Guided projectile

FIELD: weapons.

SUBSTANCE: invention relates to the field of weapons, in particular to the field of small-sized guided projectiles, mainly with subsonic and transonic flight speeds, and can be used in constructions with various aerodynamic schemes. Guided projectile, designed in the aerodynamic scheme "duck", contains a cylindrical body and a head part with a fairing, a steering unit and aerodynamic controls. Aerodynamic controls are made of a steering wheel, the arms of which are installed on the side surface of the head part fairing, and pylons rigidly fixed to the body in front of the rudder arms in the same plane. Consoles of the steering wheel and pylons are made of flat plates with airborne chords, installed on the side surface at an angle of 5–15 degrees to the longitudinal axis of the missile. Steering wheel is made with a rotational spanwise angle along the leading edge – 0 degrees from the root chord to 0.30–0.40 of the swing of the steering wheel console, then with a sweep angle of 55–65 degrees to the full swing of the steering wheel console. Swing of the pylon console is made with a ratio of 0.30–0.40 swing of the steering wheel console. Pylon side chord is made with a ratio of 0.40–0.50 to the length of the side chord of the steering wheel, and the gap between the leading edge of the steering wheel and the rear side of the pylon is 0.05–0.15 of the length of the side chord of the steering wheel console.

EFFECT: invention increases the effectiveness of the projectile control, its dynamic and ballistic characteristics, increases the flying range of the projectiles.

1 cl, 4 dwg

 



 

Same patents:

FIELD: aircraft engineering.

SUBSTANCE: invention relates to rocketry, particularly, to rockets in transport-and-launch container to be installed at sips, submarines and ground stationary and moving launchers. Rocket (1) is arranged in transport-and-launch container (2) with cylindrical part (3) and conical part (4) of guide surface. Thrust surfaces of the rocket cruising stage front part elements are composed of an integral conical surface with tape angle that allows a maximum length of contact between rocket conical thrust surface and conical guide surface of transport-and-launch container front part.

EFFECT: reduced loads and in-flight drag, increased rocket midsection.

2 dwg

FIELD: aviation.

SUBSTANCE: in case of the testing method of airborne vehicles (AV) before starting the AV, coordinates of the antenna position of the ground reception centre (GRC) are calculated and entered into the ground equipment of telemetry recording system. Current coordinates are determined during the AV flight. They are included into information packets of telemetry data, that are read off from the functional units of the AV and converted into binary code. Generated data bursts are emitted in the direction of the ground reception centre (GRC). Reception and processing of data transmitted into the GRC in the real time mode are carried out. Direction toward the AV with which the axis of the direction pattern of GRC antenna is combined, is calculated according to the obtained coordinates of AV. Testing system of the AV with telemetry system of the main parameter registration comprises the following units installed on the AV: functional units, control equipment, on-board telemetry transmitting module (OTTM), satellite navigation equipment. Ground equipment of telemetry registration system comprises the GRC with antenna, control panel, computer, guidance drive, connected in a certain way.

EFFECT: stable reception of telemetry data from the board of the airborne vehicle.

2 cl, 1 dwg

Missile // 2548957

FIELD: weapons and ammunition.

SUBSTANCE: missile includes case in the form of connected separable joint units with pyrotechnical burst connection of sealed head compartment with a sequence of homing head, inertial control system, ammunition, active thermal protection system and independent fluid or paste fuel propeller containing fuel with oxidiser and liquid-propellant rocket engine set with longitudinal nozzle, four liquid-propellant rocket engines with transverse nozzles and four liquid-propellant rocket engines generating head compartment torque, and propeller compartment with aerodynamic rudders, rudder drives, double-pulse solid fuel propeller aggregate, second pulse timing unit, correction unit.

EFFECT: efficient striking of high-altitude targets.

3 cl, 4 dwg

FIELD: aircraft engineering.

SUBSTANCE: aircraft (AC) is placed in the Launcher, or in a Launcher transport and starting barrel, or partially in Launcher TSB with an external arrangement of the jet nozzles, or a transport and starting container (TSC), or TSC of Shaft Launcher, the starting propulsion system (SPS) is fixed in AC front part, AC is partially moved forward, SPS is started, the traction is formed by two jet nozzles located on a lateral surface of SDU at an angle to a longitudinal axis of AC, the front part of LA is protected during acceleration by the fairing fixed on SPS, SPS is separated by means of draft force.

EFFECT: invention allows to decrease the weight of an aircraft structure, launcher start load and simplify a launcher design.

7 cl, 4 dwg

Controlled missile // 2546740

FIELD: weapons and ammunition.

SUBSTANCE: controlled missile includes a body, aerodynamic wings and rudders, a wiring duct arranged along the body in the vee of rudders and wings. Spread of the wings, in the vee of which the wiring duct is arranged, is less than spread of the rest wings.

EFFECT: increasing target guidance accuracy.

1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: two-stage rolling cruise missile (CM) with five degrees of freedom of spatial movement includes a housing stabilised as to the sixth degree of freedom by rotation in the form of a rotation figure with wings, rudders and an active aerodynamic nozzle, a single-duct control system, a steering gear, a detachable launching accelerator with an axial turbo-jet engine with a gas-dynamic nozzle, a cruise stage with an n duct system of formation of lift capacity in a rotation mode and a small-size disposable turbo-jet engine with a folded air intake, and a self-guidance head.

EFFECT: simpler control and stabilisation of a cruise missile, lower weight and dimensions of the cruise missile.

2 dwg

Guided missile // 2542692

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.

2 dwg

Guided missile // 2542679

FIELD: weapons and ammunition.

SUBSTANCE: guided missile (GM) comprises compartments of cylindrical thin-walled shells, a main propulsion system, an armament section, connected in series telescopically by radial screws with nuts and conical heads. The conical head has a cylindrical surface which interacts with the cylindrical opening of one compartment, and a conical part interacting with the conical opening of the second compartment. The axis of the conical opening of the first compartment is located eccentrically from the axis of the cylindrical opening of the second compartment.

EFFECT: invention enables to improve the efficiency of the guided missile.

3 cl, 4 dwg

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

Guided missile // 2540903

FIELD: weapons and ammunition.

SUBSTANCE: this missile comprises warhead screwed to another compartment and secured thereto by fastener composed by rectangular-section ring with arched hooks with inner cylindrical surface and ledges at end surface. End of connectable compartment comprises arched ledges with OD, sizes and quantity equal to those of fasteners. Arrangement of said hooks in angular direction complies with arrangement of ledges with threaded holes for fastening screws of warhead.

EFFECT: decreased length and weight, higher reliability and combat efficiency.

3 cl, 4 dwg

FIELD: transport.

SUBSTANCE: invention relates to aircraft and rocket engineering. Folding steering surface of airborne hitting means comprises the base composed of two symmetric halves secured by fasteners, folding support and tension spring fitted in said base.

EFFECT: higher reliability of unfolding.

4 dwg

FIELD: transport.

SUBSTANCE: invention relates to supersonic rocket airfoil control devices. Proposed unit consists of the shaft fitted in the case to turn therein, airfoil rigidly fitted on said shaft, steering unit, rollers and separators rigidly interconnected and fitted in rocket body. Steering unit rod is articulated with lever. Circular cavity composed by groove of the shaft and conical rolling paths on said rings house rollers arranged so that every next roller is perpendicular to previous one. Separator is arranged between said rollers.

EFFECT: operation at notable aerodynamic loads.

2 dwg

Controlled missile // 2539709

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: transport.

SUBSTANCE: invention relates to aircraft structural components and airfoils, particularly, to airfoils design for compact aircraft stabilisation in the plane of trajectory and for control in ballistic flight. Compact aircraft comprises fuselage, airfoils and tail plane. Airfoils are mounted at fuselage at the center of gravity to turn about aircraft lengthwise axis. Said airfoils represent two wings secured to turn assembly and arranged in symmetry about aircraft lengthwise axis in different planes.

EFFECT: higher aircraft efficiency, use of airfoils for flight control.

3 dwg

FIELD: rocketry, in particular, device for stabilization of aircraft winged missiles at the initial stage of independent flight.

SUBSTANCE: the body of the stabilizing device is made in the form of a convex cover sealing the nozzle of the missile solid-propellant acceleration engine, and the controls-in the form of four pairs of kinematically linked with one another aerodynamic control surfaces and jet vanes of the solid-propellant acceleration engine, each of them is positioned in the plane of installation of the aerodynamic control surface of the missile sustainer stage and linked with the drive of the mentioned control surface by means of control rods. The control mechanism of the stabilizing device control surfaces is made for separation of the links controlling the position of the device aerodynamic control surface, as well as for separation with the control rods from the sustainer stage control surface drive.

EFFECT: simplified structure and reduced overall dimensions of the stabilizing device, enhanced aerodynamic characteristics of the winged missile.

7 dwg

The invention relates to the field of rocketry

The invention relates to techniques for aircraft

Unit steering // 2154593
The invention relates to the field of unmanned aerial vehicles and can be used in the development of actuators aerodynamic rudders

The invention relates to rocket and space technology

FIELD: rocketry, in particular, device for stabilization of aircraft winged missiles at the initial stage of independent flight.

SUBSTANCE: the body of the stabilizing device is made in the form of a convex cover sealing the nozzle of the missile solid-propellant acceleration engine, and the controls-in the form of four pairs of kinematically linked with one another aerodynamic control surfaces and jet vanes of the solid-propellant acceleration engine, each of them is positioned in the plane of installation of the aerodynamic control surface of the missile sustainer stage and linked with the drive of the mentioned control surface by means of control rods. The control mechanism of the stabilizing device control surfaces is made for separation of the links controlling the position of the device aerodynamic control surface, as well as for separation with the control rods from the sustainer stage control surface drive.

EFFECT: simplified structure and reduced overall dimensions of the stabilizing device, enhanced aerodynamic characteristics of the winged missile.

7 dwg

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