Flight method of rolling missile
FIELD: weapons and ammunition.
SUBSTANCE: rolling missile is accelerated to cruising speed by means of a detachable solid-fuel launching accelerator, cruising speed is maintained with thrust of a small-size disposable turbo-jet engine, twisted and a mode of rotation about the roll axis is maintained by means of aft stabilisers that are slanted relative to the longitudinal axis and/or a gas-dynamic nozzle on the turbo-jet engine, aerodynamic lifting force is formed in the rotation mode by means of n pairs of small-size foldable wings.
EFFECT: invention allows increasing flight distance of a cruise missile.
The present invention relates to the field of precision weapons (THAT) and it relates to the new varieties in the form of a hybrid rotating missiles (BP) and cruise missiles (CU). Currently known unmanaged BP with correction of their movement on the sighting angles (used, for example, in the reaction system volley fire "Tornado") and controlled BP: single rotating anti-aircraft missiles (VSWR), such as "stinger", "Arrow", "Needle", "Mistral" and other BP, such as anti-tank.
The history of the development of rockets for military purposes began during the 2nd world war, when German engineers have created the world's first rocket is equipped with navigation and automatic piloting V-2. After the war this area weapons got rapid development and were created by the missiles of various classes and purposes. Despite all their differences, the General principle of flight of all types of missiles is the formation of the jet thrust with thrust coefficient (CT) greater than unity (CT is the ratio of thrust starting weight). Thus, the rocket unlike the aircraft (AC) with other types of CT is less than one is not required to generate aerodynamic lift, and compensation of the force vector of gravity on the active part of its trajectory is due to the vertical component of the thrust vector, and the passive after vigor�of fuel to compensate for the force of gravity is no more and the rocket continues to move, but not moving up or horizontally on the course, and forward and down the parabola.
When developing any type of aircraft), including missiles, even at the stage of research and experimental design, in addition to task for unconditional support of the formation of lifting force before the developers get up many of the tasks of the search for technical solutions (TP), the most important of which are to ensure the stabilization of the angular positions at the start, the stabilization of the missile and control in flight without loss of stability of motion in all specified regular modes, taking into account all possible internal and external disturbances.
With the development of rocket technology and solutions to the identified problems from the standpoint of the mechanics of flight, principles of stability and controllability of the movement of all known missile, despite their apparent diversity, can be divided only into two groups: missiles with 6 degrees of free movement and missiles with 5 degrees of freedom is stabilized by the 6th rotation around the roll axis. Missiles with 6 degrees of freedom (let's call them non - HP) and BP differ significantly on the mechanics of motion, the principles of ensuring the stability and control of movement. HP are far more complex principles, more sophisticated stabilization system, automatic pelotero�tion, homing on the target, because of the need to stabilize angular positions around the 3 axes, roll, heading, and pitch and control the movement also 3-coordinates that requires a large number of control forces and moments. BP have a natural stabilization without the cost of technical means through gyrostabilizers momentum of the rotating body, and are managed much easier on one channel, so they are called single-channel.
The most extensive development and spread of HP, from heavy ballistic missiles to shoot small caliber, for different purposes and applications as carriers of nuclear weapons, cluster combat elements of individual homing missiles classes "ground-to-ground, air-to-air missiles, sea-based tactical missiles are part of the reconnaissance-strike complexes (HANDS), there are HP small, medium, and long range. From the variety of HP special significance cruise missiles (CU) - based and range. CU characterized by a high probability of hitting the wide range of goals, start CU virtually no modern means of fixed missile warning, and massive use of the CD even with conventional non-nuclear warhead (BC) p�formulating action is comparable to the use of nuclear weapons. However, all the known CU are performed with 6 degrees of freedom as HP and have therefore increased the complexity of stabilization systems and management and the high cost of technical means for implementing the methods of flight stabilization and control 6 degrees of freedom spatial movement, which in turn increases the cost, its own weight and dimensions of both the missiles and launchers).
Less well-known and have a limited scope of BP, mainly as small-caliber anti-aircraft missiles for firing at low-flying air targets and as anti-tank missiles. But BP have a number of significant advantages over HP: simplicity stabilization without the cost of technical equipment, single channel operation, a large margin of stability of motion in all modes of flight, small own weight and dimensions of both the missiles and PU.
Due to the lack of diversity BP as close TP to the applicant and the closest TP is a method of flight VSWR (1, 2). The known method of flight based on acceleration VSWR jet-thrust solid-propellant rocket engine with CT is greater than one, simultaneously twist around the axis of the roll and the stabilization of its spatial movement maintaining the rotation by gyrostabilizers momentum of the rotating body, single channel motion control cancer�s in rotation mode via synchronous in frequency and phase rotation change bookmarks rudders on the sign of the angle of attack. The known method of flight does not require the formation of aerodynamic lift, as the vertical component of the thrust vector sufficient for movement of the rocket at any angle up to 90°. However, this advantage has "reverse of the medal" while CT is not necessary to generate aerodynamic lift, but the more you pull, the greater the rate of combustion of the fuel, kratkovremennoe the active part of the trajectory and the smaller the radius of the missiles. In addition, in the solid fuel includes the oxidant, although for missiles not exceeding the limits of the atmosphere, the oxidizing agent can be on Board not to take, and pick it up from the atmosphere by setting the rotary rocket on the principle of normal winged HP compact disposable turbojet engine (OTRD). This will greatly increase the range of BP and to expand the scope of BP, for example, as a rotating CU (WRC), combining the advantages of BP, as the simplicity of the stabilization and control, small weight and size, with the advantages of cruise missiles, that is, the effectiveness of target at long range and secretive approach to the targets at low and very low altitudes outside the detection zone of the radar systems of the enemy.
The purpose of the claimed method of flight is to increase the flight distance and the expansion about�ASTA use BP.
These goals are achieved in that in the method of flight BP, based on the acceleration of the rocket jet thrust, twist it around the roll axis and the stabilization of the rotation, single channel, the management mode of rotation through synchronous in frequency and phase rotation toggle bookmark rudders on the sign of the angle of attack, first spin and accelerates the missile to the primary speed with a solid propellant booster, and then maintain cruising speed quickly pull small OTRD, support mode of rotation is oblique relative to the longitudinal axis of the missile tail stabilizers or by using gas-dynamic nozzle on the nozzle OTRD and form an aerodynamic lift force in the rotation mode by simultaneous frequency and consistent for the total phase shift of n-pairs of compact folding wings, located at the corner of the roll increments of
Thus, stated in the TP method, a lifting force is formed by the thrust of the solid propellant upper stage engine on the parts of the trajectory, and then flying BP loss�goes through the formation of aerodynamic lift as expressly set forth above. This principle of development the lifting force in the rotation mode is currently unknown. It is the introduction to the proposed method of flight of this trait allows you to get the declared intermittent positive effects: sudden qualitative increase in flight distance BP and promising direction for further development of BP for their use as cruise missiles, long range while maintaining the stability of motion without the cost of technical means, compactness, small self-weight and caliber, the reduction of which is limited only by massogabaritnymi known OTRD. In the future, with the development of such WRC sufficiently small size and weight, they can be used in the composition of the reactive systems of volley fire WRC individual guidance to defeat the purposes of clusters of the enemy at long range. It is known that all BP operated in the mode of rotation, moving in a spiral at a zero coefficient command (CC), because the governing force vector rotates with the rocket, see (2). From supersonic aerodynamics it is known that the velocity of the rocket above the speed of sound in the bow at the point of its taper arise shock wave or the shock surface (shocks), whose dismissal from the rocket sharpening blunted and set spiral aerody�onicescu nozzle (adni). In addition, if the rocket an optical homing head (AFO), it is necessary not only to withdraw the shocks, but also to prevent heating of the fairing AFO, otherwise there will be interfering background infrared radiation, which can blind the infrared channel and score a useful signal from the target and even sophisticated filtering backgrounds will not help to isolate it. The rotation will help to solve these problems for VSWR "Needle", which has a cruising speed of 600 m/s, is successfully solved by the installation of the fairing AFO spiral adni. Thus, the WRC will get many advantages compared to conventional non-rotating CU. Thanks to a new combination of useful properties acquired at WRC will be possible to use two channels targeting, optical and radar, and the mechanical rotation may be used to scan the underlying surface of a simplified antenna without the phase grating. All these advantages due to the fact that spiral rotary motion, by its nature, has advantages over progressive and give developers more WRC rich possibilities of solving many design problems WRC, although the main and most important advantage of this method of flight in rotation mode is to ensure the stability of motion without the cost of hardware, which is very substantial in the field�e HP this factor ceteris paribus increases her weight and dimensions of known CU.
Fig.figure 1 shows the WRC, as one of the options for implementing the proposed method of flight BP; Fig.2 simplified block functional diagram for explaining the principle of operation of the rocket in terms of management and formation of aerodynamic lift in rotation mode.
Fig.1 marked: startup accelerator with 1 PAU 2; case 3 the primary stage of the rocket; small ATRD 4; DDT 5; folding the air intake 6; three pairs of folding of the wings 7, 8, 9; rudders 10; 11 adni.
Fig.2 marked: autopilot (AP) 1, combined with a navigation unit; a gyroscope 2-1 roll, which revolves around the sensor 2-2 reference signals; amplifiers 3, 4, 5, 6; actuators 11, 12, 13 of the wings 7, 8, 9; actuator 14 rudders 10 (for convenience, the numbering of the wings and rudders in Fig.1 and Fig.2 matches).
Method of flight WRC in Fig.1 and 2 operates as follows. In the initial state WRC fused, installed in the transport and launch container and passed preflight training, during which the memory of the navigation unit entered the coordinates for the target and the trajectory of approach to it. On the command "start" triggered lifting charge, WRC exits the launch tube, after which triggered the start of the accelerator 1, which accelerates the craft and at the same time spinning around h�making it around the roll axis due to the action on the jet DDT 2. After running out of fuel in the accelerator trigger pirozhki (in Fig.1 are not shown, since these are typical elements of any missiles) and the accelerator 1 is separated from the primary stage of WRC. After separation of the accelerator serves a command to unlock the folding of the air inlet 6, the folding of the wings 7, 8, 9 and rudders 10 and to run ATRD 4. Elements of the air inlet 6, the wings 7, 8, 9 and drive 10 out of the grooves and fixed in position. In accordance with flight instructions 1 AP begins to form single-channel control signal (CS), using the reference "meander" sign sinωt frequency of rotation ω of the rocket, t - time, and digital reference signal, a unitary impulse number code representing a single module of the vector of factor commands (CC) integral unit functions sinωt. Methods of forming the SU single-channel rotary rocket, see (3), see example of a sensor (4). SU with the AP 1 is supplied to the power amplifier 6 and then to the steering actuator 14. When the trajectory of the rocket, given in her memory flight instructions, the AP delivers the SU with zero components of the module and phase of the vector QC, and when WRC deviates from its trajectory, served QC, WRC returns to its trajectory. In either case, the wheels 10 are switched synchronously by the frequency and phase of rotation of the WRC is the sign of the angle of attack changes the switching law for sadhanamala and QC phase. Simultaneously, the sensor 2-2 orbiting gyroscope 2-1 roll, three reference forms "meander", shifted between each other in phase by 120° and an initial phase, i.e. the initial count corresponding vertical phase plane perfect wings (PEAK). These meanders are received at the inputs of the power amplifiers 3, 4, 5, and further to the actuators 11, 12, 13 of the wings 7, 8, 9, which are arranged along the longitudinal axis of the housing WRC symmetrically about its center of mass and discrete spiral with a shift angle of roll 120, the twisting direction which coincides with the direction of rotation of the WRC. The actuators 11, 12, 13 switch the sign of the angle of attack consistently 3 times per rotation of the wings 7, 8, 9, whereby all the resultant lifting force vectors are summed, integrally forming a lifting force. As is known from aerodynamics, the lifting force is proportional to the air density, wing area, the speed of circulation of the flow. For SRS, it is important to get the maximum possible lift force at the lowest possible area of the wings to reduce the number of channels of its formation. So marching speed WRC shall be not less than 600 m/s, angle of attack is close to critical, and the profile of the wings must ensure Horny vorticity of the flow, which significantly increases lifting strength.
Solve all the mentioned problems of designing WRC for re�implementation of the inventive method of flight BP known and utilized in aviation and rocket technology. A method of controlling a mode of rotation, methods of forming the SU BP is known from theory and practice of designing VSWR, TP sensor and the formation of the proposed reference signal is known, and sources indicated in the text and list of references. Thus, the solution of the inventive method of flight BP meets the criterion of industrial applicability. The novelty of the solution and its non-obviousness shown above. The expected technical result: increase range range BP for hitting distant targets of the enemy and the expansion of application fields of BP.
The LIST of references
1. Krasovskii, A. A., and others. Fundamentals of theory and design of rotating single-guided missiles. Zhukovsky Academy. Zhukovsky, 1963.
2. Technical description of MANPADS KM and KM. Technical descriptions of the products A and E (VSWR Strela, Igla - analogues and prototype).
3. The USSR, A. S.№№298319, 265518, 323169.
4. The USSR, A. S. No. 265518, 297567.
The LIST of USED ABBREVIATIONS
BP - rotating rocket; HP - non-rotating rocket; CU - cruise missile; WRC - rotating cruise missile; VSWR - rotating anti-aircraft guided missile; THEN - accurate weapon; CT is the thrust coefficient; QC - factor command; LA aircraft; TR - technical solution; BC - battle of; PU - launcher; OTG - expendable turbojet et�hotel; Adni - aerodynamic nozzle; PAU - gas-dynamic nozzle; AFO - optical homing head; AP - autopilot; SU - control signal; PEAK - the perfect plane of the wings.
Method of rotating flight of the rocket, based on acceleration reactive thrust, twist and maintenance of rotating around the roll axis, the stabilization of the rotation and single-channel spatial movement in rotation mode, characterized in that for the purpose of range increase and expand areas of application of the first spin and accelerates the missile to the primary speed with detachable solid starting the accelerator, and then maintain cruising speed quickly pull small disposable turbojet engine, support mode rotation by means of gas-dynamic nozzle, which is mounted on the nozzle of the turbojet engine and/or slanted relative to the longitudinal axis of the shank stabilizers, and form the aerodynamic lift force rotating through consistent at the current phase of rotation of the rocket aggregate toggle bookmark the sign of the angle of attack of the n-pairs of compact folding of the wings, which have the roll angle increments of
FIELD: weapons and ammunition.
SUBSTANCE: shell with gas hanger includes a smooth cylindrical part, in which there is a feed cavity connected to the outer cylindrical surface through feed devices. The feed cavity is intended to create pressure in a carrying gas layer. The feed cavity is filled with substance having high combustion speed. The feed cavity is connected to the rear part of the shell through a thermite wick. The latter is made in the form of a gasket arranged on the inner wall of the feed cavity and pressed to this wall with a spring-loaded shoe.
EFFECT: reduction of the shell size and increase of firing distance.
FIELD: weapons and ammunition.
SUBSTANCE: guided missile is made based on canard configuration. The missile with a single-channel control system and rotating in roll direction. The missile contains a main propulsion system, a steering wheel in one plane and a stabiliser with the location of fixed bearing surfaces by X-shaped pattern relating to the plane of the steering wheel console. At the head part of the housing of the guided missile in a plane perpendicular to the plane of the steering wheel console, the pylons are mounted. The fixed consoles of the pylons in a transverse plane are located at an angle of 45-60 degrees relative the consoles of the stabiliser. The consoles of the pylon on the geometric shape in the plan are made like consoles of the steering wheel with the ratio of areas of the pylon and the steering wheel as 0.5-1.0. The ratio of areas of the console of the pylon and the console of the stabiliser are made as 0.05-0.1.
EFFECT: improved control efficiency, improved ballistic and dynamic properties of the missile.
FIELD: weapons and ammunition.
SUBSTANCE: unit of control system of rocket projectile comprises a housing with ogive part, aerodynamic controllers folding-out in flight with actuators and a control unit, mounted on the ogive part. Each controller is equipped with abutment. The abutment is located in front of the front edge of the controller coaxially with the axis of folding-out. The profile of the front part of the abutment is congruent to the profile of the ogive part of the housing. The diameter of the maximum circumscribed circle of the abutments of all the controllers does not exceed the unit gauge. Folding-out axes of the controllers are biased to the axis of the unit relative to its gauge by an amount at least 0.5 of the maximum thickness of the controller at the root chord of its folding-out part.
EFFECT: improvement of accuracy of projectile shooting.
4 cl, 2 dwg
FIELD: weapons and ammunition.
SUBSTANCE: invention relates to missile engineering, namely to controlled missiles. A controlled missile includes a housing with the main control elements symmetrically arranged on it - aerodynamic surfaces and rudders, as well as a wire duct. The latter is arranged along the housing in the incline of rudders. An aerodynamic surface is additionally installed on the housing, on the side opposite to the wire duct.
EFFECT: improvement of aerodynamics of missile flight and improvement of its target guidance accuracy.
2 cl, 1 dwg
FIELD: weapons and ammunition.
SUBSTANCE: performed is topographic control of target indicator and launching facility to the terrain by ground satellite receiver, determined are coordinates of launching facility and location and ephemeris for each space vehicle of satellite positioning system, detected and measured are target coordinates, the coordinates are transmitted to artillery position control station, set is universal computer time in reconnaissanceman's console and artillery position control station, calculated and transmitted are shooting settings to launching facility automatic control unit, performed is missile launching procedure, the missile is launched from transporter-launcher container along the preset ballistic course, the missile is oriented by on-board navigation satellite receiver, when the missile approaches the target it is oriented by laser emitter.
EFFECT: providing higher probability of guided missile hitting the target.
FIELD: weapons and ammunition.
SUBSTANCE: shell is made based on the canard configuration. The shell comprises an air-dynamic steering gear in the front section of the shell housing and aerodynamic control elements - steering wheels with pylons mounted in front of them. The air-intake devices of the air-dynamic steering gear are incorporated in the pylons and made in the form of bi-plane U-shaped plates with converting into the monoplane along the rear edge. In the front edge of the pylon the U-shaped hole is made and the hole in the shell housing is made.
EFFECT: increase in efficiency of the shell operation.
2 cl, 6 dwg
SUBSTANCE: proposed set of inventions relates to military equipment, namely to method and means for parachute and fastened to it container packing. Method for packing parachute and fastened to it container with useful equipment into grenade body head includes packing of parachute canopy, shroud lines and metal extension (if present) into grenade body head. When parachute canopy is packed it is used to form dome in the grenade body head by means of special appliance. The major portion of canopy material is placed at side wall of dome. Portion of shroud lines of parachute adjacent to its canopy is wound as spiral onto the rod placed in concavity of dome. Appliance for packing parachute and fastened to it container with useful equipment into grenade body head is formed by body which consists of two coaxial and installed one inside the other bushings and by rod freely accommodated in the channel of inner bushing. On the outer bushing, at its front butt end on the outside fascia is made which centres it in grenade body head. On the inner bushing, at the side of its front butt end, outer diametrical lowering is made on which radial-longitudinal grooves are made which are symmetric to end slots of outer bushing and spaced from front butt end of inner bushing by minimum distance.
EFFECT: higher reliability of parachute deployment.
3 cl, 4 dwg
FIELD: weapons and ammunition.
SUBSTANCE: invention refers to military equipment and may be used for development of missile take-off from container. Onboard command device includes power source, electrically connected to catapult device, first-stage engine, servo units through normally closed switches, switch interacting with dummy outcome sensor, unit of engine start time delay relative to the moment of outcome sensor action, two parallel chains with inverter for supply of electric signal of required polarity to servo units.
EFFECT: providing non-use of control system for take-off and dummy displacement from take-off position.
FIELD: weapons and ammunition.
SUBSTANCE: invention relates to methods for hitting of underwater targets. The method to hit underwater targets consists in delivery of a detachable warhead of underwater action to a target location area, separation of a warhead in the end section of flight trajectory and its actuation after landing on water. The detachable warhead is delivered by the first missile. Prior to delivery of the warhead to the target location area, they deliver one radio hydroacoustic buoy. The buoy is delivered by the second missile. After buoy landing on water, as the first missile gets closer to the area of target location, by means of equipment placed on it, they provide for reception of information from the buoy on location of the target, and the point of warhead landing on water is corrected. Cruise missiles are used for delivery of the warhead and buoy to the area of target location. The cruise missile is equipped with a sustainer power plant with an air jet engine. The speed of acceleration of each missile by a speeding device in the initial section of the trajectory is limited by the value sufficient for development of an aerodynamic lifting force that sustains the flight and to start the sustainer engine, afterwards they provide for its separation from the speeding device, start of the sustainer engine and further flight to the area of target location in the atmosphere. Correction of the point of warhead landing on water is carried out due to correction of the trajectory of the first missile flight by confirmed coordinates of the target and separation of the warhead closer to the target.
EFFECT: invention provides for reduced mass of a missile complex.
4 cl, 2 dwg
FIELD: weapons and ammunition.
SUBSTANCE: underwater target hitting method consists in supply to a target location area of an underwater action separated warhead and one hydroacoustic buoy by means of a missile using an acceleration device, separation of the warhead in the final section of the flight trajectory and its involvement after splashdown. Before the underwater action warhead is separated, one hydroacoustic buoy is separated, and after its splashdown, by means of equipment arranged on the missile there provided is a reception via a radio channel of information from the hydroacoustic buoy on a target location. A point of splashdown of the underwater action warhead is corrected as per the received information. In order to deliver the separated underwater action warhead and one hydroacoustic buoy to the target location area, a cruise missile is used. The missile is provided with a propulsion power plant with an air-jet engine. The missile acceleration velocity in the initial section of the trajectory is restricted by a value sufficient for the creation of an aerodynamic lift supporting the flight and for the start of a cruise engine, after which there provided is its separation from the acceleration device, the start of the cruise engine and further flight to the location area of the target in the atmosphere.
EFFECT: reduction of the weight of an underwater target hitting device.
3 cl, 1 dwg
FIELD: armament, in particular, guided missiles.
SUBSTANCE: the guided missile has a body with on-board systems, frame with drive shafts made with journals, with air vanes hinge-installed in their end face grooves for folding in the body and fixation in the unfolded position. The guided missile is provided with control-surface deflection transducers and a printed circuit board secured through an insulator on the front end face of the frame and connected by means of a bundled conductor to the on-board systems of the guided missile.
EFFECT: reduced spread in the value of the sweep angle of the air vanes in the process of manufacture.
FIELD: guided missiles, in particular, their control actuators.
SUBSTANCE: the control surfaces are connected by means of a half-axle, in which a central hole is made along the missile longitudinal axis, alkane holes are made perpendicularly to the longitudinal axis for installation of the axles of the control surfaces. The half-axle has components for coupling to the actuation cylinders.
EFFECT: enhanced efficiency of armor-piercing capacity of the missile.
4 cl, 2 dwg
FIELD: defense engineering; production of guided missiles and projectiles.
SUBSTANCE: the invention is pertinent to the field of defense engineering, in particular, to production of guided missiles and projectiles. The technical result of the invention is simplification of testing, increased accuracy, decreased labor input and cost of the testing. The method of testing of a developed torque of an electro-pneumatic steering gear of guided missiles and projectiles is based on a torque measurement of the steering gear with the help of a reference load and an easily removable balance lever put on a rudder. Then the steering gear with a detector of the rudders motion are installed on a customizing table. The detector of the rudders motion is made in the form of a separate contact or non-contact sensor or for the purpose they use an available in the steering gear as a feedback gauge - the gauge of a piston linear motion or a gauge of angular motion of rudders. The rudders turning at a maximum angle in one side is made using application of a torque of the corresponding sign by a reference load with the weight on a definite length of an arm of a placement of the load on the lever in respect to the axis of rotation of the rudders equal to a developed torque of the steering gear at the given pressure of the feeding. Switch on the power of the gauge, measure the voltage on the gauge output by a voltmeter, remove a torque by removal of the reference load, turn the rudders at a maximum angle in other side using application of a torque of an opposite sign equal to a maximum torque of a hinged load on the rudders in respect to the rudders turning angle and an angle of attack of a missile or a projectile. Switch on power supply of the booster of the steering gear and feed onto an input of the steering gear compressed air under pressure of P =1.5Pgvn., feed onto the input of the steering gear a maximum control signal of management corresponding to the motion of the rudders at a maximum angle, measure the voltage on the output of the gauge, which should meet the first given ratio. By a smooth reduction of pressure of the feeding in the pneumo-circuit) of the steering gear and according to reduction of voltage on the output of the gauge determine pressureP
EFFECT: the invention ensures simplification of testing, increased accuracy, decreased labor input and cost of the testing.
5 cl, 1 dwg
FIELD: methods for missile radar guidance on air targets in radar guidance systems.
SUBSTANCE: guidance of missiles on an air target moving in the direction to the protected object, including the detection of the air target, evaluation of the parameters of its trajectory, missile launching, missile-to-target approach to the distance of actuation of the missile warhead blasting device, correction of the missile heading in the process of approach, blasting of the charge of the missile warhead at a distance from the protected object not less than the preset one, is accomplished in the trajectory coinciding, in the terminal leg with the predicted missile trajectory. In the terminal leg the speed of the missile is set lower than that of the air target. The result is also attained by the fact that the guidance of the missile on the air target moving in the direction to the protected object, including the detection of the air target, evaluation of the parameters of its trajectory, missile launching, missile-to-target approach to the distance of actuation of the missile warhead blasting device, correction of the missile heading in the process of approach, blasting of the charge of the missile warhead at a distance from the protected object not less than the preset one, is accomplished in the trajectory of the missile displaced in the direction to the protected object. In the terminal leg the speed of the missile is set higher than that of the air target. The result is also attained by the fact that the radar set for guidance of the missile on the air target has a missile control point and an on-board radar equipment. The missile control point includes a detection radar, a guidance radar, a computer, a servo drive, a transmitting device and an antenna device, the missile on-board equipment has a missile antenna, radio-receiving device of the missile guidance channel, actuating device, selector switch, transmitting device, radio-receiving device of the detection channel, computer.
EFFECT: reduced dynamic errors of missile guidance on an air target, and enhanced time of radio contact of the missile warhead fuse: with the air target.
5 cl, 6 dwg
FIELD: flying vehicle control systems, mainly small-sized guided projectiles.
SUBSTANCE: proposed control actuator includes adder whose first input is used as actuator input and correcting filter connected to adder output. Actuator includes also relay element, power amplifier and servo unit connected in series. Servo unit output is used as actuator output and is connected with second input of adder through feedback element. Circuit is additionally provided with harmonic signal generator and second adder. First input of adder is connected with correcting filter output and second input is connected with output of harmonic signal generator and output is connected with relay element input. Such arrangement makes it possible to change and to select parameters of correcting filter and gain factor of circuit.
EFFECT: enhanced operational accuracy and noise immunity.
FIELD: aeronautical engineering; control systems of unmanned flying vehicles provided with target coordinator and passive homing system.
SUBSTANCE: proposed method consists in selection of tracking point inside target loop and measurement of parameters of motion of flying vehicle relative to this point. During autonomous flight of flying vehicle, its selective guidance is ensured by forming limited tracking zone around selected tracking point with many threshold magnitudes and respective time intervals. When tracking point gets beyond these thresholds, its position is restored by forced correction. In case tracking within this zone is unstable after several correction cycles, guidance in target loop is performed instead of selective guidance by making several correction cycles of tracking point. In case tracking is unstable again, target is considered to be lost. Homing is replaced by forced motion of flying vehicle in way of reference tracking point over rectilinear trajectory and fixing the axis of target coordinator in direction towards selected tracking point. Attempts are made for locking-on new tracking point inside target loop. In case of successful attempt, homing of flying vehicle to new tracking point is performed. In case of unstable tracking, target lock-on is considered to absent and fixed position of target coordinator axis is restored positively. As target range reduces, approximate linear deviation of tracking point is maintained constant inside target loop.
EFFECT: enhanced efficiency of flying vehicle due to selective guidance and retaining controllability in case of loss of target.
6 cl, 6 dwg
FIELD: defense equipment, in particular, projectiles and missiles.
SUBSTANCE: the preliminarily cooled to the maximum preset negative temperature of the control drive is checked in a thermal vacuum chamber, when it is fed with air of a raised humidity. After the check a technical inspection of the drive (assemblies and parts) is carried out and the quality of coatings and insulation of the current-conducting circuits, strength, stability and serviceability are estimated. According to the results of the comparative estimate of the obtained values of the measured parameters with the preset ones in the selected conditions and technical inspection, a decision is taken on the quality of functioning of the air-dynamic control actuator cooled to the negative temperature at a compressed aid of a raised humidity. The stand for quality control of functioning of the air-dynamic control actuator of guided missile is provided with a thermal vacuum chamber with a vacuum pump, humidity chamber and a pneumatic cock with a connecting hose. The outlet of the humidity chamber is connected to the pneumatic cock and connecting hose to the inlet of the receiver. The base with the unit fastened on it and the receiver with the measuring pressure gauge and the relief valve are installed in the thermal vacuum chamber.
EFFECT: expanded potentialities of use of the stand and enhanced quality of control of functioning of air-dynamic control actuators and autopilots of guided projectiles and missiles.
2 cl, 1 dwg
FIELD: armament, in particularly, rocketry, applicable in development of missile-weapon complexes with beam-rider guidance systems, in which the missile flight trajectory, for example, close to and parallel with the ground surface, or water surface.
SUBSTANCE: from the moment of start a program-changed pitch command is formed on the missile, and at an entry of the missile in the beam area control is effected by the TV guidance system. In the horizontal plane the directions of the missile start line and beam are matched with the zero value of command messages. In the vertical plane the direction of the missile start line is adjusted in angle above the beam direction with the zero values of the command messages, and the beam-rider guidance system is controlled by the guidance system from the moment of getting of the missile to the beam area with zero values of command messages in the vertical plane, the missile is twisted in bank angle. Described are two modifications of the complex of the missile telecontrolled in beam. The first modification has a missile that includes components of missile electromechanical joining, autopilot, and a series-connected receiver and a coordinate separation unit, as well as a control station that includes a sight-guidance instrument and a start control device, which is connected via the device of the electromechanical joining of the launcher to the components of the missile electromechanical joining, the receiver is coupled by electromagnetic radiation to the sight-guidance instrument; installed on the missile are a delay unit and series-connected starting pulse shaper, variable command shaper and an adder, the heading and pitch outputs of the coordinates separation unit are connected, respectively, to the first and second inputs of the delay unit, the heading output of the delay unit is connected to the first input of the autopilot, the pitch output of the delay unit is connected to the second input of the adder, the adder output is connected to the second input of the autopilot, and the third input of the delay unit is connected to the output of the starting pulse shape, whose input is connected to the components of the missile electromechanical joining. The second modification differs from the first one by the fact, that the receiver output is connected to the first input of the delay unit, whose output is connected to the input of the coordinates separation unit, the pitch output of the coordinates separation unit is connected to the output of the starting pulse shaper, whose input is connected to the components of the missile electromechanical joining.
EFFECT: enhanced efficiency.
4 cl, 6 dwg
FIELD: armament, in particular, rocketry spinning in bank angle, applicable in missile guidance systems, in which beam-rider guidance systems are used, for example.
SUBSTANCE: the electromagnetic radiation from the control station is converted on the missile into the components of the command signal, corrected and a command signal is formed from the corrected values. A bank signal is generated on the missile in the form of electric pulses, whose durations are formed to be equal in value to angular intervals, formed at missile bank spinning, the duration of each pulse is transformed into a binary number, whose value corrects the values of the components of the command signal. Introduction in the missile guidance system of a connected-in-series roll-angle pick-off and a "duration-code" converter has enhanced the reliability due to the use of the missile of roll rate for correction of the value of the command signal on the missile.
EFFECT: enhanced reliability due to the use of the missile roll rate as a regulating value, that corrects the command signal on the rolling missile.
FIELD: armament, in particular, rocketry.
SUBSTANCE: at this method a spatial structure of electromagnetic field is produced at the control station, in which the field parameter is functionally coupled with the coordinates of the respective points of the space. A beam with zero values of the command messages is laid on the target or above the target, and the parameter of the electromagnetic field is measured on the missile, the value of coordinates is determined and the heading and pitch control commands are formed; N devices are positioned in the area of beam propagation, each of the devices transforms the field parameter to the pitch and heading coordinate signals, and then are registered from the missile start, and the position of the missile relative to the target is fixed in the flight trajectory. The process of registration and fixation in time is synchronized according to the value of the registered coordinate signals and fixed missile deviation from the target in heading and pitch, and a conclusion is made on the condition of the beam telecontrol system and its components. The method is realized by the beam telecontrol monitoring system, having a control station, coupled with the missile by electromagnetic radiation, and a telemetering system, use is made of a device for fixation of the missile flight trajectory, and the telemetering system is made in the form of N chains, in each of which connected in series are a receiver and a coordinate separation unit, the heading and pitch outputs of the coordinate separation units from the N chains are connected to a registering device, the receiver from each chain is coupled by an electromagnetic radiation to the control station, and the device fixing the missile flight trajectory is optically coupled with the missile.
EFFECT: a spatial structure of the electromagnetic field is produced at the control station, in which the parameter of the field is functionally coupled with the coordinates of the respective points of the space.
3 cl, 1 dwg