501results about "Rocket launchers" patented technology

The present application discloses a rocket support device, which is installed on a vertical frame and used to support a rocket, and includes an arrow support seat, a lifting device, a base and a buffer device; the arrow support seat includes an arrow support surface, and the arrow support surface is used to carry the rocket; the base is fixedly installed on the vertical frame, and the fixed end of the lifting device is fixedly arranged on the side of the base away from the vertical frame, and the driving end of the lifting device is drivingly connected to the buffer device, and the end of the buffer device away from the base is connected to the side of the arrow support seat away from the rocket; the lifting device can drive the arrow support seat to rise and fall through the buffer device. In the present application, the height of the arrow support seat is adjusted by the lifting device, so that each arrow support seat can play a supporting role on the rocket, so that the rocket is balanced in force during transportation or launching, and the safety of the rocket and the service life of the rocket arrow support seat are guaranteed.

Various countermeasure dispensing systems (or CMDSs) and method of use are described herein. CMDS may include a dispenser assembly operably engaged with a platform where at least one electrical connection provides electrical communication between the dispenser assembly and a sequencer. CMDS may also include a magazine assembly operably engaged with the dispenser assembly, wherein the magazine assembly comprises a magazine configured to hold at least two countermeasure expendables. CMDS may also include a breechplate assembly operably engaged with the magazine assembly and adapted to dispense the at least two countermeasure expendables. CMDS may also include at least one magazine identification switch (MIS) operably engaged with the magazine assembly and the breechplate assembly. CMDS may also include that the at least one MIS is configured to enable the sequencer and the breechplate assembly to selectively dispense at least one countermeasure expendable from the at least two countermeasure expendables.

The invention provides a launching pad and a carrier rocket launching method. The launching pad comprises a launching pad body provided with a through flow guide opening, a first heat-proof plate, a second heat-proof plate and a driving structure. The second heat-proof plate detachably covers the inner side wall of the second edge side of the flow guide opening, the first heat-proof plate is rotationally arranged on the inner side wall of the first edge side of the flow guide opening, and the driving structure is arranged at the bottom of the launching pad body and used for driving the first heat-proof plate to rotate to be in an unfolded state or a folded state. And the first heat-proof plate is horizontally arranged at the top of the flow guide opening. During maintenance, the second heat-proof plate can be quickly disassembled so as to facilitate maintenance or replacement, meanwhile, the first heat-proof plate can be rotated to a horizontal unfolding state through the driving structure, a worker stands on the first heat-proof plate to maintain the heat-proof coating, high-altitude operation is not needed, and the safety and convenience of maintenance are improved; and the heat-proof coating is coated in the horizontal state, so that adhesion and uniform distribution of the heat-proof coating are facilitated.

Various systems and methods for leveraging legacy countermeasure dispensing systems (CMDSs). The legacy CMDSs are leveraged through the expansion of breechplates and magazines in a CMDS by expanding the amount of expendables carried by a CMDS while still maintaining the legacy sequencer and dispenser in a legacy military platform, such as an aircraft. In addition, various circuitry systems are included in a circuit card of the breechplate for duplicating and / or expanding the firing lines provided in a legacy CMDS.

The invention belongs to the technical field of rocket launching, and particularly relates to a carrier rocket launching perpendicularity control method and device and a storage medium, the perpendicularity control method comprises the following steps: constructing an attitude dynamic model in a carrier rocket launching process, and the attitude dynamic model is used for describing change rules of rocket attitudes under different conditions; setting a prediction window; according to the real-time attitude state information of the rocket, predicting attitude changes of a plurality of time steps in the future in the current prediction window; designing an objective function, and optimizing the objective function through a predictive control algorithm in each time step to obtain an optimal control signal sequence; in each prediction period, executing a first signal in the obtained optimal control signal sequence, and transmitting the first signal to a rocket attitude control device; and repeating the steps. According to the invention, the launch attitude control precision of the carrier rocket can be improved, and the response speed of the system is optimized.

The invention discloses a rocket seaborne alignment method based on federated filtering and a system thereof. The rocket seaborne alignment method based on federated filtering comprises the following steps of performing equipment power-up and filter filtering parameter initialization; after equipment power-up and initialization of filtering parameters of the filter are completed, whether coarse alignment calculation can be carried out or not is judged; if the coarse alignment calculation can be carried out, carrying out coarse alignment calculation to obtain an attitude angle; and after coarse alignment calculation is completed and an attitude angle is obtained, fine alignment calculation is performed. According to the method, data of the multiple sensors are fused through the federated filtering algorithm, and the alignment precision of the rocket during offshore launching is remarkably improved. Meanwhile, the influence of the complex marine environment on rocket alignment can be effectively dealt with, and the stability of the launching process is improved. Moreover, by optimizing the structure of the federated filter, the fault tolerance performance of the system is improved, and even if a certain sensor breaks down, accurate alignment of the rocket can be ensured.

The invention relates to a folding door, in particular to a target drone zero-length booster rocket launching opening folding door mechanism. The mechanism comprises a folding door plate, a torsional spring hinge, a quick-release lock and a quick-release lock locking mechanism, the number of the folding door plates is two, the folding door plates are oppositely arranged at the rocket launching port, and when the two folding door plates are in a closed state, the folding door plates are matched with the rocket launching port; the torsional spring hinges are divided into two groups; one ends of the two groups of torsion spring hinges are respectively mounted on the two folding doors, and the other ends are respectively mounted at rocket launching ports of the target drone; the quick-release locks are divided into two groups; the two groups of quick-release locks are respectively mounted on the two folding doors; the quick-release lock locking mechanisms are divided into two sets, and the two sets of quick-release lock locking mechanisms are installed at rocket launching ports of the target drone respectively and correspond to the two sets of quick-release locks respectively. According to the target drone zero-length booster rocket launching opening composite material folding door mechanism, the function that a folding door is rapidly and reliably closed after work of a zero-length booster rocket in the launching stage is completed and cold separation is conducted can be achieved.

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 embodiment of the invention discloses an erecting control system for a rocket launched on the sea. The erecting control system for the rocket launched on the sea comprises a control module, a tilt angle sensor, a rotary encoder and an erecting frame. The first input end of the control module is in communication connection with the output end of the tilt angle sensor; the second input end of the control module is in communication connection with the output end of the rotary encoder; the input end of the tilt angle sensor is in communication connection with the erecting frame; the input end of the rotary encoder is in communication connection with the erecting frame; the marine launching angle is adjusted through the tilt angle sensor and the rotary encoder, relying on a launching ship is not needed, the launching cost is reduced, the launching maneuverability is improved, the launching period is shortened, the device can be suitable for different types of rockets, and high marine launching flexibility, good task adaptability and high launching economical efficiency are achieved.

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 relates to the technical field of carrier rocket transfer, in particular to a carrier rocket transfer device which comprises a carrier and a position adjusting mechanism. The carrier is used for bearing and transporting the erecting arm carrying the carrier rocket so as to transfer the carrier rocket to the position close to the fixed launching pad. The position adjusting mechanism is installed on the carrier. The carrier can drive the position adjusting mechanism to move up and down so as to drive the erecting arm to move up and down. The position adjusting mechanism can drive the erecting arm to move or rotate in the plane where the position adjusting mechanism is located. When the rotating base arranged at one end of the erecting arm is in butt joint with the rotating base arranged on the fixed launching pad, the erecting arm is driven by the carrier to conduct position coarse adjustment, then the erecting arm is driven by the position adjusting mechanism to move or rotate in the plane where the position adjusting mechanism is located, the position of the erecting arm is accurately adjusted, the butt joint difficulty is greatly reduced, and the butt joint efficiency is improved. The butt joint precision and the butt joint efficiency are improved when the rotating seat of the erecting arm is in butt joint with the rotating seat of the fixed launching pad.

The invention provides a launch device of a carrier rocket, a use method and a launch system. The launching device is used for executing a launching task or a test run task, and comprises a fixed launching pad which is fixed at a launching site, is in butt joint with a carrier rocket during execution of the launching task, is in butt joint with a movable launching pad during execution of the test run task, and comprises a traction assembly; the bottom end of the movable launching pad is butted with the fixed launching pad, and the top end is butted with a carrier rocket sub-stage during a test run task execution period; one end of the mooring tool is used for being detachably connected with the top end of the carrier rocket sub-stage during the test run task execution period, and the other end of the mooring tool is in transmission connection with the traction assembly in a detachable mode; and the control system is in communication connection with the traction assembly and the mooring tool during execution of the test run task, and controls the traction assembly to adjust the pre-tightening force of the traction assembly according to the pre-tightening force information fed back by the mooring tool. According to the launching device, manpower, material resources and time cost can be greatly saved, and the structural integrity of the rocket body is guaranteed.

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.

The invention provides a liquid rocket test run launching integrated launching pad, and belongs to the technical field of carrier rocket launching devices.The liquid rocket test run launching integrated launching pad comprises a launching pad body, a one-way fluid director, a switching device and a lifting device.In the test run state, a lifting platform of a lifter is located below the table top of a launching platform; and in a launching state, a lifting platform of the lifter extends out of the table top of the launching platform and is in contact with the L-shaped split flange plate. According to the liquid rocket test run launching integrated launching pad, a traditional test run platform and a launching pad of a launching site are integrally designed, and on the premise that the test function is met and the flight mission risk is reduced, the construction cost of the test run platform can be greatly saved, the transportation and transfer links are reduced, the transportation cost is saved, and the total launching period is shortened. Due to the overall modular design of the integrated launching pad, the launching pad has migration maneuverability and can meet the task requirements of different launching sites, the launching tasks of multiple sites are achieved through one set of equipment, and cost is saved.

The invention discloses a rocket erecting, overturning and docking device, system and method, and relates to the field of rocket docking. The rocket erecting, overturning and docking device comprises at least two overturning bases arranged on a fixed launching pad, at least two positioning journals arranged on a movable launching pad and matched with two supporting plates correspondingly and an auxiliary limiting assembly, each overturning base is provided with the corresponding supporting plate, each supporting plate is provided with a rotating groove, and the rotating grooves are matched with the positioning journals. According to the rocket erecting and overturning butt-joint device, the butt-joint structure is simplified, by means of cooperation of the positioning journals and the rotating grooves in the supporting plate, the butt-joint effect is improved, and the butt-joint effect is improved. The butt joint process of the fixed launching pad and the movable launching pad is more accurate, simpler and more convenient, the butt joint efficiency is effectively improved, meanwhile, the auxiliary limiting assembly is matched, radial limiting of the positioning shaft neck and the supporting plate is ensured, and overturning and shaking are avoided.

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.

The invention relates to an air cylinder, in particular to a reliable backward-falling and rebound-free backward-falling buffer cylinder for rocket launching, which comprises an air cylinder body, an air cylinder piston rod, an air cylinder piston, a spring, a buffer cylinder body, a buffer piston, a throttle lever and a connecting piece, the buffer cylinder body, the buffer piston and the throttle lever are all located in a rodless cavity of the air cylinder body, the center line of the air cylinder piston, the center line of the throttle lever and the center line of the buffer piston are located on the same straight line, the rodless cavity of the buffer cylinder body is filled with hydraulic oil, and a pressure measuring opening is formed in the buffer cylinder body. A through hole is formed in the end portion of one end, located in the buffer cylinder body, of the buffer piston, the end portion of the other end of the throttling rod is arranged in the through hole, a gap is reserved between the through hole and the throttling rod, and the gap forms an annular throttling oil channel. The supporting arm can be driven to reliably and rapidly fall backwards after a rocket is ignited, and rebounding is avoided after falling backwards.

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.