19 results about "Space Shuttle" patented technology

Combined aerospace system is a multi-stage technology to deliver payloads to orbit and to midair. The system comprises a carrier aircraft, a tow aircraft, a towed spaceplane or a rocket plane or a glider. The carrier aircraft, coupled with the spaceplane and / or the rocket plane or several gliders, takeoff from a runway and ascends to a staging altitude and speed under the carrier aircraft power. After staging, the tow aircraft will pick up the spaceplane or the rocket plane or the glider from the carrier aircraft in flight. The towed spaceplane or the rocket plane or the glider continues ascending and accelerating by the tow aircraft. The spaceplane or the rocket plane will disconnect from the tow aircraft and continue to ascend and accelerate in an atmosphere by using the ramjet engine. The spaceplane or the rocket plane equipped with a propulsion unit is used to place the spacecraft into the earth orbit. The glider will disconnect from the tow aircraft and lands in designated place. Gliders can be used for instantly delivering of correspondence, parcels, and civil goods from a supplier to wide variety of individual consumers or corporate customers.

A method for evaluating terrain uncertainty in flood warning and forecasting is provided. The method includes: S1, acquiring three types of digital elevation model (DEM) data from a shuttle radar topography mission (SRTM), an advanced spaceborne thermal emission and reflection radiometer (ASTER), and an advanced land observing satellite (ALOS); and preprocessing the three types of DEM data; S2, optimizing urban terrain characteristics; S3, constructing a multidimensional parameter space by using Latin hypercube sampling (LHS); S4, calculating flood hydrodynamics numerical value based on multidimensional sample points; and S5, constructing a global sensitivity analysis method frame suitable for urban terrain characteristics-related factors, where a Sobol quantitative method is used in the global sensitivity analysis method frame, and the Sobol quantitative method is used to evaluate uncertainties and sensitivity characteristics of multiple factors of terrain data based on a variance decomposition theory.

The utility model relates to the field of cooling wall plate structures, in particular to an active cooling wall plate structure for a space shuttle, which comprises a top plate, a bottom plate, a U-shaped fixing piece, a leading-in pipe and a leading-out pipe. Bottom plates used for being in positioning connection with the top plate are symmetrically arranged below the top plate, multiple sets of U-shaped fixing pieces used for reinforcing are transversely and symmetrically arranged on the two sides of the connecting positions of the bottom plates and the top plate, a leading-in pipe used for leading in a coolant is arranged at one end of the top plate, and a leading-out pipe used for leading out the coolant is arranged at the end, away from the leading-in pipe, of the top According to the utility model, the bottom plate and the top plate are oppositely attached, the connecting part of the bottom plate and the top plate is reinforced by the U-shaped fixing piece, the ingress pipe and the eduction pipe are positioned and assembled with the bottom plate and the top plate, and then a coolant enters a pipeline formed between the bottom plate and the top plate from the ingress pipe and is exported from the eduction pipe after a period of time. The cooling wall plate structure convenient to disassemble and assemble is adopted, cleaning and dredging can be conducted, and the efficiency and feasibility of maintenance and overhaul are greatly improved.

1. Name of the product in this design: Sightseeing vehicle (space shuttle). 2. Purpose of this design: This design is intended for sightseeing and tourism. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

1. The name of the design product: building blocks (space shuttle). 2. The use of the design product: building blocks. 3. The design features of the design product: in shape. 4. The picture or photo that best indicates the design features: perspective view.

The utility model relates to the technical field of model airplanes, and discloses a space shuttle model undercarriage mechanism which comprises two first shells, second fixing plates are fixedly connected to the left end and the right end of the front side of the first shell on the rear side, a self-locking mechanism is rotationally connected to the outer walls of the second fixing plates, and a third fixing plate is rotationally connected to the bottom end of the self-locking mechanism. A hatch cover is fixedly connected between the adjacent rear sides of the two third fixing plates, and a first fixing plate is fixedly connected to the middle of the front side of the first shell on the rear side. In the utility model, the motor is started to output power, the first rotary joint is driven to rotate through the transmission connecting rod, the wheels are driven to turn over to touch the ground, and after the transmission connecting rod is in place, the self-locking mechanism at the second rotary joint locks and prevents reverse movement, so that the transmission precision and the scene reduction degree are improved, the stable unfolding posture of the undercarriage is kept, and the cabin cover of the undercarriage is simultaneously opened in the process; and the process is ensured to be smooth and unobstructed, so that daily use requirements of operators are met.

The utility model relates to the technical field of aviation space shuttles, and discloses a positioning tool for an aviation space shuttle shell, which comprises a base, a support frame and a mounting frame, and the bottom of the support frame is fixedly mounted at the top of the base. Through the arrangement of the base, the supporting frame, the mounting frame, the adjusting mechanism, the positioning mechanism, the fixing mechanism and the sliding rod, firstly, the shell is mounted on the fixing plate, the lead screw is rotated, the lead screw drives the fixing plate to move through threaded connection, the fixing plate drives the anti-skid plate to move, the shell is fixed through the anti-skid plate, then the positioning rod is pulled, the mounting plate is moved, and the shell is fixed through the sliding rod. And the mounting plate drives the mounting frame to move, and then the positioning rod is mounted in the inner cavity of the positioning opening, so that the mounting plate is fixed, and the problems that in the prior art, the shell generally needs to be fixed through bolts during positioning, the fixing process is complex, the angle of the shell cannot be adjusted, and the fixing efficiency is reduced are solved.

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 invention relates to a lunar soil-based lunar brick making base and a lunar soil brick in-situ detection method. The lunar soil-based lunar brick making base is characterized in that an electric heating crucible and at least two sets of molds are conveyed to the moon by using a space shuttle; collecting lunar soil and conveying the lunar soil into a crucible by a lunar vehicle which already executes a task on the moon; the electric energy of the crucible is converted from solar energy, and the lunar soil in the crucible is melted by heating through the electric energy to form lunar soil slurry; pouring the molten lunar soil slurry into at least two sets of molds by the lunar rover, and cooling the lunar soil slurry in the molds to form lunar soil bricks; one part of lunar soil bricks are transported back to the earth for testing, and the other part of lunar soil bricks are left in the moon for environment testing; the brick making base comprises a lunar vehicle used for collecting and transporting lunar soil, a melting part and a maintaining and pouring part. The method has the advantages that an in-situ detection method of the lunar soil brick is provided, the lunar soil brick is manufactured in a real lunar environment and is subjected to environmental test, and real performance data of the lunar soil brick is obtained; meanwhile, a feasible scheme is provided for building a brick making base on the moon.

The utility model discloses an integrated space shuttle based on a two-stage rocket, and relates to the spacecraft technology, the integrated space shuttle comprises the two-stage rocket and a docking device, the front end of the two-stage rocket comprises a rocket fairing, and a plurality of satellites are arranged in the rocket fairing; a rocket body of the second-stage rocket comprises a space shuttle cabin, the rocket fairing is connected with the space shuttle cabin through a butt joint device, the space shuttle cabin can contain a space shuttle, and the space shuttle is provided with telescopic wings. Under the condition that a space shuttle is arranged in the space shuttle cabin body, telescopic wings of the space shuttle are in a contraction state, telescopic wing locking rings are arranged on the space shuttle cabin body and used for locking the telescopic wings of the space shuttle, and telescopic wing sliding rails are arranged at the two ends of the space shuttle cabin body. The multi-purpose rocket can be used for multiple purposes and can be repeatedly used after landing, meanwhile, the problem of heat insulation protection is solved, and accurate returning to a landing field can be achieved.

Disclosed is a complex scene deformation monitoring and classifying method based on interferometric synthetic aperture radar (InSAR) and a deep learning self-attention model, including: generating a deformation interferogram by using an InSAR extraction technology combining persistent scatterer (PS) points and distributed scatter (DS) points and relying on a shuttle radar topography mission digital elevation model (SRTM DEM) image; constructing a Delaunay triangulation network and an annular zone, obtaining a time series deformation data of PS points and DS points through adaptive arc densification and omni-directional point expansion, and extracting settlement points on a bridge; decomposing a time series by an SAR-self-attention model, decomposing InSAR time series data into a trend component and a seasonal component, and interpreting and analyzing deformation of the sea-crossing bridge; and describing time series dynamics and a seasonal pattern by comparing a curve fitting method with a seasonal and trend decomposition method.

1. The name of the design product: eraser (time and space shuttle). 2. The use of the design product: for eraser. 3. The design points of the design product: in shape. 4. The picture or photo that best indicates the design points: perspective view 1.

1. Name of the designed product: slide accessory (space shuttle slide). 2. Use of the designed product: accessory for slide. 3. Design points of the designed product: in the shape, pattern and combination thereof. 4. Picture or photo best indicating the design points: perspective view.

This utility model relates to the field of model aircraft technology and discloses an electric mechanism for the canopy of a space shuttle model. It includes a base plate, with L-shaped plates fixedly connected to the front and rear top sides of the base plate. An arc-shaped shell is fixedly connected between adjacent tops of two L-shaped plates. A bracket is fixedly connected to the inner center of each arc-shaped shell. A motor is fixedly connected between adjacent brackets. A worm gear is fixedly connected to the output end of the motor, and a worm wheel is meshed with the outer wall of the worm gear. In this utility model, the electric automated opening and closing of the canopy door is achieved by driving a worm gear transmission system and a hinge structure with a motor. Compared to traditional manual opening and closing methods, this greatly improves the convenience, efficiency, and reliability of the canopy door operation, providing a better opening and closing solution for related application scenarios. It also reduces manual operation costs and enhances the overall intelligence level of the equipment and the user experience.

1. Name of the designed product: assembled artware (spacecraft refrigerator sticker) 2. Use of the designed product: the designed product is used for assembling artware. 3. Design points of the designed product: the shape and pattern of the product and the layout of the components on the assembled state diagram. 4. Picture or photo that best indicates the design points: assembled state 1 front view. 5. The back of the designed product is not easily visible or invisible during use, so the rear view of each component is omitted. The designed product is thin, so other views of each component are omitted.

The application discloses a tank suitable for a reusable carrier, relates to the field of reusable earth-to-space shuttles, and comprises a tank body and a partition plate assembly arranged in the tank body. The partition plate assembly comprises a passage communicating between two sides of the partition plate and a movable plate. Propellant can flow downward through the passage. When the propellant shakes upward, the propellant pushes the movable plate to move upward and closes the passage. The tank can adapt to flight overload. When propellant moves forward due to the overload, the movable plate moves forward to close the opening of the top plate, so that the propellant is closed at the bottom of the tank, the movement of the propellant to the front bottom of the tank is effectively inhibited, and the manufacturing scheme is simple and reliable and has high universality.

The application relates to a DEM data fusion method based on multi-source data and machine learning, which comprises the following steps: collecting spaceplane radar terrain mapping task elevation model data, ICESat-2 satellite-borne laser radar data, land cover data and vegetation coverage data, and performing pretreatment; performing error factor analysis based on the pretreated data; sampling the data through a plurality of layered sampling methods for different factors, and respectively constructing a training set and a test set based on the sampled samples; constructing a DEM data fusion model based on extreme gradient boosting, inputting the training sets of different layered sampling methods into the DEM data fusion model, obtaining a DEM data fusion model, verifying the precision of the DEM data fusion model of the current layered sampling method through the test set corresponding to the layered sampling method, taking the highest precision as the final DEM data fusion model, and finally processing the abnormal values of the fused DEM data.

1. Name of the designed product: VR virtual experience device (space shuttle). 2. Use of the designed product: virtual environment matching device. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view 1.