Controlled missile

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

 

The invention relates to the field of rocket technology, in particular to the guided missiles, and can be used in various types and classes of missiles, the construction of which provides for the presence of the office of the Boeing company.

This structural element, which is essentially three-dimensional, oriented in the longitudinal direction and placed outside the housing, closes the control wiring, piping and electrical wires projecting beyond the main casing, and is widely known in the aviation, space and rocket technology.

In particular, in relation to aeronautical engineering, from the patent of the Russian Federation No. 2207968, class B64C 30/00, 1999 known design multipurpose highly maneuverable supersonic plane containing the rear, and from application No. 2008115362, class B64D 27/00, 2009 - the presence of the office of the Boeing company in unmanned aircraft.

The presence of the office of the Boeing company in aerospace engineering is also known from the patent of the Russian Federation No. 2072949, class B64D 37/02, 1997.

In the book "I. I. Toropov - Founder and first chief designer of nowdays, "Raduga Vympel". To the centenary of the birth", Publishing house "Avenir", 2007 shows the appearance of the missile of class "air-air" R-33 (page 162), R-73 (page 161), RVV-AE (page 164, the nearest equivalent), X-29 (page 274), each of which includes a housing accommodated in the housing propulsion system, equipment management system, combat equipment. the ri on the body symmetrically arranged basic controls - the wings and the aerodynamic control surfaces. Also on the body of the rocket placed the rear, acting for its dimensions and protecting electrocommunication from external influences.

When flying rockets with angles of attack in an arbitrary plane of the rear fuselage is at an angle to the incident flow and as a wing of small aspect ratio creates a lifting force in all the control channels, forming a parasitic crosstalk between them and at large angles of attack, causing channel instability.

The technical result, which is the claimed invention is the creation of a guided missile, the construction of which would exclude the above, bring the rear drawback, i.e., would significantly impair the effect of this deficiency on the aerodynamics of the missile and the accuracy of its targeting.

Obtaining the specified technical result is ensured by the fact that in the claimed guided missile, comprising a housing with a symmetrically positioned on the main control aerodynamic surfaces and rudders, as well as the rear, placed in the collapse of the additionally installed on opposite towards the rear side of the at least one aerodynamic surface to balance the lifting force office of the Boeing company and the formation of a vortex flow of neutrons is lisowska vortex flow, created by the rear fuselage.

The invention is illustrated by the image of a rocket with a variant that contains a single aerodynamic surface. In Fig.1 shows a view along the axis of the rocket, which shows the housing 1 of the rocket, symmetrically arranged on the housing 1 basic controls, in particular handlebars 2, and placed in the collapse of the rear fuselage 3. On the housing 1, opposite to the rear 3 side installed aerodynamic surface 4 to balance the lifting force office of the Boeing company and the formation of a vortex flow, neutralizing the vortex flow created by the rear fuselage.

Configuration of additional aerodynamic surfaces is chosen in each case, taking into account the obvious technical (structural) constraints and should give it a load-bearing properties, comparable with bearing properties office of the Boeing company.

As a possible variant, optional installed on the body of the rocket aerodynamic surfaces may be more than one, for example two, which will reduce the size and aerodynamic resistance of these surfaces. In this case, the aerodynamic surfaces are in the form of a biplane and placed in opposite to the location of the office of the Boeing company of the rocket, symmetrically relative to the vertical longitudinal plane of the missile.

Therefore clicks the zoom, additionally mounted on the body of the aerodynamic surface, with the flight of the missile to the target, especially at high angles of attack will be to balance the time and vortex flow arising from the office of the Boeing company 3, which, in turn, will eliminate parasitic drag link between the control channels and channel instability.

1. Guided missile, comprising a housing with a symmetrically placed on the main control aerodynamic surfaces and rudders, as well as the rear, placed along the body in the collapse of the rudders, characterized in that on the body opposite to the rear side, are installed, at least one aerodynamic surface, to balance the lifting force office of the Boeing company and its vortex flow.

2. Guided missile under item 1, characterized in that when two additional installed aerodynamic surfaces they are with the formation of a biplane.



 

Same patents:

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.

Guided shell // 2537357

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

FIELD: transport.

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.

2 dwg

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

Munition // 2529236

FIELD: weapons and ammunition.

SUBSTANCE: munition comprises body with tail part, drop-out supports of stabilising fins and articulation of supports with body tail part. Said tail part is shaped to truncated cone with radial lengthwise grooves. Said drop-out supports of stabilising fins are made of rolled sheet are partially fitted in said radial lengthwise grooves and having holes on body bottom side. Said grooves are open on body bottom side. Elements of articulation of supports with body tail part are composed of circular groove made at body tail nearby its bottom and split ring made of round spring rolled steel. Ring is fitted in both circular groove and holes of supports. Supports feature rolled sheet bend-off made along its extreme chord. Body tail part material nearby circular ring is locally strained to split ring generatrix.

EFFECT: simplified design.

2 cl, 2 dwg

FIELD: transport.

SUBSTANCE: invention relates to control over the flight path of bodies flying at high speeds including orbital velocities. In compliance with proposed method, this system can be used as a backup (standby) path correction system for missiles with failed guidance system. Besides, it can be used at minor bodies whereat installation of standard self-guidance system causes problems. Proposed method comprises application of silicon strips 5, 6, 7, 8 on body side surface alloyed to different degree that provides for different resonance frequency of laser absorption. Laser radiation 3 getting on strip with resonance frequency of radiation absorption causes its evaporation and occurrence of appropriate correcting reactive force. By varying the radiation frequency 3, to get correction pulses in required directions.

EFFECT: possibility to control flight path in two directions across the vector of its current velocity.

1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: guided artillery round comprises body, automatic control unit, steering unit, unit of braking devices, warhead, combined exploder, stabiliser and base gas generator. ACU comprises robot pilot, set of inertial transducers, GPS receiver, passive radar homing head with broadband receiver and receiver frequency tuner module. Unit of braking devices changes projectile drag at final section of trajectory. Said passive radar homing head responds to radio signal emitted by target and can operated in intermittent mode of target signal receipt.

EFFECT: higher accuracy of hitting.

1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to antitank and antiaircraft missile guidance systems. In compliance with this method, control signal is generated for astable drive of aerodynamic rudders with feedback and vibratory linearisation as well as appropriate deflection of rudder drive. Locked time moment is set prior to rocket launch. From the moment of launch to fixed time moment drive control signal is shaped as relay two-position width-modulation signal. Note here that drive is operated in relay mode with deactivated feedback and vibratory linearisation. Missile control system comprises appropriate control hardware (1). It comprises device (2) to measure mismatch of missile with preset guidance line and device (3) to generate control signals. Aerodynamic rudder drive (4) comprises adding amplifier (5), power amplifier (6), relay element (7), actuator (8), rudder deflection transducer (13) and generator (14) of linearisation oscillations. Additionally, it incorporates first and second switches (11, 12), time signal source (9) and logical device (10).

EFFECT: higher accuracy of guidance for rudder drive rockets.

2 cl, 2 dwg

Guided bullet // 2538881

FIELD: weapons and ammunition.

SUBSTANCE: guided bullet comprises a balancing weight, stabilising elements, aerodynamic control bodies, the drive unit of control bodies, and the beam control system which comprises a photoreceiver and onboard equipment. The balancing weight is used as the warhead of kinetic action. The warhead is made in the form of armour-piercing rod. The stabilising elements are made in the form of two consoles and are arranged in a plane passing through the longitudinal axis of the guided bullet. The aerodynamic control bodies are made in the form of a pair of all-moving aerodynamic rudders arranged on one axis located behind the stabilising elements in the direction of motion in a plane passing through the longitudinal axis of the guided bullet and perpendicular plane of location of the stabilising elements. In the guided bullet an on-board power source is located, made with the ability to initiate at the time of firing.

EFFECT: increase in the firing range.

10 cl, 7 dwg

FIELD: weapons and ammunition.

SUBSTANCE: coned-bore rocket comprises the solid rocket propulsion. The solid rocket propulsion is a part of the propulsion system, structurally combining it with rocket-ramjet propulsion. The front bottom of the propulsion system is provided with air intake device located in the ring formed by the difference of calibre of the main propulsion stage and the propulsion device. The gas generator of the rocket-ramjet propulsion is placed in the combustion chamber of the rocket propulsion concentrically with its fuel charge. The method of extending the area of applicability of coned-bore rocket in range comprises the rocket acceleration on the ascending branch of the trajectory by the solid rocket propulsion, its subsequent separation and flying of the main propulsion stage by inertia. To increase the range of flight after use of the solid rocket propulsion the rocket-ramjet propulsion is activated. The air intake device is opened, the nozzle of the rocket propulsion is transformed, increasing its critical section, and the rocket propulsion combustion chamber is used as an afterburning chamber of the rocket-ramjet propulsion. After use of the rocket-ramjet propulsion it is separated together with the rocket propulsion. To reduce flight distance after use of the rocket propulsion the rocket-ramjet propulsion is not activated and they are separated with programmable time delay.

EFFECT: increase in the maximum range of the rocket flight.

4 cl, 9 dwg

Guided shell // 2537357

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

FIELD: weapons and ammunition.

SUBSTANCE: this rocket section comprises body with heat insulation and set of fins. Sleeve of elastic material with low ablation temperature fitted in ring groove is arranged ahead of fins some 0.025…0.25 caliper from the butt of body and fins on body and inner surface. At butt between heat insulation and sleeve, said insulation has inner circular ledge abutting on sleeve.

EFFECT: higher reliability of operation due to lower heating of threaded joint between body and fins.

1 dwg

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

Cruise missile // 2534838

FIELD: aircraft engineering.

SUBSTANCE: invention relates to rocketry, particularly to cruise missile with launch-and-accelerate stage (LNC) and midflight power plant (MFP) with supersonic ramjet (SSRJ). Cruise missile comprises MFS with head air intake with central body, SSRJ and LNC. SSRJ comprises conical diffuser, fuel manifolds, combustion stabilisers, NC jointed with conical diffuser, supersonic nozzle at NC outlet and control system. LNC with jet engine is arranged in NC of missile engine and in air channel to be uncoupled and ejected. Fuel manifolds and combustion stabilisers of MFP can fold and are secured at conical diffuser arranged at NC inlet. Nozzle case is composed of two coupled cylindrical and ogival shells. Note here that nozzle critical section is adjusted with help of nozzle hydraulic drive.

EFFECT: decreased weight and sizes of cruise missile, higher in-flight thrust.

5 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: weapons and ammunition.

SUBSTANCE: device of forming time of opening or detachment of the head part of rocket projectile comprises an actuating mechanism of opening or detachment of the head part and the receiver of GLONASS signals or other satellite navigation system with the ability of prelaunch setting in it of coordinates of the point of detachment or opening of the head part. The receiver of GLONASS signals or other satellite navigation systems is equipped with a subtraction unit of the current coordinates of the projectile from the set coordinates of the point of detachment or opening of the head part. The output of the subtraction unit of comprises the difference signal generator with the threshold element, electrically connected to the actuating mechanism of detachment. Condition of triggering of the threshold element is determined by the formula |Δx|≤ε, where |Δx| is the module of magnitude of the difference signal; ε is the limiting error of determining the current coordinates of the projectile by the receiver of GLONASS signals or other satellite navigation systems.

EFFECT: increased efficiency of firing with rocket projectiles.

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to the field of projectile weapons, in particular to the steering gear and the method of controlling the flight of the controlled projectile. The steering gear of the controlled projectile comprises a housing, a base, a filter, an air intake device, solenoid valves and pneumatic cylinders of steering machines. The base separates the cavities of the projectile to the high pressure cavity and the low pressure cavity. The pneumatic cylinders are mounted with the ends of the rods to the housing of the projectile mutually perpendicular in planes of stabilization in the low pressure cavity. The housings of the pneumatic cylinders have the possibility to make a reciprocating motion on rods. The solenoid valves, which are mounted in the air intake device behind the filter, are of permanently open type. The solenoid valves, mounted on rods of the pneumatic cylinders, are of permanently closed type, and are connected pairwise by pipelines. The method of controlling the flight of the controlled projectile consists in the change of the position of the centre of mass of the projectile by means of moving movable loads placed in two mutually perpendicular planes inside the housing of the projectile.

EFFECT: simplification of design of the controlled projectile is achieved.

3 cl, 3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: guided artillery round comprises body, automatic control unit, steering unit, unit of braking devices, warhead, combined exploder, stabiliser and base gas generator. ACU comprises robot pilot, set of inertial transducers, GPS receiver, passive radar homing head with broadband receiver and receiver frequency tuner module. Unit of braking devices changes projectile drag at final section of trajectory. Said passive radar homing head responds to radio signal emitted by target and can operated in intermittent mode of target signal receipt.

EFFECT: higher accuracy of hitting.

1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to rocket engineering, namely to stabilisation devices of rocket movement. The stabilisation device of the rocket movement during underwater start comprises pivotally mounted with the housing of the start-booster stage, the grid stabilisers, the bracket, the two-position actuator of opening, folding and locking (TPAOFL) electrical connectors for connection to the control system of the rocket. The TPAOFL comprises in the single housing the force and two damping cylinders, the power rod and piston, two damping rods and pistons. In gas cavities of the power cylinder the mechanisms of locking, unlocking of the power rod with balls are integrated, and mechanisms of equalising pressure with the grooves. The grid stabilisers are fixed in the folded position on the housing of the start-booster stage of the rocket, after leaving the transport and launch container by the control system signals the stabilisers are unlocked, opened and locked in the open position, after leaving the water the grid stabilisers are folded and locked in the folded position simultaneously with the opening and locking the cruise rudders with constructive means, after reaching the desired velocity the start-booster stage is separated with folded grid stabilisers from the rocket.

EFFECT: invention enables to increase stability of the rocket movement at the start from the moving vehicle.

2 cl, 5 dwg

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