Showing papers on "Missile published in 1994"

The Rocket and the Reich: Peenemunde and the Coming of the Ballistic Missile Era

Abstract: Relates the story of the German development of missile technology, a new kind of warfare that was extremely valuable to Allied powers during the Cold War but of little value to the Germans during World War II.

Simulator and practice method

Abstract: A hunting simulator having a projection of a moving target in life-size as in a natural environment is provided for practice shooting of a missile such as an arrow, dart, bullet, etc. The missile is detected in-flight in a detection plane set apart from a projection screen so the missile is detected undisturbed before impacting on the screen. The primary detector includes a continuously-illuminating LED emitter and a CCD camera sensor collocated with the emitter with a field of view in a detection area within the plane. Retroreflective tape on a perimeter about the detection area efficiently returns emitter radiation to the sensor. Detection is when a missile causes a shadow on the tape with an interruption of reflected light to the sensor, although in an alternative embodiment, the retroreflective tape is installed on the missile instead of the detection plane perimeter. In further alternative embodiments, second and third detection planes between the primary plane and an area from which missiles are launched are used to track and identify simultaneous missiles shot by 2 or more players. Computer-generated game sequences can also be projected instead of life-like hunting scenes.

Air defense destruction missile weapon system

Abstract: An air defense missile weapon system in which a plurality of unmanned missiles penetrate, survey, identify, attack and destroy target areas that include air defense sites and sites of military interest Each of the missiles has an airframe, sensors, data links, propulsion means, and a plurality of control surfaces The missiles are launched from a carrier aircraft towards the target sites from a stand-off range The missiles preferably operate in cooperative teams of hunter and killer missiles, and are interoperable with a plurality of military aircraft and other existing weapon systems

Apparatus for defence against an attacking missile

Abstract: Craft (11) generally and in particular the transport aircraft (11) which are used for humanitarian purposes and for supplying crisis reaction forces over militarily unknown territory and which have comparatively little manoeuverability are particularly endangered by partisans who operate out of cover with modern portable guided missiles (12), against whose homing heads (13) the flares which were previously discharged from aircraft (11) no longer afford an effective defence. Therefore those and other potentially endangered craft (11) are provided with easily interchangeably and autarchically equipped containers (17) from which the defence beam (16) of a laser source (21) in accordance with pre-guidance by a warning sensor (10), are directed by way of the tracking optical system (19) of a target tracking system (20) on to the approaching guided missile (12) whose homing head (13) is already locked on to heat sources such as for example the engines of the craft (11) to be protected. For quickly and reliably detecting the guided missile (12) which is initially only in the form of a point, against the clutter background, the tracking camera is so-to-speak scanned stroboscopically on to the pulsating reflections of the defence beam (16) at the missile (12). The energy which is emitted towards the attacking missile (12) disturbs the optronic detector function in the homing head (13) by the clock of a pulsed beam (16). Superimposed thereon, in the event of a closer approach, is overloading of the IR-detector by the beam frequency which is in the working band of the homing head (13) and finally thermal destruction of the homing head (13) if the attacking missile (12) has not already previously deflected out of its path of attack due to the failure of its target tracking regulating loop. A continuous-wave illumination beam (40) of lower power and which is spectrally adjacent and which tracks on to a glint somewhat away from the defence beam (16) also serves with its reflection energy for actuation of the topography of an adaptive optical system (42) for compensating for atmospheric propagation disturbances.

Missile guidance algorithm against high-g barrel roll maneuvers

Abstract: The features of high-# barrel rolls for an aircraft and the countermeasures for a proportional navigation guidance missile against this maneuver are studied First, the features of the barrell roll maneuver, and the effects of the parameters on the miss distance are discussed The simulation results show that a high-£ barrel roll maneuver generally produces a larger miss distance than a split-S (a sustained maximum g turn) and the miss distance does not critically depend on the maneuver initiation time, if the aircraft has a certain length of "time-to-go" and maneuvers with an appropriate roll rate Second, the inference is made that the provision of a phase lead in the pitch-yaw plane in the missile guidance loop and adoption of the augmented proportional navigation guidance may be effective It is also proven that a large phase shift (but less than ir/2) results in a smaller miss distance and that the combination of the phase lead and the augmented proportional navigation produces better results

Air defence system and defence missile for such a system

Abstract: Air defense system capable of intercepting high-speed airborne missiles (3), including a fixed control installation (1) and defense missiles (2). According to the present invention: at the point (F) common to the approach trajectory (T) of the said airborne missile (3) and to the interception trajectory (t) of the said defense missile (2), the said interception trajectory is transversal to the approach trajectory; the central axis of the homing head of the defense missile (2) is inclined laterally with respect to the axis of the said defense missile (2); and the said defense missile (2) is roll-stabilized, so that the said central axis of the said homing head is arranged on the side of the said airborne missile (3).

Missile flight control with dynamic inversion and structured singular value synthesis

Abstract: An integrated methodology incorporating both dynamic inversion and structured singular value synthesis is employed to design a robust nonlinear autopilot for an air-to-air missile. The nonlinear control elements include nested fast and slow inversion loops which, when closed in the absence of modeling errors, yield a system which is approximately linear. A feedback control law is then designed for this closed-loop system in the presence of structured uncertainties. The current controller architecture addresses those uncertainties and modeling errors which pertain to the fast dynamics.

Aerodynamic characteristics of a canard-controlled missile at high angles of attack

Abstract: A low-speed wind-tunnel investigation was conducted to examine the aerodynamic characteristics of a one-thirdscale model of a canard-controlled missile at high angles of attack using force and moment measurements. The data were taken at a nominal Mach number of 0.2 for angles of attack up to 50 deg at three different canard deflection settings. The test runs were limited to 0and 45-deg missile roll angles (symmetric configurations) and two sets of tails (aft fins), one with the full area including the roll damping tabs (rollerons) and the other without the rollerons. The data indicate that the rollerons act as an effective fin area at low speeds and high angles of attack, and make the missile more stable. The test data were also used to validate the aerodynamic characteristics of the missile as predicted by the Missile Datcom program. The agreement between the Datcom predictions and the test data is fairly good, with the latter indicating a slightly higher static stability.

Rotationally mounted flexible band wing

Abstract: A vehicle such as a missile (20) includes an aerodynamically shaped missile body (22) having a longitudinal centerline, a set of control surfaces (26) joined to the missile body (22), and, preferably, a propulsion system (28) operable to drive the missile body (22) forwardly. A cylindrical rotational bearing (32) is mounted on the missile body (22) with its cylindrical axis parallel to the longitudinal centerline (24) of the missile body. A flexible band wing (38) is supported from the rotational bearing (32). The flexible band wing (38) may rotate about the centerline (24) of the missile body (22) responsive to aerodynamic forces exerted on the missile body (22) and the flexible band wing (38) to aid in making maneuvers without requiring the missile (20) to bank to align the flexible band wing (38) with the direction of the maneuver.

Control of a bank-to-turn (BTT) missile with saturating actuators

Abstract: In this paper, a method is presented for enhancing the performance of a stable EMRAAT bank-to-turn (BTT) missile in the presence of multiple saturating actuators. The method involves the design of a saturation detection system, called an error governor which maintains, to the extent possible, the multivariable properties of the original autopilot design. The system prevents saturation, ensures finite-gain L/sup /spl infin// stability, and maintains, to the extent possible, the directionality properties of the original autopilot.

Three dimensional imaging millimeter wave tracking and guidance system

Abstract: An improved imaging system. The inventive imaging system (10) is adapted to transmit a plurality of first radar signals at millimeter wave frequencies at an area including an object along with background clutter. The return signals are processed to provide a three dimensional image for applications demanding visibility through fog, haze, smoke and other obscurants. Such applications include enhanced vision for helicopters, ships, buses, trucks, traffic observation stations for an intelligent highway or security cameras for plants and military installations. In a guidance system application, for example, the inventive system would include an electronically scanning antenna (12) to provide range and amplitude signals representative of a target area. The range and amplitude signals (18, 20) are compared to stored signals (26, 30) to create the three dimensional image. The stored signals are selected for comparison based on the dive angle of the missile (28, 32). The three dimensional image is then processed (22, 24, 34, 36, 38, 40) to derive guidance commands for the missile.

Missile and spacecraft coning instabilities

Abstract: : The destabilizing effect of yaw or Magnus-type moments on the angle-of-attack behavior of spinning missiles is well known to the missile designer. Yaw moments can also have a destabilizing (or stabilizing) effect on the attitude or coning motion of spinning spacecraft. The analogy might not be readily apparent because of the difference between the angle of attack of a spinning missile in atmospheric flight and the coning angle of spin-stabilized spacecraft. A concise treatment of the dynamics associated with coning instabilities is presented, and illustrative examples of classical missile and spacecraft coning instabilities are reviewed.

New results in optimal missile avoidance analysis

Abstract: Optimal missile avoidance of a constant speed aircraft from a coasting missile of first-order dynamics, guided by proportional navigation is analysed in the plane. This model allows the investigation of the "missile outrunning" and "end game evasion" maneuvers in the same engagement. Three regions of different optimal avoidance strategies are identified. All strategies are compromises in satisfying different optimal evasion principles: bleeding energy from the missile and minimizing of the closing velocity (principles of "missile outrunning"), and a final maneuver of a critical duration, perpendicular to the line of sight (principles of optimal "end game evasion"). Due to the missile's aerodynamic drag, the aircraft is able to reduce missile maneuverability by an "outrunning" maneuver so that in the "end-game" a larger miss distance can be generated.

Capture region for true proportional navigation guidance with nonzero miss-distance

Abstract: TRUE proportional navigation (TPN) is a version of pro- portional navigation (PN) guidance law in which the missile lateral acceleration is applied perpendicular (normal) to the line of sight $(LOS)^1$ rather than to the missile velocity, as in the case of pure proportional navigation $(PPN).^2$ The TPN guidance law has been found to be analytically more tractable than the PPN guidance law. Guelman' obtained the capture region of TPN, for a nonmaneuvering target, defining capture in terms of zero miss-distance. However, guided missiles carry warheads that have a nonzero lethal radius and thus, in practical situations, it is possible to define capture in terms of an acceptable nonzero miss-distance. It is obvious that the capture region, as obtained by $Guelman,^1$ for zero miss-distance will expand further under this assumption. In a previous $paper,^3$ the capture region for TPN with nonzero miss-distance was obtained through extensive computations. In this Note we present a complete analytical solution to the problem.

Device for guiding a missile

Abstract: The invention relates to a device for guiding a missile (1; 30) with a missile tip (2) and a cylindrical section (3) adjoining the tip of the missile; the device is provided with at least one control block (4; 31, 32) with exhaust openings (13-15) of corresponding nozzle bodies (10-12) arranged perpendicularly in relation to the missile's surface. In order to accomplish effective guidance, particularly of high-speed missiles (1; 30), in a simple and cost-effective manner it is proposed that the control block (4; 31, 32) be constructed with a plurality of small, fast-burning rocket motors (7-9; 33-36) that are arranged radially on the missile's periphery (1; 30) and that are ignitable in a predeterminable sequence and number.

Nonlinear autopilot and guidance for a highly maneuverable missile

Abstract: In this paper, both guidance law and autopilot for the bank-to-turn (BTT) terminal homing missiles have been developed and been successfully integrated. Based on differential geometric control theory, the proposed autopilot offers the potential for improving the level of safety and the performance over those autopilot designs based on linearized models. And, according to the concept of the proportional navigation, but under milder constraint, a new guidance law is proposed to intercept a nonmaneuvering target in the aerial engagement scenario. To demonstrate the efficiency of our autopilot and guidance law, the computer simulation of the BTT missile is illustrated in several engagement scenarios and shows the satisfactory results.

New guidance law for a missile with varying velocity

Abstract: A new guidance law for a missile with varying velocity i s presented. First, the basic guidance equations to compute thc missile acceleration command and time-to-go are derivcd. These equations are available whenever we can predict the intercept point in some way. Taking into account a missile thrust. we obtain the guidance law during boost phase. On the other hand. the guidance law af te r thrust cutoff i s derived by considering an a i r drag. Three forms of guidance laws arc proposed for each phase. One of them, which is called the analytical guidance law, gives the theoretical gujdancc acceleration commands to guide a missile on the collision course. Though this guidance law i s mcaningful from the mathematical viewpoint, the guidance equations are too complicated to perform the computation in real time. Thus, we present the approximate guidance law in order to reduce the computation time. This guidance law i s useful when i t i s implemented on a powerful guidance compulcr on thc ground or on the parent a i r craft. Ncxt, the approximate guidance law i s transformed into the convcnicnt form to realize i t on an existing homing missile. Since the obtained form i s similar to a conventional augmenled proportional navigation. we ca l l i t the modified augmcnted proportional navigation. The guidance laws presenled as well as a conventional proportional navigation and an augmented proportional navigation are applied to a simple model of a short range airto-air miss i lc . Some simulations are performed and then the inner launch envelopes are generated. The simulation results show that the guidance laws presented can intercept the target using fa r smaller acceleration requirement than prepared for the conventional navigations. When the miss i l e velocity varies significantly, the performance of the conventional navigations arc seriously influenced. The inner launch envelopes show that the guidance laws presented provide an overall performance improvement over the conventional navigations. Especially, the modified augmented proportional navigation i s useful and at t ract ive from the real i s t i c viewpoint. * Asso. Professor. NDA. Yokosuka. Japan 239, Member AIAA ** Postgraduate Rcsearcher. NDA. Yokosuka. Japan 239 *** Lecturc. NDA, Yokosuka, Japan 239, Member A I A A = missile axial acceleration vector, a m = 1 a m ] = target la teral acceleration vector, a ,= 1 a, 1 = target la teral acceleration perpendicular to LOS = target axial acceleration vector, a , = 1 a , 1 = zero-l i f t drag coefficient = desired acceleration command vector = acceleration due to gravity = specific impulse = mass of missile = navigation constant = effective navigation constant = position vector of the impact point with respect to the present target position. P = I PI = position vector of the impact point with respect to the present missile position. Q = I Q I = relative distance vector, R = IR I = missile reference area = differential operator = thrust = total f l igh t time = time-to-go or intercept time = I , ,W/T = closing velocity = missile velocity vector, V, = 1 V , 1 = correct missile velocity vector. V,= I V,, I = target velocity vector. V , = 1 V , 1 = missile weight = i n i t i a l missile weight = ba l l i s t i c coefficient = vm v,, = missile flight-path angle = 4 , E = missile flight-path rate vector = P S C ~ d 2 r n = $ , d m = target flight-path angle to LOS = a i r density = LOS angle = LOS rate vector = missile flight-path angle to LOS = the angle between P and LOS Copyrighl c 1994 by the American I n s t i t u t e of Aeronautics and Astronautics. Inc. All r i g h t reserved.

Surveillance and tracking of ballistic missile launches

Abstract: This paper begins with an overview of system requirements and design issues that must be considered in the design of algorithms and software for the surveillance and tracking of ballistic missile launches. Detection and tracking algorithms and approaches are then described for the processing of data from a single satellite and from multiple satellites. We cover track formation, missile detection, track extension, and global arbitration, and indicate how these functions fit together coherently. We include both profile-dependent and profile- free aspects of detection, tracking, and estimation of tactical parameters. In some instances, particularly in the area of track monitoring and in a discussion of how we accommodate intersatellite bias errors in line-of-sight measurements, we describe original work that has not been previously reported in the technical literature.

The Analysis of a Generic Air-to-Air Missile Simulation Model

Abstract: A generic missile model was developed to evaluate the benefits of using a dynamic missile fly-out simulation system versus a static missile launch envelope system for air-to-air combat simulation. This paper examines the performance of a launch envelope model and a missile fly-out model. The launch envelope model bases its probability of killing the target aircraft on the target aircraft9s position at the launch time of the weapon. The benefits gained from a launch envelope model are the simplicity of implementation and the minimal computational overhead required. A missile fly-out model takes into account the physical characteristics of the missile as it simulates the guidance, propulsion, and movement of the missile. The missile9s probability of kill is based on the missile miss distance (or the minimum distance between the missile and the target aircraft). The problems associated with this method of modeling are a larger computational overhead, the additional complexity required to determine the missile miss distance, and the additional complexity of determining the reason(s) the missile missed the target. This paper evaluates the two methods and compares the results of running each method on a comprehensive set of test conditions.

A chronology of the missile technology control regime

Abstract: The Missile Technology Control Regime (MTCR) is an informal, non-treaty association of states that have an established policy or interest in limiting the spread of missiles and missile technology. The MTCR's origins date back to the 1970s, when the U.S. government became aware of dangers posed by the missile programs of developing nations. Several events, including South Korea's 1978 ballistic missile test, Iraq's attempt in 1979 to purchase retired rocket stages from Italy, India's July 1980 SLV-3 test, and the former German firm OTRAC's 1981 testing of a rocket in Libya, contributed particularly to U.S. apprehensions. The concerns of the United States were translated into a Reagan administration initiative that resulted ultimately in an agreement by seven founding members to limit the spread of missiles and missile technology and in the release of guidelines on April 16, 1987. According to the guidelines, the MTCR's original purpose was to "reduce the risks of nuclear proliferation by placing controls on equipment and technology transfers which contribute to the development of unmanned, nuclear-weapon delivery systems." Over time, that goal was expanded to "limit the risks of proliferation of weapons of mass destruction by controlling transfers that could make a contribution to delivery systems for such weapons." The MTCR currently provides the central institutional arrangement, as well as the base international norm, for dealing with missile proliferation. But while the international community now recognizes the spread of missiles and missile technology as a crucial security issue, the sweeping political changes witnessed over the last three years demand a re-examination of the regime's focus, strengths, weaknesses, and ability to combat missile proliferation in a new, rapidlychanging international order. China's and North Korea's continuing aid to foreign states' missile programs increases the importance that a well functioning regime is in place to deal with missile proliferation issues. This report is intended to provide the necessary background data with which to undertake this reassessment.

Missile detection and location

Abstract: Electronic detection and location of missiles, such as darts (D), in which either ambient electromagnetic noise or specifically transmitted electromagnetic impressed signals are altered by interference from the missile, and this change is detected by receivers (12, 20) to detect the missile and its location The material (14) of the target area (T) into which the missile is embedded is electrically nonconductive

Automatic RF countermeasures dispensing module controller

Abstract: Automatic countermeasures dispensing module controller for radio frequency countermeasures processes information generated by a missile approach detector and radio frequency receivers which is correlated to generate a radio frequency countermeasures dispensing command. A countermeasures module is connected to provide effective countermeasures against radio frequency guided missiles. Voice warning messages are generated and a threat display symbol is generated on a cockpit display system that provides an audio and visual monitor of the threat. The number of countermeasures employed is counted. If a radar warning receiver or pulsed radar jammer is in operation and a missile approaching event is detected, the region of missile approach is read from a missile approach detector. The missile threat is displayed and correlated with the radar warning receiver or pulsed radar jammer for the indicated region with a missile approach detector. If the correlation is positive then a RF dispensing command is generated to dispense an RF countermeasures module.

An analysis of the North Korean Nodong Missile

Abstract: In this paper, we analyze the North Korean missile program based on publicly available information and a technical understanding of missile systems. In particular, we present models for the 1,000 kilometer‐range Nodong missile and a 1,300 kilometer‐range variant, both based on Scud technology. These models are single‐stage missiles with four clustered Scud‐engines and would have a circular error probable (CEP) of two to four kilometers or larger. We conclude that a 1,000 kilometer‐range missile with a one tonne payload could be built using Scud technology. Moreover, it appears feasible to extend the range to roughly 1,300 kilometers (with the same payload) if the missile body can be constructed out of high‐strength aluminum rather than steel, although it is unclear whether North Korea has such a capability. If both missiles are based on Scud technology, their existence would not imply a breakthrough in North Korean missile technology. These missiles would then represent essentially the longest‐range missi...

Arrangement for combating an engaging flying body or missile

Abstract: The vehicle carries a laser source whose laser beam is directed towards the approaching flying body (12) or missile via the following optics (19) of a target-seeking system in order to disable the flying body's thermo-optical sensor head (13) by noise pulses, over-driving it or destroying it. A camera is used as the tracking sensor for the target-seeking system (20) and is gated with the pulsed reflex energy of a pulsed countering laser beam (16) via an intermittently driven gate. A warning sensor with a wide field of view warns of potential engaging missiles and aligns the target following system, with its relatively narrow field of view, and countering beam with the threat.

Magnetic target toy

Abstract: A washer shaped magnetic missile is combined with a launcher having a probe which supports the missile by extending through its aperture. The washer and launcher magnetically couple but relatively weakly so that deceleration of a travelling launcher will release the missile, off the probe toward a target. The forward face of the missile may be adapted for magnetic, or other couple to a target. There is also shown a flimsy target which may cling to a ferromagnetic surface for use with the missile.

Hit verification technique

Abstract: An interceptor's point of impact on a targeted missile is quickly revealed in the milliseconds preceeding and following the impact by illuminating the target with radar signals at a high pulse repetition rate and observing the reflected radar echoes on an A-scope display. The position within the returned radar echo of a double echo and related changing phenomenon indicates the point of impact. Failing intercept, the miss distance is computed from the relative slant ranges to the targeted missile, the interceptor, and the double echo. The type warhead killed is revealed by a spectrograph slaved to the radar's antenna. Various techniques assist with the interpretation of the displayed patterns, including subtraction of previously stored patterns and display of the difference, display of characteristic patterns of various known missiles and interceptors stored in "look up" tables, and neural networks.

U.S. Army Missile Command dual-mode millimeter wave/infrared simulator development

Abstract: The advent of missile seekers with dual-mode millimeter wave and infrared common-aperture sensors has led to a requirement to develop the simulation tools necessary to test these systems. Traditionally, one of the most important techniques for supporting systems development has been a full seeker hardware-in-the-loop simulation. The development of simulation facilities capable of supporting the new generation of advanced dual-mode guided systems has been limited due to some major technological challenges which are yet to be solved. This paper provides an overview of the development of such a simulation facility at the U.S. Army Missile Command for supporting hardware-in-the-loop simulations of dual-mode systems. The major technological challenges which limit common-aperture dual-mode simulator development are presented with the current approaches which are being taken to overcome these challenges.

Deployable mass and sensor for improved missile control

Abstract: A flexible, aerodynamic inflatable nose fairing for use in combination with flat nosed canister-launched missiles having a wide, circular, cylindrical shape. The inflatable nose fairing is fabricated as a fiber-reinforced elastomeric membrane having a laminate construction which includes a silicone rubber inner or base layer as the gaseous pressure membrane or bladder, surrounded by two or more ply layers made up of resin-impregnated yarns. Also disclosed is a deployable mass assembly and sensor for providing improved missile control. The deployable mass assembly includes a telescoping actuator which is effective to provide stabilization control to the missile by shifting the center of gravity of the missile forwardly to compensate for a change in the center of pressure of the missile due to the change in length of the missile which occurs as the nose fairing is inflated into its deployed position.

Self-initializing internal guidance system and method for a missile

Abstract: A guidance system for internally controlling the flight path of a missile includes a guidance platform having dispersion control means mounted on the guidance platform for detecting acceleration of the missile due to lift and side forces. The dispersion control means includes dispersion detection means to calculate the velocity and position errors relative to a drag-only trajectory from the detected acceleration due to the lift and side forces. The internal guidance system also includes missile positioning means for controlling the position of the missile platform to substantially eliminate the velocity and position errors. The guidance system also includes level finding means for determining a substantially horizontal level axis and the orientation of the missile relative to a level axis. The missile positioning means also performs other functions such as missile leveling in which the wings-level axis of the missile is aligned to the level axis. Accordingly, the position of a free-falling missile may be internally controlled to increase the targeting accuracy of the missile without initialization of the missile from the launch platform.