scispace - formally typeset
Search or ask a question

Showing papers on "Missile published in 1982"


Patent
30 Mar 1982
TL;DR: In this article, the authors propose a system for airborne and seaborne use in which directional control about a flight axis comprises a nose (2) deflectable angularly in relation to the flight axis of the body (1) of the missile to form steering means by changing the fluid flow over the body.
Abstract: A missile for airborne and seaborne use in which directional control about a flight axis comprises a nose (2) deflectable angularly in relation to the flight axis of the body (1) of the missile to form steering means by changing the fluid flow involve over the body (1) and means (4,5) between the nose (2) and the body (1) to effect angular deflection about a universal pivoting point (3) between the nose (2) and the body (1).

46 citations


Patent
03 Dec 1982
TL;DR: In this article, a guidance method is provided for the terminal portion of the trajectory of a guided missile having a sensor and comprising two sections coupled together by a central shaft and free to rotate with respect to one another about the longitudinal axis of the missile; one section comprises a drive means for controlling the roll attitude of this section and a gas generator which feeds a nozzle for providing a transverse throat force.
Abstract: A guidance method is provided for the terminal portion of the trajectory of a guided missile having a sensor and comprising two sections coupled together by a central shaft and free to rotate with respect to one another about the longitudinal axis of the missile; one section comprises a drive means for controlling the roll attitude of this section and a gas generator which feeds a nozzle for providing a transverse throat force and the other section has a stabilizing tail unit formed by a set of fins able to be opened out.

39 citations


Patent
11 Jan 1982
TL;DR: In this article, a training device for simulated anti-armour weapons system utilizes a microcessor system to perform a number of functions including solving dynamic flight equations of a simulated missile and determining the gunner's aiming error.
Abstract: A training device for simulated anti-armor weapons system utilizes a microcessor system to perform a number of functions including solving dynamic flight equations of a simulated missile and determining the gunner's aiming error. A miniature terrain board having a miniature target with an infrared source provides the aim point for a gunner using a simulated weapon launcher. An infrared sensing device mounted in the weapon provides input to the microprocessor while a CCTV provides an instructor with a gunner's view. Sound, visibility, and recoil associated with weapons use are simulated by peripheral devices under the control of the microprocessor. The gunner's aiming error and view are displayed in real time on an instructor's console which provides for instructor input and recording of gunner performance.

35 citations


Patent
William R. Yueh1
22 Sep 1982
TL;DR: In this paper, a third order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go is proposed to augment proportional navigation with a target acceleration feed forward term and a navigation ratio.
Abstract: A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a third order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation with a target acceleration feed forward term and a navigation ratio which is a function of time-to-go and the control effort weighting factor. This third order system may also implement another optimal control law to even greater advantage, taking into account not only target acceleration but also missile acceleration in a feedback loop which, together with the navigation ratio, are both functions of time-to-go and autopilot dynamics, whereby first order autopilot time lag is accounted for. This system is particularly useful for high and medium altitude targets and results in significant miss distance improvement for terminal guidance against small maneuvering targets.

32 citations


Journal ArticleDOI
TL;DR: A hardware-in-the-loop simulation has been developed to evaluate the performance of active missiles from prelaunch to inter cept and initial comparisons with flight results support the credibility of the facility.
Abstract: A hardware-in-the-loop simulation has been developed to eval uate the performance of active missiles from prelaunch to inter cept. The facility is used for system integration, design verifica tion,...

26 citations


Patent
05 Aug 1982
TL;DR: A missile launch system includes a missile launch support structure mounted on a launch platform and including a pair of spaced apart rails having longitudinal slots formed therein, and a cooperating missile launch container having a cylindrical bore for receiving and supporting a missile for launching includes radially extending ribs spaced and oriented to engage and slide along the slots in the rails.
Abstract: A missile launch system includes a missile launch support structure mounted on a launch platform and including a pair of spaced apart rails having longitudinal slots formed therein, and a cooperating missile launch container having a cylindrical bore for receiving and supporting a missile for launching includes radially extending ribs spaced and oriented to engage and slide along the slots in the rails for supporting the missile launch container for launching of the missile.

23 citations


Patent
William R. Yueh1
22 Sep 1982
TL;DR: In this article, the authors proposed a method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme with target and missile information terms and a navigation ratio which is a function of time-to-go.
Abstract: A method for augmenting a noise-adaptive predictive proportional navigation terminal guidance scheme. In a fourth order configuration with noise adaptive varying gain parameters calculated as a function of time-to-go, this system implements an optimal control law to augment proportional navigation with target and missile information terms and a navigation ratio which is a function of time-to-go. By employing a fourth order system, enhanced use may be made of information already available in the guidance computer and missile control system to decouple target motion information from the missile control signals. Decoupled target motion information facilitates blind-mode operation in the end game, the last few seconds before intercept. Decoupled missile control information enables the airframe to be controlled to predefined orientations for aimed warhead applications. This system is particularly useful for high and medium altitude targets and results in significant miss distance improvement for terminal guidance against small maneuvering targets. The system has additional benefits in that it results in nearly optimal miss distance behavior with sensitivity to unmodeled errors being substantially less than that in modern guidance systems.

23 citations


Journal ArticleDOI
TL;DR: In this article, a series of quantitative and qualitative tests were conducted to expand the aerodynamic data base of square cross-section missiles, including measuring forces and moments acting on square missiles, and measuring flowfield pressures on the leeward side of square missiles at various configurations and orientations in a subsonic wind tunnel.
Abstract: : A series of quantitative and qualitative tests were conducted to expand the aerodynamic data base of square cross-section missiles. Quantitative tests included measuring forces and moments acting on square missiles, and measuring flowfield pressures on the leeward side of square missiles at various configurations and orientations in a subsonic wind tunnel. Force and moment data is presented showing the effects of variation in body corner radius, nose and fin shapes, pitch angle, and roll angel. Flowfield pressure and crossflow velocity data are presented for missiles of various pitch angels, roll angles, body corner radii, and fineness ratios (length to width ratio). In addition, flowfield data is shown along the axial length of a square missile. Qualitative tests included photographic tuft grids in the flowfield and photographing oil shear stress patterns on the surface of various missiles. These qualitative photographs are presented for various missile configurations and orientations.

23 citations


Journal ArticleDOI
TL;DR: The purpose of this paper is to present two techniques from the field of conflict analysis which permit the assessment of a wide variety of conflict situations.
Abstract: The purpose of this paper is to present two techniques from the field of conflict analysis which permit the assessment of a wide variety of conflict situations. One method for modelling a conflict at a given point in time is the improved metagame analysis technique of Fraser and Hipel (1979a; 1983) which is a reformulation and extension of metagame analysis (Trustees of the University of Pennsylvania, 1969a; 1969b; Howard, 1971). Inherent advantages of the improved metagame method are that it produces more realistic results than traditional metagame analysis, it is easy to use in practice, and the practitioner does not have to know any of the underlying theory in order to employ the technique. The efficacy of the approach has been supported by a host of real-world applications (Fraser and Hipel, 1979a; 1983; Shupe et al., 1980; Wright et al., 1980; Fraser, 1981; Fraser et al., 1983; Takahashi et al., 1983; Savich et al., 1983; Kuhn et al., 1983; Meleskie et al., 1982; Stokes and Hipel, 1983). Furthermore, Kilgour et al. (1983) have clearly demonstrated from a theoretical viewpoint that the improved metagame analysis method can readily model a conflict with any finite number of players and options. A brief description of the method for applying the technique is presented in this paper through the modelling and analysis of the Cuban Missile Crisis of 1962. The interested reader should consult other references for the details of this technique of conflict analysis (Fraser and Hipel, 1979a; 1983). The second dynamic method called the stare transition form (Fraser,

23 citations


Patent
28 Jan 1982
TL;DR: In this paper, a missile container for storing a missile and having an extraction mechanism for extracting the missile from the container and placing the missile in the proper launch attitude is described, but the mechanism is not described.
Abstract: A missile container for storing a missile therein and having an extraction mechanism for extracting the missile from the container and placing the missile in the proper launch attitude.

21 citations


Patent
30 Sep 1982
TL;DR: A naval harrassment missile for autonomously flying to a designated target area such as an enemy naval warship is described in this paper, where the target is either a high explosive or a self-forging fragmentation warhead.
Abstract: A naval harrassment missile for autonomously flying to a designated target area such as an enemy naval warship. The missile designed for searching, finding and harrassing the target. The missile may send a homing signal to guide other missiles to the target or by a homing signal attack the target using either a high explosive or a self-forging fragmentation warhead.

Proceedings ArticleDOI
01 Dec 1982
TL;DR: The design of an optimal guidance and control system for a short range air-to-air missile is undertaken and a Generalized Likelihood Ratio approach to maneuver detection is employed with maximum likelihood estimation techniques to estimate target acceleration.
Abstract: The design of an optimal guidance and control system for a short range air-to-air missile is undertaken. An optimal target tracking filter is used to track target position and velocity, and a Generalized Likelihood Ratio approach to maneuver detection is employed with maximum likelihood estimation techniques to estimate target acceleration. The estimated target variables are then used with a modified linear quadratic regulator to generate the required guidance commands to minimize miss distance.


Patent
29 Jan 1982
TL;DR: In this article, an airborne missile launcher for air launching of man-portable, tube-launched missiles includes a central support frame with attachment means for detachable attachment to an aircraft or other launching platform, with a central frame member having a launch tube saddle support assembly at each side of the frame member.
Abstract: An airborne missile launcher for air launching of man-portable, tube-launched missiles includes a central support frame with attachment means for detachable attachment to an aircraft or other launching platform, with a central frame member having a launch tube saddle support assembly at each side of the frame member with quick detachable clamp means and an alignment guide for quickly positioning and securing launch tubes into position with auto connecting means for automatically connecting the electronics control system and coolant gas to the launch tube assembly upon clamping the assembly into position. An aerodynamic shell encloses the support structure and includes a quick release cover for providing access to the tube clamp assemblies for loading and unloading launch tubes.


01 Dec 1982
TL;DR: In this article, an extended Kalman filter with the adaptive feature of estimating the measurement variance on line is proposed to improve the performance of a short range, air-to-air missile against a highly maneuverable target when angle only measurements are available.
Abstract: The presence of a microprocessor makes it possible to utilize a digital filter to process the measurement data and obtain a state estimate to be used in a digital guidance system for tactical homing missiles. Of particular interest is the case of the short range, air-to-air missile against a highly maneuverable target when angleonly measurements are available. Two schemes are proposed which improve the homing performance. The first is an extended Kalman filter with the adaptive feature of estimating the measurement variance on line. The second is an adaptive guidance scheme based on an exponential cost function which is used in conjunction with the filter.

Patent
26 Aug 1982
TL;DR: In this paper, a voice-controlled system for a single aircraft against a plurality of simultaneously appearing (i.e., existing) targets, such as two or more aggressor aircraft (or tanks, or the like) attacking the sole defender aircraft, is presented.
Abstract: A voice-controlled weapons launching system for use by a pilot of an aircraft against a plurality of simultaneously appearing (i.e., existing) targets, such as two or more aggressor aircraft (or tanks, or the like) attacking the sole defender aircraft. The system includes, in combination, a voice controlled input device linked to and controlling a computer; apparatus (such as a television camera, receiver, and display), linked to and actuated by the computer by a voice command from the pilot, for acquiring and displaying an image of the multi-target area; a laser, linked to and actuated by the computer by a voice command from the pilot to point to (and to lock on to) any one of the plurality of targets, with the laser emitting a beam toward the designated (i.e., selected) target; and a plurality of laser beam-rider missiles, with a different missile being launched toward and attacking each different designated target by riding the laser beam to that target. Unlike the prior art, the system allows the pilot to use his hands full-time to fly and to control the aircraft, while also permitting him to launch each different missile in rapid sequence by giving a two-word spoken command after he has visually selected each target of the plurality of targets, thereby making it possible for the pilot of a single defender aircraft to prevail against the plurality of simultaneously attacking aircraft, or tanks, or the like.

Patent
01 Jul 1982
TL;DR: In this paper, a simple lobe structure of the transmitted signal(s) is obtained using a linearly polarized antenna array with electronic phase switching between the aforementioned equal power lobes, and the monitor operates with a single transmitter.
Abstract: A monitor determines, from the ground, the orientation (roll and attitude)f a missile by observation of the character of a transmitted signal(s) therefrom. By transmitting to a ground receiver a linearly polarized signal(s), the missile identifies a given plane fixed with respect to its body frame. This plane is identified at the ground receiver by comparing the ratio of the signal(s) received in any two cross-polarized directions. To resolve the attendant 180° ambiguity, the monitor employs an antenna array disposed on the missile that is switchable, back and forth, between two equal power lobes. The monitor operates with a single transmitter, and the simple lobe structure of the transmitted signal(s) is obtained using a linearly polarized antenna array with electronic phase switching between the aforementioned equal power lobes.

Patent
07 Jun 1982
TL;DR: In this paper, a spin-stabilized training missile is equipped with a stabilizer device for reducing spinning in order to decrease the flight range of the training missile, which is designed so that its stabilization attainable solely by the spin upon firing is not sufficient for a stable flight in the practice range.
Abstract: A spin-stabilized training missile is equipped with a stabilizer device for reducing spinning in order to decrease the flight range. The training missile is designed so that its stabilization attainable solely by the spin upon firing is not sufficient for a stable flight in the practice range. The required additional stabilizing in the practice range is obtained by a stabilizer device or control airfoil effecting simultaneously, after leaving the practice range, such a spin reduction that the training missile becomes unstable and the range of flight is controlled.

Journal ArticleDOI
TL;DR: In this article, the authors compared analytical and experimental supersonic aerodynamic data for a class of canard-controlled missile configurations similar to the sidewinder missile, and evaluated three aerodynamic prediction computer codes, including program MISSILE2, by comparison with the test data.
Abstract: Techniques to predict the aerodynamic characteristics of slender cruciform missiles have been developed and are constantly being updated and improved. This paper presents comparisons between analytical and experimental supersonic aerodynamic data for a class of canard-controlled missile configurations similar to the sidewinder missile. Three aerodynamic prediction computer codes, including program MISSILE2, a recently improved version of program MISSILE, are evaluated by comparison with the test data to assess their accuracy. The major emphasis is placed on the roll control characteristics. In addition, tail span optimization, longitudinal and lateral control, induced roll, and missile roll orientation effects are addressed.

Journal ArticleDOI
H-O. Jonsson1, G. Malmberg1
TL;DR: This paper studies how a Differential Dynamic Programming method can be used to compute optimal thrust vector controls for vertically launched missiles and substantiates the practicality of a technique to control the convergence to overcome its difficulties with DDP.
Abstract: This paper studies how a Differential Dynamic Programming (DDP) method can be used to compute optimal thrust vector controls for vertically launched missiles. Furthermore, the results of this investigation substantiate the practicality of a technique to control the convergence to overcome its difficulties with DDP. The problem under consideration requires the missile to perform a high-angle-of-attack maneuver. This, together with the control deflection limitation, implies nonlinear system dynamics. The optimal trajectories computed represent the performance that is possible to achieve given certain physical missile properties. The relative importance of different missile constraints is thus possible to compute.

01 Nov 1982
TL;DR: In this paper, two planar missile airframes were compared having the potential for improved bank-to-turn control but having different aerodynamic properties, including Cortical cross-coupling effects.
Abstract: Two planar missile airframes were compared having the potential for improved bank-to-turn control but having different aerodynamic properties. The comparison was made with advanced level autopilots using both linear and nonlinear 3-D aerodynamic models to obtain realistic missile body angular rates and control surface incidence. Cortical cross-coupling effects are identified and desirable aerodynamics are recommended for improved coordinated (BTT) (CBTT) performance. In addition, recommendations are made for autopilot control law analyses and design techniques for improving CBTT performance.

Patent
12 Jul 1982
TL;DR: In this article, an improved airframe body decoupling system for a body gimballed sensor on an interceptor aircraft or guided missile is presented, where the true measure of sensor position is differentiated and then externally decoupled to produce the desired line of sight rate for use by the guidance/control section of the proportional navigation guidance system.
Abstract: An improved airframe body decoupling system for a body gimballed sensor on an interceptor aircraft or guided missile. Body rate gyro information is employed for internal decoupling so as to eliminate decoupling match sensitivity to receiver errors. The true measure of sensor position from the gimballed antenna potentiometer is differentiated and then externally decoupled to produce the desired line-of-sight rate for use by the guidance/control section of the proportional navigation guidance system.

Patent
26 Aug 1982
TL;DR: In this paper, the system for aiming of a missile with a strapdown inertial measurement unit (IMU) does not possess the capability of self-aiming and requires uncoupling prior to launch to avoid expending the northfinder.
Abstract: The system for aiming of a missile strapdown Inertial Measurement Unit forases in which the IMU does not possess the capability of self-aiming involves no mechanical link between northfinder and IMU which would require uncoupling prior to launch to avoid expending the northfinder. The technique maintains an automatic, hands-off capability by use of a laser link for azimuth transfer rather than a manual, optical link. The northfinder and laser system are launcher mounted and are therefore not expended with the missile.

Journal ArticleDOI
TL;DR: In 1969, there was a lengthy debate in the US senate and before its committees on the ABM (or AntiBallistic Missile) which was designed to shoot down the ICBM (or InterContinental Ballistic Missile) as mentioned in this paper.
Abstract: In 1969 there was a lengthy debate in the US senate and before its committees on the ABM (or AntiBallistic Missile) which was designed to shoot down the ICBM (or InterContinental Ballistic Missile). The ABM had been developed over many years at a cost of a few billions of dollars, and it was now proposed to manufacture and install this weapons system for the defense of the continental United States at a cost of many billions of dollars. This debate was salutary because, among other things, it was the first time that the technological arguments, which should be one of the important considerations in such a political decision as whether to deploy an ABM, were fully explored before the public.

01 Aug 1982
TL;DR: This report is intended to be a users manual for a computer program called AERODSN, which estimates the stability coefficients of typical missile configurations with wings or tail fins or both, and Static stability and damping derivatives at zero angle of attack are predicted.
Abstract: : This report is intended to be a users manual for a computer program called AERODSN, which estimates the stability coefficients of typical missile configurations with wings or tail fins or both. The Mach range is from zero to approximately 4.0. The roll orientation is zero (plus configuration). Wings and tails must be in line. Control deflections are allowed. A limited amount of body alone experimental data is included (ogive cylinder or cone cylinder); however, body alone tables can be input if desired. A conical boattail segment can be added. This program does not predict drag. Static stability and damping derivatives at zero angle of attack are predicted. (Author)

Patent
26 Nov 1982
TL;DR: In this paper, a guidance system for a beam rider missile, having a novel coded light beam projector at an aiming station, for use by a missile-mounted receiver, is presented.
Abstract: A guidance system for a beam rider missile, having a novel coded light beam projector at an aiming station, for use by a missile-mounted receiver. The projecting means contains a rotating transparent reticle through which the beam is transmitted, the reticle having an opaque radial portion in a curved "leaf" shape. When the diameter of the projected beam is held constant at the missile distance during flight, the position of the missile in polar coordinate form is given by the relative angular position and duration of the blocked-out portion of the beam received at the missile.

Patent
15 Jun 1982
TL;DR: A gas jet by controlling to change the direction of flight of a guided missile is described in this paper, where a set of fixed nozzles (T1 to T4) arranged in an annular element inside which are arranged coaxially of the movable liners (2 and 3) provided with lights respectively (A1 to A4 and (B1 to 84), means are provided for positioning these lights with respect to the NOVs of the inlet ports in order to direct the gas flow in a specific nozzle.
Abstract: A gas jet by controlling to change the direction of flight of a guided missile, said device comprising an energy source providing a gas flow to a set of fixed nozzles (T1 to T4) arranged in an annular element ( 1) inside which are arranged coaxially of the movable liners (2 and 3) provided with lights respectively (A1 to A4) and (B1 to 84); means are provided for positioning these lights with respect to the nozzles of the inlet ports in order to direct the gas flow in a specific nozzle. The device is used in missiles, projectiles, rockets etc ...

Patent
02 Jul 1982
TL;DR: In this article, an impulse generator for providing an impulsive force substantially normalo the axis of a missile to provide the missile with the desired angle of attack is presented, which includes radial explosive paths to its periphery and from each point on the periphery detonation is transferred to the periphery of the main charge causing it to implode.
Abstract: An impulse generator for providing an impulsive force substantially normalo the axis of a missile to provide the missile with the desired angle of attack. The device includes radial explosive paths to its periphery and from each point on the periphery detonation is transferred to the periphery of the main charge causing it to implode.

Patent
06 Apr 1982
TL;DR: In this paper, an annular control device with ejection nozzles and gas passage channels was used for guided missiles, including combat missiles, and was shown to be effective in the field.
Abstract: Control device comprising an annular member (1) provided with ejection nozzles N (T the rotary member comprises M of gas passage channels (C This control device is used in guided missiles, including combat missiles.