49results about "Rocket launchers" patented technology

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.

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 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.

An unmanned aerial vehicle (UAV) launch tube (100) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture (305), and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).

The application discloses a kind of oblique launch support orientation device and the launch method using it, in the device, by setting the guide rail of special form, adapter and projectile foot, by guide rail and projectile foot cooperation to constrain projectile lateral movement and circumferential rotation, by the adapter for projectile provides upward support force, by projectile foot for projectile provides downward support force, to constrain the low disturbance and subsidence of projectile, and with simple structure, action reliable, little features such as the influence of projectile aerodynamics, can provide guarantee for safe and reliable oblique launch.

The modular ammunition launching system (1) comprises: - a chassis (2) defining at least one housing (6), - an ammunition receiving pod (4) 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 receiving pod (4) and mounted removably and movablely on the chassis (2), said modular system comprising at least one pairing device comprising a first pairing element (52, 56) integral with the chassis (2), a second pairing element (54, 58) integral with the coupling plate (24), the movement of the coupling plate (24) from the reloading position to the functional position resulting in the coupling of the first pairing element (52, 56) and the second pairing element (54, 58) in the functional position.

This invention discloses a rocket body protrusion protection mechanism and its operating method, belonging to the technical field of launch vehicles. It includes a thermal insulation cover and a control module. The key feature is that a passive spring module is located below the thermal insulation cover, and a ball joint flange connects the thermal insulation cover and the passive spring module. The two ends of the ball joint flange are connected to the thermal insulation cover and the passive spring module, respectively. An active adjustment module is located below the passive spring module. The active adjustment module includes an X-axis adjustment component, a Y-axis adjustment component, and a Z-axis adjustment component, which are stacked vertically. Both the passive spring module and the active adjustment module contain sensor components for signal feedback, and these sensor components are connected to the control module. This invention is a rocket body protrusion protection mechanism that actively adjusts its position and passively adapts to the rocket body's roll and linear displacement attitude.

The application provides a vertical rack system for liquid rocket auxiliary support and a working method thereof, which comprises a vertical rack main structure, an upper clamp, a lower clamp, a main support bracket, an auxiliary support bracket, a spring limiting tool and a screw elevator structure; the upper clamp and the lower clamp are fixedly connected on the vertical rack main structure at intervals; the main support bracket and the auxiliary support bracket are arranged on the vertical rack main structure at intervals; and the auxiliary support bracket is connected on the vertical rack main structure through the spring limiting tool and the screw elevator structure. The application improves the support stability, reliability and safety of the vertical rack main structure on the rocket during the transfer, erection and launching process of the rocket, improves the reliability, efficiency, precision and safety of the docking of the vertical rack and the launching platform, and realizes the fast, safe and high-precision transfer, erection and launching docking process.

The Modular Launching System (1) comprises: - a chassis (2) defining at least one housing (6), - a munitions receiving box (4) movable relative to said chassis (2) between a functional position and a reloading position. The Modular Launching System comprises a coupling plate (24) integral with the receiving box (4) and mounted to slide on a first rail (26) integral with the chassis (2), said coupling plate (24) being movable on said first rail (26), said modular system comprising a support arm (30) extending outward from the chassis (2) and comprising a second rail (28) extending in line with the first rail (26), said coupling plate (24) being movable on said second rail (28) between the intermediate position and the reloading position.

Rocket launcher control system comprising a storage unit having one or more supercapacitors. Control system (16) for rocket launcher (12), comprising: - a human-machine interface (20) for entering firing parameters and including an integrated electric battery (26), - a control device (22) for receiving firing parameters, and an incoming electric current (34) from the integrated electric battery, the control device comprising: a regulation unit (38) for producing an electric current to be stored (40); a storage unit (42) having one or more supercapacitors (44) for receiving the electric current to be stored in the supercapacitor(s) and for producing a release electric current (46); a conditioning unit (48) for receiving the release electric current and for producing an output electric current (36) intended to be sent to the rocket launcher.Figure for the abbreviation: figure 2.

The application provides a reusable launch vehicle ground test and launch integrated system and method, wherein the reusable launch vehicle ground test and launch integrated system comprises the following: front-end equipment cluster and general test and launch software platform for bidirectional data interaction through a standardized data interface; the general test and launch software platform is deployed and runs in a distributed container cluster of a test and launch network architecture environment, the general test and launch software platform and the test and launch network architecture environment are configured and distributed and data is converged through a data synchronization mechanism; an integrated collaborative control module is bidirectionally interactive with the general test and launch software platform for instruction issuing and state feedback, and collaborative control of the whole system is realized. Through fixed deployment of the distributed front-end test and launch equipment cluster and standardization interface adaptation, the general test and launch software platform and the integrated collaborative control module of the micro-service architecture are collaboratively controlled. The consistency of test efficiency and state is maintained, and the purpose of improving test data utilization and continuity is achieved.

The application discloses a rocket zero-level boost launching well and a launching method, and belongs to the technical field of space launching. The launching well comprises an ultra-deep vertical well body, a bottom high-pressure steam power system, a well wall multi-stage sectional steam nozzle, a large-mass heat-insulation pressure-bearing piston, a manned spaceship and a top pressure relief and condensation recovery system. The outer wall of the piston is provided with elastic guide wheels and is slidably matched with the well wall track to realize central stable upward movement. The manned spaceship is detachably clamped on the upper end of the piston and does not directly contact with the well wall. When launching, the spaceship is not ignited in the well, and the piston and the spaceship are pushed upward by the bottom and well wall sectional steam static pressure, and the whole course overload is controlled within 1.5G-2.5G. After the spaceship is out of the well mouth, the engine is ignited to enter the orbit, the piston falls back, the steam is condensed and recovered, and the rapid reuse is realized. The application has the advantages of low overload, no ablation, high safety, extremely low cost, high-frequency repeated use and the like, and is suitable for low-cost manned space launching.

The modular ammunition (20) launch system (1) comprises at least one ammunition receiving chamber (4) forming at least one firing channel (18) for a munition (20) emitting a pyrotechnic jet (24) in a longitudinal direction (L), the modular system further comprising at least one attenuation device (32). Said attenuation device (32) comprises at least one jet-breaking element (35) arranged to separate the pyrotechnic jet (24) from the munition (20) into at least two sub-jets (35), each extending in a direction different from the other sub-jet (35) and from the longitudinal direction (L).

A launch system and method for a launch vehicle that can save initial launch fuel includes a support structure, characterized in that: the support structure consists of a horizontal support frame (3) and an ascending section support frame (4), a horizontal track section (5) is installed on the horizontal support frame (3), an inclined track section (6) connected to the horizontal track section (5) is installed on the ascending section support frame (4), a launch acceleration pipe (10) is fixedly installed on the horizontal support frame (3) and the ascending section support frame (4), an electromagnetic catapult (14) is installed on the electromagnetic catapult slide rail (13), a rocket trolley (8) is installed on the horizontal track section (5) and the arc track section (6), and a rocket bracket (9) is provided on the rocket trolley (8). The present invention has a reasonable structure, can obtain sufficient initial velocity before launch ignition, can save launch fuel, can increase the effective payload, and is conducive to saving launch costs.

The application provides a multi-degree-of-freedom rocket erecting frame support base, which comprises a first translation mechanism, a second translation mechanism, a pusher, an adapter frame, a first fixed frame, a second fixed frame, a moving frame, a first lifting mechanism and a second lifting mechanism; the first translation mechanism is in sliding connection with a first adapter part of the adapter frame, and the second translation mechanism is in sliding connection with a second adapter part of the adapter frame; the pusher is fixed between the first adapter part and the second adapter part; the first fixed frame is in sliding connection with a first moving part of the moving frame, and the second fixed frame is in sliding connection with a second moving part of the moving frame; the first lifting mechanism is fixedly connected with the first moving part, and the second lifting mechanism is fixedly connected with the second moving part; the first moving part is provided with a first support frame, the second moving part is provided with a second support frame, and the first support frame and the second support frame form a support space for supporting a rocket. The scheme can improve the adaptability, protection capability and stability of the rocket erecting frame support base.

The present invention relates to a weapon barrel (10) having a convertible guide rail set, wherein the weapon barrel (10) has primary guide rails for a first caliber which are fixedly connected to the weapon barrel (10), and the primary guide rails have at least one lower primary guide rail (11), a starboard primary guide rail (12), and a port primary guide rail (13). The weapon barrel is characterized in that fastening elements (40) are arranged in the weapon barrel (10) adjacent to the lower primary guide rail (11), the starboard primary guide rail (12) and the port primary guide rail (13), wherein: the convertible guide rail set comprises at least one protective set (20); the protective set (20) has six protective elements; the protective elements can be arranged on the fastening elements (40) and in the arranged state completely cover the fastening elements (40); the protective elements are no taller than the primary guide rails and therefore do not influence the first caliber; the convertible guide rail set comprises at least one guide set (30); the guide set (30) can be arranged on the fastening elements (40) and, in the arranged state, the guide set (30) performs the function of the guide rail; the guide set (30) is designed for a second caliber; and the second caliber is smaller than the first caliber.

The application relates to the field of rocket launching, and particularly discloses a synchronous erecting control method for multiple hydraulic cylinders, which comprises a simulation calculation process; a control system discriminates and operates the values of strain flowers A and the values of strain flowers B; the difference range epsilon threshold of the values of strain flowers A and the values of strain flowers B in the same group of erecting oil cylinders in the control system is measured 实测1 , epsilon 实测2 , epsilon 实测N / 2 , epsilon 实测1 , epsilon 实测2 , epsilon 实测N / 2 When the measured absolute value is greater than the epsilon threshold, the control system automatically and real-timely feeds back and controls the erecting oil cylinder. The scheme directly monitors the deformation and stress conditions of the left and right sides of the final erecting arm, and most truly reflects the erecting arm state, and is applicable to different mass center offset errors of different missile types without the need of re-adjustment, so that the adjustment efficiency is improved.

The application discloses a buffering and anti-rebound mechanism for offshore rocket launching and a use method thereof, and belongs to the technical field of rocket launching, and comprises an anti-overturning device base and an anti-overturning arm, the anti-overturning arm is arranged on the anti-overturning device base and is hinged to the anti-overturning device base, a one-way brake assembly and a shock absorption assembly are arranged on the anti-overturning device base, the one-way brake assembly is arranged at a middle position between the two shock absorption assemblies, the one-way brake assembly and the shock absorption assembly are arranged on the same side of the anti-overturning arm, and the anti-overturning arm is inclined to rotate towards the direction close to the one-way brake assembly and the shock absorption assembly; the one-way brake assembly comprises a brake arc, a brake shoe, a friction lining, a compression spring and a brake connecting rod unit; and the shock absorption assembly comprises a hydraulic damper unit, a roller unit and a shock absorption connecting rod unit. The one-way brake assembly and the shock absorption assembly are used for buffering and absorbing the shock of the anti-overturning arm, and the buffering and anti-rebound effects are achieved during the overturning process and after the overturning process.

Modular ammunition launching system including a pairing device. The modular ammunition launching system (1) includes: - a chassis (2) defining at least one housing (6), - an ammunition receiving pod (4) 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 removably and movablely on the chassis (2), said modular system including at least one pairing device comprising a first pairing element (52, 56) integral with the chassis (2), a second pairing element (54, 58) integral with the coupling plate (24), the movement of the coupling plate (24) from the reloading position to the functional position resulting in the coupling of the first pairing element (52, 56) and the second pairing element (54, 58) in the functional position.Figure for the abridged version: 2.

The present application belongs to the technical field of platform leveling control, and particularly relates to a platform leveling control method and a platform system, the platform system comprising a platform, a launching rack, the launching rack comprising a launching rack plane parallel to the platform plane, the platform plane being supported by a plurality of telescopic leveling legs, and further comprising a leveling controller connected to the leveling legs; the platform plane and the launching rack plane are respectively provided with a platform detection device and a launching rack detection device for detecting the inclination of the planes, and the leveling controller executes instructions to realize platform leveling: first, the leveling legs are adjusted until the inclination of the platform plane detected by the platform detection device does not exceed a first set threshold; second, the leveling legs are adjusted until the inclination of the launching rack plane detected by the launching rack detection device does not exceed a second set threshold. The control method combines coarse leveling and fine leveling according to the horizontal inclination, avoids the influence of the uneven platform on the launching rack, and improves the leveling precision.

The utility model discloses a frame type launching rack of ground barrier launching integrated device, including launching rack seat, support base, launch frame, bullet cage and drive push rod, the launching rack seat is installed in the launching box, and the support base is set up on the launching rack seat, constitutes the base body of launching rack, and the launch frame is movably arranged on the support base, and the bullet cage is slidably arranged in the launch frame, and the fixed end of drive push rod is movably connected on the support base, and the telescopic end of drive push rod is movably connected on the launch frame, realizes the lifting and compound motion of launch frame and bullet cage whole, and its structure is reliable, and the use performance is good, through the cooperation of L shaped frame, bullet cage and drive push rod, has realized the compound motion of compact storage from the box to the uncoiling lifting and the forward stretching rocket bomb outside the box, utilizes the telescopic of drive push rod, and efficiently completes the establishment of launching preparation posture, effectively realizes the ground barrier task of quick deployment, concealed storage and accurate launching.

A vertical launch system comprising a container having a first end and a second end opposite the first end. The container defines an interior space extending between the first and second ends. The container further defines a first level near the first end and a second level adjacent to the first level. The vertical launch system further comprises a first plurality of missiles arranged in the interior space of the container and located on the first level of the container, and a second plurality of missiles arranged in the interior space of the container and located on the second level of the container such that the first and second plurality of missiles are arranged in a stacked configuration. In addition, the vertical launch system comprises a plume deflector disposed inside the container.The plume deflector is positioned between the first level and the second level.

The application discloses a rocket and launching platform unlocking device, and relates to the technical field of rocket launching unlocking devices.The unlocking device comprises a locking assembly, a driving assembly and a control assembly.The locking assembly is arranged at a launching platform, and the launching platform is used for fixing a rocket to be launched.The locking assembly is provided with a locking portion at the top, and the locking portion has a first working state and a second working state.The driving assembly is in transmission connection with the locking assembly, and the driving assembly is used for driving the locking portion to switch between the first working state and the second working state, so as to unlock and release the rocket to be launched.The control assembly is in signal communication with the driving assembly, and the control assembly is used for controlling the driving assembly to execute operation instructions, and the operation instructions at least include start instructions and close instructions.The unlocking device can effectively realize quick and reliable unlocking of the rocket and the launching platform, and ensures smooth launching of the rocket.

The application discloses a docking device and relates to the technical field of carrier rockets, wherein the docking device is used for docking two adjacent rocket assemblies, and the docking device comprises two docking mechanisms, one of the rocket assemblies is arranged in one of the docking mechanisms, and the other rocket assembly is arranged in the other docking mechanism. The technical scheme provided by the application avoids the whole attitude adjustment depending on super-large lifting equipment, but the segmented attitude fine adjustment is performed on the rocket assemblies, the requirements for the equipment bearing capacity and the operation precision in the docking process are effectively reduced, the stress concentration point in the docking process is dispersed, the local stress is prevented from being too large to cause the damage of the rocket assembly structure, and the safety and the operation efficiency of the vertical docking of the medium and large solid carrier rockets in the three-horizontal mode are improved.

The application discloses a kind of offshore rocket launch anti-overturning quick opening equipment and its control method, belong to offshore rocket launch technical field, including anti-overturning base and drive base, hinged with anti-overturning arm on anti-overturning base, rocket body is placed on anti-overturning base, anti-overturning arm is placed in the side of rocket body, drive base is equipped with drive assembly, drive assembly is used to drive the rotation of anti-overturning arm, brake flywheel assembly is arranged in anti-overturning arm, brake flywheel assembly is used to brake the rotation of anti-overturning arm, drive assembly is connected with brake flywheel assembly by shaft coupling.The application can more efficiently improve the opening speed of anti-overturning arm under the premise of adding little weight to anti-overturning arm, and can adjust the speed value of opening anti-overturning arm, thereby improving the safety and reliability of offshore rocket body launch.

This invention relates to the technical field of spacecraft launch, and more specifically, to a spacecraft launch device, comprising: a launcher, the launcher being provided with a slide rail and a support platform, the launcher being used to move along a launch track; a transition section, one end of the transition section being detachably connected to the tail of the spacecraft, and the other end being connected to the support platform; an adapter, one end of the adapter being detachably connected to the periphery of the spacecraft, and the other end being slidably connected to the slide rail; in the drive phase, the spacecraft is connected to the launcher via the transition section, and the combination of the launcher and the spacecraft accelerates, then the combination of the launcher and the spacecraft slides without power, entering a uniform motion phase. After reaching the designated position, the transition section and the spacecraft separate, and the spacecraft and the adapter slide off the launcher along the slide rail by inertia, and the adapter and the spacecraft separate, realizing a launch-by-push launch of the spacecraft. This enables large-scale launches of spacecraft and improves flight efficiency.

The utility model discloses weather modification equipment technical field, specifically related to a kind of rain enhancement hail prevention rocket launcher control box, including box, upper panel, lower panel and aluminium plate assembly;The box includes box upper portion and box lower portion, and the box upper portion and box lower portion are rotatably connected;The upper panel cover is located the opening of the box upper portion;The lower panel cover is located the opening of the box lower portion;The aluminium plate assembly is set in the inner bottom of the box lower portion.This control box is high in intelligent level, compatible entity button operation and two kinds of operating modes of capacitive screen touch operation, compatible and rain enhancement hail prevention rocket launcher's two kinds of communication modes of wireless communication and wired communication, and moisture-proof and prevent outdoor work environment from causing damage to each component in box.

Control system (16) for rocket launcher (12), comprising: - a human-machine interface (20) for entering firing parameters and including an integrated electric battery (26), - a control device (22) for receiving firing parameters, and an incoming electric current (34) from the integrated electric battery, the control device comprising: a regulation unit (38) for producing an electric current to be stored (40); a storage unit (42) comprising one or more supercapacitors (44) for receiving the electric current to be stored in the supercapacitor(s) and for producing a release electric current (46); a conditioning unit (48) for receiving the release electric current and for producing an output electric current (36) intended to be sent to the rocket launcher.

The application discloses a weather influencing rocket launching device based on an artificial intelligence algorithm and relates to the technical field of artificial intelligence algorithms.The weather influencing rocket launching device comprises a multi-source data acquisition and adaptation module, which acquires meteorological data, 44 / 56 mm rocket parameters, launching frame states and environmental data; an AI launching parameter optimization module, which optimizes a firing angle and propellant parameters by using a hybrid model and adapts a 4-7.5 km shooting height at a medium-high altitude; an AI risk early warning module, which identifies risks such as ignition abnormalities; an AI timing control module, which corrects sowing and self-destruction timing; a launching execution module, which drives a launching frame and ignition; a self-destruction cooperation module, which ensures that the residual debris is less than or equal to 100 g or low-altitude parachute opening; a data storage module, which stores data; and a man-machine interaction module, which displays and operates.The application uses AI to improve the precision of launching parameters, adapts different caliber rockets and medium-high altitude environments, has high catalyst utilization, has strong data storage and iteration capabilities and comprehensively optimizes rain enhancement and hail prevention operation efficiency.

A multi-launcher space launch assembly includes a movable platform for the assembly, transporting, and vertical positioning of varied launchers. The platform cooperates with a fixed table and a jet deflector, which are situated in a launch area. The infrastructure also includes adaptable fluid refuelling modules compatible with various flow and pressure profiles. The system is adapted to accommodate variations in the height and diameter of launchers by way of modular components.