Supersonic projectile

FIELD: weapons and ammunition.

SUBSTANCE: in a supersonic projectile the rudders are placed on the pointed nose of the hull at a distance from the front end of the projectile selected within the values calculated by the formula: . Each of them is equipped with an aerodynamic fairing made in the form of a rotation body, protruding beyond the front edge of the rudder by the value (0.10-0.25)ar. The longitudinal axis of the fairing is displaced from the root chord by a distance (0.15-0.35)br. The arc-shaped blades of the stabiliser are shifted from the bottom cross section of the jet engine towards the nose of the hull by (0.3…0.6) d and are fixed on the axes parallel to the longitudinal axis of the projectile shell. The arc-shaped blades of the stabiliser are oriented by convex surfaces in the clockwise direction in a rear view, where Lp is the distance from the nose to the middle of the root chord of the rudders; Lm.c. is the distance from the nose of the projectile to its mass center after fuel burnup of the jet engine; L is the length of the projectile; Lstab is the distance from the nose of the projectile to the middle of the root chord of the stabiliser blades; is the relative area of the projections of 2 stabiliser blades; Sstab is the area of the projections of 2 stabiliser blades; is the area of the midship section of the projectile; d is the calibre of the projectile; k=(8-16)[1+0.1(n-3)] is the coefficient which takes into account the number of the stabiliser blades; nbl=3-6 is number of stabiliser blades; is the relative area of 2 rudders; Sp is the area of the projections of 2 opposite rudders; br is swing of one rudder; ar is the length of the root chord of the rudder.

EFFECT: invention allows to create a supersonic projectile of multiple-launch system with increased firing range due to the rational selection of the ratios of the airframe geometric parameters and to ensure maximum aerodynamic quality, increased combat effectiveness due to reduced dispersion of aeroballistic characteristics, increased accuracy of firing.

1 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: aircraft engineering.

SUBSTANCE: proposed drove folding rudder consists of the root part, folding part, spring-loaded retainers and folding pin with spring. Rudder folding part comprises support with bore made therein. Frame end inner surface is tapered while support ends are provided with guide chamfers.

EFFECT: optimised sizes of aerodynamic rudder as-folded, higher reliability.

4 cl, 7 dwg

Projectile fin // 2512041

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to military equipment, particularly to guided projectiles. Proposed fin includes a shell, vanes mounted on pins in the shell, and locking device. Locking device includes case, front cover, inertial load with a through orifice where a central screw is installed and fixated by a nut at the cover side, and recoil springs placed in blind holes of inertial load as thrusts between the inertial load and central screw cap. At the front end of central screw cap, an annular pad out of easily deformable material is installed with cylindrical grooves on its side surface, where recoil springs propped against the front end of central screw cap are placed. External diameter value of the nut prevents cap deformation under a force applied onto the nut by inertial impact on central screw cap, and nut height for which supporting area of the nut is calculated so that a force applied via the nut to the cap under impact does not exceed cap material fluidity.

EFFECT: enhanced reliability of fin functioning under intense barrel stress.

3 dwg

FIELD: aircraft engineering.

SUBSTANCE: invention can be used in descent airships. Proposed device comprises two pairs of similar aerodynamic turning elements arranged at aircraft tail in symmetry in horizontal and vertical planes and their drives. Mirror planes of aerodynamic elements are shifted relative to airship lengthwise axis. Aerodynamic elements are composed of a cylinder part produced by cutting parts extending beyond airship side surfaces. Rotational drives of aerodynamic elements are located at one plane perpendicular to airship lengthwise plane.

EFFECT: higher operating performances, better maneuverability.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: compact controlled ammunition contains a casing, steering surfaces and useful load. The ammunition is made in accordance with the normal aerodynamic arrangement. The casing of the ammunition is made as narrowing in the tail part. Steering surfaces are installed in the narrow part of the casing and do not protrude beyond the limits of the cylindrical surface, the guide of which matches the perimetre of the casing midship section, and generatrices are parallel to the longitudinal axis of the body.

EFFECT: optimised weight and dimension characteristics of the ammunition.

3 cl, 3 dwg

Rocket // 2412087

FIELD: transport.

SUBSTANCE: invention relates to space engineering and is intended for space flights. Proposed rocket is airframe and fin. Fins made in the form of elongated ellipses are arranged to be extended and moves apart.

EFFECT: rocket stabilisation.

2 dwg

Rocket // 2407679

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering. Proposed rocket comprises tail unit consisting of one fixed and two triangular moving vanes.

EFFECT: better stability in starting from vertical position.

2 dwg

Rocket // 2407664

FIELD: transport.

SUBSTANCE: invention relates to aerospace engineering. Proposed rocket comprises tail unit with hollow balls arranged on its ends.

EFFECT: simplified travel of rocket over planet surface.

2 dwg

Projectile fin // 2397434

FIELD: weapons and ammunition.

SUBSTANCE: proposed fin comprises casing, vanes with slots fitted on casing pins and locking mechanism. The latter comprises case, stepped bob-weight, cylindrical hook arranged between case and weight, split ring, return springs fitted in blunt holes of said bob-weight, and front cover. Bob-weight has central through bore accommodating central screw locked by nut fitted on front cover side. Return springs thrust against central screw head front face, while nut with OD equal to bob-weight OD is screwed on bob-weight front face. Annular clearance accommodating split ring is arranged between nut rear face and bob-weight. Cylindrical hook has open inner recess surrounding split ring on the side of front face. Cylindrical hook is fitted as far as it can go into locking mechanism casing. Hook rear end face extends beyond central screw.

EFFECT: higher reliability of fin operation.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: projectile stabiliser comprises body, vanes with cutouts hinged in said body in symmetry about projectile lengthwise axis, vanes opening device representing a central compression spring arranged as-compressed between vanes and body in aforesaid cutouts made on lower edges of all vanes. Holes are made in said body, above vanes hinges and perpendicular to vane lateral surface, the number corresponding to that of vanes. Said holes accommodate spring-loaded cylindrical retainers. Outer surfaces of said retainers that are directed towards lateral surfaces of the vanes have tapered surface. Every vane has appropriate tapered holes to come in contact with tapered surfaces of retainers when vanes are opened.

EFFECT: simultaneous opening and rigid locking of vanes.

2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: aerodynamical stabiliser consists of fairing with fixing slots and blades that fold on axes. Fairing shell in zone of fixing slots location is arranged with local bulges equal to 0.8-1.2 of blade thickness in root section. Bulges make it possible to provide for contact of blade eyes with fairing along surface equal to 0.25-0.35 of blade root section area. Thickness of end part of blade in millimetres makes millimetres, where Mmax is maximum flight Mach number; is frequency of own bending vibration of blade at maximum aerodynamical heating, Hz.

EFFECT: increased distance and accuracy of shooting due to elimination of blades and fixing slots shape variations in fairing as a result of temperature deformations and absence of vibrations and provision of low amplitude of blade bending vibration.

3 dwg

FIELD: rocketry, in particular, means for stabilization of small-sized rockets.

SUBSTANCE: the stabilizing moment is produced by continuously braking the incoming air flow by propulsive jets. The broken flow acts on the rocket side surface in the zone shifted relative to its center of mass. The action of the reactive forces on the body in cross section is mutually balanced. The side nozzles are positioned in the aft part of the rocket pairwise opposite each other with an inclination to its side surface towards the rear end face through an angle exceeding the angle of attack of the rocket.

EFFECT: simplified angular stabilization of the rocket in flight in dense atmosphere layers, enhanced its tactical characteristics and reduced cost.

2 cl, 2 dwg

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