The optimal control with exponential decay rate problem of the air-to-air missilesystem is studied. A nonlinear, coupling and uncertain dynamic model of the air-to-air missile with six degrees of freedom is considered. Because it is difficult to design the controller for the air-to-air missile control system, the nonlinear and coupling uncertain control system is simplified, and a linear model is obtained. Then, based on optimal control approach, an optimal controller with exponential decay rate is designed for the air-to-air missile. Numerical simulations illustrate the effectiveness of the proposed controller.
4-19. The Javelin supports a rifle squad or platoon. In some units, these weapons are organic to the platoon. In units not assigned Javelins, the commander should plan for some form of mutually supporting weapon fires. At times, the platoon may be supported by heavy close combat missile systems, which have a much greater range than the Javelin. During planning, the leader considers the threat, then positions unit weapons accordingly to cover AAs. He also considers the fields of fire, tracking time, and minimum engagement distance of each weapon. The platoon leader selects a primary position and sector of fire for each weapon. He also picks alternate and supplementary positions for them. Each position should allow flank fire and have cover and concealment. The leader should integrate the CLU into his limited visibility security and observation plan. If time permits, the gunner prepares range cards for his primary, alternate, and supplementary positions.
Abstract. The purpose of this paper is to achieve the conceptual model and analysis on the support system of space-based anti-missile information. In this paper, Unified Modeling Language (UML) is used to conduct the model and analysis of the system. With respect to features such as functional requirements, data features, object relationships, dynamic behaviors and information interaction, a variety of view models were established to describe the concepts. Use case diagrams, class diagrams, sequence diagrams, communication diagrams and analysis class diagrams were drawn thanks to the IBM Software Delivery Platform. The producrs provided a conceptual analysis about the space-based information support on anti-missilesystem and foundation for the simulation of the follow-up system. It indicates the complexity of the system and the necessity of modeling and analisis through this paper.
In this paper, the guidance and control problem of the air-to-air missilesystem is studied. A nonlinear, coupling and uncertain dynamic model of the air-to-air missile with six degrees of freedom is considered. Then, based on Lyapunov stability theory, a Lyapunov function is employed, and a controller is designed for the air-to-air missile. To verify the effectiveness of the integrated guidance and control law, we carry out its simulation and their analysis show preliminarily that the integrated guidance and control law can guarantee the accuracy of the air-to-air missile hitting an arbitrarily maneuvering target and guarantee the stability of its attitude. Thus it is effective for interception．
midcourse and terminal phases the system may be designed to track acceleration commands to effect an intercept of the target. This article explores several aspects of the missile flight control system, including its role in the overall missilesystem, its subsystems, types of flight control systems, design objectives, and design challenges. Also discussed are some of APL’s contributions to the field, which have come primarily through our role as Technical Direction Agent on a variety of Navy missile programs.
The inputs to the flight control system are outputs from the guidance law that need to be followed to ulti- mately effect a target intercept. The specific form of the flight control system inputs (acceleration commands, attitude commands, etc.) depends on the specific appli- cation (discussed later). In general, the flight control system must be designed based on the expected charac- teristics of the commands, which are determined by the other elements of the homing loop and overall system requirements. Characteristics of concern can be static, dynamic, or both. An example of a static characteris- tic is the maximum input that the flight control system is expected to be able to track. For instance, a typical rule of thumb for intercepting a target that has constant acceleration perpendicular to the LOS is for the missile to have a 3:1 acceleration advantage over the target. If the missilesystem is expected to intercept a 10-g accel- erating threat, then the flight control system should be able to force the missile to maintain a 30-g acceleration. An example of a dynamic characteristic is the expected frequency content of the command. For instance, rapid changes in the command are expected as the missile approaches intercept against a maneuvering threat, but the input commands may change more slowly during
The intended missilesystem uses the command line of sight (CLOS) guidance method to hit its target even this target is moving or stationary . The operator has to keep the sight reticle on the target center and as a result, missile spatial position is measured and sensed via the sight or night detectors located in the ground station, the miss angle between the actual missile position and the virtual line of sight is calculated in missile guidance unit (MGU) and consequently it generates the steering commands sent to the missile via the command wire . These commands are received by the on-board missile electronics and in turn the missile control surface deflects according the angel commanded resulting in a new missile position. The actual angle carried out by the missile in yaw plane is measured by the free gyro and the difference between the achieved missile angle and the commanded angle sent via the wire (∆ψ) is
The project deals with the optimization of ring stiffeners of missile primary goals of preventing resonance between engine and ring stiffener, retain structural stability of missile body in its highest operating frequency range appropriate location for cutouts in ring stiffeners. All this is done by simple concept of determining the highest possible oval mode of vibration of ring stiffener which is a cylinder itself, under the highest possible operating frequency and the shifting this oval mode by making changes in the design. Natural frequencies and mode shapes of finite length thick cylinders are of considerable engineering importance because of strong potential applications and more demanding requirements imposed on cylindrical structures. Normally this cylindrical have various free vibration modes and some of these modes may be in the range of machines operating frequency. The main objective of the project is to shift the system natural frequency away from machines operating range. Our project particularly concentrates on a turbo generator in which the forcing function tends to deform the structure into oval shape. Our project main aim is how to shift oval mode frequencies using topology optimization scheme in the context of a finite element (FE) approach. In detail, this includes:
minimum effective range, and o__ b________.
3. Limitations to the missile effective range include the fire control system,
seeker, time of flight, closing velocity, and m_______ capability.
4. 1 DOF simulation requires modeling only the thrust, weight, and a____ f____. 5. A 3 DOF simulation that models 3 aero forces is called p____ m___ simulation. 6. A simulation that includes 3 aero forces ( normal, axial, side ), 3 aero moments
7. JFK was unaware of symmetry of Soviet and US missile deployments. JFK: "It's just as if we suddenly began to put a major number of MRBMs in Turkey. Now that'd be goddam dangerous, I would think." McGeorge Bundy and Alexis Johnson then explain "Well, we did, Mr. President."
Laser guided missile manage machine is processed the usage of MATLAB. It describes the effect comparisons which had been evolved for the section lead compensator design through Nichols Chart. Laser guided missile manage gadget may be designed to growth near into a diffusion of properties ,along with stabilization of risky systems, reimbursement properties, Nichols analysis and Bode diagram. The analysis has given with the conclusions for the design of a new advent of control assist structures. the section lead compensator satisfies the all of the circumstance of the machine. In conclusion, segment lead repayment can offer height closed-loop modulus Mp, bandwidth consisting of the section margin it can be plotted. Remarks manage method inside SMC framework, an outer loop manipulate scheme is present to create sliding regimes for a category of nonlinear clean affine structures. the main worries are to set off sliding regime at the structures with the relative degree on higher than one. To have a look at the effect of higher relative diploma and with the nearby diffeomorphic coordinate transformation principles to design stronger sliding mode controllers that feature high-tracking performances. inside this method, pitch-axis missile autopilot topologies are create and implemented in MATLAB surroundings. The agility and robustness of the controllers are analyzed thru extraordinary laptop- simulation eventualities. to triumph over the intend boundaries as a result of application of standard sliding modes and the ovoid actual-time implementation limits consisting of high order differentiation, the intend become focused around the first relative diploma multiple. pitch-axis tail-managed missile autopilot topologies were first of all designed to efficaciously attain fast and excessive manoeuvrability monitoring missions. It suggests that the design of GCA using with the OLSM approach impressively enhances the device overall performance and to ensures the robust robustness properties regardless of the machine is operated at the limits of its flight envelope.
(c) Hence normally designers tend to limit the amount of phase advance to about 60 deg. This means that if one is going to design a guidance loop with a minimum of 45 deg phase margin, the total phase lag permissible from the missile servo and the aerodynamics at guidance loop unity gain cross-over frequency will be 15 deg. (d) Hence the servo must be very much faster and likewise the weathercock frequency should be much faster (say by a factor of five or more) than the guidance loop undamped natural frequency i.e., the open-loop unity gain cross-over frequency. (e) This may not be practicable for an open-loop system especially at the lower end
Unmanned Combat Air Vehicles, or UCAV, are increasingly an important capability available to military commanders and, as they become more capable, they will be able to replace cruise missiles in many of their traditional roles. This article looks at some of the possible tends for both UCAVs and cruise missiles in order to predict if cruise missiles will be able to survive the competition. A cruise missile is basically a small, pilotless airplane. Cruise missiles have an 8.5-foot (2.615-meter) wingspan, are powered by turbofan engines and can fly 500 to 1,000 miles (805 to 1,610 km) depend on the configuration. A cruise missile's job in life is to deliver a 1,000-pound (450-kg) high-explosive bomb to a exact location -- the target. The missile is destroyed when the bomb explodes. Cruise missiles come in a number of varying and can be launched from submarines, destroyers or aircraft.
President Clinton and Prime Minister Hashimoto.
In August 1998, North Korea's test launch of a three- stage rocket, possibly an intercontinental ballistic missile (ICBM) Taepodong 1, spurred the argument for JMD. The rocket flew over Japanese territory, and the Japanese people were stunned and deeply humiliated by the intimidating test of a missile "over their heads." At the Security Consultative Committee (SCC or "2 plus 2") meeting on September 20, 1998, the Director of Japan's Defense Agency and the US Secretary of Defense expressed a commitment to proceed with further work in the direction of conducting cooperative research on missile defense. In October the Security Council of Japan convened, and the JDA announced that it would begin internal coordination in the Cabinet with an additional budget
The growing use of networking is generating tremendous amount of various application for data that are transmitted at high speeds over long distances. These security aspects include determining the types of attacks that might be launched on a computer system or network, and using various protection mechanisms against these attacks to ensure the validity of information. The system implemented here uses the GSM with the help of Nokia 6070. The security issue is handled by using RC4. The coding of the command for the position and angle of the missile is done by the back end VB. The decoding at the receiver is done by 80c59 and execute with movement of the stepper motor. The system here is implemented with GSM, AT command by VB, RC4 and 80c59. This can also be implemented by any other combination for the desired results and application.
Fig. 1 shows the collision triangle and heading error. For successful interception, missile velocity vector and target velocity vector needs to be inside the collision triangle, and they are inside collision triangle if they satisfy collision conditions which are: (a) rate of change of LOS is zero and (b) closing velocity is negative or the LOS separation is reducing in between the missile and target. The lead angle is theoretically correct angle for missile to be on collision course because missile is not always fired in the collision course. The missile is fired in the direction of targets and that results into an error in the lead angle. This error is the „Heading Error (HE)‟. From [4 and 5], we state the N as time varying navigation ratio:
Above nozzles are modelled as methods of reducing the length of spike nozzle centre body by replacing the ideal spike with a conical spike. While this method does indeed result in much shorter nozzle length, we can go even further by removing the pointed spike altogether and replacing it with a flat base.Influence of large scale pressure changes on nozzles paper was presented by Venkateshwarn, S. Merle : As any fluid dynamics recognizes, the significant disadvantage of the “flat” plug is that a turbulent wake forms aft of the base at high altitudes result in high base drag and reduced efficiency. However, this problem can be greatly alleviated in an improved version of the truncated spike that introduces a “base bleed”, or secondary subsonic flow, into the region aft of the base.The circulation of this secondary flow and its interaction with the engine exhaust creates an “aerodynamic spike “that behaves much like the ideal, isentropic spike. In edition, the secondary flow re- circulates upward pushing on the base to produce additional thrust. It is this artificial aerodynamic spike for which the aero spike nozzle is named linear aero spike. All of these nozzles are far been annular, or circular when viewed from below. Still another variation, of the aero spike nozzle is not an annular nozzle at all. A second approach pioneered by the “Missile Dyne Company (now division Boeing) in the 1970’s, places” the combustion chambers in a line along two sides of the nozzle.This approach results in a more versatile design allowing the use of lower-cost modular combustors. These modules can be combined in varying configurations depending on the application.
More materiel was shipped in 1962. The CIA spotted 57 ships in the month of August. By then, their conclusion was that the Cubans were building up an anti-aircraft defence system to Soviet standards. Confirmation came from the CIA that launch sites were under construction. Their surface-air SAM-2 missiles could destroy aircraft flying at high altitude. USS Oxford, fitted with listening devices, patrolled the Cuban zone in order to intercept radio communications. The NSA detected the presence of air- traffic controllers speaking Spanish with strong Slavic accents.
response to Russia’s annexation of Crimea. Moscow justifies resumption of develop- ment work on new nuclear warheads and delivery systems by the necessity to over- come US missile defence systems. In the coming years Russia intends to operate five different types of intercontinental missiles with manoeuvrable warheads and/or the ability to reach the United States via the southern hemisphere. The development and procurement of long-range cruise mis- siles can also be seen as a response to US missile defence plans. Russia has also re- peatedly threatened to withdraw from nuclear arms control agreements and to station nuclear-capable Iskander short- range missiles in Kaliningrad. In March 2015, the Russian ambassador in Copen- hagen even warned of the possibility of nuclear strikes against Danish naval vessels involved in NATO missile defence.