105 results about "Launch pad" patented technology

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

The invention discloses a universal liquid carrier rocket launching pad technology. A satellite general assembly test subsystem realizes recovery and detection of a satellite and forms a star cover assembly; the rocket horizontal final assembly test subsystem realizes subsystem test, matching test and total inspection test of a first-stage rocket body and a second-stage rocket body in a horizontal state, and the first-stage rocket body, the second-stage rocket body and a star cover combination body form a whole rocket in the horizontal state; the rocket horizontal transfer subsystem transfers the whole rocket to the fixed launching platform in a horizontal state; the rocket launching subsystem erects the whole rocket and achieves testing, filling and launching of the whole rocket. According to the universal liquid carrier rocket launching pad technology, by adopting a three-plane test launching mode of horizontal final assembly testing, horizontal transferring and vertical launching, the construction cost of a rocket launching site is effectively reduced, the operation process is simplified, the rocket launching efficiency and frequency are improved, and the requirement for rapid and batch launching is met.

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 discloses a data fusion method for predicting the health state of a transmitting station based on digital twinning, and the method comprises the following steps: constructing a virtual entity of the transmitting station, constructing a data source of the transmitting station, fusing health state data, carrying out fault diagnosis and prediction, and carrying out the maintenance decision of the transmitting station: finding out possible hidden danger factors of the transmitting station; all components of the launching pad are predicted and maintained according to a previous strategy, potential faults are reduced, and the use value is maximized. The reliability and the safety of the transmitting station are improved, the digital twin can monitor the state of each part of the transmitting station in real time and identify potential fault problems in advance, the preventive maintenance can reduce accidental faults, improve the safety and the reliability of the transmitting station and avoid transmitting failures caused by the faults, and through real-time data analysis, the reliability of the transmitting station is improved. The health state of the transmitting station is dynamically updated, possible faults are predicted, and a maintenance plan is adjusted according to actual conditions.

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

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

The invention provides launch preparation equipment and a launch preparation system of a carrier rocket. The launching preparation equipment comprises a transfer platform system, a chassis assembly, an erecting frame, a hydraulic system and a movable launching platform. The launching preparation equipment comprises a basic configuration and a simplified configuration; when the launching preparation equipment adopts a basic structure, the launching preparation equipment comprises a transfer platform system, a chassis assembly, an erecting frame and a hydraulic system and is used for being matched with a first launching station to form a launching preparation system; when the launching preparation equipment is of a simplified structure, the launching preparation equipment comprises a transfer platform system, an erecting frame and a movable launching platform and is used for being matched with a second launching station to form a launching preparation system. The launching preparation equipment provided by the invention can be assembled into a basic configuration and a simplified configuration, is respectively adaptive to a first launching station and a second launching station, and can be flexibly combined with the launching stations according to different conditions of the launching stations, so that the additional launching cost is greatly reduced.

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

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

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 invention relates to the technical field of pipe electric heating protection, and discloses a seaborne rocket launching pad pipe electric heating protection structure and a using method thereof.The seaborne rocket launching pad pipe electric heating protection structure comprises a bottom plate, a supporting rod is fixedly connected to the top of the bottom plate, a groove disc is fixedly connected to the top of the supporting rod, a sliding plate is fixedly connected to the bottom of the inner wall of the groove disc, and a through hole is formed in the surface of the sliding plate; the device further comprises a protection part, the protection part comprises a protection plate, the bottom of the protection plate makes contact with the top of the groove disc, and the bottom of the protection plate is fixedly connected with a sliding groove frame. According to the invention, the surface of the groove disc is provided with the protection part, the protection part is used for protecting the pipe power supply, when the pipe power supply needs to be overhauled, the protection part is started to expand outwards, and at the moment, the protection part moves away from each other on the surface of the sliding plate, so that the pipe power supply structure is overhauled, and the top of the bottom plate is provided with the extrusion part. The extrusion parts are located at the ends, close to each other, of the protection plates, and the extrusion parts can extrude the protection parts when the protection plates contract.

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 utility model relates to a launching pad toy for simulating the launching of a space shuttle, which comprises a base, a left pier, a right pier and a bridge frame, the left pier and the right pier are arranged on the base at intervals, the bridge frame is transversely arranged on the left pier and the right pier, the bridge frame comprises a launching bridge and a launching frame, one end of the launching bridge is rotatably connected with the left pier through a rotating shaft, and the other end of the launching bridge is rotatably connected with the right pier through a rotating shaft. The launching bridge is provided with an installation cavity close to the rotating connection position of the launching bridge, the launching frame is embedded in the installation cavity, arranged on the rotating shaft in a sleeving mode and rotationally connected with the launching bridge, an inner cavity is formed in the left pier, a transmission mechanism is arranged in the inner cavity and connected with the launching frame, the transmission mechanism comprises a driving part, and the driving part penetrates through the left pier and extends to the outside. According to the technical scheme, after assembly is completed, a matched space shuttle toy can run, the scene launched by a space shuttle can be simulated, then the playability is high, children can have the continuous playing interest, and the edutainment function of the children can be played for a long time.

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 invention discloses a control method for accurately and quickly obtaining various elements based on a multi-network model, comprising the following steps: setting an element solving neural network model to obtain shooting elements in a windless state, wherein the shooting elements include a sight, a range and a ballistic height; setting a longitudinal wind neural network model to obtain the average longitudinal wind during the flight of a shell according to the sight and the ballistic height in the shooting elements in the windless state, as well as the actual wind speed and wind direction, as the average ballistic longitudinal wind; setting an element correction neural network model, taking the average ballistic longitudinal wind as input, outputting a sight correction amount, correcting the shooting elements in the windless state, and obtaining the final shooting elements; adjusting the launch platform according to the final shooting elements, and launching the shell. The control method for accurately and quickly obtaining various elements based on a multi-network model provided by the invention fully considers real-time meteorology, can improve the accuracy of element solving, has a small amount of calculation, is short in time consumption, does not require cumbersome firing table query, can be deployed in a fire control computer, and can effectively avoid missing the target.

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 ground launching rack which comprises a supporting module, the supporting module comprises a spliced frame structure, a lifting mechanism, a first half shaft sleeve and a second half shaft sleeve are arranged at the top end of the supporting module, and the first half shaft sleeve is arranged at the top end of the supporting module and located below the lifting mechanism; the second half shaft sleeve and the first half shaft sleeve are detachably connected to form a first cylindrical structure, the rotating module is used for mounting a missile, the lifting mechanism is used for lifting the rotating module, a rotating shaft matched with the first cylindrical structure is arranged on the rotating module, and the limiting mechanism is arranged at the top end of the supporting module and used for controlling the inclination angle of the rotating module. According to the ground launching rack, scattered transportation is convenient through the supporting module, stable supporting is provided after assembly, the rotating module is lifted in place through the lifting mechanism to achieve lifting and carrying of ammunition, the first half shaft sleeve and the second half shaft sleeve are matched with the rotating shaft for installation, and then the rotating module is conveniently rotated to adjust the angle; and the device is suitable for field environments with inconvenient driving.

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 invention relates to the technical field of rescue unmanned aerial vehicles, and discloses a vertical lifting disc type unmanned aerial vehicle which comprises an unmanned aerial vehicle shell, and a support is fixed to the unmanned aerial vehicle shell; the driving assembly is arranged on the support and used for driving the unmanned aerial vehicle to take off; the auxiliary assembly is arranged in the unmanned aerial vehicle shell and used for assisting the driving assembly; and the fire extinguishing assembly is arranged in the unmanned aerial vehicle shell and used for extinguishing a fire scene, the fire extinguishing assembly comprises a launching pad, the outer wall of the launching pad is fixed in the unmanned aerial vehicle shell, a plurality of dry powder fire extinguishing bombs are arranged in the launching pad, and a plurality of foam fire extinguishing bombs are arranged in the launching pad. Through cooperation of the interiors of the fire extinguishing assembly and the water spraying assembly, the dry powder fire extinguishing bomb and the foam fire extinguishing bomb achieve the effect of improving the fire extinguishing efficiency, and the problems that a traditional fire extinguishing mode is low in efficiency and slow in response when coping with multiple types of fire disasters are solved.

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.