Missile Flight Research Articles

Robust Smooth Sliding-Mode-Based Controller with Fixed-Time Convergence for Missiles considering Aerodynamic Uncertainty

This paper designed a smooth fixed-time-convergent sliding mode controller for a missile flight system considering aerodynamic uncertainties. Fixed-time convergence theory is incorporated with the sliding mode control technique to ensure that the system tracks desired commands within uniform bounded time under different initial conditions. Unlike previous terminal sliding mode approaches, not only is the bound of settling time independent of initial state, indicating that performance metrics like convergence rate can be predicted beforehand, but the control input is designed to be smooth based on adaptive estimations and some mathematical results without introducing any discontinuous items like the signum function, which avoids the problem of chattering consequently. A cascade control structure is employed with the derived control algorithm, and therein, the control input signal is obtained. Finally, a number of simulations are carried out and demonstrate the effectiveness of the designed controller.

대함유도무기 비행시험 업무 정립을 위한 최적 프레임워크 개발 - 표준 프로세스를 중심으로 -

본 논문의 목적은 대함유도무기 비행시험의 업무 효율 증대를 위한 프레임워크 구조 정 의와 프레임워크 개발 결과를 제시하는 것이다. 우선 프레임워크 구조 정의를 위하여 프레 임워크 구성요소 식별, 영역 분류, 단계 구분 및 프레임워크 템플릿 개발을 수행하였다. 프 레임워크의 구성요소는 표준 프로세스, 표준 산출물, 이슈사항 체크리스트로 구성되어 있 다. 프레임워크의 영역 분류는 체계수행, 시험안전, 시험지원으로 나누어져 있다. 프레임워 크의 단계 구분은 비행시험 계획, 준비, 수행, 후속으로 이루어져 있다. 프레임워크 개발을 위한 프레임워크 템플릿과 ID 식별코드 체계를 함께 제시하였다. 프레임워크 구조 정의를 한 후 대함유도무기 비행시험을 위한 총 15개 프레임워크가 개발되었다. 개발된 프레임워 크에 대한 평가 설문을 실시하여 프레임워크의 실용성을 입증하였다. 대함유도무기 비행시 험에 적용코자 개발된 프레임워크는 표준화된 업무 정립을 통해 대함유도무기 체계개발 성 과 창출에 기여할 것으로 판단된다.

MISSILE VERTICAL LAUNCH SYSTEM WITH REACTION CONTROL JETS

The paper deals with a concept of a missile vertical launch system using reaction control jets. The purpose of the study was a detailed investigation of a method optimizing fuel consumption in the first phase of the missile flight to increase the range and optimize the flight path. In the designed system the missile is ejected vertically and turned to the desired position by using corrective engines before the sustainer motor is started. The dynamics and controllability of the missile at low velocities were studied. The physical and mathematical model of the object has been described, taking into account the nonlinearities connected with the dynamics of the rocket itself, the disturbances caused by firing the rocket engine as well as some effects the unsteady aerodynamics. A method identifying the aerodynamic characteristics of the missile and an algorithm controlling the correction engines is presented. A prepared mathematical model of the missile was used to create a simulating environment. The results of numerical simulations in the form of graphs and tables are presented.

Analysis of Infrared Radiation Characteristics and Penetration Measures of Warhead

Ballistic target recognition occupies a unique and important position in many application fields of target recognition because of its challenge and important position of ballistic missile defense in national security; recognition time of defense system becomes very limited because of ballistic missile high-speed flight; recognition distance of defense system is also due to stealth technology. The integrated application of active jamming and passive decoy greatly increases the difficulty of identification of defense system. Because of its special status and challenge, ballistic target recognition has attracted wide attention of researchers at home and abroad, making it one of the most important issues in infrared target recognition research at home and abroad. In this paper, the infrared characteristics of a ballistic missile warhead target/decoy are analyzed, and the corresponding penetration measures are put forward according to the analysis results.

A Study on Waste Factors and Improvement Priorities of Missile Flight Test Works

A Study on Waste Factors and Improvement Priorities of Missile Flight Test Works

Autopilot and guidance law design considering impact angle and time

The authors propose an autopilot based on partial integrated guidance and control for missiles to achieve interception at a pre-specified impact angle and a close approximation of impact time. The scheme has an outer loop comprising the engagement model and slow dynamics (to generate a pitch-rate command that causes the missile to establish a collision course with the target), and an inner loop comprising the fast dynamics (to make the pitch rate track its command signal). The authors divide the missile flight into two phases; in the first phase the controller causes the missile line-of-sight (LOS) angle (impact angle) to converge to the pre-specified value at a pre-specified time, and to remain there thereafter (and hence establishes a collision course at the desired impact angle). In the second phase, the missile will fly along the LOS until interception occurs. The authors also provide an estimated calculation of the impact time and give the factors that influence the estimate, which helps the user systematically choose the missile parameters in order to achieve a certain impact time; this result can be applied to the case of salvo attack of multiple missiles without online data links. Finally, simulations are performed to verify the scheme effectiveness.

Research on Simulation System of Missile and Arrows Based on Unity3D

Aiming at the demand of visualization system development in flight simulation, a projectile missile flight simulation system is designed and developed. Using Unity3D to build the 3D model of the simulation object and reproduce the real environment design semi physical simulation system. By interfacing with Google Earth API platform and calling function, the 3D terrain modeling is realized by 3D Terrain Modeling Technology. And the database-based outer trajectory simulation platform simulation program data link, receive the simulation data of the ballistic simulation program, the whole process of the real-time three-dimensional animation reproduction of the reaction trajectory simulation, and add the bomb selection, playback settings, perspective tracking, explosion effects and other functions. The actual engineering shows that the system can be realistic to reflect the process of flying ammunition and has good stability and versatility.

The Control of Anti -Aircraft Missile Flight Path in Atmospheric Disturbances

Abstract The control of homing surface-to-air short-range anti-aircraft missile takes place in the atmosphere, in which there are different types of atmospheric disturbances such as: turbulence, gust and wind shear. The atmospheric disturbances is generated with the Dryden power spectral density model. This paper presents a method for control of flying objects such as anti-aircraft missile moving in a disturbed environment. The method of proportional navigation will be applied for the guidance of missile on the ground target. The research will include the analysis of influence of atmospherics on the hitting the target accuracy, the shape of the flight path and the values of generated control forces. Numerical research will be carried out with use of Matlab/Simulink software. Obtained results will be presented in the graphical form.

Aeroservoelastic modelling and control of a slender anti-air missile for active damping of longitudinal bending vibrations

Slender anti-air missiles experience longitudinal bending in supersonic flight and yet their autopilots are designed under the rigid-body assumption. Such autopilot design employs notch filters to remove the modal frequencies of the elastic airframe but this approach limits the autopilot bandwidth. In this paper, aeroservoelastic modelling and control of the ASTER 30 missile is proposed to enable autopilot design with extended bandwidth.The aeroservoelastic model combines missile flight dynamics, actuator dynamics and airframe elasticity, the latter focusing on longitudinal bending treated as a continuous Euler–Bernoulli beam problem. The beam is discretised leading to a nodal model and the modal analysis is then performed. The modal model is expressed in the state-space form and its order is reduced to enable optimal sensor placement and active damping control. The aeroservoelastic model of the ASTER 30 missile is further refined for control purposes by optimally choosing actuator inputs together with the number and position of sensors to be mounted on the missile airframe. Once these choices are made, several variants of active vibration damping control are proposed and analysed in order to enable an extended bandwidth for the autopilot by countering the airframe deformation measured by these sensors.

The Trajectory Controller Design and Implementation of a Certain Vehicular Missile Virtual Mark

To solve the trajectory control problem of vehicular missile virtual mark ,we design a kind of stepping motor control system based on single chip microcomputer, according to the generation principle of missile control instruction, single chip microcomputer generates longitudinal direction and horizontal direction control signal, realizes simulation of missile flight trajectory on the graphic. This design adopts to 8051 single chip microcomputer, study and explore missile trajectory operation rule, and combine with control theory, establish stepper motor control system based on single-chip, design hardware and software structure, simulate actual missile trajectory, finally realizes a vehicle-mounted striker anti-tank missile training simulation system of trajectory control.

Design and Manufacturing Process for a Ballistic Missile

Abstract Designing a ballistic missile flight depends on the mission and the stress to which the missile is subject. Missile’s requests are determined by: the organization of components; flight regime type, engine configuration and aerodynamic performance of the rocket flight. In this paper has been developed a ballistic missile with a smooth fuselage type, 10 control surfaces, 8 directional surfaces for cornering execution, 2 for maneuvers of execution to change the angle of incidence and 4 stabilizers direction. Through the technology of gluing and clamping of the shell and the use of titanium components, mass of ballistic missile presented a significant decrease in weight and a structure with high strength.

Numerical analysis of dynamics of an automatically tracked anti-tank guided missile using polynomial functions

The paper presents algorithms of automatic control of an intelligent anti-tank guided missile (ATGM) with possibility of attacking the target from the upper ceiling and with possibility of the missile flight through indicated points in space. The polynomial functions are used to designate the program trajectories. Numerical analysis of the operation of chosen algorithms is performed. The results are presented in a graphical form. As it results from the conducted tests, the proposed algorithms of automatic control of ATGM with the use of polynomial functions work properly during attack on the target from the upper ceiling, for both mobile and immobile targets.

Choice of Rocket Engine Parameters at the Optimization of Flight Trajectories

The choice of parameters for designing the rocket engine providing the maximum range of missile flight is considered. The choice problem is stated as a problem of conditional optimization, in which the criterion function is inversely proportional to the range of missile flight. The problem solution is carried out by the Newton's method, the method of a deformable polyhedron and by the genetic algorithm. It is shown that the solved problem contains some local minima, which are easily established, by the Newton's method and the method of a deformable polyhedron. The global minimum established by genetic algorithm, corresponds to missile flight along an unstable trajectory. In this case, the maximum range of missile flight can be provided by application of regulating devices.

COMPARATIVE ANALYSIS OF TUNING MISSILE AUTOPILOTS USING INTELLIGENT METHODS

This article explores basic technical and design challenges associated with the missile flight control system, including its role in the overall missile system, its subsystems, types of flight control systems, design objectives, and design challenges.

Employing supercomputer technology for aircraft accident investigation

We consider a software package for simulation and visualisation of surface-to-air guided missile flight and target defeat. We illustrate the research with the results of investigating the aircraft accident that took place in July 2014 in Ukraine.

Analysis of Nonlinear Missile Guidance Systems Through Linear Adjoint Method

In this paper, a linear simulation algorithm, the adjoint method, is modified and employed as an efficient tool for analyzing the contributions of system parameters to the miss - distance of a nonlinear time-varying missile guidance system model. As an example for the application of the linear adjoint method, the effect of missile flight time on the miss - distance is studied. Since the missile model is highly nonlinear and a time-varying linearized model is required to apply the adjoint method, a new technique that utilizes the time-reversed linearized coefficients of the missile as a replacement for the time-varying describing functions is applied and proven to be successful. It is found that, when compared with Monte Carlo generated results, simulation results of this linear adjoint technique provide acceptable accuracy and can be produced with much less effort.

Optimal Compensator for Anti-Ship Missile with Vectorization of Engine Thrust

This paper presents a method of controlling an anti-ship missile with the use of the linear-quadratic regulator (LQR). The equations of dynamics of the flight were linearized and written in the form of equations of state. To control the anti-ship missile, a double executive gas-dynamic (moveable nozzle of exhaust gases) and aerodynamic (moveable control surfaces) system is applied. The missile flight is considered in a three dimensional space, whereas the controlling vector is comprised of four components: two components to control the height of the flight and two components to control the direction of the flight. The results are presented in a graphic form.

GPS Inertial Missile Guidance System

<span>The task of this work is to design the guidance system for the<br /><span>missile which would guide the missile accurately to hit the target as<br /><span>directed. Guidance is the main component of the missile system which<br /><span>helps in hitting the target accurately. The missile can be guided by<br /><span>the number of ways which includes by using laser, GPS infrared or<br /><span>radio waves on its way to the target. This paper proposes a model to<br /><span>guide the missile with the help of GPS and INS. This model requires a<br /><span>computer or controller which should be installed in the missile to<br /><span>control the missile flight according to the guidance provided by GPS<br /><span>and INS. The system works by knowing the missile current position<br /><span>and the position of the target. The position of the target is known by<br /><span>using Google maps which is feed in the missile controller before the<br /><span>missile is launched. Missile current position is known by using GPS<br /><span>while the missile current orientation and heading is known by using<br /><span>INS. Missile current position is compared with the target position to<br /><span>calculate the desired heading towards the target, then missile<br /><span>controller auto pilots the missile according to the desired heading<br /><span>towards target to hit the target.</span></span></span></span></span></span></span></span></span></span></span></span></span></span></span></span></span><br /><br class="Apple-interchange-newline" /></span>

The impact of launcher turret vibrations control on the rocket launch

Abstract The paper discusses the missile lift-off from a launcher placed on a motor vehicle. The stimulation of the assembly vibration results from the input generated by the road and the missile firing. The unfavourable input generated in the course of assembly operation has an impact on the characteristics of the initial missile flight parameters. The aim of the paper is to apply the hybrid vibroisolation system of the launcher turret in order to improve the conditions of the missile launch from the assembly. The active system reducing the occurring disturbance allows to control the launcher turret vibrations. Owing to that it is possible influence effectively the initial missile flight parameters.

비행시험 발사통제 시스템의 신호처리 알고리즘

The Missile Flight Test Launch Control System is to operate in conjunction with the Fire Control System during flight test to guided weapons. Also, this is a system for the test control and situation monitoring depending on the type of guided weapons and testing purposes. Message structure, communication protocols, such as data types for interworking with the fire control system and the Missile Flight Test Launch Control System are defined in the Launch Control ICD(Interface Control Document). ICD are composed differently of each guided weapons system and each test object. Previously, in order to interwork with the Fire Control System, the interlocking software was developed, which had a variety of problems. Therefore, we developed a new parsing algorithm in order to recognize the variety of Launch Control ICD and verified that the algorithm operates normally by checking transmitting and receiving various message in conjunction with the fire control system.