83 results about "Launch pad" patented technology

The invention provides an unmanned aerial vehicle cluster deployment system, a vehicle-mounted system and an unmanned aerial vehicle cluster deployment method. The system comprises a mechanical transportation module, a processor, an unmanned aerial vehicle maintenance area, a load maintenance area, a battery maintenance area and an unmanned aerial vehicle launching pad. The processor is used for sending a first transportation instruction to the mechanical transportation module when receiving an unmanned aerial vehicle cluster task deployment instruction; the mechanical transportation module is used for receiving the first transportation instruction, transporting the unmanned aerial vehicle to the unmanned aerial vehicle launching pad, transporting the unmanned aerial vehicle to the load maintenance area to obtain a task load and transporting the unmanned aerial vehicle to the battery maintenance area to obtain a battery based on the first transportation instruction, and installing the task load and the battery during transportation of the unmanned aerial vehicle; the unmanned aerial vehicle maintenance area is used for placing unmanned aerial vehicles; the load maintenance area is used for placing task loads; the battery maintenance area is used for placing batteries; and the unmanned aerial vehicle launch pad is used for placing the unmanned aerial vehicle which is transported by the mechanical transportation module and provided with a task load and a battery so as to complete unmanned aerial vehicle cluster deployment. And the unmanned aerial vehicle cluster can be rapidly deployed.

The invention provides an intelligent launching pad management system based on AI visual auxiliary supervision. The system carries out target identification through a YOLO model, carries out behavior sequence analysis in combination with an LSTM model, and carries out cross-modal dynamic feature fusion through spatio-temporal feature alignment, time sequence and spatial feature enhancement and a graph convolution network and graph attention mechanism to generate globally optimized feature representation. And further utilizing a knowledge reasoning engine to combine with the case database and the equipment knowledge graph to generate an intelligent emergency processing scheme. And finally, generating a preliminary potential safety hazard analysis report based on a Transform technology, and performing semantic calibration in combination with the central control module and the domain knowledge base to generate an accurate and normalized alarm analysis report. The system also has the functions of adaptive algorithm optimization, multi-modal data fusion processing and real-time alarm and feedback, realizes the intelligent and automatic management of the launching pad, improves the safety supervision efficiency and fault processing capability, and effectively improves the intelligent level of the safety management of the launching pad.

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.

The utility model discloses an inclined nozzle angle engine shell suitable for a high-altitude aircraft, which comprises a shell assembly, a top cover assembly is matched with the top of the shell assembly, a bottom sealing cover is matched with the bottom of the shell assembly, four inclined nozzles are arranged on one side of the bottom sealing cover, and the four inclined nozzles are uniformly distributed. According to the engine shell with the inclined spray pipe angle suitable for the high-altitude aircraft, the spray pipe is obliquely arranged, the direction of hot airflow sprayed by the spray head is changed, the hot airflow sprayed downwards originally is sprayed towards the side face, and therefore the hot airflow sprayed towards the side face is changed into the hot airflow sprayed towards the side face. Damage of sprayed hot air flow to the launching pad and surrounding objects can be greatly reduced, launching cost is reduced, meanwhile, the reflecting plate is arranged below the spraying pipe, most of heat emitted by the spraying pipe can be reflected to the outer side perpendicular to the spraying pipe, and the influence of the heat of the spraying pipe on the surrounding objects is further reduced.

The invention relates to the technical field of spaceflight launching equipment testing, in particular to a load test device and method for a fixed launching pad of a medium-large carrier rocket. The technical problems that in the prior art, a fixed launching pad load test device is insufficient in bearing capacity and single in loading mode, and multi-point loading and ballasting working condition tests cannot be met at the same time are solved. Comprising a test platform, a test tool, loading equipment and test equipment. The test tool comprises a base, a portal, a loading beam, a support and a lug, and is connected with a foundation embedded steel plate through bolts; the loading equipment consists of a plurality of hydraulic jacks and a hydraulic pump station, and is uniformly controlled by a PLC (Programmable Logic Controller) multi-point synchronous jacking control system; and the test equipment comprises a micrometer and a laser tracker and is used for accurately measuring the deformation of the fixed table body. The device is simple in structure, safe and reliable in structure, flexible in loading mode, high in bearing capacity and capable of achieving multi-point-position and multi-working-condition load tests with the maximum 2025 t ballast and 625 t pull load.

The invention provides a rocket launching pad hydraulic system. The rocket launching pad hydraulic system comprises an oil source, a plurality of sets of control valve sets and a plurality of execution hydraulic motors. The oil source is connected with a plurality of execution hydraulic motors through a plurality of sets of control valve groups; each set of control valve group is connected with one or more execution hydraulic motors; each set of control valve group is used for controlling one or more execution hydraulic motors connected with the control valve group; the oil source outputs high-pressure oil, and the high-pressure oil is conveyed to the execution hydraulic motor through the control valve set and used for driving the execution hydraulic motor to rotate. The execution hydraulic motor is connected with the supporting disc or the windproof pressing device on the launching pad and drives the supporting disc or the windproof pressing device to act. The operation convenience of the hydraulic system controlled by the multiple hydraulic motors is improved, simultaneous action or independent action of the multiple hydraulic motors can be achieved, variable torque output control or high and low speed rotation control of the single hydraulic motor can be achieved, and all redundant backup is achieved from the angle of safety.

The present invention discloses a tunnel construction method, which includes the steps of: manually excavating to form a front-section tunnel, and providing primary support on the inner wall of the front-section tunnel; constructing concrete guide platforms on both sides of the arch bottom of the front-section tunnel; installing a launching pad at the front end of the front-section tunnel, aligning the launching pad with the concrete guide platforms or making the launching pad higher than the concrete guide platforms, assembling a shield machine on the launching pad, and installing a reaction frame on the side of the launching pad away from the front-section tunnel; the shield machine advances along the concrete guide platforms to the rear end of the front-section tunnel, and segments are spliced between the shield machine and the reaction frame; a sealing part is constructed between the segments behind the shield machine and the primary support to form a backfill space; the bottom layer of the backfill space is filled backward from the sealing part towards the front end of the front-section tunnel; the arch waist layers on both sides of the backfill space are filled forward; the top layer of the backfill space is filled backward. This tunnel construction method can avoid radial displacement of the segments during the filling process, avoid misalignment, damage, and water leakage between the spliced segments, improving both the construction quality and the construction efficiency.

The invention relates to the technical field of space flight and aviation, in particular to a liquid rocket launching platform which comprises a fixed launching pad, a movable launching pad, a windproof pressing device, spiral lifting equipment capable of stretching up and down and spiral supporting equipment. The bottom surface of the movable launching pad is fixed with the top surface of the fixed launching pad; the lower ends of the spiral lifting device and the spiral supporting device are fixed to the top face of the movable launching pad and distributed around the flow guide hole of the movable launching pad. The top of the spiral lifting equipment can monitor pressure; a shell of the windproof pressing device is fixedly connected with the part, close to the top, of the spiral lifting equipment, and a telescopic piece of the windproof pressing device is located obliquely above the spiral lifting equipment and can be inserted into a fixing hole of a rocket launching supporting leg placed on the top of the spiral lifting equipment. The supporting stability of the movable launching pad on the liquid rocket can be improved, the influence of wind load on the vertical state of the liquid rocket is avoided, and it is guaranteed that the liquid rocket can be successfully launched.

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 invention relates to a butt joint locking system which at least comprises an erecting vehicle and a launching pad which are suitable for a rocket, the erecting vehicle at least comprises an axis vehicle serving as a chassis and an adapter frame arranged on the axis vehicle, and a loading structure used for bearing the rocket is arranged on the adapter frame. A locking device is arranged on the launching pad, and when the transfer frame is located at a preset butt joint position relative to the launching pad, the locking device locks the transfer frame on the launching pad. The docking lock system further includes a navigation device that guides the erection vehicle to move toward the docking position when the erection vehicle is within a predetermined area near the launch pad, where the docking lock system stops movement of the axis vehicle when the erection vehicle is moved to a distance from the launch pad within a range of a predetermined first threshold, and stops movement of the axis vehicle when the distance from the launch pad is within a range of a predetermined second threshold. And the transfer frame is allowed to slide in a horizontal plane relative to the axis vehicle. By means of the butt joint locking system, butt joint positioning of the erecting vehicle and the launching pad of the rocket can be achieved with high precision.

Systems and methods are provided for automating a delivery station including a launch pad area in which delivery vehicles are loaded with packages for delivery and a queuing area in which additional vehicles wait to proceed to the launch pad area. Input devices, such as cameras, may be provided in the launch pad area to determine when the delivery vehicles are loaded and conditions are satisfied for the delivery vehicles to exit the delivery station. An indication may be provided to the delivery vehicles (or delivery drivers) to exit the delivery station using an output device, such as a speaker and / or a light-emitting device, for example.

The utility model relates to the technical field of climbing casting trolleys, and provides a climbing casting trolley, which comprises a chassis device, the launching device is arranged on the chassis device, and the launching device is used for throwing materials; the adjusting device is arranged on the chassis device, and the adjusting device is used for adjusting the casting angle and the casting force; and the material supply part is arranged on the adjusting device, and the material supply part is used for supplying materials to a launching platform. The throwing device has the advantages that materials are conveyed to the launching pad through the feeding piece, the adjusting device adjusts the throwing angle, and the position of the launching pad is adjusted so as to adjust the throwing force. Through the adjustments, the casting distance is precisely controlled, so that after the adjustments are completed, the launching device can precisely cast the materials to a designated position.

The invention discloses a high-strength rocket launching pad heat-proof coating and a preparation method thereof, belongs to the technical field of material preparation, and solves the problems that a heat-proof coating in the prior art is insufficient in cracking resistance and cannot resist crack initiation and expansion under extreme thermal stress; and the coating and the base material or the interior of the coating are layered. The high-strength rocket launching pad heat-proof coating provided by the invention is sprayed on a metal base material, and the heat-proof coating structurally comprises an organic layer and an inorganic layer in sequence from inside to outside; the base material of the organic layer comprises a resin-based heat-proof coating FRC-100; the base material of the inorganic layer comprises a water-hardened inorganic fireproof coating FRC-410, high-silica glass high-temperature-resistant inorganic long fibers are added in the inorganic layer, and an upper steel wire mesh and a lower steel wire mesh are embedded in the inorganic layer; and a KH-560 silane coupling agent layer is sprayed between the organic layer and the inorganic layer. Through the progressive design of the three elements of interface bonding, microcosmic enhancement and macroscopic stabilization, the crack resistance and the self stability of the heat-proof coating are remarkably improved.

The application relates to a launching platform outside-inverted supporting arm which comprises a supporting arm body and an actuating cylinder arranged on the left side of the supporting arm body, the lower end of the supporting arm body is hinged to a first support fixed on a launching platform frame through a first pin shaft, the actuating cylinder comprises a cylinder body, the lower end of the cylinder body is hinged to a second support fixed on the launching platform frame through a second pin shaft, a piston is arranged in the cylinder body, the piston is coaxially fixed with a piston rod which extends out of the upper end of the cylinder body, the piston rod is hinged to a third support fixed on the middle part of the left side of the supporting arm body through a third pin shaft, a rubber shock absorber is arranged in the cylinder body below the piston, the rubber shock absorber is provided with an air hole which penetrates the rubber shock absorber from top to bottom, the air hole is connected with a gas charging and discharging channel, and a reset spring is arranged in the cylinder body above the piston and sleeved on the piston rod. The supporting arm has the advantages of simple structure, convenient control, sensitive action, safety and reliability and strong practicability.

The present invention discloses a hoisting and erecting device for a rocket offshore launch platform, which relates to the field of hoisting and erecting technology, and comprises a fixed frame and a steel wire rope, wherein a rotating shaft mechanism is embedded and installed on the top of the fixed frame, and an erecting frame is hingedly connected to the right side of the fixed frame through the rotating shaft mechanism, and a docking arm is fixedly installed on the top of the erecting frame, and a connecting ring is arranged on the top of the erecting frame. The hoisting and erecting device for a rocket offshore launch platform provides a supporting force for the bottom of the erecting frame that is gradually erected through an auxiliary support component, so that when the erecting frame is erected, the device not only reduces the load-bearing force of the flexible steel cable, but also improves the stability of the erecting frame during erection. In addition, an auxiliary fixing component is arranged, which has a better fixing effect on the fixed frame, enhances its connection effect with the offshore launch platform, and makes the fixed frame have a better gripping force on the launch platform, so as to improve the stability of the fixed frame, which is conducive to providing a stable working environment for the winch.

The invention provides an erection control method, device and equipment based on Kalman filtering, and the method comprises the steps: carrying out the time updating of Kalman filtering according to a posterior state result at a previous moment, and obtaining a prior state result at a current moment; whether the corresponding angle sensors are in an expected state at the current moment or not is judged according to the measurement residual errors of the two angle sensors at the current moment, one angle sensor is installed on the erecting frame, and the other angle sensor is installed on the launching pad; and if at least one angle sensor is in an expected state at the current moment, performing measurement updating of Kalman filtering according to the measurement information of the corresponding angle sensor at the current moment and the prior state result at the current moment, and obtaining a posterior state result at the current moment. According to the method and the device, the adverse effect of oil cylinder shaking, sensor damage or accidental abnormity on the Kalman filtering estimation result can be reduced, so that the control precision of the erecting action is improved, and the control time is shortened.

The present invention relates to the technical field of pipe electrothermal protection, and discloses a pipe electrothermal protection structure for a sea rocket launch pad and its usage method, including a bottom plate. A support rod is fixedly connected to the top of the bottom plate, a groove plate is fixedly connected to the top of the support rod, a sliding plate is fixedly connected to the bottom of the inner wall of the groove plate, and through holes are formed on the surface of the sliding plate. It further includes: a protection component, which includes a protection plate. The bottom of the protection plate contacts the top of the groove plate, and a chute frame is fixedly connected to the bottom of the protection plate. In the present invention, a protection component is provided on the surface of the groove plate to protect the pipe electricity by using the protection component. When it is necessary to repair the pipe electricity, the protection component is started to expand outwards. At this time, the protection component will move away from each other on the surface of the sliding plate so as to repair the pipe electricity structure. An extrusion component is provided on the top of the bottom plate, and the extrusion component is located at one end where the protection plates are close to each other. When the protection plates contract, the extrusion component can extrude the protection component.

The utility model discloses a diversion trench cover plate, and belongs to the technical field of diversion trench cover plates, the diversion trench cover plate comprises a basic module and a cover plate module, the basic module comprises a launching pad, two mounting assemblies are arranged at the top of the launching pad, the cover plate module is arranged on the launching pad, and the cover plate module comprises a cover plate assembly arranged in the launching pad. The cover plate structure comprises a cover plate assembly and a launching pad, a mounting assembly is arranged between the cover plate assembly and the launching pad, and an auxiliary assembly is arranged between the cover plate assembly and the top of the launching pad. According to the cover plate structure, the cover plate main body can be driven to be opened or closed through the arrangement of the cover plate, the cover plate structure can simply and conveniently open or close the cover plate main body when needed, and the practicability is improved.

An apparatus for payload delivery to a cell includes a laser source configured to generate laser energy and a substrate implanted with photoacoustic launch pads. The apparatus is configured to create a pore in a cell membrane by: absorbing the laser energy by the substrate; increasing the temperature of the photoacoustic launch pads in response to the laser energy; creating a vapor nanobubble by causing fluid surrounding the cell to absorb heat and expand in response to the increased temperature of the photoacoustic launch pads; causing the vapor nanobubble to collapse, disrupting a membrane of the cell; forming a pore in the cell membrane in response to disrupting the membrane of the cell; and delivering a payload into the cell based on causing fluid surrounding the cell containing the payload to enter the cell via the pore.

The present invention provides a containerized carrier rocket aiming system for emergency launch, comprising: a launch box, an inertial measurement unit (IMU), a launch platform, and a camera device. The launch box is designed to be placed horizontally on the ground. The IMU is installed in the launch box, away from one end of the rocket body and located on the long axis of the launch box, and is horizontally fixedly connected to the bottom plate of the launch box. The launch platform is hinged to the launch box and is used to drive the rocket body to complete an upright position from a horizontal position in the box to a vertical position, or to reverse from a vertical position to a horizontal position in the box. The rocket body is placed on the launch platform of the launch box and can complete a certain angle of rotation. The camera is installed in the launch box, facing the scale grid at the rear of the rocket body, and is used to read the angle value displayed on the scale grid. The present invention can meet all firing requirements without a firing dead zone, thereby improving reliability.

The utility model provides a quick anti-loose fixed boarding ladder for a vehicle-mounted unmanned aerial vehicle launching pad. The quick anti-loose fixed boarding ladder comprises a boarding ladder assembly and a plurality of lock catch assemblies, the boarding ladder assembly is rotationally arranged on the side portion of the vehicle body seat plate, a plurality of fixing pieces are arranged on the side portion of the boarding ladder assembly, and the lock catch assembly is arranged on the unmanned aerial vehicle launching pad; the boarding ladder assembly can rotate downwards to a boarding position and rotate upwards to a locking position relative to the boarding ladder assembly, and when the boarding ladder assembly is located at the locking position, the lock catch assembly is matched with the fixing piece in a locking mode. The quick anti-loosening fixed boarding ladder for the vehicle-mounted unmanned aerial vehicle launching pad can position and limit the position of the unmanned aerial vehicle launching pad after being lifted, solves the problem of safe fixation of the unmanned aerial vehicle launching pad in the transportation process, improves the safety coefficient of the unmanned aerial vehicle launching pad in the moving transportation process, is convenient for personnel to step on the vehicle to carry out operation after being put down, and improves the safety of the unmanned aerial vehicle launching pad. The whole structure is simple, operation is convenient, and manufacturing cost is low.

This invention relates to a docking and locking system, comprising at least an erector and a launch pad suitable for a rocket. The erector includes at least an axle carriage serving as a chassis and a transfer frame mounted on the axle carriage, with a superstructure for supporting the rocket mounted on the transfer frame. A locking device is provided on the launch pad, which locks the transfer frame to the launch pad when the transfer frame is in a predetermined docking position relative to the launch pad. The docking and locking system also includes a navigation device that guides the erector towards the docking position when the erector is within a predetermined area near the launch pad. When the erector moves to a distance relative to the launch pad within a predetermined first threshold, the docking and locking system stops the axle carriage and allows the transfer frame to slide horizontally relative to the axle carriage. Using the docking and locking system of this invention, high-precision docking positioning of the rocket's erector and launch pad can be achieved.

A system and method for automating markerless motion capture by integrating radar tracking, embedded computing, machine vision, and machine learning techniques. A radar gun tracks object speed and triggers an embedded computer system. The embedded system decodes signals from the radar gun and triggers high-speed cameras to capture video footage. Machine learning algorithms optimize camera settings and triggering accuracy over time by analyzing captured biomechanical data.

The present invention relates to the technical field of rocket hot launch, and discloses an offshore rocket hot launch erection device and an erection method. The erection mechanism includes a deck. A support frame is fixedly connected to the top of the deck, and an erection frame is rotatably connected to the top of the support frame. When the rocket needs to be erected, the erection oil cylinder is started to extend, pushing the fixed block to move, pushing the push plate to move. When the push plate moves, it will push the first connecting rod to move, causing the first connecting rod to rotate and fold, pushing the first fixed frame to rise, thereby driving the erection frame to rotate on the top of the support frame, making the erection frame erect. At the same time, when the push plate moves, it will also slide on the inner wall of the sliding groove, making the rocket slowly erect until the rocket stands on the launch pad, changing the inclined erection oil cylinder into a horizontal erection oil cylinder, reducing the influence of the hull shaking on the erection oil cylinder, and making the thrust applied by the erection oil cylinder more stable.

The invention, which belongs to the unmanned aerial vehicle cluster autonomous launching field, discloses a rocket-assisted unmanned aerial vehicle cluster autonomous launching control system comprising a ground control station, N unmanned aerial vehicle clusters and X standby unmanned aerial vehicle clusters. The vehicle-mounted ad hoc network data chain is wirelessly connected with all airborne ad hoc network data chains at the same time, and uplink and downlink remote control telemetry data are sent and received through an antenna; each unmanned aerial vehicle is provided with an airborne exploder and is equipped with a booster rocket; the ground control station sends a take-off instruction to the cluster unmanned aerial vehicle, ignition is executed through an airborne exploder of the unmanned aerial vehicle, and autonomous and ordered rocket boosting launching control of the one-station multi-vehicle type unmanned aerial vehicle cluster is achieved; after the rocket is successfully ignited, the unmanned aerial vehicle is pushed away from the launcher, and the ignition cable is stressed and tightened to be automatically disconnected from the exploder; after fuel burns out, the rocket is safely separated from the unmanned aerial vehicle under the action of gravity and aerodynamic resistance, and rocket boosting launching is completed. According to the invention, the system complexity is reduced, and the launching efficiency and safety are improved.

The invention provides a launch preparation device of a carrier rocket and a remote control system. A carrier is arranged below a transfer rack; the launching platform is arranged at the tail end of the transfer rack; the erecting frame is hinged to the transfer rack; the holding clamp mechanism is arranged on the erecting frame and is configured to clamp a carrier rocket; the bracket mechanism is configured to be connected with the tail end of the carrier rocket; in the first state, the locking mechanism is connected with the bracket mechanism so as to axially limit the bracket mechanism; in the second state, the locking mechanism is separated from the bracket mechanism; the two ends of the hydraulic telescopic piece are connected with the erecting frame and the end, close to the launching platform, of the transfer rack correspondingly. The temperature adjusting assembly is arranged on the transfer rack, and the temperature adjusting assembly is configured to adjust the temperature in the fairing of the carrier rocket before the carrier rocket is erected; the electric control assembly is arranged on the side wall of the transfer rack and electrically connected with the clamp holding mechanism, the hydraulic assembly, the locking mechanism and the temperature adjusting assembly. The preparation time of the carrier rocket before launching is shortened.

The utility model provides a water rocket launching pad convenient for physics teaching, which comprises a base and an overturning platform, the overturning platform is provided with a quick joint for connecting a water rocket, and a movable outer ring sleeved on the quick joint; one end of the first wire core is connected with the movable outer ring and can pull the movable outer ring to axially move along the quick connector; one end of the second wire core is connected with the overturning platform, and the pulling force of the second wire core on the wire coil can enable the overturning platform to rotate around the first direction; one end of the tension spring is connected with the turnover platform, the other end of the tension spring is connected with the base, and the tension applied to the turnover platform by the tension spring can enable the turnover platform to rotate around the second direction. The water rocket is controlled to launch through the first wire core, meanwhile, the posture of the overturning platform is controlled through the second wire core, on the premise that an operator keeps a safe distance from the water rocket, the control structure is simplified, the pitching angle of the overturning platform is conveniently controlled, and meanwhile the water rocket can be conveniently overturned. And the motion relation among the structures of the water rocket launching pad can be displayed for young students.

The invention belongs to the technical field of micro-particle acceleration, and particularly relates to a single-micro-particle high-pressure pneumatic acceleration device based on a reverse gate type structure and a use method.The device is characterized in that the interior of a high-pressure air chamber is divided into a first air chamber and a second air chamber through a piston; the high-pressure air source is respectively communicated with the first air chamber and the second air chamber; the first air chamber is communicated with the atmosphere through an air pressure control valve; the second air chamber is communicated with the contraction section of the Laval accelerating tube; the piston extends into the contraction section of the Laval accelerating tube; the expansion section of the Laval accelerating tube is communicated with the bore; the reverse door type launching pad comprises a fixed shell and a reverse door; the fixed shell is connected and communicated with the bore; the reverse door is installed in the fixed shell and is an elastic hemisphere. Compared with the prior art, the problems that in the prior art, single microparticle pneumatic accelerated emission is prone to being interfered by airflow, equipment is complex or difficult to achieve, and cost is high are solved. According to the scheme, through the design of the reverse gate type launching pad, controllable and airflow interference-free pneumatic acceleration of a single microparticle is achieved.