11 results about "Astronautics" patented technology

The utility model relates to the technical field of dies, and provides an aerospace support forming die which comprises a lower die, supporting columns are fixedly installed on the periphery of the bottom of the lower die, side plates are fixedly installed on the two sides of the lower die, sliding grooves are formed in the left sides and the right sides of the opposite sides of the side plates, and hydraulic machines are fixedly installed on the tops of the side plates. A hydraulic rod is fixedly mounted at the bottom of the hydraulic machine; an upper mold is fixedly mounted at the bottom of the hydraulic rod; according to the forming mold of the support for aerospace, through cooperative use of a second spring structure and a vertical rod structure, during work, fan blades rotate to drive a toothed rod to rotate, left and right cylinder sleeves are driven by a vertical rod to move downwards to the bottommost part of a threaded column, and after the fan blades stop rotating, round sleeves automatically rotate and move upwards to reset under the elastic force action of first springs; and the top of the striking block continuously collides with the bottom of the heat conducting plate, so that the formed support and the inner cavity of the lower mold are loosened, and the effect of conveniently and rapidly taking out the cooled support is achieved.

The utility model relates to the technical field of aeronautics and astronautics, and discloses an aviation space shuttle engine mounting base which comprises a base body, a first sliding groove, a second sliding groove and a third sliding groove. The lifting part is arranged at the top of the base; an engine body is placed on the top of a sliding bottom plate, then a clamping plate is driven to slide along the track of a second sliding groove, the engine body is clamped and fixed, and therefore a sliding frame is driven to slide, then a brake column is pressed downwards, a brake column drives a lower pressing block to slide downwards, and therefore the lower pressing block extrudes trapezoidal clamping blocks on the two sides; when the bottom end of a lower pressing block makes contact with the top of a limiting block, a trapezoidal clamping block and a friction plate extrude and fix the inner wall of a second sliding groove, meanwhile, an elastic clamping hook is inserted into a clamping opening and clamped and fixed to the clamping opening, the purpose of rapidly fixing the position of the sliding frame is achieved, and on the contrary, the purpose of rapidly adjusting the position of a clamping plate is achieved by pressing the elastic clamping hook.

The utility model relates to the technical field of aerospace cables, and discloses a silver-plated copper-clad aluminum wire cable for aerospace, which comprises at least two conductors, insulating layers are arranged on the outer sides of the conductors, a shielding layer is arranged between the outer sides of the two insulating layers, and a sheath layer is arranged on the outer side of the shielding layer. Compared with a traditional pure copper conductor, the overall weight of the cable is remarkably reduced, the effective load of a spacecraft can be improved, and the launching cost is reduced. The silver plating layer ensures high conductivity of the cable and ensures efficient transmission of electric power or signals; meanwhile, high-performance materials of the insulating layer and the sheath layer are selected, so that the temperature resistance, chemical corrosion resistance and mechanical strength of the cable are enhanced, and the cable is suitable for an extreme aerospace environment.

The invention discloses a low-resistance acoustic lining panel with elliptical holes and a design method thereof, the low-resistance acoustic lining panel comprises a perforated plate, a plurality of uniformly distributed through holes are formed in the perforated plate, the hole opening direction of the through holes is perpendicular to a fixed wall, and the through holes are elliptical holes; the short axis direction of the elliptical hole is the same as the airflow direction; the short axis length of the elliptical hole is greater than the thickness of the acoustic viscosity boundary layer corresponding to the target sound wave frequency; the elliptical holes are uniformly distributed in rows and columns on the fixed wall, and the elliptical holes in adjacent rows are distributed in a staggered manner, so that the elliptical holes in the middle row and the center connecting lines of the left and right adjacent elliptical holes in the front and back rows can form an equilateral triangle. According to the acoustic liner perforated plate, the hole shape of an existing acoustic liner perforated plate is changed into the oval shape from the original round shape, the size of the oval hole is designed, the flow resistance coefficient of the acoustic liner can be reduced on the premise that the overall acoustic performance of the acoustic liner is not changed, the considerable resistance reduction effect is achieved, and therefore oil consumption of an airplane can be reduced.

The invention discloses a detection algorithm for dynamic faults of a memory, and aims to realize 100% coverage of all non-associated static faults (including single-unit faults and coupling faults), non-associated dynamic single-unit faults (SCF) and Saa / Svv type double-unit dynamic faults (DCF). Based on the analysis of a system fault model, the designed March YZ algorithm is integrated with an optimized operation sequence, on the premise of reserving the fault activation, sensitization and detection capabilities, detection sequences of dTF, dWDF, dCFtr and dCFwd type dynamic faults are emphatically adjusted, and redundant read-write cycles are eliminated. The complexity of the March YZ algorithm is only 62n, is reduced by 8n compared with the existing March MD2 (70n), and is reduced by 4n compared with the March WY (66n); the test time is reduced by 11.4% and 6.1% respectively while full fault coverage is realized, the operation energy consumption of a memory is reduced by 5-15%, the area overhead of an MBIST circuit is reduced, and the method is adaptive to advanced process SoC (System on Chip) of 5nm and below, and can be applied to high-reliability scenes such as automotive electronics, aeronautics and astronautics, industrial control and the like.

The present application relates to a kind of parachute supersonic speed condition open umbrella after breathing frequency spectrum determination method, belong to the field of aeronautics and astronautics aerodynamic deceleration.This method is first by acceleration sensor obtains the working process load time curve of parachute supersonic speed condition.Then the Fourier transform is carried out to parachute load, obtains the load frequency curve, by extracting extreme value in frequency load curve, to obtain the accurate frequency data of parachute breathing action under supersonic speed condition.The present application can calculate all parachute breathing action frequency, without limit to umbrella type and open umbrella condition.

The utility model discloses a kind of high-strength special conductors, it relates to cable technical field, including main conductor, the main conductor includes PBO fiber silk, PBO fiber silk outside four around twisted has tinned soft copper stranded wire, tinned soft copper stranded wire outside four around braided has tinned copper wire, tinned copper wire outside four around winding has shielding copper band one, shielding copper band one outside four around winding has insulating sleeve one, the insulating sleeve one four around cladding has filler, the filler is completely filled in insulating sleeve two inside. Multiple main conductors exist in the insulating sleeve two. The special conductor structure form that the utility model in multiple main conductors, multiple tensile structure are jointly constituted, make conductor structure more round and stable;Main conductor and tensile structure use PBO fiber silk, its excellent performance, improve the softness of conductor while can promote the strength of conductor, meet the electrical performance and mechanical performance requirement under special environment such as aeronautics and astronautics.

Method and Apparatus for Creating Artificial Gravity in Spacecraft and Space Stations Using Anti-Parallel Reaction Engines is disclosed. The reaction engines are activated to spin the spacecraft or the space station and generate centrifugal gravity. The spacecraft is designed to be cylindrical in shape to maximize the surface area available for the installation of the engines. The station is designed to be circular in shape as well. The method has several applications in astronautics and space exploration, specifically for long-duration space missions where exposure to microgravity can cause adverse health effects to crew members. The method is highly efficient, providing a sustainable and controlled gravity environment without the need for large, heavy, and power-hungry traditional gravity generation systems. The invention also offers a high degree of flexibility with scalability for spacecraft of different sizes and shapes. The anti-parallel arrangement of the reaction engines ensures stability and a controlled spin rate, mitigating the risks associated with traditional mechanical alternatives. The invention offers significant improvement in the field of space exploration, providing safe, sustainable, and cost-effective solutions for generating artificial gravity in spacecraft.

The invention discloses a composite material propeller blade structure and a manufacturing method thereof. The composite material propeller blade structure comprises a supporting pipe; the girder layer comprises a middle girder, a front edge girder and a rear edge girder; the skin layer comprises a first skin, a second skin and a third skin; the threaded sleeve is arranged on the outer side of the first skin, and external threads are arranged on the outer side of the threaded sleeve; the cloth liner layer is arranged on the outer side of the first skin; and the metal pipe fitting is used for being connected with a propeller hub and is in threaded connection with the threaded sleeve. According to the invention, the blades made of the composite material are arranged and are cured to form a whole body, so that firm interface bonding is formed, loads are effectively transmitted, stress concentration is avoided, the propeller can be suitable for low-rotating-speed and large-load electric vertical take-off and landing aircrafts, and the structural weight is reduced and the reliability is improved while the connection reliability is ensured.

The utility model provides an air tightness detection device for aerospace parts, and belongs to the technical field of spacecraft processing and manufacturing. The device is simple and ingenious in structure, high in workpiece detection adaptability and easy to operate, and the detection result is convenient to observe. Universal wheels are arranged at the bottom of an object carrying sliding plate of the device, a workpiece frame is placed on the object carrying sliding plate, the object carrying sliding plate is slidably inserted in a housing, a workpiece is in ventilation communication with external air supply equipment through a reducing flange joint and an air injection pipe, a liquid containing pipe is fixedly arranged on the housing, and marking liquid is filled in the liquid containing pipe. External air supply equipment operates to inflate air into the workpiece for air tightness detection, and the detection result is mastered by observing the liquid level change of the liquid containing pipe. The device is flexible in structure, convenient in workpiece mounting and dismounting, suitable for detection of workpieces of various structural sizes, simple and convenient in detection operation, convenient in observation of detection results, adjustable in height of the bearing plate, capable of stably supporting and bearing the workpieces, and capable of reducing the burden of a user for carrying the workpieces at the same time.

The forming die comprises an upper cover plate, a lower cover plate, a penetrating connection rod, a sleeving connection rod, an upper die plate, a lower die plate, a liquid injection opening and supporting legs, a movable body and a driving hydraulic cylinder are arranged to enable the movable body and the driving hydraulic cylinder to generate upward jacking force on the bottom on a lifting plate, the positions of the side ends of the hinged connection rods are changed, and the supporting legs are arranged on the upper die plate and the lower die plate. The lifting plate is driven to rotate to drive the hinged connecting frame to swing and move and gradually tend to be vertically placed, meanwhile, the changing frame is driven by the lifting plate to move, the swinging and folding block can assist in driving the buckling and pressing block to move and drive the buckling and pressing block to turn over and swing, the buckling and pressing block is transversely placed from the vertical direction, and the front end of the buckling and pressing block is buckled and pressed on the upper end face of the side of the upper cover plate. The two movable bodies are arranged, the downward pressing effect is generated on the two sides of the upper cover plate at the same time, and the situation that the distance between the upper mold plate and the lower mold plate is increased due to thermal expansion of injection molding liquid, the upper cover plate can move upwards autonomously, and the forming effect of the support is affected is avoided.