paper, the generation and distribution of downwash turbulence from the rotor of armed helicopter is analyzed, and the velocity of the turbulence is caculated with preset generalized wake model Then the motion characteristics and orbit changes of the missile under the downwash turbulence in initial stage of its launching is studied Finally the impact of this kind of changes on launching of the air to air missile is given

Three-dimensional guidance model and law for air-to-air missile against maneuvering target

Abstract: The threedimensional vector equations for missiletarget pursuitevasion motion are given,the threedimensional pursuitevasion motion model is established,a threedimensional guidance algorithm is presented based on Lyapunov stability theory under the conditions that the accurate information of the target is unknown,exceed acceleration commands of missile in the final stage of the engagement and accurate information on the acceleration and velocity relative heading angle of the target in the proposed algorithm are not required.The rightness of the model and the effectiveness of the proposed arithmetic are showed by the 6DOF simulation. 