Supersonic projectile

FIELD: weapons and ammunition.

SUBSTANCE: supersonic projectile consists of a head and a missile parts with cylindrical thickenings on the outer surface of the housing. The cylindrical thickenings are made with diameter d1=(0.98-1) d with a relative elongation of and are located at a relative distance from each other . The transition at thickenings from a smaller diameter to a larger one is carried out at an angle of not more than 25°, and a decrease in diameter d2 behind the thickenings is (0.3-1.5) % of d1. The first cylindrical thickening is located at the head part in the area of the junction with the missile part and at least two cylindrical thickenings have a diameter equal to the diameter of the midsection - d.

EFFECT: invention allows to create a supersonic projectile of multiple-launch system with increased firing range, dispersion and accuracy by reducing resistance characteristics during body flow with incoming air and ensuring alignment of the projectile from the guiding fighting vehicle during loading and starting.

1 dwg

 



 

Same patents:

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. Assy for separation of aircraft compartments comprises main compartment, sliding compartment, housing, exploder, bolt, separating retainer and shifting piston supporting the latter. Housing is secured at said main compartment. Bolt joints said main and sliding compartments. Separating retainer is composed by retainer ring spilt to three independent segments. Groove is made on aforesaid bolt for segments to be fitted therein. Said segments are retained in bolt groove displaced by piston Piston is arranged in said housing. Said bolt is retained by segments in said housing via sliding piston.

EFFECT: simplified design of proposed assy.

6 cl, 3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: two-stage antitank guided missile consists of first stage and hitting stage. First stage comprises engine, airfoils, interference source with power supply and uncoupler. First stage can jam the active protection system sensors and makes the stage to carry hitting stage to target area. Hitting stage comprises computer, set of inertial mechanisms, satellite navigation system signals receiver, steering unit, accelerating engine with movable nozzles, movable airfoils, war head, fuse, homing head with two homing channels, that is, active radar channel and semi-active laser channel, antenna section and receivers arranged conformally at hitting stage tail and transceiver. Hitting stage after target capture gets uncoupled from first stage to hit the tank at turret top part.

EFFECT: efficient antitank missile.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: proposed missile comprises axially symmetric body with oxidiser and propellant tanks and liquid-propellant rocket with combustion chamber and turbo pump unit, and four radial control nozzles. Combustion two-zone chamber comprises cylindrical part with oxidiser atomisers, nozzle with propellant main manifold, extra propellant atomisers, annular and extra manifolds. Turbo pump unit comprises turbine, oxidiser and propellant pumps, extra propellant pump, top and bottom ball hinges. Ball hinge with inner ball and outer spherical shell is arranged between combustion chamber and oxidiser pump. Said four control nozzles are communicated with combustion chamber first zone via pipes.

EFFECT: higher reliability of launching and specific characteristics of liquid-propellant engine.

6 cl, 7 dwg

FIELD: weapons and ammunition.

SUBSTANCE: in compliance with first version, rocket comprises liquid-propellant engine, tanks and pulsating generator. The latter is composed of closed chamber operating on rocket fuel components. Its inlets are communicated with fuel tanks fluid sections via check valves and its outlets are communicated with fuel tank gas sections. Gas generator or tanks are equipped with safety valves. In compliance with another version, fuel components are fed in gas generator by two articulated displacement pumps. In compliance with the other version, rocket comprises gas generator charge communicated via check valves with tank gas sections. In compliance with one more version, fuel tanks are provided with separation bellow or elastic bag secured to tank outlet or opposite it. In other version, every fuel tank has separation web with bypass acceleration valve opening in direction opposite the thrust vector. In one more version, rocket incorporates two vibratory or rotary displacement pumps to feed fuel in oxidiser tank and oxidiser into fuel tank, respectively.

EFFECT: decreased weight and dimensions.

20 cl

FIELD: weapons and ammunition.

SUBSTANCE: atmospheric rocket comprises tanks, a liquid rocket engine (liquid-propellant engine) and impellers. The impellers are kinematically connected to the fuel pumps. The impellers are mounted with the ability of rotation under the influence of air flow. In another version of the rocket, the impellers are mounted on the edge of the liquid-propellant engine nozzle with the ability of rotation under the action of gases flowing from the nozzle and under the influence of air flow.

EFFECT: reduced cost of rocket.

12 cl, 2 dwg

FIELD: weapons and ammunition.

SUBSTANCE: anti-helicopter and anti-stealth missile comprises a motor, a warhead, a homing system, a block or a programme of a processor for rotations in the specified point or after the specified time by the specified angle in the specified direction and a unit or a programme of a processor for target searching along the zigzag, spiral or combined trajectory.

EFFECT: ability to kill targets with the controlled weapons due to natural or artificial irregularities of the area relief.

3 cl, 2 dwg

Air target imitator // 2442947

FIELD: military equipment.

SUBSTANCE: invention refers to means of air target imitation, particularly to moving air target imitators. The imitator includes rocket engine with stabilizers and warhead. The warhead includes inserted tracers of forward and backward group, current sources, unit of electronic delay of tracers launching. Imitator is equipped with rotation tail unit around lengthwise axis made as flat fins. The fins are fixed radially at the engine behind the stabilizers, under an angle to lengthwise axis. The tracers of backward group are fixed at the engine and oriented with their operation faces backwards. Tracers of back group are launched from start station with imitator start. Tracers of forward group are located in the warhead, oriented with their operating faces forward. Tracers of the forward group are launched with delay unit from on-board power source. Tracers of each group are located symmetrically to lengthwise axis of air target imitator.

EFFECT: extension of possibilities of air target imitator.

4 cl, 1 dwg

FIELD: weapons and ammunition.

SUBSTANCE: double-stage coned-bore controlled missile comprises cruise stage of lower calibre and separated engine made of composite material with powder charge and cylindrical frame with coned-ogive front part. Coned-ogive part of engine body is arranged with length of (1.6…6.5) of calibre, and thickness of its wall is arranged as increasing in direction from cylindrical part of body to front end of engine. Charge is fixed to body of engine along the whole side surface, and engine and cruise stage are arranged with weight ratio of 2.2…3.9 with ratio of charge weight to common weight of missile of 0.3…0.62.

EFFECT: reduced aerodynamic resistance and increased reliability of missile due to establishment of optimal ratio of weight characteristics of missile stages, geometric parametres of coned-ogive front part of engine.

2 dwg

FIELD: defense technology.

SUBSTANCE: multistaged air-defense missile comprises at least two stages with at least one liquid propellant rocket engine at lower stage (LPRE). Fuel and oxidant tanks are connected to LPRE. Controlled aerodynamic rudders and wings are installed on upper stage and at least one solid propellant rocket engine. Solid propellant boosters with solid propellant rocket engines are connected to lower stage parallel to its axis. Each LPRE comprises combustion chamber with system of regenerative cooling, turbopump set and gas generator. Turbopump set comprises oxidant and fuel pumps and main and startup turbine. Gas generator is installed coaxially with turbopump set. Outlet of fuel pump is connected to inlet of regenerative cooling system and to inlet of gas generator, outlet of oxidant pump is connected to the second inlet of gas generator, outlets of gas generator and system of regenerative cooling are connected to cylindrical portion of combustion chamber.

EFFECT: improved technical characteristics of rocket in wide range of flight modes at various height.

2 dwg

Air-defense missile // 2380650

FIELD: defense technology.

SUBSTANCE: air-defense missile comprises at least two stages with at liquid propellant rocket engines (LPRE) and fuel and oxidant tanks connected to them. Controlled aerodynamic rudders and wings are installed on upper stage of missile. Solid propellant boosters with solid propellant rocket engines are connected to lower stage parallel to its axis. Each LPRE comprises combustion chamber with system of regenerative cooling, turbopump set and gas generator. Turbopump set comprises oxidant and fuel pumps and main and startup turbine. Gas generator is installed coaxially with turbopump set. Outlet of fuel pump is connected to inlet of regenerative cooling system and to inlet of gas generator, outlet of oxidant pump is connected to the second inlet of gas generator, outlets of gas generator and system of regenerative cooling are connected to cylindrical portion of combustion chamber.

EFFECT: improved technical characteristics of rocket in wide range of flight modes at various height.

2 dwg

Aircraft complex // 2263611

FIELD: aircraft equipment.

SUBSTANCE: proposed complex includes supersonic aircraft with elongated wells on its surface whose axes are parallel to airframe axis and armament for suspension in these wells protruding beyond cross sectional area. Cross sectional areas of wells may have the following forms: rectangle, square, trapezium, triangle, equilateral triangle, rhomb or curvilinear triangle. Cross sections of armament have respective form and are so located that interference of shock waves in space between armament and aircraft planes may be eliminated.

EFFECT: reduction of aerodynamic drag.

7 cl, 15 dwg

Progectile // 2309376

FIELD: armament, in particular, projectiles and missiles.

SUBSTANCE: the projectile has a jet engine, blades made in the form of arches whose bases are fastened in hinge joints located in eyes. The hinge joint axles of each blade are aligned. An the process of flight the stabilizing force of the arch blades is produced by their surfaces.

EFFECT: enhanced stiffness of the blades at a decrease of action of cross wind on the projectile.

4 dwg

FIELD: rocketry, in particular, take-off of missiles from air missile carriers.

SUBSTANCE: the winged missile is suspended from an aircraft missile launcher I a position turned by 45 deg. about the longitudinal axis, after the take-off the missile is turned to the initial flight position. The missile air-intake fairing is released by sending a pulse to it in the direction of winged missile motion up to execution of the mentioned banked turn. In the initial flight section the control of the winged missile motion is accomplished with the aid of joint operation of the missile aerodynamic control surfaces and the fin controls.

EFFECT: reduced terms and costs of perfection of production of the winged missile aircraft version, provided compact arrangement of the winged missiles on aircraft launchers without folding of the "plus-shaped" wing and fin assembly, as well as provided a reliable and safe take-off from the aircraft.

6 dwg

FIELD: aero-space engineering; aircraft missile complexes used in space.

SUBSTANCE: proposed aircraft missile complex includes heavy ballistic missiles, more than 100 tons in mass which are equipped with liquid propellant engines and are launched in air for injection of spacecraft into orbits. Aircraft missile complex includes aircraft, airframe whose fuselage carries launch vehicle for air launch, device for connection of launch vehicle with aircraft, associated systems for their functioning and ground transportation and acceleration platform equipped with engines for its acceleration. Airframe fuselage may be divided over horizontal plane. Transportation and acceleration platform is just aircraft having remaining service life adequate for ground transportation of airframe with launch vehicle, provided it was operated as part of aircraft missile complexes.

EFFECT: increased overall dimensions and launch weight of launch vehicle and consequently increased masses of spacecraft injected into orbits.

4 cl, 1 dwg

FIELD: aeronautical and space engineering; space aircraft missile complexes.

SUBSTANCE: invention deals with heavy ballistic missiles (more than 100 tons in mass) equipped with liquid-propellant engines and launched in air for injection of spacecraft into orbits. Proposed aircraft missile complex includes aircraft, launch vehicle, device for mating the launch vehicle with aircraft used as towing vehicle, systems ensuring their proper functioning and ground transportation and acceleration platform equipped with acceleration engines. Mounted additionally on launch vehicle body are fairing with wing mounted on it and nose and tail fairings. Stabilizer and vertical tail unit are mounted on tail fairing. Fairings may be separated from launch vehicle. Area of launch vehicle wing may be changed after aircraft takeoff due to availability of separately attached parts of wing which are equidimensional and symmetrical relative to longitudinal axis of wing; they are interconnected and may be separated with the aid of detonating elongated charges located over perimeter of separable parts of wing.

EFFECT: increased flight range and altitude due to reduced mass and drag of wing; increased mass of spacecraft injected into orbits.

3 cl, 1 dwg

FIELD: aeronautical and space engineering; aircraft missile complexes with heavy ballistic missiles (more than 100 tons in mass) equipped with liquid-propellant engines and launched in air for injection of spacecraft into orbits.

SUBSTANCE: aircraft missile complex includes aircraft, launch vehicle, device for mating the launch vehicle with aircraft used as towing vehicles, systems ensuring their proper functioning and ground transportation and acceleration platform equipped with acceleration engines. Mounted additionally on launch vehicle body are fairing with wing mounted on it and nose and tail fairings. Tail fairing is provided with stabilizer and vertical tail unit. Fairings may be separated from launch vehicle. Area of launch vehicle wing may be changed after aircraft takeoff due to separation of parts of wings which are secured separately; they are equidimensional in pairs and are symmetrical relative to wing longitudinal axis; they are separated with the aid of detonating elongated charges located over perimeter of profiles of separable parts of wing.

EFFECT: increased flight range and altitude due to reduced mass and drag of wing; increased mass of spacecraft injected into orbits.

3 cl, 1 dwg

FIELD: aeronautical and space engineering; aircraft missile complexes with heavy missiles (more than 100 tons in mass) equipped with liquid-propellant engines and launched in air for injection of spacecraft into orbits.

SUBSTANCE: proposed aircraft missile complex includes aircraft, airframe with air-launched missile inside its fuselage, device for mating the launch vehicle with aircraft, systems ensuring their proper functioning and ground transportation and acceleration platform equipped with acceleration engines. Airframe fuselage is separable in construction; it may be separated over horizontal plane. Area of airframe wing may be changed after aircraft takeoff due to availability of separable parts of wing which are equidimensional and symmetrical in pairs relative to longitudinal axis of wing.

EFFECT: increased overall dimensions and launch weight of launch vehicle; increased masses of spacecraft injected into orbits.

3 cl, 1 dwg

FIELD: aeronautical and space engineering; rocketry.

SUBSTANCE: proposed aircraft missile complex includes aircraft (8), launch vehicle (1), transportation and acceleration platform (5) with launch vehicle mounted on it by means of mechanical linkage and members, rope-lanyard (7) and systems ensuring proper functioning of missile complex. Mounted on launch vehicle body are wing with center-wing section (6), nose fairing (3) and tail fairing (4) with stabilizing surfaces mounted on it forming controllable stabilizer and vertical tail unit (10). Rope-lanyard is connected with center-wing section and with aircraft used as towing aircraft for towing the launch vehicle to point of launch.

EFFECT: enhanced efficiency of use of aircraft and missile complex as a whole.

2 cl, 1 dwg

FIELD: rocketry and space engineering.

SUBSTANCE: invention can be used in space aircraft missile complexes, mainly with heavy ballistic missiles, mass exceeding 100 tons, furnished with liquid-propellant rocket engines and launched in air for orbit injection of spacecraft. Proposed aircraft missile complex contains aircraft, airframe with air start launch vehicle located inside fuselage, device for matching launch with aircraft playing part towing tugs, system providing their functioning and ground transportation-acceleration platform with its acceleration engines. Fuselage of airframe is made for division along horizontal plane. Transportation acceleration platform is essentially aircraft with residual service life and resource and modified for arrangement and ground transportation of airframe with launch vehicle and for operation in aircraft missile complex.

EFFECT: possibility to increase overall dimensions and takeoff weight of launch vehicle and, as result, to increase orbit injected masses of spacecraft.

4 cl, 1 dwg

FIELD: aeronautical and space engineering; space missile complexes with heavy ballistic missiles.

SUBSTANCE: proposed aircraft missile complex is mainly provided with heavy ballistic missiles, up to 100 tons in mass which are equipped with liquid-propellant engines and are launched in air for injection of spacecraft into orbits. Proposed aircraft missile complex includes aircraft, airframe whose fuselage is used for air-launching launch vehicle, device for mating the launch vehicle with aircraft, systems ensuring their functioning and ground transportation and acceleration platform equipped with accelerating engines. Airframe fuselage may be divided over horizontal plane.

EFFECT: increased overall dimensions and launch weight of launch vehicle and consequently masses of spacecraft injected into orbits.

3 cl, 1 dwg

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