52 results about "Launch pad" patented technology

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 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 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 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 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.

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.

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 invention relates to the technical field of rocket pinning and releasing launching, in particular to a self-weight return type pinning and releasing device which comprises a pinning and releasing assembly, a thermal protection cover installed on a launching platform body and a return support. The restraining and releasing assembly comprises a frame body and a restraining and releasing mechanism installed in the frame body. A lug plate at the lower part of the frame body is hinged with the return support through a pin shaft; the vertical plane where the axis of the pin shaft is located is a plane A, and the mass center of the restraining and releasing assembly is located on the side, away from the rocket body, of the plane A; the thermal protection cover is provided with a hollow cavity used for containing the reversed restraining and releasing assembly. In the reversing stage, the restraining and releasing assembly can automatically rotate and reverse around the pin shaft in the direction away from the rocket body under the action of the gravity of the restraining and releasing assembly. And the reversed containment release assembly can enter the inner cavity of the thermal protection cover, and the thermal protection cover is used for blocking the gas flow, so that the risk that the containment release assembly is damaged by the high-temperature gas flow is effectively reduced.

The application belongs to the technical field of rocket test device, and particularly relates to a medium-sized carrier rocket launching pad loading test device and a test method. The device comprises a test platform, a support structure, a loading structure and a test structure. The loading structure comprises a plurality of hydraulic jacks, an adapter ring and a stand. One end of the stand penetrates the launching pad and is fixedly connected with the foundation. The other end of the stand is fixedly connected with a cross beam. The adapter ring is sleeved on the outer side of the stand and is connected with the top of the plurality of rocket simulation legs. A plurality of hydraulic jacks are arranged on the surface of the adapter ring and are connected with the same pipeline. The experimental device provided by the application has the advantages of simple and reliable loading device, strong loading capacity, 1000-ton loading, high-precision loading of the plurality of hydraulic jacks connected with the same pipeline, small driving force value error of the hydraulic jacks, and measurement of the loading deformation.

The present application relates to a kind of aircraft launching system, including ground base frame and the launching platform unit and swing bar unit arranged on ground base frame, ground base frame is made of multiple frame monomers splicing, ground base frame is fixed on ground by pressing plate and pre-buried threaded column, launching platform unit includes platform body installed on ground base frame by multiple lifting legs, platform body is provided with flow guide hole, platform body is installed with multiple support arms corresponding with aircraft support point on the periphery of flow guide hole, the lower side of platform body is provided with flow guide device installed on ground base frame in the position corresponding with flow guide hole, swing bar unit includes rotating shaft installed on ground base frame by two bearing seats, rotating shaft is fixed with truss type swing bar, one end of rotating shaft is equipped with rotary drive device.It has the advantages of simple structure, easy to disassemble and assemble, good mobility, strong practicality.

Methods and apparatus for tail deployment in air launched effects (ALE) systems are disclosed. A disclosed example apparatus for deploying a tail for a launchable aircraft includes a spring having a first end and a second end, and a rotational hub operatively coupled to a rotational joint of a fuselage of the aircraft, the rotational hub operatively coupled to the first end of the spring, the second end of the spring operatively coupled to the tail, the spring to urge the tail to move relative to the fuselage when the aircraft is launched from a host.

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

According to the aircraft launching pad and the integrated transferring and erecting launching system, the aircraft launching pad is designed in a modular mode, switching between the test run state and the launching state of the launching pad can be achieved, and the tension and compression load requirements of the test run working condition are met. In addition, through reasonable layout and distribution of the internal space of the launching pad, effective protection of filling and gas supply pipelines and modular design of a cover plate of the launching pad surface, the aircraft launching pad is convenient to disassemble, and maintenance after launching is facilitated. The launching pad cover plate is driven by the motor, and the butt joint device and the erecting vehicle alignment locking device are hydraulically driven, so that the automation level of the launching pad diversion trench cover plate, the butt joint device and the pressing device is remarkably improved, manpower is saved, and efficiency is improved.

The invention discloses a high overload test device based on an electromagnetic coil. The device comprises a launching pad, a mainboard, a track, a multi-stage acceleration section, a multi-stage deceleration section, a capacitor bank, a boost module and a recovery device. The multi-stage acceleration section and the multi-stage deceleration section are respectively composed of a multi-stage electromagnetic coil and a photoelectric module and are coaxially sleeved on the non-metal track, and a data recording unit and an overload sensor are arranged in the test assembly; according to the invention, a discrete parameter reverse design method based on a target continuous overload curve is adopted, and the charging voltage of each stage of capacitor is flexibly configured, so that the limited discrete electromagnetic pulse can effectively approach a complex continuous overload environment, and the universality that the same device simulates multiple overload curves is realized; through cooperative work of the multiple stages of speed reduction coils and the recovery device, stable and impact-free speed reduction and safe and lossless recovery of the shots can be achieved, and the device has the advantages of being high in safety, good in controllability, high in flexibility, capable of achieving lossless recovery of the shots and the like.

The invention discloses a reverse flow docking method for a separated launching pad and a launching vehicle, and relates to the technical field of rockets. The reverse flow docking method comprises the following steps: moving the launching vehicle to a position connected with the launching pad; two symmetrical foundation blocks are arranged on the side, away from the launching vehicle, of the launching platform, and the distance between the two foundation blocks is larger than the width of the launching vehicle; a telescopic driving device is connected to the foundation block, and the other end of the telescopic driving device is connected with the side edge of the launching vehicle through an inhaul cable; a laser indicator is arranged between the launching vehicle and the launching platform; according to the technical scheme, before butt joint is carried out, the launching vehicle and the launching platform are aligned through cooperation of the telescopic driving device and the laser designator, the axial deviation of the launching vehicle relative to the launching platform is adjusted through the telescopic driving device, the alignment state of the launching vehicle relative to the launching platform is detected through the laser designator, and then the alignment state of the launching vehicle relative to the launching platform is adjusted through cooperation of the telescopic driving device and the laser designator. Therefore, the problems of collision and inaccurate positioning during butt joint are avoided.

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

This invention provides a design method for frequency adjustment of a rocket body wind load model. First, the target value of the first-order frequency of the wind load model is determined based on the first-order frequency of the actual rocket body erected on the launch pad and the similarity principle of the Strouhal number (Sr). The wind load model is then designed based on the target first-order frequency value. A frequency adjustment device is designed to ensure that the adjusted frequency value is between 0.9 and 1.2 times the target value. Modal tests of the wind load model are conducted outside a wind tunnel to verify whether the first-order mode of the model meets the requirements after adjustment. The model is then installed inside the wind tunnel and modal tests are performed. Through frequency adjustment, the first-order frequency of the model is ultimately guaranteed to meet the requirements. This invention solves the problems of frequency deviation between theoretical models and actual products, as well as the deviation of the first-order frequency of products with different fixed support boundaries. It ensures that the first-order bending frequency of the wind load model installed in the wind tunnel for wind testing meets the design requirements. Furthermore, this frequency adjustment device can be used for rocket wind load models of similar diameters and can be repeatedly applied to multiple models.

The invention discloses a pneumatic-based separation mechanism for on-orbit repeated filling and launching of a miniature spacecraft. The pneumatic-based separation mechanism is characterized by comprising a base, a launching pad, two memory alloy pin pullers and four guide rails, a launching cavity is formed in the base and provided with an end cover, a center launching hole is formed in the end cover, the launching pad is arranged in the launching cavity, the top of the launching pad can stretch out of the center launching hole, the launching pad and the center launching hole are in clearance fit, a plurality of exhaust holes are formed in the side wall of the launching cavity, and an air inlet is formed in the center of the bottom face of the base. The four guide rails are fixed to the four corners of the top face of the cubic base, and the four guide rails and the cubic base form a launching track. And the two memory alloy pin pullers are symmetrically fixed on the side wall of the base above the end cover of the base. According to the mechanism designed through the design method, memory alloy unlocking is adopted to replace traditional firework unlocking, impact is reduced, repeated filling and using can be achieved, a cold air propelling mode is adopted, and pollution to the environment is avoided.

The application provides a launch vehicle erecting system integration device and a working method, which comprises an erecting box assembly, a rocket launching platform, a launching rotary support, a first double-sided tooth groove support arm, a second double-sided tooth groove support arm, a rocket support bracket, a pulling rope system and a central controller. The rocket launching platform is arranged at one end of the erecting box assembly, and the launching rotary support is rotationally connected to the end of the erecting box assembly provided with the rocket launching platform. The first double-sided tooth groove support arm, the second double-sided tooth groove support arm and the pulling rope system cooperate to erect the rocket, and the launching is completed. The erecting is driven by a brand-new motor, the system composition is relatively simple, the reliability and safety of the erecting and launching system are improved, the erecting and launching process is fast in response and high in precision, the rocket can be erected and launched at any site and terrain, and the future mobile launching demand of the launch vehicle is met. After launching, the device can return to the initial state, the rocket can be hoisted again for the next launching, and the rocket launching efficiency is improved.

The invention provides a rocket vertical supporting and leveling system and a rocket vertical supporting and leveling method, and belongs to the technical field of rocket launching, the rocket vertical supporting and leveling system comprises a launching pad, a plurality of lifting devices and a supporting tray, and the lifting devices are evenly arranged on the launching pad in the circumferential direction; the supporting tray ball head is hinged to the top of the lifting device, and the supporting tray is used for supporting a rocket. A plurality of lifting devices on the launching pad pre-level the supporting tray in a joint debugging and monotonous control mode, when the rocket is erected in place, the lifting devices synchronously act, the supporting tray integrally ascends and descends, abuts against the butt joint face of the rocket and is finely adjusted to vertically level the rocket, the benchmark of the butt joint end face of the supporting tray and the rocket is stable, and then the rocket is launched. And the technological process is efficient and reliable. According to the rocket vertical supporting and leveling system, the problem that the technological process is complex due to the fact that deviation exists in mutual adjustment of four executing mechanisms of a lifting device of an existing rocket supporting and leveling system is solved.

1. Name of the product in this design: Rocket Fixing Device. 2. Purpose of this design: To securely connect a rocket to the launch pad support arm. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

The invention relates to a 3D printing static model demonstration teaching device integrating a launching pad and a rocket, and the device is characterized in that the device comprises a 3D printing truss type launching tower, a 3D printing detachable service arm, a 3D printing segmented rocket model, and a 3D printing integrated pedestal. The problems that an existing traditional static spaceflight teaching model is high in mold cost, long in customization period, low in structure reduction degree, incapable of being repeatedly disassembled and assembled for interaction and single in adaptive scene are solved, precise forming and modular design of the model are achieved through the 3D printing technology, the closed-loop teaching requirement of structural cognition-disassembly observation-assembly practice is met, and the model is high in practicability. The professional and interactive performance of aerospace teaching is improved, and the teaching input cost is reduced.

The invention provides a rocket erecting frame. The rocket erecting frame comprises a main beam front section and a main beam rear section, wherein the main beam front section is of a frame type structure; the main beam middle section is connected with one end of the main beam front section, and the main beam middle section is of a truss type structure; the main beam rear section is connected with the main beam middle section, the main beam rear section is of a box beam type structure, a first frame is installed on the first side face of the main beam rear section, a second frame is installed on the second side face of the main beam rear section, and the first frame and the second frame are of a symmetrical structure; the top of the first frame and the top of the second frame are each provided with a launching pad connecting frame, and one end of the first frame and one end of the second frame are each provided with a limiting base; the main beam tail section is connected with the other end of the main beam front section, and the main beam tail section is of a frame type structure. The rocket erecting frame structure with the large aspect ratio is achieved, the rocket erecting frame structure can adapt to long-core-level and large-tonnage rockets, and erecting stability and safety are improved.

The invention relates to the technical field of aerospace transportation, in particular to a vertical take-off and landing single-stage injection repeatable heaven and earth back-and-forth carrying method which comprises the following steps: preparing for vertical boosting launching, and simultaneously finishing all preparations before rocket launching; the vertical boosting launching device releases stored energy and boosts the rocket to accelerate; after boosting launching is completed, the rocket engine is ignited to take off and leave the boosting device; the rocket continuously accelerates to the orbit injection speed and then enters a preset orbit; the rocket is adjusted to be in a tail windward configuration needed by reentry, and the rocket is decelerated to enter a reentry window; a rocket enters the atmosphere with the tail nozzle taper plug outsole as a windward side, and the thermal protection capacity of the taper plug outsole is enhanced through a regeneration cooling structure in the taper plug outsole structure. And the rocket vertically lands to the original boosting launching rack and waits for a re-launching task at the original position. According to the invention, by constructing an integrated vertical take-off and landing, single-stage orbit injection, orbit reentry and in-situ recovery process, high-frequency, low-cost and flight-based operation of a sky-ground back-and-forth carrying task is realized.