430 results about "Rocket launch" patented technology

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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