373results about "Rocket launchers" patented technology

The invention discloses a fixing device for a rocket, and relates to the technical field of spaceflight launching equipment, and the device comprises a bearing mechanism which is provided with an embracing clamp assembly and an embracing clamp adjusting assembly for driving the embracing clamp assembly to act; the holding clamp assembly comprises two holding clamp main bodies, each holding clamp main body is provided with a connecting section and a clamping section, the holding clamp adjusting assembly comprises a first mounting seat, a second mounting seat and a limiting seat which are mounted on the bearing mechanism, a driving part is arranged on the first mounting seat, a driving screw rod is rotationally connected between the second mounting seat and the limiting seat, and a driving shaft of the driving part is connected with the driving screw rod; the driving lead screw is provided with a first lead screw section and a second lead screw section which are oppositely arranged in a threaded mode, the driving lead screw is driven by the driving piece to rotate, so that the first driving nut and the second driving nut move along the driving lead screw, then the two holding clamp bodies are driven to rotate relative to the bearing mechanism, and the two clamping sections are matched to clamp or loosen a rocket to be fixed. And the operation process is simple and efficient.

The utility model provides a supporting and quick separating mechanism of a rocket stabilizing device, the supporting and quick separating mechanism is connected to the bottom of the rocket stabilizing device, and the supporting and quick separating mechanism is connected to an anti-overturning device chassis of the rocket stabilizing device and is supported at the bottom of an anti-overturning arm of the rocket stabilizing device; after the rocket is ignited, the supporting and quick separating mechanism is unlocked, and the anti-overturning arm is released; before the rocket is not ignited, the supporting and rapid separating mechanism is connected to the bottom of the anti-overturning arm in a supporting mode. The supporting and rapid separating mechanism comprises a two-stage deloading supporting mechanism and an aluminum strip; the two-stage load shedding supporting mechanism is connected to the anti-overturning device underframe and is connected to the bottom of the anti-overturning arm in a supporting manner; the aluminum strip is arranged at the bottom of the rocket, and the two ends of the aluminum strip are connected with the two-stage load shedding supporting mechanisms correspondingly. According to the supporting and rapid separating mechanism, stable supporting and unlocking releasing of the anti-overturning arm of the rocket stabilizing device are achieved, so that the anti-overturning arm is rapidly opened, and rocket launching is not hindered.

The invention relates to the technical field of rockets, in particular to a supporting device for a rocket and a transferring and erecting integrated launching vehicle. The supporting device comprises an erecting arm body and a plurality of auxiliary supporting mechanisms. The auxiliary supporting mechanism comprises a supporting bracket, a disc spring force limiter and at least two linear guide rails. The pre-pressure of the disc spring force limiter is adjustable, so that the rigidity of the supporting bracket is matched with the rigidity of the rocket body; the linear guide rails are arranged on the two sides of the supporting bracket respectively. According to the supporting device for the rocket and the transferring and erecting integrated launching vehicle, the supporting bracket is kept to be in a balanced state through the linear guide rail, the floating function is achieved, and the clamping stagnation phenomenon is prevented; force limiting supporting is achieved by adjusting the pre-pressure of the disc spring force limiter, the rigidity of the supporting bracket is made to be close to the rigidity of a rocket body, and therefore it is guaranteed that the additional bending moment cross section load generated by the erecting arm to the rocket is within the allowable range.

The invention discloses a bomb blocking and locking device and a design method, the bomb blocking and locking device is installed between a launching tube and a launching power device, the bomb blocking and locking device comprises a flange plate, a locking piece and an anti-rotating pin, and the flange plate is connected with the launching tube and the launching power device through mechanical interfaces; a locking ring face protruding out of the front disc face is coaxially formed on the front disc face of the flange disc, the rear end of the launching tube is matched with the front disc face of the flange disc, and the locking ring face is inserted into the launching tube and matched with the rear end of the aircraft. Locking through holes are distributed in the locking ring face in the circumferential direction and comprise straight-through holes and step through holes which are distributed in a staggered mode. And bullet tail threaded holes matched with the locking through holes in a one-to-one mode are formed in the rear end face of the aircraft, after the aircraft is assembled in the launching tube, the anti-rotating pins are assembled into the corresponding bullet tail threaded holes through the straight through holes, and the locking pieces are assembled into the corresponding bullet tail threaded holes through the step through holes so as to achieve bullet blocking and locking of the aircraft.

The utility model discloses a flow and pressure controllable water spraying noise reduction system and rocket launching auxiliary equipment relates to rocket launching auxiliary equipment technical field, and it is including: water storage tank, flow pump group, flow pump group connects water storage tank and drainage pipeline, water spraying pipe, water spraying pipe's first end connects drainage pipeline, and the second end of water spraying pipe sets up first control valve, circulating water pipe, circulating water pipe's first end connects drainage pipeline, and the second end of circulating water pipe connects water storage tank, and sets up second control valve on circulating water pipe. The above-mentioned flow and pressure controllable water spraying noise reduction system has solved the technical problem that the current water spraying noise reduction system cannot adjust water spraying flow, and water spraying timeliness is poor, and cannot provide large flow water flow in time, and influences the noise reduction effect, and before the rocket launches, the cooling water in the drainage pipeline keeps certain flow rate circulation, guarantees that the cooling water in the water spraying pipe can be in time, and the sufficient amount of water spraying pipe is sprayed from water spraying pipe, reaches the best noise reduction effect.

Heavy inert gas insulation layers are provided for one or more components of a launch system for a plurality of missiles. The layer may be integrated into the walls of the components or provided in inserts attached to the components. An inert gas fills a sealed void space in the walls or the insert. The inert gas has a density of at least 1.5 Kg / m3 and a thermal conductivity (Tcond_gas) of no greater than two-thirds of a thermal conductivity of air (Tcond_air) to form the heavy inert gas insulation layer. The inert gas may be Argon, Krypton, Xenon or a synthetic gas and is suitably held at a pressure of 760 Torr (1 atmosphere) or greater at sea level. The heavy inert gas insulation layer delays desensitization or inhibits premature reaction of the energetic materials inside the missiles due to high external temperatures. The insulation layers allow for more compact and dense configurations of the launch system and missiles.

The utility model provides an anti-overturning arm auxiliary closing mechanism of a seaborne launch rocket stabilizing device. The anti-overturning arm auxiliary closing mechanism comprises a first anti-overturning arm auxiliary closing mechanism and a second anti-overturning arm auxiliary closing mechanism. The first anti-overturning arm auxiliary closing mechanism and the second anti-overturning arm auxiliary closing mechanism are arranged at the bottom of a first anti-overturning device and the bottom of a second anti-overturning device of the seaborne launch rocket stabilizing device correspondingly. When the first anti-overturning device is in an overturning state, the first anti-overturning arm auxiliary closing mechanism adjusts the first anti-overturning device to be in a vertical state; and when the second anti-overturning device is in an overturning state, the second anti-overturning arm auxiliary closing mechanism adjusts the second anti-overturning device to be in a vertical state. According to the supporting device, in-place supporting of the marine launch rocket stabilizing device is achieved, the anti-overturning arm auxiliary closing mechanism and the anti-overturning arm of the marine launch rocket stabilizing device can be switched to be in a supporting state or a separation state, and the reliability, stability and safety of the marine launch rocket stabilizing device are improved.

The utility model provides a cushioning and anti-springback mechanism for a rocket stabilizing device, the rocket stabilizing device comprises an anti-overturning device used for being supported on two sides of a rocket, and the cushioning and anti-springback mechanism is arranged at the bottom of the anti-overturning device; the cushioning and springback-preventing mechanism comprises a cushioning mechanism for playing a role in cushioning the rocket stabilizing device and a springback-preventing mechanism for preventing the rocket stabilizing device from springback; the anti-overturning device comprises an anti-overturning arm and an anti-overturning device bottom frame, the bottom end of the anti-overturning arm is rotationally connected to the anti-overturning device bottom frame, and the top end of the anti-overturning arm is connected with a rocket body of the rocket in a clasping mode. And the cushioning mechanism and the anti-springback mechanism are fixedly connected to the anti-overturning device underframe and are arranged below the anti-overturning arm. According to the anti-springback device, the effects of cushioning and springback prevention are achieved in the dumping process of the rocket stabilizing device, and the dumping safety and reliability of the rocket stabilizing device are improved.

Heavy inert gas insulation layer(s) are provided for containers configured to contain components that include an energetic material. The heavy inert gas insulation layer delays desensitization or inhibits premature reaction of the energetic material due to high external temperatures. The layers may be formed in hollow walls of the container itself or as inserts that are attached to the container. An inert gas fills a sealed void space in the walls or the insert. The inert gas has a density of at least 1.5 Kg / m3 and a thermal conductivity (Tcond_gas) of no greater than two-thirds of a thermal conductivity of air (Tcond_air) to form the heavy inert gas insulation layer. The inert gas may be Argon, Krypton, Xenon or a synthetic gas and is suitably held at a pressure of 760 Torr (1 atmosphere) or greater at sea level.

The present invention relates to a spring arrangement for use in a countermeasure magazine, said spring arrangement including a plurality of elements, wherein each one of said elements has a base portion and a plurality of spring portions extending from a first edge of said base portion, and wherein said spring portions of each element are distributed along a length of said base portion, and wherein said elements include mating connection means such that said elements may be connected to each other.

A receiving device (40) for guided missiles (3) for airborne deployment from aircraft (2) and a deployment device (50) for airborne deployment of guided missiles (3) are proposed, wherein the deployment device (50) has a receiving device (40) and / or is designed to interact with the receiving device (40), and wherein the receiving device (40) comprises a container (41) with a receptacle (43) for at least one guided missile, which is designed to disintegrate in a predetermined manner by an air flow prevailing during airborne deployment.

The invention relates to the technical field of rocket launching, in particular to a steam protection rocket launching system which comprises a steam energy storage system, a steam conveying system, a steam releasing system and a launching rack structure. The steam energy storage system comprises a steam boiler, a steam pressure accumulator and a steam energy storage control unit and is used for preparing and storing high-pressure steam before rocket launching. The steam conveying system comprises a steam blending table and a steam supply pipeline and is used for conveying high-pressure steam in the steam pressure accumulator to the steam release system; the steam release system comprises a steam injection unit and a steam injection control system and is used for releasing steam when the rocket is ignited, launched or recovered, forming a steam protection air curtain and reducing thermal shock of high-temperature airflow on the structure. By establishing the high-pressure steam protection air curtain, active protection of structural parts, pipeline parts, hydraulic parts and other parts of the rocket launching system influenced by the gas tail flame area of the rocket engine is achieved, and the durability and reliability of the launching system are improved.

Spacers include a base configured to be placed within depressions of one of a cover or a baseplate of a reticle pod, and a contact surface configured to contact the other of the cover and the baseplate. The spacers are configured to space the cover and the baseplate apart from one another such that sealing surfaces of the cover and the baseplate are separated by a gap. The depressions can be gripper pockets of the baseplate. Multiple spacers can be used in a reticle pod to provide the gap between sealing surfaces. The spacers can be installed to prepare a reticle pod for shipment.

A hybrid pad system positioned between a missile and a launch tube is provided herein. The hybrid pad system includes an outer sheet and an inner sheet spaced from the outer sheet. A web region can be positioned between the outer sheet and the inner sheet. A restoration region can be positioned between the outer sheet and the inner sheet and tangentially offset from the web region. A support can be operably coupled with the inner sheet.

Modular ammunition launching system comprising a reloadable ammunition receiver in multiple positions. The modular launching system (1) comprises: a chassis (2) defining at least one housing (6), an ammunition receiver (4), said receiver (4) being movable relative to said chassis (2) between a functional position and a reloading position. Said modular launching system comprises a coupling plate (24) integral with the receiver (4) and mounted to slide on a rail (26, 28) integral with the chassis (2) so as to allow movement of the receiver (4) between the functional position and the reloading position, said coupling plate (24) being movable in rotation relative to the rail (26, 28) about a reloading rotation axis (R3) when the receiver (4) is in the reloading position. Figure for the abbreviation: 7

The utility model provides a kind of automatic stop's suspension general hanging beam device, fixedly connected on ground or vehicle-mounted launcher, missile and guide launcher form missile launcher combined system, missile launcher combined system is hung in suspension general hanging beam device, press tightly stopper, fixed guide launcher and electrical connector pass through suspension general hanging beam device, suspension general hanging beam device includes beam body, automatic stop mechanism, hook assembly and anti-swing stop mechanism, wherein, automatic stop mechanism, hook assembly and anti-swing stop mechanism are respectively installed on beam body, when guide launcher is hung, hook assembly hook can be automatically inserted into lifting lug hole, with safety pin stop hook, guide launcher can be hung, i.e. It is realized;When guide launcher is unloaded, pull handle, drive hook to be stopped by automatic stop mechanism, guide launcher can be conveniently unloaded, and operation is simple.

The modular launching system (1) comprises: - a chassis (2) defining at least one housing (6), - an ammunition receiving pod (4), said receiving pod (4) being movable relative to said chassis (2) between a functional position and a reloading position. Said modular launching system includes a coupling plate (24) integral with the receiving pod (4) and mounted to slide on a rail (26, 28) integral with the chassis (2) so as to allow movement of the receiving pod (4) between the functional position and the reloading position, said coupling plate (24) being movable in rotation relative to the rail (26, 28) around a reloading rotation axis (R3) when the receiving pod (4) is in the reloading position.

The utility model provides a launcher enabling a rocket to rotate forwards, which comprises a rocket body, a rocket airfoil mounted at the tail of the rocket body, a fixing frame arranged on the outer side of the rocket body, a fixing plate mounted on the inner side wall of the fixing frame, an adjusting ring arranged in the fixing plate, clamping pressure plates arranged on the upper surfaces of the fixing plate and the adjusting ring, and bolts arranged in the clamping pressure plates. Bolts penetrate through the clamping pressing plates to be spirally connected with nuts, and spiral guide rails are movably installed at the tail ends of the inner sides of the adjusting rings. According to the launching device capable of enabling the rocket to rotate forwards, the safety, stability and reliability of the rocket during launching can be improved, and the anti-jamming capability of the rocket is effectively improved.

The application belongs to the field of aircraft auxiliary take-off equipment, and particularly relates to an aircraft launching system and an aircraft. The aircraft launching system comprises a driving part I and a fixed releasing mechanism. The output end of the driving part I has a circular circumferential rotation stroke or a linear movement stroke. The fixed releasing mechanism comprises a support, a fixed releasing rod and two connecting rods, and the support, the fixed releasing rod and the two connecting rods form a parallelogram mechanism. The support is arranged opposite to the fixed releasing rod. The support is connected with the output end of the driving part I. The fixed releasing rod is provided with a fixed releasing structure for fixing and releasing the aircraft. The fixed releasing mechanism formed by the parallelogram mechanism can lower the fixed releasing rod to leave a flight space when the aircraft takes off, so that the aircraft can be prevented from colliding with the fixed releasing mechanism when taking off, and the use safety of the launching system is improved.

Proposed are a method for controlling at least one guided missile (3) to be launched by an aircraft (2) during flight, a guided missile (3) and an aircraft (2), wherein at least one control command (T) is transmitted by light signal (L) from the aircraft (2) to the guided missile (3).

The invention belongs to the technical field of noise elimination and flame suppression equipment, and particularly discloses a noise elimination and flame suppression device which comprises a noise elimination and flame suppression shell, the noise elimination and flame suppression shell is in a hollow ring shape, the noise elimination and flame suppression shell is filled with a noise elimination and flame suppression agent, and the noise elimination and flame suppression shell can be crushed under the action of high-temperature and high-pressure fuel gas. The two-phase mixed combustion noise reduction and flame reduction technology is adopted, so that the emission noise is greatly reduced, when the initial velocity of a bullet is about 200 m / s, the emission noise can be reduced to 170-175 decibels under the open field condition, the noise can be reduced to 180-185 decibels when the bullet is emitted in a limited space, the emission noise can be remarkably reduced, the sound pressure can be reduced to 1 / 3 of the sound pressure which is not additionally provided with the noise elimination and flame reduction device, and the noise reduction and flame reduction effects are good. After emission, a calcium chloride solution at the emission port and the tail part of an emission object is atomized to wrap flames, so that flame at the emission port and emission tail flames can be obviously reduced, and flame visible to naked eyes basically does not exist; the training clothes can be kept complete when being launched in a limited space, and cannot be burnt out, broken down or ignited by tail flames or post-spraying objects.

The invention belongs to the technical field of marine rocket launching, and particularly relates to a marine rocket launching platform with a rocket body stabilizing structure. A base for mounting a rocket is arranged on the ship body; a group of fixing rings are arranged on the ship body, and a group of first hydraulic rods which are annularly and uniformly distributed are fixedly connected to the inner walls of the fixing rings; the output end of the first hydraulic rod is fixedly connected with a supporting and stabilizing block which is used for supporting and stabilizing a rocket. The rocket is installed on the base, at the moment, the rocket is located in the center of the fixing ring, when the ship body operates on the sea, the first hydraulic rod is started, the output end of the first hydraulic rod pushes the supporting and stabilizing block, the supporting and stabilizing block moves towards the side close to the rocket body, and at the moment, the supporting and stabilizing block makes contact with the rocket body; and therefore, the rocket body is supported stably, and the stability of the rocket during transportation is improved.

The invention relates to the technical field of spaceflight, and discloses a message transmission method, device and system in the launching process, and the system comprises a target command node, a target launching platform and a communication satellite. The target command node is used for acquiring target transmitting information; generating a first instruction message based on the target emission information; sending a first instruction message to a communication satellite; receiving an execution result sent by the communication satellite; the target transmitting platform is used for receiving a first instruction message sent by the communication satellite; based on the first instruction message, executing control logic corresponding to the first instruction message to obtain an execution result; sending an execution result to a communication satellite; the communication satellite is used for receiving a first instruction message sent by the target command node or an execution result sent by the target launching platform; and based on the first instruction message and a preset mapping relationship, sending the first instruction message to a target transmitting platform whose identification address is the first address. According to the invention, the message transmission efficiency in the transmitting process can be improved.

A method for controlling at least one guided missile (3) to be launched from an aircraft (2) during flight, a guided missile (3) and an aircraft (2) are proposed, wherein at least one control command (T) is transmitted from the aircraft (2) to the guided missile (3) by means of a light signal (L).

The utility model relates to a rocket launching platform opposite spraying noise reduction water supply system which comprises a foundation, a launching platform, supporting frames, a water tower, a water tank, a spraying pipe and a spraying head, the launching platform is arranged on the foundation, the supporting frames are arranged on the two sides of the launching platform respectively, and the two supporting frames are symmetrically arranged; spray pipes are arranged on the supporting frames respectively, and a plurality of spray heads are arranged on the spray pipes in parallel. A water tower is arranged on the foundation on one side of the supporting frame, a water tank is arranged at the upper end of the water tower, and water conveying pipes connected with the two spraying pipes are arranged on the two sides of the water tank respectively. The mode that water stored in the water tower enters the cooling system is utilized, the water flow source is stable, and the water flow in the water conveying pipe is stable through the water pre-filling device; water flow in the water conveying pipe enters the spraying pipe through the water inlet pipes, water hammer is avoided, and system stability is improved; cooling water is sprayed out through the high spraying nozzles and the low spraying nozzles, the large-range opposite-flushing water spraying effect is formed, and the cooling and noise reduction effects are better.

The application provides a modular airborne detection and attack micro-rocket launching device, which comprises a weapon station module, a shell cabin module and a female head, a male head and a transmission module are respectively electrically connected to two ends of an electric control module and are controlled by the electric control module; a rotating shaft rotates along an axis; the shell cabin module is detachably connected to the rotating shaft and rotates with the rotating shaft; a shell cabin body is used for accommodating spare bullets; the female head is detachably connected to the male head, at this time, the weapon station module, the female head and the shell cabin module are in a non-integral structure, and the weapon station module, the female head and the shell cabin module can be separately disassembled, so that the modules of the modular airborne detection and attack micro-rocket launching device cannot be separately maintained, the maintenance convenience of the modules of the modular airborne detection and attack micro-rocket launching device is improved, in addition, the shell cabin module is detachably connected to the rotating shaft and rotates with the rotating shaft, so that the angle of the shell cabin module relative to the transmission module can be adjusted.

Provided is a detent apparatus for a rocket, The detent apparatus includes a detent including a first end portion, a second end portion opposite to the first end portion, an extension extending between the first end portion and the second end portion, and a detent protrusion configured to engage with the rocket, a first elastic body configured to elastically support the first end portion of the detent and connected to the first end portion, and an electrical safety device configured to prevent rotation of the detent including a hinge fixing frame having a hinge axis parallel to the detent rotation axis, a detent support configured to rotate around the hinge axis and support the detent, a hinge axis shaft arranged on the hinge axis, a solenoid configured to rotate the detent support by pushing the detent support, and a micro switch activated when the detent support rotates.

The invention discloses a reusable catapult system cabin connecting structure design method, and aims to solve the problems that a catapult test and a suspension test need to be repeatedly tested when necessary, a catapult structure needs to bear large overload force, if the structural strength and rigidity are not enough, a cabin needs to be reprocessed after each test is finished, the consumed cost is high, the development period is long, and the design cost is low. According to the reusable catapult system cabin connecting structure, the state of catapulting and hanging test bullets can be quickly recovered only by replacing screws at the connecting position after a test is finished, and repeated use of a launcher can be completed by replacing launcher guide rails according to catapults of different models and sizes.

The application discloses a manual adjusting device for the caliber of a human shadow rocket launcher director, which comprises a track assembly and a supporting assembly. The supporting assembly comprises four bearing rail frames. The track assembly comprises two groups of U-shaped track assemblies arranged in the left and right openings of the supporting assembly. Each U-shaped track assembly comprises an upper U-shaped large track, an upper U-shaped small track, a lower U-shaped large track and a lower U-shaped small track. The upper U-shaped small tracks are connected through a first linkage rod. The lower U-shaped small tracks are connected through a second linkage rod. A linkage plate is arranged between the two groups of U-shaped track assemblies. First and second inclined grooves are formed in the side walls of the linkage plate. The first and second linkage rods pass through the first and second inclined grooves respectively. The diameter of the envelope circle of the U-shaped small tracks can be changed through manual adjustment, so that one director can adapt to the launching requirements of rocket projectiles with various calibers.

The application provides a composite power driving system and control method for launching rocket erection, belonging to the field of launching rocket erection, and the driving system comprises a track combination system, a matching system, a whole rocket transport vehicle and a central control system. The track combination system is composed of a sliding mechanism and a swing boom; the matching system comprises a supporting rack and a buffer damping device. The central control system coordinates the work of each component, the whole rocket transport vehicle transports the launching rocket along the supporting rack slope to the horizontal plane, and the sliding mechanism and the swing boom cooperate to push the rocket to move. The laser sensor is used to realize the accurate positioning and connection of the rocket and the boom, the buffer damping device reduces the swing, and the stable erection of the rocket is ensured. The system also integrates a solar energy collection matrix and a gas flow collection and power generation device, and recycles energy to supply power for the transport vehicle. The application realizes the high-precision, automatic and efficient erection of the launching rocket, and reduces the energy consumption and operation complexity.