45 results about "Rocket propellant" patented technology

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.

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.

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 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 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.

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 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 invention relates to the technical field of spaceflight, and discloses a carrier rocket propellant sinking method and system based on a solid-liquid rocket engine, the carrier rocket propellant sinking system comprises a main body assembly, the main body assembly comprises a main engine, a kerosene storage tank is arranged on one side of the main engine, and a liquid oxygen storage tank and a sinking engine combustion chamber are arranged on one side of the kerosene storage tank; and the air inlet is arranged on the liquid oxygen storage tank. The solid-liquid rocket engine has the beneficial effects that the oxygen air pillow of the liquid oxygen storage box is adopted as an oxidant of a combustion chamber of the bottom-sinking engine, the solid-liquid rocket engine is formed by matching with a polyethylene solid fuel grain or materials such as HTPB and PMMA which are commonly used for engine grains, and the fan-shaped vibration isolation plate is arranged in front of the grains to restrain the unstable combustion phenomenon; multiple times of starting are achieved through high-power laser ignition, compared with a traditional scheme, the higher specific impulse and propellant utilization rate are achieved, the negative weight is reduced, the efficient and light-weight requirements of the recoverable rocket are met, propellant management can be achieved in the low-gravity environment, and deceleration thrust can be provided during returning.

A dual-mode composite energetic material out-of-cavity active regulation and control ignition system comprises an electric control displacement platform, an upper computer, a vector network analyzer, a microwave signal source, a power amplifier, a directional coupler and a power measurement and display unit, and the electric control displacement platform is connected with a high-temperature-resistant vessel and a microwave resonant cavity. The microwave resonant cavity comprises a metal outer cavity, the metal outer cavity is a hollow cylinder with an opening in the lower end, a bottom cover with a hole is arranged at the lower end opening of the metal outer cavity, the bottom cover with the hole is of an annular shutter structure with an opening in the center, a center probe is further coaxially arranged in the metal outer cavity, and the center probe penetrates through the center opening of the bottom cover with the hole from inside to outside and extends outwards. Switching of two ignition mechanisms is realized by regulating and controlling microwave parameters and ignition areas, and the ignition process suitable for most composite energetic materials is realized; the method can be used for research, development and verification of novel energetic materials and quality detection and real-time ignition of solid rocket propellants, and has very important military application value and scientific research value.

The application discloses a kind of for rocket engine cabin, anti-condensation air supply system of inter-bay section instrument cabin, comprising: fresh air pipeline unit, all fresh air handling unit, pressurized fan unit, air supply pipeline unit and control unit;Wherein, all fresh air handling unit and pressurized fan unit are using N+1 redundancy backup mode, and quantity one-to-one correspondence, N is the number of required unit calculation;All fresh air handling unit and pressurized fan unit are installed in air-conditioning room, under the control of control unit, fresh air pipeline unit will outdoor fresh air be sent to all fresh air handling unit, and all fresh air handling unit will be handled to the set state point according to the temperature requirement proposed by rocket propellant filling system, then be pressurized by pressurized fan unit and be sent to docking interface by air supply pipeline unit, and be docked with the active end device of space department, finally be sent into engine cabin and inter-bay section instrument cabin.

The invention discloses a ram-type thin plate storage tank short shell structure for a carrier rocket propellant storage tank, and belongs to the field of aerospace manufacturing. Comprising a short shell body, the short shell body is made of a stainless steel sheet, and main reinforcing ribs and auxiliary reinforcing ribs are integrally formed on the inner surface and the outer surface of the short shell body through a high-precision multi-direction force application overall stamping process to form a gradient rigidity transition structure; the main reinforcing rib is a semicircular channel with the groove width to depth ratio of 4.7: 1, and the end part of the main reinforcing rib is provided with a hemispherical end to reduce stress concentration; a smooth straight section area conformal with the barrel section is reserved at the lower end of the short shell and serves as an integrated welding connector, and the structural design and stamping parameters are subjected to finite element simulation optimization. The mass of the structure only accounts for 8%-10% of the whole storage tank, the lightweight effect is remarkable, force transmission is continuous and efficient, the rigidity and buckling resistance are greatly improved, welding and assembling time is shortened, the manufacturing cost is reduced, the period is shortened, the assembling and butt joint precision is high, and the structure is suitable for large spaceflight thin-wall structures such as carrier rocket propellant storage tanks.

The present invention provides a hybrid rocket engine ignition device, a hybrid rocket engine ignition method, and a rocket propulsion system that can be reliably reignited, miniaturized and lightweight, and mounted on relatively small satellite systems. [Solution] A high-temperature gas generating means is provided to generate high-temperature gas using rocket propellant. The system is configured to ignite a hybrid rocket engine using the high-temperature gas generated by the high-temperature gas generating means.

The invention relates to the technical field of propellant transfer injection equipment, in particular to an automatic docking device for rocket propellant transfer injection pipelines and a control method, and aims to solve the problems that manual docking of traditional propellant transfer injection pipelines is low in efficiency and poor in precision, and potential safety hazards of propellant leakage exist. The device comprises a plug cover dismounting unit, a joint butt joint unit, a positioning detection unit, an interface sealing unit and a controller. Precise recognition and positioning of a target are achieved through the positioning detection unit, the three-dimensional mechanical arm drives the blanking cap dismounting unit and the connector butt joint unit, automatic dismounting of a transfer injection opening blanking cap and automatic butt joint of a propellant transfer injection pipeline are achieved, and the connector sealing unit detects the butt joint sealing performance. Manual intervention is not needed, the docking efficiency is improved by more than 5 times compared with manual work, and the method is suitable for propellant transfer injection scenes with high-risk and high-cleanliness requirements in the fields of spaceflight, chemical engineering and the like.

The invention discloses a propellant release connector butt-joint rocket locking device which is applied to release propellant of a rocket recovered and hung on a tower mechanical arm, and the butt-joint rocket locking device comprises a mounting platform; a mounting disc which is driven by a first driving mechanism to rotate around the vertical direction is arranged on the mounting platform; a plurality of arrow holding mechanisms are uniformly distributed on the mounting disc in the circumferential direction at intervals, and the multiple arrow holding mechanisms are driven by a second driving mechanism to synchronously get close to the circle center in the radial direction and synchronously get away from the circle center in the radial direction; a plurality of rocket bearing mechanisms used for bearing rockets are evenly distributed on the mounting disc in the circumferential direction at intervals. An industrial robot is arranged on the installation disc, a connector is arranged at the execution tail end of the industrial robot, and the connector is driven by the industrial robot to be in butt joint with a discharging opening of a rocket and used for discharging propellants. And the efficiency of propellant discharge treatment can be improved.

The invention discloses ternary boron-based alloy powder and a preparation method thereof, the ternary boron-based alloy powder is prepared by taking boron powder with high calorific value, aluminum powder and high-activity aluminum-lithium alloy powder as raw materials, ball-milling and uniformly mixing the raw materials, and alloying the raw materials through high-temperature heat treatment, and the mass percent of boron, aluminum and lithium in the alloy powder is 67: (29-32): (1-4). According to the B-Al-Li alloy powder, common metal fuel lithium and aluminum are selected to be alloyed with boron, the combustion energy release defect of boron fuel is overcome, the B-Al-Li alloy powder shows remarkably improved oxidation efficiency and more excellent energy output characteristics, and the B-Al-Li alloy powder is suitable for being used as a metal fuel additive and applied to the fields of solid rocket propellants and explosives.

This invention provides a pre-cooling control method for a rocket propellant refueling system, comprising: setting up a return pipe between the refueling pump outlet pipe and the storage tank; starting the refueling pump to operate at a first frequency; opening a first regulating valve in the return pipe; when the propellant gas content in the return pipe is lower than a first set value, closing the regulating valve in the return pipe; opening a second regulating valve between the supercooler and the storage tank; adjusting the refueling pump to operate at a second frequency, wherein the second frequency is greater than the first frequency; real-time acquisition of a first pressure value in the supercooler inlet pipe and a second pressure value in the supercooler outlet pipe; when the difference between the second pressure value and the first pressure value is greater than a second set value, shutting off the refueling pump; opening the first regulating valve in the return pipe; and closing the second regulating valve. This control method can improve the reliability of the rocket propellant refueling pre-cooling process.