433 results about "Rocket launch" patented technology

The multi-channel data acquisition system provided by the present invention includes an acquisition computer, an acquisition display and an acquisition end printer, the acquisition computer is equipped with a plurality of A / D acquisition cards and a buffer, and each A / D acquisition card input terminal is provided with a voltage Isolation conditioner, the acquisition computer is connected to the control computer and the echo computer through the back end of the Ethernet, the control computer is installed with a dual-screen display card, and connected to the master and slave monitors and the control terminal printer respectively, and the echo computer is connected to the echo display and the echo printer. The invention also provides a method for multi-channel data acquisition. The invention has the advantages of being able to measure multiple channels, suitable for multi-signal recording occasions, convenient display and printing of data and waveforms, high degree of automation and accuracy, and conducive to intelligent acquisition, especially suitable for rocket launching and weapon testing , petrochemical and other dangerous and heavily polluted on-site signal detection and recording occasions.

The invention discloses an automatic docking and falling connector with an active follow-up function of a carrier rocket. The connector comprises an executing mechanism, signal detection devices, an error compensation mechanism and a locking device; a base frame of the executing mechanism is fixedly connected with oscillating bars stretching out from a carrier rocket launch tower, the circumferential direction of the base frame is symmetrically provided with hydraulic cylinders, and the cylinder bodies of the hydraulic cylinders are fixedly connected with the base frame; the ends of piston rods of the hydraulic cylinders are fixedly connected with sliding blocks, the sliding blocks are connected with the error compensation mechanism through connecting rods, and the connecting rods are connected with the sliding blocks and the error compensation mechanism through spherical hinges; the signal detection devices are arranged at the upper end and lower end of the base frame and are corresponding to the positions of protruding marks on a rocket body, the protruding marks at the two ends are mutually perpendicular, one protruding mark is parallel to the axial direction of the rocket body, and the extension line of the protruding mark penetrates the charging valve center line of the rocket body. The automatic docking and falling connector with the active follow-up function of the carrier rocket can reduce the force borne by the rocket body and shorten the docking and falling time.

A rocket launch system (1) includes a tubular rocket launcher carriage (2) with electromotive cableway traction drives (26) conveyed beneath a two axis pivot (63) anchored to the earth, elevated into a co-axial transfer tube (124, 143) leading to three primary tether cables (27) whose weight is offset by balloons (164). The carriage is conveyed to a docking station (166) supported into the stratosphere by a pair of secondary cables (184) suspended under an attachment frame (162) for tensioning balloons. The carriage is engaged by a carriage end gripper (196) guided by two secondary and two tertiary cables (186) and lifted by a lower hoist (198) guided by the secondary cables. This lower hoist is supported by an upper hoist (168) suspended from the tensioning balloons attachment frame. The carriage, which engages a lift ring (183) guided by two secondary cables, is elevated further, rotated as desired, with rocket release and nearly recoilless ejection during freefall of the carriage, with engine ignition occurring at a safe distance.

The invention belongs to the technical field of rocket launching, and particularly relates to a water injection, cooling and denoising system for rocket launching. The system comprises outer water injectors, inner water injectors, a lattice girder, a lower water storage device, two water injection main lead pipes and a head water tank, a launching site is provided with the head water tank, the two water injection main lead pipes are led out from the head water tank and are both connected with the lower water storage device, the outer water injectors and the inner water injectors are arranged on the lower water storage device, the outer water injectors are positioned on two sides of a travel portion of a launching platform and parallel to the travel direction of the launching platform, top ends of the outer water injectors are higher than a platform top of the launching platform, tops ends of the inner water injectors are lower than the platform top of the launching platform, and the lattice girder is used fro supporting the outer water injectors and the inner water injectors. The system is developed aiming at bundled rocket launching technical conditions, and is applicable to occasions such as single-nozzle rocket launching test and simulation test adopting similar heat launching technical conditions.

This invention will allow a reusable thrust-powered sled mounted on an inclined track to launch spacecraft or airborne vehicles from earth at supersonic speeds using existing technology properly integrated into an inclined track system. If launched up a tunnel track, a rear blast shield can trap the rocket exhaust to provide a pneumatic boost upon launch. The sled can also launch ramjet or scramjet powered vehicles from earth by achieving the Mach 2+ speed necessary to ignite their engines. This system is much safer than the traditional method of launching rockets since weather is less a factor and the launch can be aborted if problems develop. Moreover, it is far less costly since the engines on the sled can be reused hours after a launch and the track can accommodate a variety of sleds to launch objects of many different sizes.

The invention relates to the technical field of speed reducers, in particular to a bevel gear-double cycloid speed reduction device for a rocket launching movable platform. The device is a two-stage speed reduction device characterized by comprising a bevel gear pair and double-cycloid transmission, wherein (A) the cycloid transmission comprises a base, an output shaft, support bearings, a cycloid wheel, an eccentric bearing, an inner cycloid gear ring, a front base, an input shaft and a W output mechanism, the input shaft is supported in an inner hole of the front base through a bearing, the shaft extension end is connected with the eccentric bearing, and the input end is connected with a big bevel gear; the front base is integrated with the inner cycloid gear ring and the base in sequence; the output shaft is supported in the inner hole of the base through a bearing; and (B) two symmetrically installed small bevel gear shafts engaged with the big bevel gear are supported in wall holes of a front base box through bearings, and the small bevel gear shafts are connected with a motor; and another small bevel gear shaft is connected with a manual handle. The invention has the advantages of two-stage speed reduction, small axial size, light weight and high-degree lightweight; cycloid gear teeth are uninterrupted, so that the bearing capacity is greater than that of planet transmission with only four planet wheels; and the cost is low and is reduced to 40-55%.

The invention discloses a monitoring system for a carrier-rocket launch fuel-gas flow field. The monitoring system includes a first test main array group and a second test main array group, wherein the first test main array group includes an in-diversion-hole fuel-gas flow field test array, a table-board fuel-gas flow field test array and an on-cross-beam fuel-gas flow field test array. The second test main array group includes a near-diversion-trench-entrance fuel-gas flow field parameter test array, a diversion-trench-drainage-guide-face fuel-gas flow field parameter test array, a guide-trench-top fuel-gas flow field parameter test array and a diversion-trench-side-face fuel-gas flow field parameter test array. The test scheme of the carrier-rocket launch fuel-gas flow field is applicable to carrier-rocket launch fuel-gas flow field testing and fuel-gas-flow ablation characteristic assessment and capable of being transplanted conveniently into a shrinkage-scale launch simulation test or fuel-gas flow field testing and fuel-gas ablation characteristic assessment in a special simulation test.

The invention relates to a spatial flexible filter supporting mechanism, which comprises a mirror seat and at least three flexible supporting pieces, wherein each flexible supporting piece consists of a fixed end, an axial stress unloading part, a radial stress unloading part and an adhesive boss; the fixed ends are connected with the mirror seat through screws; the axial stress unloading parts are positioned between the fixed ends and the radial stress unloading parts; the adhesive bosses are arranged at the ends of the radial stress unloading parts; the part of the filter, which is close to the rim, is adhered with the adhesive bosses through adhesives; and the gravity of the filter is positioned in a polygon consisting of the adhesive bosses. The structural stress resistance and the thermal stress resistance of the filter supporting mechanism are improved; due to the flexible shock absorption function, the filter supporting structure can resist the impact shock at a rocket launch section, and can be used in the fields of designing aerospace and aviation filter supporting structures, designing structures of optical active supporting mirrors, designing structural shock absorption and the like.

The present invention provides a search method for a multi-constrained earth-moon transfer orbit cluster with equal launch intervals. The method is used for designing n earth-moon transfer orbit clusters meeting multiple constraints and with equal launch intervals within a launch day, and the method takes full advantage of a feature that rocket launch parameters can be adjusted. The method is completed through outer-layer and inner-layer search, and the inner-layer search comprises preliminary search and refine search of a single orbit. A preliminary orbit search algorithm adopts a simulated annealing simplex hybrid algorithm, and a refine orbit search algorithm adopts a class differential correction algorithm. Firstly, preliminary design and search of the orbit are carried out based on an improved conic curve splicing method, an initial orbit parameter value is rapidly calculated, the refine orbit search algorithm is used to carry out refine design on the orbit, and an earth-moon orbit meeting the constrained condition is obtained. The outer-layer search completes continuous multi-orbit search with equal launch intervals, so that n earth-moon transfer orbits meeting the multiple constrained conditions with equal launch intervals are finally obtained.

The invention provides an erecting device for rocket launching and a rocket launching auxiliary system. The erecting device comprises an erecting arm, an umbilical cord rod arranged on one side of the erecting arm and a power cylinder used for enabling the umbilical cord rod to rotate relative to the erecting arm; and one end of a erecting arm is connected with one end of the umbilical cord rod through a rotating shaft, one end of the power cylinder is fixedly connected to the part, close to the rotating shaft, of the umbilical cord rod, and the other end of the power cylinder is used for fixedly connecting with a fixing part arranged at the other side of the erecting arm. According to the erecting device and the rocket launching auxiliary system, the erecting arm can be pre-leveled by enabling the umbilical cord rod to be coaxially connected with the erecting arm, so that the umbilical cord rod can fall back quickly at a moment when the rocket took off, the structure of the erecting device is simplified, and the reliability of backward fall of the umbilical cord rod is improved.

The invention discloses a detection system for a single-jet-pipe rocket launch water-spray cooling noise-reduction effect. The system includes a portal frame, a simulating rocket, a rocket positioning and adjustment device, a water-spray device, a noise detection device and a fuel-gas flow field and fuel-gas-flow ablation intensity detection device. The water-spray device is installed around an engine jet pipe of the simulating rocket. The noise detection device includes a noise test array frame installed around the simulating rocket and noise array sensors installed on the noise test array frame. The fuel-gas flow field and fuel-gas-flow ablation intensity detection device includes a jet-flow field and ablation intensity test board installed under the simulating rocket and a jet-flow field and ablation intensity sensor array installed on the jet-flow field and ablation intensity test board. Based on the system, researches of a rocket launch water-spray cooling noise-reduction mechanism and effect evaluation can be carried out and a reference is also supplied to the water-spray cooling noise-reduction effect of follow-up complete simulating rocket launch technical conditions.

The invention relates to the technical field of air attack, and discloses an air-to-surface rocket fire extinguisher and method. The air-to-surface rocket fire extinguisher involved in the method comprises a multi-rotor aircraft, rocket fire-extinguishing bombs, and a rocket launcher. The air-to-surface rocket fire extinguisher is connected to the rocket launcher by means of a bottom mounting hole 8. The rocket fire-extinguishing bombs 15 are uniformly distributed in the rocket launcher. The air-to-surface rocket fire extinguisher is capable of completely overcoming the influence of such factors as narrow surface and buildings on fire extinguishment and rescue by launching high-efficiency fire-extinguishing bombs in high accuracy at set distances from multiple directions and multiple angles, and is quick in action, and convenient to fold and unfold; a large number of fire-extinguishing bombs can be carried; therefore, the air-to-surface rocket fire extinguisher will become a new emerging air power for fire extinguishing equipment in China.

The invention relates to a pressure reducer air supply loop adopting redundant design and a control method. The pressure reducer air supply loop comprises pressure reducers, electromagnetic valves, hand stop valves, pressure gauges and a pressure sensor which are arranged on a low-temperature propellant pressurization air source intake pipeline. A first throttling valve, a second throttling valve, a third throttling valve and a fourth throttling valve adjust the pressure reducers. The pressure gauges monitor pressure of outlets of the pressure reducers. The pressure sensor monitors air supply pressure. Switching of the pressure reducers is controlled by the three-position two-way electromagnetic valves. According to the pressure reducer air supply loop adopting redundant design and the control method, redundancy of the pressure reducers is achieved, the pressure reducers can be electrically switched according to collected data, the requirement for a narrow window of air supply in a task is sufficiently met, the single-point problem of ground pressurization air supply of a low-temperature propellant rocket is solved, the goal of zero-window launching is realized, and rocket launching reliability is improved.

The invention discloses an open-cycle liquid oxygen kerosene engine system and a use method. The system uses low-cost liquid oxygen and kerosene as propellants to meet starting and ignition functionsof an engine, reduce the production cost of the engine, and meet requirements of non-toxic rocket launch at the same time. The engine system adopts a turbine, a kerosene pump and an oxidant pump, wherein the turbine, the kerosene pump and the oxidant pump are coaxially arranged; an inlet of the oxidant pump communicates with an oxidant supply source, an inlet of the kerosene pump communicates withthe kerosene supply source, and an outlet of the oxidant pump and an outlet of the kerosene pump communicate with a thrust chamber; a gunpowder starter is arranged on the turbine; the turbine communicates with a gas generator through a pipeline, an exhaust pipe is arranged on the turbine, and a pyrotechnic igniter is installed on a head part of the gas generator; one end of an oxidant output secondary pipeline communicates with an oxidant output main pipeline, the other end of the oxidant output secondary pipeline communicates with the gas generator; and one end of a kerosene output secondarypipeline communicates with a kerosene output main pipeline, and the other end of the kerosene output secondary pipeline communicates with the gas generator.

A water bottle rocket system for launching single rockets, multistage rockets, multiengine rockets or multistage multiengine rockets. Rocket bodies are comprised of ordinary plastic beverage bottles. The propellant used is preferably water and compressed air. The system offers adjustable launch supports to vary the launch angle for both single engine or multiple engine rockets. A charging manifold is provided for charging with liquid or gas propellant. Multiengine rockets are simultaneously charged with propellant through launch base internal channels.

Systems and methods are disclosed for passively detecting air turbulence using one or more infrasonic sensors mounted on an aircraft. The system may include one or more infrasonic sensors that are mounted on the aircraft and configured to detect infrasound. The system may also include a processor configured to receive output signals from the one or more infrasonic sensors and detect air turbulence away from the aircraft based on the output signals received from the one or more infrasonic sensors. The detected air turbulence may include natural or man-made turbulence including wake turbulence, clear air turbulence, mountain waves, or events such as a rocket launch.

A rocket launch tower is provided, including: a vertical support structure including two or more guide towers defining a vertical shaft between the two or more guide towers, each guide tower including one or more pulleys engaging one or more cables; a platform located within the vertical shaft and connected to the one or more cables; a drive mechanism that applies a force to the one or more cables to accelerate the platform along a trajectory within the vertical shaft; one or more sensors collecting data regarding the position of the platform along the trajectory within the vertical shaft and communicating the platform position data to a controller, the controller in communication with an acceleration control system including one or more brakes acting on the platform; wherein the controller causes the acceleration control system to actively correct the platform acceleration towards an intended platform acceleration.

The invention discloses an eight-supporting-point leveling method for a rocket launching platform. The method comprises the following steps: (1) analyzing stress situations under different working conditions, determining eight stress supporting points, and mounting leveling support legs on the supporting points; (2) determining a leveling reference point, measuring the ground height values of other supporting points, calculating the height differences between the other supporting points and the reference point, namely, the total extension amount of the support legs, converting the total extension amount into the rotation circle number of the support legs, and calculating the leveling accuracy of the other supporting points according to dynamics simulation, platform structural simulation and the positions of corresponding supporting points; (3) lifting the platform till the supporting points are suspended, and adjusting the extension and retraction of the support legs in sequence according to the rotation circle number till the requirement of the leveling accuracy is met; (4) lowering the platform till the support legs are landed to finish leveling. By adopting the leveling method, the structure of a leveling system is simplified, operation becomes easy and convenient, and the leveling accuracy is high.

The invention discloses a swing rod mechanism of a rocket launching platform and a swing rod applied to the mechanism and relates to equipment for the rocket launching platform. The swing rod mechanism is mounted on the umbilical tower of the launching platform and used for bearing a feed-discharge gas supply pipeline and a satellite cable. The swing rod mechanism comprises the swing rod, a connecting device for connecting the swing rod to the umbilical tower and a drive device for driving the swing rod to rotate. The drive device comprises a rack for driving a driven gear, a hydraulic oil cylinder connected with the rack and a hydraulic control system for controlling the hydraulic oil cylinder. The hydraulic oil cylinder drives the swing rod to rotate sequentially through the rack, the driven gear and a rotary shaft.

The invention discloses an aircraft carrier rocket assist catapult which is mainly composed of a catapult track, a booster rocket and a canister launcher. The catapult track is arranged on a hangar foreground of a shipboard aircraft. The shipboard aircraft catapults directly on the catapult track. The rear side of the catapult track and a hangar floor are located in the same plane and connected through a pin shaft, a catapult track groove is formed in the middle, the rocket canister launcher is arranged on the lower side, and an upper opening of the canister launcher is tightly attached to the track groove. A sliding block tractor is arranged in the groove. A tractor hanging machine pull rod part is arranged on the upper portion of the catapult track, and a rocket hanging device is arranged on the portion, stretching into the canister launcher, of the lower portion of the catapult track. A backflow discharge flue and the canister launcher are arranged side by side. The booster rocket can be repeatedly used. After a first airplane is ignited and launched, the canister launcher is blown, then an appropriate amount of liquid propellant is injected into the booster rocket, and ignition is carried for launching again. The front and back slope of the catapult track can be adjusted through a hydraulic lifting device, and the sliding block tractor and the canister launcher automatically return under the effect of a spring and the track slope.

The related rocket-draw-line form manual thunder-initiation system comprises: a rocket launch control device, a rocket draw-line device, and a monitor and measurement system with a video camera, a camera, a digital high-speed video camera, and all of an electric field meter, an electric field variometer and a lightning magnetic field detector connected to a computer. Wherein, connecting the gas pipe from air compressor in launch-control chamber to the pneumatically- operated switch lighter under rocket, connecting the wire drawn on rocket tail axis to the draught rod grounded by a coaxial shunt arranged with an E / O converter in a Faraday iron cage with insulator. With this invention, it obtains lots of simultaneous observed data and plays an important role in our research on thunder and lightning physics and manual thunder initiation.

The invention provides a rocket launching demonstration device and a demonstration method. The rocket launching demonstration device comprises a rocket assembling device and a rocket launching device; the rocket assembling device comprises an assembling module, an assembling table, an operation button and a storage tank; the assembling module is an undistorted model corresponding to a plurality of parts of the Long-March II-F rocket; an assembling groove for correspondingly accommodating the assembling model is formed in the upper end face of an assembling station; the operation button comprises a launching button arranged on the assembling table; the storage tank is arranged in the assembling table; the rocket launching device comprises a rocket launching site tower dynamic simulation model and a Long-March II-F rocket dynamic simulation model; a linear guide rail for the Long-March II-F rocket dynamic simulation model to be lifted and descended is arranged in the rocket launching site tower dynamic simulation model. According to the rocket launching demonstration device and the demonstration method provided by the invention, the rocket assembling table is added in the front of a launching tower; when rocket launching needs to be demonstrated, a small rocket model needs to be assembled firstly, understanding of audiences for a rocket structure is further reinforced by a scene, and the rocket launching demonstration device and demonstration method further accords with the requirement of a science and technology museum for dissemination of scientific knowledge.

The invention discloses a thermal protection method for a launch pad. The thermal protection method is characterized in that water spray main channels are arranged on components of the launch pad, water nozzles are formed in the various water spray main channels, cooling water sources are connected with the various water spray main channels, cooling water is sprayed out of the various water nozzles after a rocket is ignited, is sprayed on flame of a nozzle of an engine of the rocket and is preliminarily mixed with high-temperature gas flow sprayed out of the nozzle of the engine to form cooling water mist, and momentum and heat are exchanged between the high-temperature and high-speed gas flow and water flow sprayed out of the water nozzles in the procedure, so that the temperature of the gas flow sprayed on the launch pad can be reduced. The thermal protection method has the advantages that the intensity of ablation of the gas spray flow to launch equipment in a rocket launch procedure can be effectively reduced, and the cost is low.

The invention discloses an information control platform used for informationized rocket launching. The information control platform platform comprises a back plate arranged in a case, and a power supply management module, a master control management module, a calculation resource module, a data storage module, a communication management module and a network switching module inserted on the back plate. The power management module supplies power to all the modules of the information control platform; the master control management module is used for realizing centralized management and control ofall the modules; the calculation resource module is used for completing a ground test process, a launching control process and a command process; the data storage module provides a shared space of data storage for the information control platform; the communication management module is used for achieving various wired and / or wireless communication between the front end and the rear end of a rocket launching platform; and the network switching module realizes interconnection and intercommunication of all the modules inside the information control platform. Equipment is highly integrated; the network management and maintenance are convenient; the requirement of fast flexible launching can be met; interfaces are simple; the testing efficiency is high; and the launching period of a commercialrocket can be obviously shortened.

The invention relates to a solid rocket erecting system and an erecting method. The erecting system comprises a constant-displacement pump, a shut-off valve, a reversing valve, a mechanical-hydraulicthrottling valve and an erecting hydraulic cylinder, wherein the mechanical-hydraulic throttling valve is provided with a bypass throttling port and an induction rod; the constant-displacement pump issequentially connected with the shut-off valve and an oil inlet P of the reversing valve through a first pipeline; a working oil port A of the reversing valve is connected with a front cavity of theerecting hydraulic cylinder through a second pipeline, a working oil port B of the reversing valve is sequentially connected with the mechanical-hydraulic throttling valve and a back cavity of the erecting hydraulic cylinder through a third pipeline, and an oil return port T of the reversing valve is connected with an oil tank through a fourth pipeline; and a piston rod of the erecting hydraulic cylinder is hinged to the front half part of a rocket launching tube, and the induction rod of the mechanical-hydraulic throttling valve is connected with a cam mechanism which is arranged at the hingejoint position of the rear half part of the rocket launching tube. The erecting system has the advantages of being simple in structure, easy to control, safe, reliable and high in erecting speed. Theerecting method has the advantages of being reasonable in logic, easy to control, high in efficiency, high in reliability and high in safety.

The invention discloses a leveling control system and method for a rocket launching platform. The leveling control system of the rocket launching platform comprises: a first detector arranged on a movable supporting leg of the rocket launching platform and used for feeding back the length of the movable supporting leg; a second detector used for detecting a first inclination angle of the rocket launching platform relative to the first shaft and a second inclination angle of the rocket launching platform relative to the second shaft; and a control module used for calculating the distance needing to be adjusted of the movable supporting leg by utilizing the first inclination angle and the second inclination angle and controlling the movable supporting leg to be adjusted until the platform meets the precision requirement. By means of the leveling control system of the rocket launching platform, leveling of the launching platform can be rapidly and accurately completed, the second detectoris used for judging the inclination angles in the two axial directions, the control module calculates the distance needing to be adjusted of each movable supporting leg, the corresponding distance isadjusted through the first detector, the control module controls the movable supporting legs to be leveled, and the first detector enables the leveling process to be faster and more accurate.

A system for air-launching a liquid fueled rocket launch vehicle using a tubular rocket support structure for holding the launch vehicle and for supplying the launch vehicle with make-up cryogenics, electrical power, and control signals, and for providing coupling to a launch-assist aircraft. The tubular rocket support structure contains cryogenic fluids, in addition to fuel and oxidizer, to cool the fuel and oxidizer during the pre-launch phase. The tubular rocket support structure has features that keep the liquid fuel and oxidizer from sloshing away from the tank outlet ports to the launch vehicle's rocket engine after release from the aircraft but before rocket launch. In operation, the aircraft controllably releases the tubular rocket support structure containing the launch vehicle, and the launch vehicle then launches from the rocket support structure.

The invention discloses an air reed type slow release mechanism which can improve the reliability of launching a rocket. The air reed type slow release mechanism comprises a gas supply system (1), a slow release cylinder (2), a traction cylinder (3), a soleplate (4), a traction arm (5), a swinging lever (6) and a lever arm (7); the soleplate (4) is connected with a rocket launching pad; the lever arm (7) is fixed on the soleplate (4); the lower ends of the slow release cylinder (2) and the traction cylinder (3) are movably fixed on the soleplate (4) respectively; the upper end of the slow release cylinder (2) is movably connected with the lever arm (7); the upper end of the traction cylinder (3) is connected with the lower end of the traction arm (5); the upper end of the traction arm (5) is fixedly connected with the swinging lever (6); the other end of the swinging lever (6) is movably connected with the lever arm (7); and the gas supply system (1) provides high-pressure gas for the slow release cylinder (2) and the traction cylinder (3). The mechanism can meet the requirement of traction load of 180 KN and can achieve the function of slow release after the rocket is launched.

The invention discloses a rocket weapon or emitter launching system. The rocket weapon or emitter launching system is characterized by comprising a base platform which is fixedly arranged on the ground during use, a rising vertical platform which one end of the rising vertical platform is rotatably fixed at a fixed position of the base platform, an inclined supporting platform which one end of theinclined supporting platform is connected with the rising vertical platform in a rotatable mode and the other end of the inclined supporting platform is a free end, wherein a locking structure is arranged at the position, away from the fixed position, of the base platform, when the rising vertical platform is vertically rotated to a preset angle, the free end of the inclined supporting platform is fixedly locked on the base platform through the locking structure arranged on the base platform. According to the system and the method, a pure mechanical structure scheme is adopted to complete thedesign of a box type rocket launching device, the problems of emission tasks under the conditions of low cost, fast rhythm and high reliability are solved, and the system and the method have the characteristics of easiness in operation, low in cost, high in strength, and the emission mode types of the box type rocket is widened.