Rocket in transport-and-launch container

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

 

The invention relates to the field of rocketry, specifically the missiles in transport-launch containers (TLC), placed on ships, submarines and ground-based stationary and mobile launchers (PU).

Widely known for PU launch missiles. During the launch Tomahawk from torpedo tubes of submarines (Rodionov B. I. Novichkov N. N. "Cruise missiles in naval battle", Voenizdat, 1987, pp. 16-18) TMV is used as a guide apparatus launchers for missile launch.

Also known PU for surface ships (Anisimov, V. D. "a New generation of shipboard launchers". Foreign military review, No. 9, 1999, pp. 45-48). Tbms mortar launch consists of two cylindrical shells nested one inside another, with the inner one is used to store and launch rockets.

Known TPK cruise missiles "Tomahawk", designed to host and launch missiles from vertical PU submarine (Shipbuilding abroad No. 7, 1986, pp. 48-51. "Rocket launchers vertical launch KR "Tomahawk" on the submarine "Los Angeles"). OPC is made in the form of a steel cylinder. The inner cylindrical surface of TMV is directing for the support platforms of the rocket at the start.

Known modular multi-ship PU vertical start (RU 2213925, EN 2393409), in which the inner surface of T�To be made in the form of a cylindrical shell.

The famous "Cruise missile in transport-launch container" according to the patent RU 2215981 in which along the surface of the fuselage mounted support pads in contact with the inner surface of TMV.

During the launch with a number of reference zones as they are released from TPK inner surface is formed as a cylindrical shell, resets reactions in these reference zones, causing increased dynamic loading subsequent pylons and missiles in General.

The closest combination of features according to the claimed invention is "a Launcher for missiles mnogopolyusnogo bearing" according to the patent RU 2494334, which is selected as the closest analogue prototype. This PU contains a TPK with a cylindrical guide surface and a socket in the front part at which the slide support elements of the rocket at the start. The disadvantage of this design is the repeated shock loading of the rocket at the similarity of each reference zone of the rocket with the guide surface of TMV.

The aim of the invention is to reduce the load on the rocket and TPK at the start, reducing the aerodynamic resistance of the primary stage of the rocket in flight and increase the midsection of the rocket within the constraints of a given internal diameter TBM.

This object is achieved in that at the start of cancer�s from TPK, the front part of the guide surface of which is made in the form of a socket, the support elements of the front part of the primary stage of the rocket is made in the form of a single conical surface with a front diameter equal to the inner diameter of the corresponding section of TMV in the initial position of the rocket, and the angle of the cone providing the maximum length of contact of the conical bearing surface missiles with a conical guide surface of the socket TPK in the process of start. The required value of the cone angle of the bearing surface of the rocket is determined by calculation, taking into account the elastic characteristics of missiles and tbms, gaps in the support zones of the rocket, located in the TPC, for the conditions of the external loading of the rocket at the start and longitudinal parameters of the movement of missiles in TPK, causing the maximum load on the rocket at launch.

The absence of protruding elements starting supports on the front of the primary steps would reduce its aerodynamic drag in flight.

Fig.1 shows a General view of the location of the missiles in TPK in the initial position, i.e. before the movement of the rocket. Fig.2 - position missiles in TPK at the moment of maximum contact length of the conical bearing surface missiles conical portion of the guide surface of TMV.

Missile (1) is located in a TPK (2) having a cylindrical body (3) and conical (4) �Asti guide surface. The support surface of the front part of the primary stage (5) missiles made in the form of a short cylindrical section (6), rolling in the cone (7). The device operates as follows: at the initial stage of the movement of missiles in TPK with a cylindrical part (3) of the guide surface of TMV sustainer stage of the rocket will contact only the cylindrical section (6) of the bearing surface. At the transition of the cylindrical portion (6) of the bearing surface missiles with a cylindrical guide surface (3) tapered (4) occurs by gradual withdrawal of the guide surface (4) from the bearing surface (6) of the rocket. Thus there is a gradual withdrawal reactions in the bearing surface (6) and the increase of the reaction in the support surface (7) missiles. However, due to the conical shape of the bearing surface (7) missiles a similar effect occurs care the contacting portion of the bearing surface (7) of the guide surface (3) TIC, resulting in decrease of the maximum response in the support surface (7). In further longitudinal motion of the rocket in the TPC due to the elastic properties of the rocket and the presence of gaps between the supports of the missile and track surface TPK occurs contact support surface (7) missiles with a tapered section of the guide surface (4) of TMV. This realizes the double effect of nursing support surface (7) missiles �t of the guide surface (4) of TBM reducing the growth reaction in the support surface (7) missiles. At the same time increases the contact area of the bearing surface (7) missiles, which leads to lower stresses in the contact zone of this surface. Subsequent longitudinal movement of the missiles in TPK causes the loading of the next support zone (8) missiles, which leads to a gradual decrease in the reaction at the support surface (7) to zero. Such is the nature of the contact support surface (7) missiles will reduce the maximum response in that the support 20÷30%, because of the work of the external load will be spent on further rotation of the missile relative to TPK. While the load on the support surface (7) is distributed over a larger area than in concentrated supporting zones. The presence of the socket in the front of the TBM will also reduce the maximum load in the mount (8) and a support (9) located at the starting stage of the rocket, and the rocket in General at the start.

In other cases, the operation of missiles in TPK - transportation, external impact force on the launcher - loading missiles from TPK will occur in the zone of the cylindrical portion (6) of the bearing surface, which is supported by the mounting ring for the perception of the load.

In the tandem division of the stages of the rocket bearing surface 6 and (7) will be �to ahadiths at the primary stage (5), that will reduce its aerodynamic drag in flight because of the lack of protruding elements starting speed, and will also increase the internal volume of the primary stage for the possible placement of additional equipment and fuel.

The rocket in the transport and launch container (TPK) with a conical guide surface of the front of having a number of starting zones supports, characterized in that the supporting elements of the front part of the primary stage of the rocket is made in the form of a single conical surface with a front diameter equal to the inner diameter of the corresponding section of TMV in the initial position of the rocket, and the angle of the cone providing the maximum length of contact of the conical bearing surface missiles with a conical guide surface of the front of the TBM in the process of start.



 

Same patents:

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: weapons and ammunition.

SUBSTANCE: invention relates to missile engineering and is intended to be used in rockets launched from a launching transporting container. The design of the retention mechanism assembly represents a bracket, on which a limit stop, a turnbuckle and a grip arranged on the rotation axis in the front part of the retention mechanism bracket are mounted. The grip design has an attachment axis of the turnbuckle serving as a fastening element of the grip design with a flag, by means of which the rear face of the rocket is held down to the limit stop of the retention mechanism. The flag design has a rotation axis fixed on the bracket. In the zone of the rotation axis in the flag there is a T-slot for fixation of the turnbuckle; on the opposite side there is a platform with holes for attachment of a fastening plate. The fastening plate attaches flags of two assemblies of the retention mechanism.

EFFECT: achievement of reliable fixation at transportation, and minimum disturbances at start-up at the moment of the plate burnout.

4 cl, 4 dwg

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to defence equipment, particularly, to target lock-on and portable AA rocket launching with the help of optical self-guidance head (OGH). This device comprises gyro coordinator speedup unit, OGH signal detector, operator control signal receiver, operator warning unit, analysis time relay and rocket start program device. Besides, it incorporates input signal vector narrow-band reconfigurable meter, timing system, scanning generator, directed deflection signal generator to feed signals to OGH tracking circuit when rocket is located at the launcher. OGH tracking over radiation source is evaluated and said generators are cut off after making the decision on rocket launch.

EFFECT: reliable launching, simplified operation of operator.

7 dwg

FIELD: transport.

SUBSTANCE: this launcher comprises bed with cells to installation of container-launchers to be secured at ship deck. Every said cell is provided with protective cover with opening drive. Said cover is fitted at the base via sealing backing of viscoelastic material secured over cover edges. Opening drive comprises leverage including rocker to drive said cover at opening-closing via first and second dead points. Rocker is articulated with bell crank first arm. Second arm of said bell crank is coupled with the link the other end of which make a hinge with thrust element. The latter is plug-connected via screw element extending through protective cover to adjust screw element vertical position. Said link is composed of split-jointed parts to be disengaged by the action of launched object nose part at emergent ejection of the latter from container-launcher with said cover at closed position. Leverage can half-open the protective as-closed cover when under-cover pressure exceeds the preset value. Then, it can automatically return it to initial position at pressure equalized with barometric pressure.

EFFECT: higher reliability and safety.

10 cl, 6 dwg

FIELD: transport.

SUBSTANCE: invention relates to systems for payload delivery to upper air and higher. Proposed system (1) comprises tubular rocket launching cart (2) with friction drives of cable-rope path (26) displacing below two-pin hinge (63) secured to ground and lifted to coaxial portable tube (124, 143) extending to three main fastened cables/ropes (27), their weight being equalized by balloons (164). Then, said cart displaces to connector station (166) retained above the ground in stratosphere by two secondary cables/rope (184) suspended from fastening frame (162) to tensioning of said balloons. Said cart is retained by end grip (196) of said cart directed in two secondary and two tertiary cables/rope (186) to be lifted by bottom lifter (198) guides by secondary cables. Said bottom lifter is retained by top lifter (168) suspended from fastening frame of tensioning balloons. Said cart hooked by lifting ring (183) guided by secondary cables/ropes upward revolves in necessary direction with release of rocket and, fact, recoilless ejection during free fall of said cart downward with engine ignition at safe distance.

EFFECT: safe, non-polluting reusable system.

50 cl, 67 dwg

FIELD: armaments and ammunition.

SUBSTANCE: control system of grenade launcher comprises laser distance gauge, processor or memory block, grenade with timer programmed for explosion after expiration of self-destruction time, and with set difference between time of self-destruction and time of explosion, fuse control transistor.

EFFECT: invention increases accuracy of grenade firing.

Aircraft (versions) // 2547964

FIELD: aircraft engineering.

SUBSTANCE: aircraft has a hull with a pressure shell, power frames attached to a shell and the units fixed on power frames including the starting propulsion system with a jet nozzle attached to the hull by the device designed with a possibility of fastening release, and a control system. In the first version the starting propulsion system is located in a front part of the hull of the aircraft, and its jet nozzle is designed as a nozzle unit comprising the jet nozzles located on its lateral surface with an inclination of a longitudinal axis of each jet nozzle at an angle 10-30° to a longitudinal axis of the hull. The protective fairing of front part of the hull made from heat-resistant material is attached to the starting propulsion system under its jet nozzles. In the second version of the aircraft it is placed in the transport and starting barrel (TSB) fitted with the device of partial aircraft move with release of the nozzle unit from his cavity. In the third version TSB cover is designed as a protective fairing of the front part of the hull from heat-resistant material and attached to the starting propulsion system under jet nozzles of the nozzle unit.

EFFECT: higher reliability.

15 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

FIELD: weapons and ammunition.

SUBSTANCE: device for missile launch contains a running launch pipe with front and back end faces, which is connected with the carrier, a reflector hingedly fixed at a back end face of the running launch pipe and the reflector driving mechanism. The reflector is made consisting of bow-shaped trapezoid plates fixed hingedly on the launch pipe and installed with overlapping one with reference to another, forming a convex hemispherical screen. Plates are fitted with the driving mechanism.

EFFECT: improvement of reliability of operation of the device by decrease of gas-dynamic impact of discharge jet onto the reflector and the starting pipe with decrease of power impact onto the carrier during the missile launch.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: device for missile launch contains a running launch pipe with front and back end faces, which is connected with the carrier, a gas reflector located at a back end face of the running launch pipe and connected to it. The gas reflector is designed as a circular solid fuel charge with the ignition source located in the circular housing from outer side of the running launch pipe. In the bottom part of the circular housing from the back end face of the running launch pipe a circular row of exhaust outlets is made.

EFFECT: improvement of reliability of work by decrease of power impact of a shock wave on the carrier during start of missile from the launch pipe due to interaction of shock wave with powder flows of gas flowing from the circular housing.

3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: fireproof cover of a multi-barrel launching unit (LU) from pressed fibre glass with flat layers, which is fixed on the front end face of a launching pipe by means of a locking device, includes an outer surface with conical and radial surfaces, a fire-resistant coating with an epoxy composition from epoxy resin, Aerosil glass powder, technical carbon, a hardening agent - polyethylenepolyamine, asbestos fibres cut to pieces and with partial saturation of edges of cut layers of fibre glass depending on saturation depth, thickness of one layer and epoxy composition.

EFFECT: invention allows improving reliability of a fireproof cover.

4 cl, 3 dwg

FIELD: weapons and ammunition.

SUBSTANCE: method of missile takeoff from the transporter-launcher containers (TLC) consists in inflation with the gas which does not support combustion of sub-cap volume of TLC with simultaneous ingress of gas through the obturator in the bottom volume, after which the inflation is switched off when achievement of the desired pressure in the sub-cap container volume, followed by inflation of the bottom volume of the container with gases from powder pressure accumulator (PPA). The device for implementation of missile takeoff from the TLC comprises an obturator, a PPA, a high-pressure cylinder with an on-off valve connected to the sub-cap container volume by the pipeline, a pressure indicator unit with the pipeline, the opposite end of which is located in the sub-cap container volume.

EFFECT: creation of conditions for reliable underwater missile takeoff from TLC by eliminating hydraulic, oscillating and vibrating effects on the missile housing.

2 cl, 2 dwg

FIELD: rocketry, in particular, launchers of surface ships and submarines.

SUBSTANCE: the transport-launching module has a sealed casing in the form of a cup with the front and rear covers with a seal. A rocket with a nose cone is installed inside the cup. The rocket nose cone partially projects from the cup, and in the assembled state of the transport-launching module serves at the same time as the front cover of the transport-launching module cover. The transport-launching module is provided with a changeable ring component, whose one end face is conjugate to the respective end face of the cup. Longitudinally positioned threaded members (for example, bolts) are passed through the changeable ring component, with the aid of them the changeable ring component is connected to the cup. BY means of longitudinally positioned break-off components made in the form, for example, of explosive bolts, as well as of radially positioned break-off components made, for example, in the form of explosive bolts the changeable ring component is fastened to the rocket nose cone. Inside the transport-launching module provision is made for an obturator, which is positioned in the bottom (tail) section of the rocket. The cup is made with an inner smooth cylindrical surface. Detachable means for creation of a behind-rocket volume of the preset value are installed on the rear cover with the id of brackets.

EFFECT: reduced thermoerrosion effect on the casing of the transport-launching module at a launch of the rocket, which makes it re-usable.

7 cl, 6 dwg

Up!