66results about How to "Reduce negative quality" patented technology

The invention aims to provide a propellant supply system for an RBCC large regulating-ratio liquid-propellant rocket engine. The system comprises an oxidizing agent supply system, a fuel supply system and a gas blowing-down system, and the systems communicate with the engine respectively, wherein the fuel supply system is also connected to a fuel pressurization system. The fuel supply system comprises a fuel storage tank used to provide fuel to the engine, wherein a fuel flow regulating system used to adjust a flow rate and a mixing rate of a propellant is disposed on an output pipeline of the fuel storage tank; and the fuel flow regulating system comprises a plunger pump, and the plunger pump is connected to a motor drive device used to control actions of the engine. The system solves the problems that an existing propellant supply system cannot be integrated in an RBCC, and the flow rate and the mixing rate of the propellant cannot be adjusted within a large scope simultaneously.

The invention discloses a planetary rotor engine. Crankshafts (4) are arranged in a cylindrical stator (1) of the planetary rotor engine, and the two ends of the cylindrical stator (1) are sealed through end covers. Main shaft necks at the two ends of the cylindrical stator (1) are supported in the centers of the crankshafts (4), and planetary columns (5) are supported on planetary shaft necks in the middle sections of the crankshafts (4). A set of telescopic blades (6) are inserted in each planetary column in the radial direction. The planetary columns and the left sides and the right sides of the blades are in sliding and sealing fit with the inner walls of the end covers, the outer sides of the blades and the inner wall of the stator. An inner cavity of the stator is divided into a set of cylinders by the blades. The planetary columns rotate in the opposite direction while revolving around the axis of the stator, so that the volumes of the cylinders are increased and decreased periodically, and the strokes including air suction, compression, acting and exhausting are completed in sequence. Fuel gas expands to push the blades and the planetary columns to act in pairs, so that the acting torque is increased; the cylinders are densely arranged, so that the power is sufficient; the rotating direction is opposite to the revolving direction, so that the speed, relative to fixed part, of moving parts is low, and the friction between the moving parts and the fixed part is small.

The invention discloses a preparing method for a cable embedded composite material shell. The preparing method comprises the following steps that firstly, a heat insulation structure is manufactured;secondly, the shell is manufactured through fiber wet process winding; thirdly, cable pavement is conducted; and fourthly, demoulding is conducted. A cable cover is not needed for pavement of a cableon the shell, the passive mass of the shell is reduced, the cable pavement technology is simplified, and the machining efficiency is improved. The cable is embedded between carbon fiber composite material layers of the shell, the cable can well adapt to stress deformation of the shell, the two outermost sides of the cable are filled with light foam materials, and the structure coordination of a winding layer is guaranteed.

The invention discloses a multifunctional simulation engine for adiabatic layer ablation test, which comprises a gas generator. One end of the gas generator is sequentially connected with a low speedsection, a medium speed section, a high-speed section, an overload section and a plume section and forms a through cavity; the low speed section, the medium speed section and the high-speed section are coaxially connected; the overload section is raised up and coaxially connected with the plume section; the end portion of the overload section is provided with a jet exhaust; the plume section is arranged on the periphery of the jet exhaust; a test piece A, a test piece B and a test piece C are respectively correspondingly installed in the inner cavity of the low speed section, the medium speedsection and the high speed section; a test piece D is mounted at the lower section of the inner cavity of the overload section; a test piece E is mounted on the upper section of the inner cavity of the overload section; and a test piece F is arranged at the corresponding jet exhaust of the plume section. According to the multifunctional simulation engine for adiabatic layer ablation test in the invention, the test pieces are mounted in the inner cavity of each section, thereby detecting and understanding the ablation phenomenon of each section.

The invention relates to a preparation method of a composite air cylinder and relates to the technical field of manufacturing of composite pressure vessels. The preparation method of the composite aircylinder comprises the steps that a step-by-step broaching mode is adopted for winding layers in the spiral direction of the composite air cylinder, and various winding angles are determined according to the linear trajectory of a geodesic line; and in the winding process, a non-geodesic line winding mode is adopted, variable-angle variable-speed-ratio winding is carried out on an end socket section, and variable-pitch winding is carried out on an edge area of a cylinder body section. Thus, the winding angles of various points of the end socket area are relatively increased, the difference between the internal radius and the external radius of each 'fiber stacking ring' is increased to 1.5-2 times of the actual yarn sheet width, an end socket approaches the uniform thickness, the surplusmass of the end socket can be reduced effectively, the characteristic coefficient of the vessel is increased, and the lightweight purpose of the air cylinder is realized.

The invention discloses a triaxial quartz flexure accelerometer small-size signal sampling device comprising an accelerometer. The device also comprises a signal collection mechanism that comprises apre-amplification module, a switch module, a differential amplification module, an AD conversion module and a controller-integrated FPGA main control module which are sequentially connected with the accelerometer in series; and the switch module is also connected with the FPGA main control module. By using the triaxial quartz flexure accelerometer small-size signal sampling device adopting the abovementioned structure provided by the invention, a digital sub-system substrate and an analog sub-system substrate are perpendicularly interconnected via solder balls, so that the whole size is reduced, the miniaturization is achieved; meanwhile, by using the FPGA main control module, the collection and conversion from an accelerometer analog signal to a digital signal are achieved, the linear relation between the output digital signal and the acceleration signal is ensured, and the stability of zero and scale can be ensured, so that the performance of the header of the accelerometer is furthest ensured.

The invention provides a basket type igniter of a rotary solid rocket engine. The basket type igniter comprises an ignition top cover, a top cover hard heat insulation layer, a top cover soft heat insulation layer, a front heat insulation sleeve, an O-shaped sealing ring, a rear heat insulation sleeve, an igniter shell and an ignition gunpowder box. The top cover hard heat insulation layer is placed in the ignition top cover, and the top cover soft heat insulation layer adheres to the top cover hard heat insulation layer. The ignition gunpowder box is connected with inner threads of the igniter shell, the igniter shell is provided with the O-shaped sealing ring in a sleeving manner, and the igniter shell is connected with the ignition top cover through outer threads of the igniter shell and is abutted to the top cover soft heat insulation layer. The front heat insulation sleeve adheres to an end face of the ignition top cover, and the rear heat insulation sleeve adheres to the front heat insulation sleeve. The basket type igniter is high in structural quality performance, compact in ignition structure, low in negative mass, good in sealing performance, good in manufacturability, high in reliability, capable of being applied to an ignition system of the rotary solid rocket engine, low in machining precision, convenient to install, high in connection reliability, reliable in ignition performance and capable of being used for the solid rocket engine which is ignited from the head.

The invention provides a heat insulation layer structure of a solid rocket engine long-tail nozzle, and a preparation method thereof. The heat insulation layer structure comprises an ablation layer, afirst heat insulation layer and a low-density heat insulation layer which are arranged in an attached mode, wherein the ablation layer takes a phenolic resin as a matrix material and takes carbon fiber as a reinforcing material, the first heat insulation layer takes a phenolic resin as a matrix material and takes high silica glass as a reinforcing material, and the low-density heat insulation layer takes a phenolic resin added with a light filler as a matrix material and takes glass fiber as a reinforcing material. According to the heat insulation layer structure, the low-density heat insulation layer is arranged on the basis of the ablation layer and the heat insulation layer, and by utilizing the characteristic of low heat conductivity of the low-density material, under the condition that the ablation resistance is not influenced, the heat insulation performance of the heat insulation layer of the long-tail nozzle is improved, ablation and heat insulation are balanced, and the heatprevention efficiency of the heat insulation layer of the long-tail nozzle is improved; and the mass ratio of the long-tail nozzle product can be increased, and the problems of low mass ratio and highthermal conductivity of a traditional structure of the long-tail nozzle are solved.

The invention discloses an inner heat insulation layer structure of a front seal head of a solid rocket engine and a forming method of the inner heat insulation layer structure. A multi-step structureof an inner profile surface of the inner heat insulation layer is realized. The forming method of the inner heat insulation layer comprises the step 1 of manufacturing a mold according to an inner heat insulation layer structure, the step 2 of sandblasting the inner wall surface of the front seal head, the step 3 of preparing a liquid heat insulation layer, the step 4 of pouring the liquid heat insulation layer with the set mass into the front seal head, the step 5 of assembling the mold and the front seal head to a set position to ensure the designed thickness of the heat insulation layer, the step 6 of putting the product into an oven for curing, and the step 7 of taking out the product after the curing time is met, cooling the product to normal temperature, taking out the mold, and shaping and cutting the heat insulation layer to obtain the designed heat insulation layer. The heat insulation layer is high in size control precision, good in quality consistency and simple in process,and the forming method can meet the forming requirements of inner heat insulation layers in various irregular shapes.

The invention discloses a sliding plate rotor engine. The sliding plate rotor engine is characterized in that two ends of a barrel-shaped stator (1) are closed through end covers (2); an internally arranged engine spindle (3) is supported on the centers of the end covers; an eccentric wheel (4) which is connected onto the engine spindle (3) is sleeved with a sliding plate ring (5); the sliding plate ring is fixedly connected with a radial fixedly-connected sliding plate (6) and is hinged to a group of outward hinge-connection sliding plates (7); the end surfaces of two ends of each of the eccentric wheel, the sliding plate ring and the sliding plates are in sliding and sealing match with the inner walls of the end covers; the parts, which face the sliding plates, of the outer wall of the stator are each provided with a longitudinal shaft seat (1a); a round shaft body (8) is arranged in each shaft seat (1a); the sliding plates radially penetrate through the corresponding round shaft bodies and are in sliding and sealing match with the corresponding round shaft bodies; and the part, between every two adjacent shaft seats, of the stator wall is provided with an air inlet valve (9), an air exhaust valve (10) and a sparking plug (11). The inner cavity of the stator is divided into a plurality of sealed air chambers through the sliding plates; and the volume of each chamber is increased and decreased regularly along with the rotation of the spindle, so that circulation of air suction, compression, working and air exhaust is realized. Rotation power is directly output; the structure is simplified; the heat efficiency is high; the power consumption is low; the size is small; and the mass is light.

The invention discloses a low-density ablation-resistant ethylene propylene diene monomer material and a preparation method thereof. The low-density ablation-resistant ethylene propylene diene monomer material is prepared from 100 parts of ethylene propylene diene monomer, 15-30 parts of a reinforcing filler, 10-20 parts of organic fiber, 5-15 parts of inorganic fiber, 5-15 parts of an ammonium salt flame retardant, 3-5 parts of a light filler, 5-15 parts of a metal hydroxide filler, 10-20 parts of a tackifying resin, 5-10 parts of a petroleum softening agent and 2-4 parts of a peroxide vulcanizing agent, and is formed through mixing, open milling and hot-pressing vulcanization. According to the invention, the material not only has low density, but also can significantly improve the strength of a carbon layer and improve the ablation resistance and scouring resistance of the material by compounding the organic fiber and the inorganic fiber and matching with the ammonium salt flame retardant and the metal hydroxide filler, and is suitable for a high-temperature strong-scouring working environment of a solid rocket engine.

The invention discloses a forming method of a fiber-wound solidification rocket engine multiphase heat-insulating layer. The multiphase heat-insulating layer is jointly composed of ablation-resistantEPDM and a phenolic resin impregnated carbon fiber three-dimensional weaving body; on the one hand, under the condition that the thickness of the heat-insulating layer is not increased, ablation resistance of heat-insulating materials can be improved, the negative mass of an engine shell is reduced, and the mass ratio of an engine is increased; on the other hand, a multilayer patch mode and the design of a sandwich structure are adopted, and the formed multiphase heat-insulating materials have good manufacturability; and through two times of prepressing, on the one hand, gas between the two types of heat-insulating materials and between EPDM film layers is discharged, on the other hand, good interface bonding between the phenolic resin impregnated carbon fiber three-dimensional weaving body and the heat-insulating layer on the upper and lower positions is guaranteed, and the defects such as bulges, gas entrapment and debonding between the multiphase heat-insulating materials of the EPDM and the phenolic resin impregnated carbon fiber three-dimensional weaving body are prevented.

The invention discloses an inserting plate rotor engine. A spindle (6) is arranged on the axis of a cylindrical case (1) with the two ends closed by end covers (5), a cylindrical rotor (2) is mountedon an eccentric shaft (6a) on the spindle in a sleeving mode, no less than three inserting grooves (4) with inward groove openings are hinged to the inner wall of the case in an even distribution mode, inserting plates (3) matched with the inserting grooves are outwards hinged to the outer wall of the rotor in an even distribution mode, the two ends of the eccentric shaft, the two ends of the rotor, the two ends of the inserting grooves and the two ends of the inserting plates are closely attached to the inner walls of the end covers correspondingly for sliding fit, all the inserting plates are inserted into the corresponding inserting grooves, an interlayer between the rotor and the case is divided into a plurality of closed cavities which are each provided with an intake valve (7), an exhaust valve (8) and a spark plug (9) to serve as engine air cylinders, and the volume of each air cylinder is periodically increased and decreased along with rotation of the spindle to complete the air suction, compression, work and exhaust stroke to drive the spindle to do work. The inserting plate rotor engine is large in power, small in size and simple in structure.

The invention discloses a projectile base separation mass reduction extended-range projectile. The projectile base separation mass reduction extended-range projectile comprises a warhead, a solid engine and a projectile base separation mechanism. The solid engine comprises a solid engine shell, a solid engine cartridge case, a spray tube used for spraying a combustion product and a fixed firing igniter. The solid engine cartridge case is arranged inside the solid engine shell. The projectile base separation mechanism comprises a projectile base, a base bleed shell and a base bleed igniter. According to the projectile base separation mass reduction extended-range projectile, the projectile base separation mechanism is separated from the projectile through fuel gas generated from base bleedpowder charge and solid engine powder charge, and the solid engine continues to propel the remaining effective load to fly; through the projectile base separation mechanism, the negative mass of the projectile in the flying process is effectively reduced, and the projectile flies much farther under the same powder charge condition. Through the projectile base separation design method, the negativemass of the projectile in the flying process is effectively reduced. Moreover, the method is simple and easy to realize. The projectile base separation mass reduction extended-range projectile has the advantages of being safe, reliable and low in using requirement.

The invention relates to a preparation method of an ablation-resistant anti-scouring ethylene-propylene-diene monomer rubber heat insulating material. The preparation method comprises the following steps: S1, adopting an ethylene-propylene-diene monomer rubber material as a matrix material, and adding an ablation-resistant auxiliary material, fibers, a softener, a reinforcing agent, a vulcanizingsystem and other preservatives into the matrix material; S2, carrying out plastication and mixing procedures, and formulating a basic formula meeting mechanical and ablation performance; S3, manufacturing small samples, mechanical test pieces and ablation test pieces, and detecting mechanical and ablation performance; S4, analyzing performance detection data on the basis of detection, and adjusting the proportion of the auxiliary materials; S5, adjusting the formula, and then preparing small samples; S6, preparing mechanical test pieces, ablation test pieces, heat-conducting test pieces and density test pieces, carrying out detection to obtain detection data, and finally detecting a final formula; and S7, preparing a novel material according to the final formula to obtain the heat insulating material. The heat insulating material provided by the invention has the advantages of low density, good anti-scouring and ablation-resistant performance, excellent bonding performance and excellent comprehensive performance.

The invention designs a forming method of a high-frequency vibration resistant high-pressure gas cylinder wound with a support, which is characterized by comprising the following steps: S1, cleaning the surface of a lining, and brushing an adhesive; s2, longitudinally winding, annularly winding and reinforcing the winding layer according to the thickness of the composite layer required by the design, and then pre-curing; s3, bonding of the support is completed; s4, outer reinforcement and winding of the support are completed; and S5, the wound gas cylinder is subjected to final curing. According to the gas cylinder connecting structure, the negative mass of the extrusion type rocket engine high-pressure gas cylinder is reduced, and the reliability of the gas cylinder connecting structure is improved; the winding core mold is simple in principle, easy to process, detachable and low in cost; and the prepared composite material has the advantages of high reliability, good loading capacity and the like.