67 results about "Rocket propellant" patented technology

The invention discloses an on-line full-supercooling methane filling system and a filling method thereof, and relates to the technical field of rocket fuel filling systems, the on-line full-supercooling methane filling system comprises a first methane storage tank, a second methane storage tank, a first gas storage tank, a second gas storage tank, a second gas storage tank and a pre-cooling discharge pipeline, the first gas storage tank is connected with a rocket propellant storage tank and the pre-cooling discharge pipeline through a tube pass of a supercooler; the second methane storage tank is connected with the tube pass of the subcooler through a second pipeline; and the liquid nitrogen storage tank is provided with a third pipeline, and the third pipeline is connected with the shell pass of the subcooler. According to the on-line full-supercooling methane filling system, the technical problem that the risk of failure of a launching task is increased due to the fact that liquid level control is unstable when on-line supercooling filling is conducted on a rocket is solved, and the risk of failure of the launching task is increased when the flow in the methane filling process is adjusted. The flow of methane in the tube pass of the subcooler and the liquid level of liquid nitrogen in the shell pass of the subcooler are controlled to be unchanged, the situation of methane icing caused by unstable liquid level control is avoided, and then the risk of failure of a launching task is reduced.

The invention discloses a carrier rocket propellant management device which comprises a porous partition plate, a screen structure, a screen support, a storage box, a conveying pipe and a pressurizing pipe. The porous partition plate is installed on the upper portion of the storage box and used for restraining the propellant from shaking in the long-time small negative overload section, and the low-temperature liquid propellant is prevented from being mixed with the air pillow. The porous partition plate is a disc formed by splicing fan-shaped pore plates and is mounted at the upper part of the storage box; the screen structure is positioned at the lower part of the storage box; the screen structure is formed by splicing a plurality of fan-shaped components into a circle and comprises an outer ring, a middle ring and an inner ring; the screen support comprises a plurality of vertical partition plates and a framework and is used for supporting the screen structure and playing an anti-vortex role at the same time; the framework is fixed on the vertical partition plate; the storage box is communicated to a rocket engine through a conveying pipe; and the pressurizing pipe is used for conveying pressurizing gas to the storage box. The device has the functions of gas isolation and liquid storage, can meet the matching requirements of a sinking engine, is beneficial to secondary weight reduction, and improves the effective load.

The invention relates to a reusable propellant storage tank of a carrier rocket, and belongs to the technical field of liquid rocket propellant storage and management. The propellant storage box comprises a storage box body, and a lower-layer partition plate assembly, a middle-layer partition plate assembly and an upper-layer partition plate assembly which are arranged in a storage cavity of the storage box body, and the three layers of partition plate assemblies are of disc-shaped structures covering the cross section of the storage box. A first circulation area is arranged in the middle of the lower-layer partition plate assembly, a sealing plate and a second circulation area surrounding the sealing plate are arranged in the middle of the middle-layer partition plate assembly, a third circulation area is arranged in the middle of the upper-layer partition plate assembly, and the first circulation area, the second circulation area and the third circulation area are staggered in the radial direction, so that a nonlinear damping type liquid circulation path is formed in the storage tank. Therefore, violent shaking of the propellant in a weightlessness or variable acceleration environment is inhibited, and reliable restarting of the engine is guaranteed. According to the storage box, the structure is simple and reliable, the shaking restraining effect is remarkable, and the storage box is particularly suitable for propellant management of a reusable carrier rocket.

This application provides a horizontal assembly and welding method for ultra-long cylindrical sections with circumferential seams, comprising: hoisting the long cylindrical section into a horizontal fixture and controlling the horizontality of the long cylindrical section and the coaxiality of the cylindrical section axis with the axis of the support mechanism; adjusting the roundness of the assembled cylindrical section by controlling the support tension of the inner support fixture and using an auxiliary local external pressure method; eliminating local misalignment after cylindrical section assembly by local positioning welding and local correction; and eliminating local gaps after cylindrical section assembly by in-situ milling of the cylindrical section end face and full positioning seam sealing welding, wherein the milling includes rough milling and fine milling. This application enables the horizontal assembly and welding of ultra-long cylindrical section propellant tanks for next-generation medium-sized launch vehicles with circumferential seams, solving the problem of deformation during horizontal assembly of thin-walled ultra-long weak rigid cylindrical section products, reducing product production costs, and improving product assembly and welding efficiency, providing effective technical support for a high-efficiency, mass production model for rocket propellant tank products.

The invention discloses a low-temperature propellant large-flow supercooling filling system and method, relates to the technical field of propellant supercooling filling, and aims to solve the problem that the filling procedure of the online supercooling filling technology is complicated. The system comprises a propellant filling system which is connected with a rocket storage tank and used for filling a propellant into the rocket storage tank; the temperature adjusting system is connected with the propellant filling system and used for adjusting the temperature of a propellant in the propellant filling system in real time, the liquid nitrogen filling system is connected with the temperature adjusting system and used for filling liquid nitrogen into the temperature adjusting system, and the control system is used for controlling the operation states of the propellant filling system, the temperature adjusting system and the liquid nitrogen filling system. The supercooling process of the low-temperature propellant is separated from the formal filling process, the formal filling process is simplified, the number of tested equipment in the formal filling process is reduced, and the system reliability is improved.

A rocket propellant tank and layout (15) is disclosed. The tank (15) includes a housing operationally coupled to a rocket engine (20). The housing comprises a plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f) arranged longitudinally along the housing and is adapted to store a propellant. A plurality of separator walls (24, 41, 42, 32, 33, 34) are disposed adjacent to each of the plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f). A set of control valves (45) are coupled to each of the plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f). The set of control valves (45) are adapted to facilitate a controlled transfer of the propellant from each of the plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f) to the rocket engine (20).

The invention relates to the technical field of solid rocket propellants, and particularly discloses a phosphoric acid modified cyclic borate bonding agent and a preparation method and application thereof.The bonding agent does not contain nitrogen atoms, contains a cyclic structure, further introduces high-polarity phosphorus-oxygen (P = O) groups and has multiple hydroxyl groups capable of participating in a curing reaction; the compatibility with nitrate in a high-energy propellant is good, and ammonia release caused by the adoption of a bonding agent containing amido is avoided; the catalyst has good hydrolytic stability, and can generate a bonding effect with a nitramine filler in a coordination bonding manner; by improving the surface and interface performance of the solid filler and increasing the infiltration speed of the adhesive to the solid filler, the pharmaceutical process performance of the propellant can be improved; and the polymer can also be used as a chain extender and a reinforcing agent to optimize and regulate a matrix network structure, so that the purposes of high strength and high elongation are achieved. The bonding agent can meet the development requirements of NEPE high-energy propellants on high mechanical properties and optimized process properties.

The subject of the invention is a solid rocket propellant grain comprising frontal surfaces and a lateral surface, characterised in that it comprises a first type layer which is completely filled in cross-section with a solid propellant material with an inhibited lateral surface (101a), and a second type layer which has at least one recess (103) in a solid propellant material with a non-inhibited lateral surface (101b), wherein at least one second type layer is surrounded by the first type layer on both sides.

The invention provides a precooling control method of a rocket propellant filling system, which comprises the following steps: arranging a backflow pipeline between a filling pump liquid outlet pipeline and a storage tank, starting a filling pump to operate according to a first frequency, and opening a first regulating valve of the backflow pipeline; when the gas content of the propellant in the backflow pipeline is lower than a first set value, the adjusting valve of the backflow pipeline is closed, a second adjusting valve between the subcooler and the storage tank is opened, the filling pump is adjusted to operate according to a second frequency, and the second frequency is larger than the first frequency; and a first pressure value of the liquid inlet pipeline of the subcooler and a second pressure value of the liquid outlet pipeline of the subcooler are collected in real time, and when the difference value between the second pressure value and the first pressure value is larger than a second set value, the filling pump is closed, the first adjusting valve of the backflow pipeline is opened, and the second adjusting valve is closed. According to the control method, the reliability of the rocket propellant filling precooling process can be improved.

The utility model relates to the technical field of anti-unmanned aerial vehicles, and particularly discloses an anti-unmanned aerial vehicle rocket engine secondary ignition system which is characterized by comprising a launching bin, a rocket body, a rocket body function bin, a sliding piston, a resin supporting piece and a sabot. Wherein the rocket body is installed in the launching bin, the rocket body function bin is connected with the bottom of the rocket body, the sabot is connected to the launching bin and located below the rocket body function bin, the first primer is arranged in the sabot, the second primer is arranged in the rocket body function bin, and the sliding piston and the resin supporting piece are arranged in the rocket body function bin. The sliding piston can slide relative to the rocket body function bin, piston propellants are arranged between the sliding piston and the primary primer, the resin supporting piece is located between the sliding piston and the secondary primer, the rocket body is provided with rocket propellants, and the rocket propellants are arranged close to the secondary primer. And the bullet support is provided with a guide hole through which the firing pin penetrates to be in contact with the primary primer.

This invention discloses a propellant venting connector docking and locking device for venting propellant from a rocket being recovered and suspended from a robotic arm on a launch tower. The docking and locking device includes an installation platform; an installation plate driven by a first drive mechanism to rotate vertically on the installation platform; multiple rocket-holding mechanisms evenly distributed circumferentially on the installation plate, driven by a second drive mechanism to synchronously move radially toward each other towards the center and synchronously move radially away from each other towards the center; multiple rocket-bearing mechanisms evenly distributed circumferentially on the installation plate to support the rocket; an industrial robot is installed on the installation plate, and a connector is provided at the end effector of the industrial robot. The connector is driven by the industrial robot to dock with the rocket's venting port and is used to vent the propellant. This invention can effectively reduce the safety risks to personnel involved in the handling of rocket propellant after recovery and improve the efficiency of propellant venting and handling.

The embodiment of the invention provides a mixing ratio adjusting method and system for a propellant of a liquid carrier rocket, and the method comprises the steps: obtaining the flight data of the liquid carrier rocket and the state data of the propellant; determining a flight stage of the liquid carrier rocket according to the flight data; according to the state data of the propellant, the mixing ratio and the mixing ratio change rate of the propellant are determined; according to the flight stage, the mixing ratio and the mixing ratio change rate, the valve adjusting strength of the propellant is determined; and adjusting the valve of the propellant according to the valve adjusting strength of the propellant. According to the invention, through intelligent sensing and self-adaptive adjustment, the mixing ratio in the whole flight process of the rocket can be accurately controlled, and the propulsion efficiency and the flight safety are improved.

The present application relates to rocket propellant storage and transportation system, specifically relates to a kind of rocket propellant vehicle-mounted storage and transportation system and its filling method, for solving the insufficient airtightness of existing rocket propellant vehicle-mounted storage and transportation system in the process of transportation, temperature control is unreliable, the temperature, pressure, liquid level and other conditions of rocket propellant cannot be monitored in real time, and the residual rocket propellant in the pipeline of vehicle-mounted storage and transportation system cannot be handled.The rocket propellant vehicle-mounted storage and transportation system includes automobile chassis, tank body, filling pipeline system and control system;The tank body of the present application has good heat preservation effect and sealing, can fully ensure the temperature and pressure of rocket propellant in tank body constant during transportation, and temperature, pressure and liquid level in tank body can be monitored in real time through first pressure gauge, liquid level meter, thermometer control system, fully ensure the stability of the physicochemical properties of rocket propellant in tank body.

The present invention discloses a method for preparing an epoxy resin matrix for composite low-temperature storage tanks, and relates to the technical field of polymer materials. The present invention introduces mesoporous silica material into the epoxy resin structure, and utilizes the mesoporous channels of the mesoporous silica to construct a cured molecular network structure of resin molecular chains and mesoporous silica interspersed segments, thereby reducing the thermal expansion coefficient of the resin, thereby significantly reducing the temperature stress generated in the carbon fiber composite material due to the ultra-low temperature environment, and effectively inhibiting the initiation of microcracks; the use of a three-roller rolling process can better remove the solvent and make the mesoporous silica more evenly dispersed, thereby increasing the strength of the resin matrix, and further inhibiting the initiation and expansion of microcracks. The epoxy resin matrix of the present invention is suitable for composite storage tanks for rocket propellants.

The utility model provides a forming device for a butt joint tailor-welded longitudinal seam of a rocket storage tank cylinder section large plate, which comprises a shaping guide component, an upper support component, a lower support component and a lower support component, the upper bracket component comprises an upper outer bracket component and an upper inner bracket component; the upper outer bracket part comprises an outer guide part; the outer guide part comprises at least one outer arc-shaped guide plate; the upper inner bracket part comprises an upper inner guide part; the upper inner guide part comprises an inner arc-shaped guide plate; each inner arc-shaped guide plate is arranged on the circumferential inner side face of the corresponding outer arc-shaped guide plate in a sleeving mode. The end of the outer arc-shaped guide plate and the end of the inner arc-shaped guide plate are placed at a discharging port and a feeding port of a welding station correspondingly. The outer arc-shaped guide plate and the inner arc-shaped guide plate are used for receiving a steel plate output by a welding station and limiting and guiding the steel plate from the two side faces of the steel plate correspondingly. The forming equipment can conduct guiding and bending forming on the steel plate.

This invention provides a rocket propellant tank bracket positioning system and method based on database and machine vision, including the following steps: S1: establishing a database of external brackets for various propellant tank models; S2: retrieving propellant tank data from the external bracket database according to the propellant tank model; S3: the automated positioning system for the external brackets corrects the downward displacement of each position of the propellant tank model under gravity in the external bracket model database based on measurement results; S4: rotating the reference for the external bracket positioning and assembly of the propellant tank to a suitable position; S5: generating assembly and marking schemes for each external bracket based on machine vision results; S6: operators welding each bracket sequentially at the bracket welding station according to the marked positions determined by each reference; and S7: grinding away the weld seams. This application features rapid positioning technology that enables one-time accurate marking of batch propellant tank brackets, reducing repeated adjustments and improving production line consistency.

The present application relates to the technical field of rockets, and particularly relates to a regulating valve, an engine and a rocket. The regulating valve comprises: a first valve body, a fluid passage is formed in the first valve body, a first valve seat and a valve core are arranged in the fluid passage, a first grid structure is formed in the first valve seat, and a second grid structure is formed in the valve core; a driving mechanism is connected with the valve core, used for driving the second grid structure to move, and forming a flow channel with stepless regulation of the flow area between the second grid structure and the first grid structure. The regulating valve, the engine and the rocket provided by the present application can realize stepless regulation of the gas flow by driving the second grid structure to move, and the regulation ratio of the regulating valve is increased, thereby meeting the needs of accurate control of the rocket propellant flow.

The invention provides a method for catalyzing rapid spontaneous combustion of an N (CN) 2-IL-H2O2 system by twin-crystal Cu NPs, belongs to the field of rocket propellants, and aims to solve the problem that the N (CN) 2-IL-H2O2 system does not spontaneously ignite. The twin crystal Cu NPs and N (CN) 2-IL ionic liquid are mixed, the obtained mixed fuel is dropped into a cylindrical open glass bottle oxidant pool containing H2O2, and the ignition delay time is tested. The ignition process is recorded by a high-speed camera, and obtained data is an average value of three times of ignition tests. The spontaneous combustion performance of the N (CN) 2-IL-H2O2 system is reduced by utilizing the twin boundary defect of Cu NPs, and the ignition delay time is as low as 25 ms. The method is simple in operation and rapid in reaction, relatively low ignition delay time can be obtained, and accurate synthesis of the twin crystal Cu NPs is beneficial to industrial application of an N (CN) 2-IL-H2O2 propulsion system and rapid development of the aerospace industry in China.

The utility model relates to the technical field of rocket storage tanks, in particular to a tool for handheld resistance welding of a stringer and a stiffening plate of a rocket storage tank. The tool comprises a supporting mechanism and a mounting mechanism, the supporting mechanism comprises a second supporting beam, and a first supporting beam is mounted on the second supporting beam; a fifth supporting beam is mounted at the top end of the second supporting beam, and the mounting mechanism is mounted on the fifth supporting beam and used for mounting handheld welding tongs. A sixth supporting beam is installed at the top end of the fifth supporting beam, a stringer is placed on the sixth supporting beam, and a reinforcing plate is placed at the position, needing to be reinforced, of the stringer; when the handheld electrode holder is installed on the installation mechanism, an electrode of the handheld electrode holder corresponds to the position, needing to be reinforced, of the stringer so as to be used for welding the stringer and the reinforcing plate. According to the utility model, the labor cost for welding the stringer and the stiffening plate can be reduced, the welding efficiency is improved, the condition of welding deviation can be avoided, and a good welding effect between the stringer and the stiffening plate is ensured.

A rocket propellant tank and layout (15) is disclosed. The tank (15) includes a housing operationally coupled to a rocket engine (20). The housing comprises a plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f) arranged longitudinally along the housing and is adapted to store a propellant. A plurality of separator walls (24, 41, 42, 32, 33, 34) are disposed adjacent to each of the plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f). A set of control valves (45) are coupled to each of the plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f). The set of control valves (45) are adapted to facilitate a controlled transfer of the propellant from each of the plurality of compartments (17a, 17b, 17c, 17d, 17e, 17f) to the rocket engine (20).

The application belongs to the technical field of aerospace propellants and energetic materials, and relates to a compounded self-ignition ionic liquid, a preparation method and application. The compounded self-ignition ionic liquid is composed of a self-ignition ionic liquid and a promoter, wherein the self-ignition ionic liquid is cyanoborohydride 1-allyl-3-ethyl imidazole or cyanoborohydride 1-allyl-3-methyl imidazole, and the promoter is 1,3-dimethyl-4,5-diiodo imidazole iodine salt or 1,3-dimethyl-4,5-diiodo imidazole triiodine salt; the self-ignition ionic liquid accounts for 80wt%-95wt%, and the promoter accounts for 5wt%-20wt%. The compounded self-ignition ionic liquid has high density, low viscosity and good thermal stability, and when used in the field of rocket propellants, can achieve good self-ignition effect with H2O2 and fuming nitric acid, and is superior to a single self-ignition ionic liquid.

A rocket propellant tank 8 comprises an inner tank 10 and an outer tank 12 concentrically arranged with the inner tank nested within the outer tank wherein the inner tank contains liquid oxygen, and the outer tank contains liquid hydrogen. The outer tank may be toroidal and is defined by an inner wall (18, figure 5) and outer wall (20). The inner tank is defined by an outer wall (14) which is spaced radially inward from the inner wall of the outer tank to form a gap (24) which is filled with insulation, for example aerogel material. An inner or outer wall of the tank may be formed from composite material, for example carbon fibre, and may have a thickness of 4mm or less. A pole 30 may extend through a longitudinal axis of the inner tank connecting end caps (16, figure 3) of the inner tank and forming a conduit for carrying cables. Upper and lower bulkheads (32, 34) may be provided, spaced from the end caps, and connected to the inner and outer tanks by circular rings (36, figure 6).

This application provides an intelligent measurement system and method for rocket propellant tank volume. The system includes: a nitrogen tank, a manual ball valve, a delivery pump, a check valve, a gas-locked ball valve, a pressure sensor, a pressure gauge, a pneumatic ball valve, a recovery pump, an electric regulating valve, a propellant tank, a safety valve, a standard container, a first temperature sensor, and a second temperature sensor. The nitrogen tank, delivery pump, recovery pump, standard container, and the propellant tank under test constitute the gas path execution unit. The intelligent control center includes an adaptive predictive control module and a multi-parameter dynamic inversion processing module. The intelligent measurement system and method for rocket propellant tank volume provided by this invention eliminates the need for manual intervention during the entire measurement process, resulting in high measurement efficiency and ensuring intelligent measurement of rocket propellant tank volume through automatic output of reliable results.

The present application relates to propellant transfer equipment technical field, specifically for a kind of rocket propellant transfer pipeline automatic docking device and control method, to solve the problems of traditional propellant transfer pipeline manual docking low efficiency, poor precision, and there is propellant leakage security risk, specifically includes: movable base, plug removal unit, joint docking unit, positioning detection unit, interface sealing unit and controller.The present application realizes the accurate identification and positioning of target by positioning detection unit, three-dimensional mechanical arm drives plug removal unit and joint docking unit, realizes the automatic removal of transfer port plug and the automatic docking of propellant transfer pipeline, and interface sealing unit detects the sealing performance of docking.The present application does not need manual intervention, and the docking efficiency is more than 5 times higher than manual, suitable for aerospace, chemical and other fields high-risk, high-purity propellant transfer scene requiring.

The invention provides a rocket propellant storage tank rear bottom structure, a propellant storage tank and a liquid rocket. The rocket propellant storage tank rear bottom structure comprises a storage tank rear bottom, a tunnel connector, a plurality of outflow flanges, an anti-collapse cover plate, a filter screen and a plurality of vortex eliminating fin plates. The tunnel connector is located in the center of the storage box rear bottom, and the multiple outflow flanges are arranged on the storage box rear bottom and distributed around the tunnel connector in a circumferential mode. The outer contour of the anti-collapse cover plate is connected with the inner wall of the rear bottom of the storage box; the inner contour of the filter screen is connected with the tunnel joint, and the outer contour of the filter screen is connected with the inner contour of the anti-collapse cover plate; the plurality of vortex eliminating fin plates are circumferentially distributed around the tunnel joint, the vortex eliminating fin plates are arranged below the anti-sloughing cover plate and the filter screen, and the bottom edges of the vortex eliminating fin plates are connected with the inner molded surface of the rear bottom of the storage box in an attached mode. The outflow device is integrally designed, has vortex eliminating, collapse preventing and propellant filtering functions, is compact in system structure, reasonable in overall layout, good in stability and high in maintainability, and meets general design requirements.

The utility model discloses a monitoring system for a low-temperature and high-pressure rocket propellant storage tank, belongs to the technical field of image information transmission, and solves the technical problems of low monitoring transmission rate and error codes of the rocket propellant storage tank. The system comprises a camera device, an image controller, a power supply, a network port switching server, a front-end photoelectric converter, a rear-end photoelectric converter, an image monitoring upper computer and a power supply control upper computer, and the power supply control upper computer is sequentially communicated with the rear-end photoelectric converter, the front-end photoelectric converter, the network port switching server and the power supply. The power supply control upper computer is used for controlling on and off of a power supply. The camera device is located at the top in the storage box and sequentially communicated with the image controller, the front-end photoelectric converter, the rear-end photoelectric converter and the image monitoring upper computer, and the image monitoring upper computer is used for displaying images and environment temperature information. And the front-end photoelectric converter is communicated with the rear-end photoelectric converter through an optical fiber. The device is used for monitoring the low-temperature and high-pressure rocket propellant storage tank.

The embodiment of the utility model provides a management device for rocket propellant supply control, and belongs to the field of rocket propellant supply control. The management device used for rocket propellant supply control comprises a partition plate used for dividing a propellant storage box into two parts, and further comprises a plurality of straight-through communicating pipes arranged on the partition plate at intervals; and the anti-reflux device is arranged at one end, far away from the partition plate, of each straight-through communicating pipe. According to the management device, the situation that the pressure of the storage tank is reduced due to the fact that the cryogenic propellant is violently mixed with the main body pressurized gas of the propellant storage tank is effectively avoided, and the configuration requirement of a pressure supplementing gas cylinder is reduced.

The invention relates to the technical field of rockets, in particular to a regulating valve, an engine and a rocket. The regulating valve comprises a first valve body and a second valve body, a fluid channel is formed in the first valve body, a first valve seat and a valve element are arranged in the fluid channel, a first grating structure is formed in the first valve seat, and a second grating structure is formed in the valve element; the driving mechanism is connected with the valve element and used for driving the second grating structure to move, and a flow channel with the overflowing area steplessly adjusted is formed between the second grating structure and the first grating structure. According to the regulating valve, the engine and the rocket, the driving mechanism drives the second grating structure to move, stepless regulation of the gas flow can be achieved, the regulation ratio of the regulating valve is increased, and therefore the requirement for precise control over the flow of a rocket propellant is met.