45results about How to "Improve aerodynamic performance" patented technology

The utility model relates to the field of antenna support discloses an unmanned aerial vehicle antenna support including low shelter bionical support structure, low shelter bionical support structure includes support frame, the inner wall fixedly connected with support rod of support frame, the inner wall fixedly connected with mounting rod of support frame, the bottom outer wall rotationally connected with gyroscope structure of mounting rod, the gyroscope structure includes first ring, the inner wall rotationally connected with second ring of first ring, the inner wall rotationally connected with third ring of second ring, the inner wall rotationally connected with signal receiver of third ring through pivot. In the utility model, through setting up low shelter bionical support structure, reduce the support to the signal shelter, and reduce the weight of self, through setting up gyroscope structure, realize antenna real -time attitude compensation, make signal receiver always steady point to target, solve the problem that the antenna is easy to disconnect with ground because of fuselage attitude change.

The utility model discloses a turbine rotor blade, a turbine rotor and an engine turbine, which belong to the technical field of turbine engines and are used for solving the problem of insufficient connecting strength of an extension root and a tenon caused by overweight of the turbine blade. The turbine rotor blade provided by the utility model comprises a cavity, one end, positioned at the blade tip, of the cavity is provided with an opening, and the other end of the cavity is closed; the cavity sequentially comprises a first cavity section, a second cavity section, a third cavity section and a fourth cavity section in the radial direction of the blade. The first cavity section and the second cavity section are formed in the center of the interior of the tenon; the third cavity section and the fourth cavity section are respectively arranged in the extension root and the blade body and are respectively matched with the extension root and the blade body in appearance; the chordwise width of the first cavity section and the second cavity section along the blade is smaller than the chordwise width of the third cavity section along the blade. According to the turbine rotor blade, the strength and the rigidity of the blade are effectively considered, and the overall performance of an engine turbine is improved.

Tractor (2) of a commercial vehicle (1) comprising lateral fairings (20) each having a fixed portion (21) attached to a chassis (5), a movable portion (22), and a mounting arrangement (25) to vary a fairing height of the movable portion (22) in accordance with a fifth-wheel height (Hfw) of a fifth-wheel coupling (15), wherein the mounting arrangement (25) is chosen between: - a discontinuous mounting arrangement (25) comprising a first mounting member and a series of second mounting members, the series of second mounting members comprising separate second members aligned at different mounting heights, - a continuous mounting arrangement (25) comprising a pinion and a rack configured to cooperate with each other to move the movable portion (22) with respect to the fixed portion (21) within a range of mounting heights when the pinion (30) is driven in rotation.

This invention discloses an optimization design method for S-curve nozzles used in aero-engines that considers structural deformation, belonging to the field of aero-engines. The method selects key geometric parameters of the S-curve nozzle as characteristic parameters, chooses the structural deformation value at a characteristic location and two aerodynamic performance parameters as objective functions, then conducts orthogonal experimental design and constructs a response surface model based on the characteristic parameters and objective functions. After each optimization step, a cyclical evaluation is performed to obtain the final optimization result. This invention solves the problem of high aerodynamic performance loss caused by large structural deformation in S-curve nozzles used in aero-engines in existing technologies.

The application discloses a design method of a fan blade, the fan blade, a fan and an extractor hood. The fan blade is arranged in a fan impeller. The design method comprises the following steps: taking a plane perpendicular to the rotating axis of the fan impeller as a characteristic plane, defining the blade profile of the fan blade on the characteristic plane as a characteristic curve, and the characteristic curve is a double circular arc curve; taking the blade profile of a single circular arc blade on the characteristic plane as a first circular arc of the characteristic curve, taking the inlet angle of the characteristic curve, the outlet angle of the characteristic curve and the radius of a second circular arc of the characteristic curve as three factors, obtaining a linear regression equation about the flow of the fan and a linear regression equation about the total pressure efficiency, and taking the optimal solution as the size parameter of the fan blade. The design method of the fan blade obtains the design parameters of the double circular arc curve on the basis of the current single circular arc blade, improves the internal flow state of the fan and improves the aerodynamic performance of the fan.

The application relates to a blade, an impeller and a ventilation device, the blade comprises a plurality of control surfaces arranged in layers along the height direction of the blade, the blade comprises an arc-shaped leading edge, the distance between the leading edge and the central axis of the impeller is an inner diameter of the blade, and the inner diameters of the plurality of control surfaces are different from each other. The impeller of the application changes the design of the blade along the height direction of the blade under the same hub groove structure, so that the leading edge of the blade is designed by using different control points, and the shape of the groove for accommodating the motor of the hub is matched, the air volume is increased, the aerodynamic noise is reduced, the power consumption is reduced, and the aerodynamic performance of the ventilation device is improved.

The utility model provides a centrifugal fan, the centrifugal fan includes volute and sets up in the volute a plurality of blades, the blade still includes: the bending section, the bending section extends from the import end of blade to the export end of blade, along the height direction of blade, the export end of blade forms the first part of being located above the bending section and the second part of being located below the bending section through the bending section, the first part and the second part staggered setting, wherein, the height of first part and the export end height ratio of blade 0.5 0.8. Through setting bending section, to make blade's first part and second part have the phase difference along the height direction of blade, break the shedding vortex of blade export end, reduce the wide frequency noise of fan. And make the airflow downward can reduce the collision with the wall, can effectively promote the aerodynamic performance and efficiency of fan and reduce the aerodynamic noise.

The invention discloses a predetermined time adaptive control method for a wing-riding separation variant gliding aircraft, and the method specifically comprises the following steps: firstly, constructing a time scale function, and effectively avoiding the problems of unlimited increase of control quantity and singularity; secondly, designing a preset time sliding mode surface based on the time scale function; thirdly, providing a neural network parameter identification strategy, and converting a system identification problem into a parameter estimation problem so as to adapt to a flight scene with uncertain aerodynamic parameters; and finally, designing a preset time self-adaptive sliding mode controller, and realizing convergence in specified time under the condition of ensuring that the system state is not dependent on an initial condition. The adaptive gain of the controller can be dynamically adjusted according to the system environment, jitter can be inhibited, tracking errors can be reduced, and the influence caused by centralized uncertainty can be weakened; in conclusion, the control method not only realizes accurate attitude tracking, but also achieves preset time convergence characteristics irrelevant to initial conditions and control parameters, and has excellent quick responsiveness, stability and robustness.

The miniature unmanned aerial vehicle comprises a force bearing rack, a first rotor wing unit and a second rotor wing unit, the first rotor wing unit comprises at least two upper rotor wing assemblies arranged on the first face of the force bearing rack, and a height difference exists between paddle rotating planes of the adjacent upper rotor wing assemblies; the horizontal projections of the blade rotation tracks of the adjacent upper rotor assemblies form a first overlapping area; the second rotor wing unit comprises at least two lower rotor wing assemblies arranged on the second face of the force bearing rack, the first face and the second face are oppositely arranged, the lower rotor wing assemblies and the upper rotor wing assemblies are arranged in a staggered mode, and a height difference exists between paddle rotating planes of the adjacent lower rotor wing assemblies. And the horizontal projections of the blade rotation tracks of the adjacent lower rotor assemblies form a second overlapping area. The upper rotor wing assembly and the lower rotor wing assembly with the height difference are arranged on the force bearing rack, and the overlapped area design of the assemblies on the horizontal projection is adopted, so that the space utilization efficiency is improved.

The invention is suitable for the technical field of automobile aerodynamics, and provides a self-adaptive flexible spoiler experimental development method under a yaw working condition, and the method comprises the steps: arranging and driving a flexible spoiler in a wind tunnel; the parameters of the spoiler are optimized with the wind resistance coefficient as the target at the multiple yaw angles; designing a piecewise linear rule controller based on an optimization result; pressure monitoring points are arranged on the two sides of a vehicle body, the regression relation between the pressure difference and the yaw angle is established, and the yaw angle is recognized in real time; developing a self-adaptive resistance reduction optimization program, driving the spoiler to be adjusted to the optimal form in real time according to the identified yaw angle, and verifying the resistance reduction effect of the spoiler; a mathematical method is used for calculating the curved surface shape of the spoiler, and reference is provided for automobile appearance design. Aerodynamic configuration self-adaptive adjustment of the vehicle under the crosswind working condition can be achieved, the wind resistance optimization capacity of the real vehicle in the running process is remarkably improved, and an effective experimental method and design basis are provided for low-wind-resistance development of the vehicle.

The invention discloses a downwind type small wind driven generator turbine which comprises a rotor blade body axially swept back from a blade root to a blade tip, the front edge of the blade is provided with a bionic nodule structure changing in a sine rule, and the rear edge of the blade is provided with a sawtooth-shaped corrugated structure; the blades and the hub are connected to form a wind turbine rotor, the rotor is located on the downwind side of the tower, wind flow firstly passes through the tower and then acts on the rotor blades, the downwind layout enables the blades to be capable of natural feathering under the action of wind loads, therefore, dynamic load impact on the tower is reduced, and the yaw system structure is simplified. The tower shadow effect can be remarkably relieved through the whole sweepback type blades, and aerodynamic noise is reduced; the front edge nodules of the blades are bionic to fin limbs of the seat head whale, so that the lift-drag ratio can be effectively increased, broadband noise is reduced, and violent fluctuation of power and load is inhibited; sawtooth ripples on the rear edge of the blade imitate a comb-shaped structure on the rear edge of the flying feather of the owl, so that vortex shedding frequency concentration can be inhibited, and high-frequency noise can be remarkably reduced.

The application discloses a kind of parameterized modeling-based optimization design method and system of centrifugal fan volute profile, belong to industrial centrifugal fan design field.The method includes: firstly, volute profile away from volute tongue side is constructed, determine the width of two circular arcs away from volute tongue side of volute;Second volute tongue profile parameterization constraint, define volute tongue opening degree β, volute tongue radius R, volute tongue center and impeller center distance D key parameter, volute tongue geometry is controlled by three parameters independently;Finally, profile fusion and optimization, adopt single circular arc to connect volute profile away from volute tongue side and volute tongue profile tangentially, avoid geometric over definition problem, complete overall modeling.By improving the degree of freedom of volute tongue area, effectively reduce the flow separation and impeller interference at volute tongue, optimize the uniformity of volute internal flow field.

The present application relates to a kind of vane and impeller with the vane, vane includes vane body, the front end of the vane body is vane leading edge, rear end is vane trailing edge;The thickness of the vane body is gradually increased thick gradually decreasing from vane leading edge to vane trailing edge, and form a smooth vane body;The maximum camber position of the cross section of the vane body is located at 25%-75% of vane chord length.The vane of the present application can effectively save material and reduce noise by changing the maximum camber position of vane cross section and using front bending and rear sweep form.

The invention discloses a lateral air inlet air duct structure and a ventilation device applying the same, and relates to the technical field of ventilation electrical appliances, the lateral air inlet air duct structure comprises a machine shell, a volute is arranged in the machine shell, the volute is provided with an air inlet and an air outlet, the air inlet is formed in the bottom of the machine shell, the air outlet is formed in one side of the machine shell, and a flow collecting space is formed in the volute; the air inlet and the air outlet are both communicated with the flow collecting space, an impeller assembly is arranged in the flow collecting space, a motor is installed on the volute, a rotating shaft of the impeller assembly is connected with the output end of the motor, and the impeller assembly corresponds to the air inlet; a lamp cover is connected below the machine shell, and an air inlet channel is formed between the lamp cover and the machine shell. And a lateral air inlet duct is formed between the lamp cover below the shell and the shell, so that the air volume loss is reduced. The impeller assembly is arranged corresponding to the air inlet and guides air into the flow collecting space during rotation, and the lateral air inlet amount is increased. When passing through the air inlet duct, airflow can dissipate heat for electrical elements on the lamp cover, and the working state of the elements is prevented from being affected by too high temperature.

The utility model relates to the technical field of range extending type automobile, especially increase a kind of active air intake grille structure for range extender, including grille frame, the upper or front area of car rear wheel package is provided with grille mounting hole;Grille frame one end is embedded and fixed in the inboard of grille mounting hole, forms air inlet end, the other end is equipped with air outlet end, for connecting the air intake system of range extender;Drive assembly is located on grille frame, for driving flap to carry out overturning movement, to open or close air inlet end. By arranging air inlet end in the upper or front area of car rear wheel package, and setting flap controlled by drive assembly, active opening and closure to air inlet end are realized. When vehicle is in pure electric driving mode, range extender does not need to work, flap closes air inlet end under the action of drive assembly, effectively reduces vehicle front end airflow interference, reduces air resistance, improves pure electric cruising range;When range extender starts, flap is automatically opened, guarantees engine air intake demand.

The utility model discloses an axial flow impeller and belongs to the field of impellers. One end of each protrusion is connected into the hub in a sleeved mode; the annular connecting pieces are connected with the other ends of the bulges; the through holes are formed between the annular connecting piece and the adjacent bulges; the connecting ring is sleeved in the annular connecting piece; and the blades are connected outside the hub. The plurality of small sharp wings are connected to the tops of the blades at intervals. And the triangular groove-shaped structure is connected to the tail edge part of the blade. And the grooves are formed in the roots of the blades. The hub, the protrusions, the annular connecting piece and the blades are connected in an integrated injection molding mode. The utility model has the technical effects that the noise can be reduced conveniently, and the heat dissipation performance is good.

The invention provides the follow-up assembly for controlling the seam at the rear edge of the wing and the wing assembly comprising the follow-up assembly. The follow-up assembly has the advantages of few parts, simple structure, short transmission path, simple transmission process and high transmission efficiency. An input end of a follow-up assembly (200) for controlling a gap of the trailing edge of the wing is connected to a trailing edge flap of the trailing edge of the wing, an output end of the follow-up assembly is connected to a lower deflection plate capable of rotating relative to the trailing edge of the wing, the follow-up assembly comprises a connecting rod assembly, the connecting rod assembly is arranged between the trailing edge flap and the lower deflection plate, and an input end of the connecting rod assembly is connected to the trailing edge flap; the output end is connected to the lower deflection plate; the guide limiting part can guide the guide limiting end of the connecting rod assembly to move in a reciprocating mode, when the trailing edge flap descends relative to the trailing edge of the wing, the trailing edge flap drives the lower deflection plate to move through the follow-up assembly, so that a gap is formed between the lower deflection plate and the trailing edge flap, and the trailing edge flap drives the lower deflection plate to move through the follow-up assembly. And the airflow flowing through the gap is kept stable.

This invention discloses a combined power cycle system and method for cooling incoming air using ammonia-water, relating to the aerospace field. The system can switch between turbine-ramjet operating modes through an adjustable structure. Particularly during turbine-ramjet switching, ammonia-water is used to cool the high-temperature incoming air in the intake duct. The absorbed ammonia-water is then distilled to separate high-temperature ammonia gas and water. This invention combines heat exchanger precooling and jet precooling, effectively increasing the pressure ratio of the fan and compressor through multiple air cooling processes. This improves the compressor outlet gas temperature, thereby reducing compressor power consumption and providing greater thrust. Ammonia, as a supplementary fuel, has a higher specific impulse, addressing the thrust gap during engine mode transitions and effectively widening the operating speed range of the turbine engine.

This utility model relates to the field of commercial vehicle exterior technology, and discloses a corner spoiler structure for a commercial vehicle sun visor, a cab assembly, and a commercial vehicle. The sun visor is a horizontally oriented U-shaped structure, with at least two spoiler strips protruding from the outer side of each corner. This utility model adds strip-shaped spoilers to break up large vortex airflow at the corner positions. Taking into account both spoiler performance and aesthetics, the corner strip-shaped spoiler is arranged to fit the tail corner shape without affecting the integration of components such as lights, thus achieving the goal of improving aerodynamic performance.

The invention discloses a turbomachinery air cylinder inner side meridian molded line design method based on flutter suppression, and relates to the technical field of turbomachinery blade flutter suppression. Obtaining a radial basis function model; the radial basis function model is used for predicting the minimum aerodynamic damping value of the turbomachinery blade; the design parameters of the meridian profile on the inner side of the turbomachinery air cylinder serve as optimization variables, the maximum minimum aerodynamic damping value of a blade corresponding to the design parameters predicted by the radial basis function model serves as an optimization target, iterative optimization is conducted through an intelligent optimization algorithm, and the optimal design parameters are obtained; the design parameters represent radial distances from a plurality of points arranged at equal intervals in the axial direction between the front end position of a meridian molded line inlet section on the inner side of the turbomachinery air cylinder and the front edge position of a blade to a hub; and according to the optimal design parameters, the meridian molded line of the inner side of the turbomachinery air cylinder is determined. According to the method, the design aerodynamic performance of the meridian molded line on the inner side of the turbomachinery air cylinder is improved, and the flutter suppression capacity of the blade is enhanced.

The invention discloses a self-adaptive low-wind-resistance multifunctional air purification filter screen and application thereof, and belongs to the technical field of air purification. The filter screen comprises a functional filter area formed by a plurality of fold units, the fold cross section is in a wing-shaped streamline curve or organ type, and the core is that a gradient rigid shaping mechanism is arranged on the surface of the filter screen, so that the filter screen has the directional bending capacity, the overall shape can be kept stable, and the filter screen can be adaptively attached to the mounting surface to ensure sealing. Meanwhile, the accommodating cavity defined by the folds, the shaping mechanism and the selectable covering layer is integrally filled with an air conditioning material, so that integrated synchronous purification of the particulate matters, the gaseous pollutants and the odor is realized. The invention further discloses specific application of the filter screen serving as the wall-mounted air conditioner external self-adaptive external air conditioner filter screen, and tool-free quick mounting and dismounting by hands can be achieved by arranging the elastic clamping parts. The device has the advantages of ultralow wind resistance, efficient purification, stable structure, convenience in installation and high universality.

The application discloses a synthetic jet control multi-section wing high-lift device, and relates to the technical field of flow control, which comprises a multi-section wing and a synthetic jet mechanism. A mounting groove is arranged in the middle of the multi-section wing, and the mounting groove is arranged close to the trailing edge of the multi-section wing. The synthetic jet mechanism is installed in the mounting groove. The jet direction of the synthetic jet mechanism is tangential to the side wall of the multi-section wing. The synthetic jet mechanism is driven by an alternating power source. The synthetic jet control multi-section wing high-lift device can improve the aerodynamic performance of the wing in the full angle of attack range.

The utility model relates to a sectional type electric tail wing which comprises a spoiler (10), a multi-connecting-rod assembly (20) and a driving mechanism (30), the spoiler comprises a large panel (11) and a small panel (12), and the small panel can ascend and descend from a groove (111) in the large panel; the two multi-connecting-rod assemblies are arranged on the two sides of the small panel respectively, and each multi-connecting-rod assembly is connected with the large panel and the small panel. The driving mechanism is arranged between the two multi-connecting-rod assemblies and can synchronously drive the two multi-connecting-rod assemblies, so that the inclination angles of the large panel and the small panel are different in the lifting process of the spoiler. According to the sectional type electric tail wing, on the basis of an original single spoiler, the large panel and the small panel which can achieve different inclination angles are divided, the angle and the height of the tail wing plaque can be better adjusted, the aerodynamic performance of a vehicle at different speeds is improved, and the wind resistance coefficient generated in the vehicle running process is increased or reduced.

A partitioned turbine blade with an oscillating jet cooling structure and its operating method are disclosed, belonging to the fields of energy and power engineering and turbine blade cooling. The blade includes a blade shell, a jet oscillator, a cooling airflow delivery chamber, internal impact holes, external film cooling holes, and turbulence columns. In this invention, the cooling airflow impacts and cools the inner wall of the blade through the impact holes. Utilizing the characteristic of the jet oscillator to generate a large-area high-frequency sweep without moving parts, a single row of jet oscillators is used on the suction side and leading edge of the blade. Considering that the cooling demand on the pressure side is greater than that on the suction side, the pressure side fluid oscillators are arranged in two staggered rows to generate a large-area, full cooling film on the blade surface for blade cooling.

This invention discloses a method, control method, and device for identifying laminar flow separation bubbles at the trailing edge of an airfoil. By deploying pressure sensors on the trailing edge face of the airfoil and utilizing the characteristic that the face pressure equivalently represents the pressure on the upper surface of the trailing edge, this invention achieves accurate and effective acquisition of pressure data in the key monitoring area of ​​the laminar flow separation bubble at the trailing edge, providing a reliable data foundation for bubble identification. Simultaneously, this method determines real-time peak frequency data based on the acquired pressure data and identifies laminar flow separation bubbles by combining the time stability judgment condition of the peak frequency of the trailing edge face pressure signal under low Reynolds number and small angle of attack conditions. Based on the physical law of the invariance of the peak frequency of the trailing edge pressure at low Reynolds number, a specific bubble identification criterion is constructed, providing accurate and real-time judgment basis for subsequent closed-loop control of the laminar flow separation bubble at the trailing edge of the airfoil.

The utility model discloses a kind of based on round elliptical three muscle pvc enclosure, comprising: enclosure main body, the enclosure main body includes plate body and base, base is located at plate body bottom;Panel structure is set in the both sides of the plate body, panel structure includes two groups of protrusions, two groups of protrusions are respectively located at the both sides of plate body, protrusion is the hollow structure of round elliptical, with better mechanical properties, can evenly disperse received external force, improve the impact resistance and wind resistance of enclosure.Combined with high-strength PVC material, the protrusion design of round elliptical hollow structure significantly improves the strength and impact resistance of the enclosure.When subjected to external force impact, the protrusion can evenly disperse force, reduce local stress concentration, avoid the enclosure to be easily damaged, meet the needs of long-term use.

The utility model discloses a low scattering and pneumatic integrated telescopic hexagonal groove countersunk head screw, it includes screw cap, countersunk head round platform thread and stem. Screw cap includes six prismatic marbles spring and six prismatic inner groove, when not considering the tolerance gap between six prismatic marbles and six prismatic inner groove, the stem is the cylinder that is connected with the bottom surface of screw cap, and the thread is the ordinary thread that is equidistantly surrounded in the stem, that is, the triangular tooth shape. The low scattering pneumatic telescopic hexagonal groove countersunk head screw provided by the utility model provides the design principle of low scattering pneumatic screw radar stealth and pneumatic shape, which is a design method for the comprehensive mechanical properties of the low detectability of the screw pneumatic, and the design idea is unique and ingenious, the pneumatic low detectability effect is remarkable, the mechanical properties are good, and the design part has high universality. It can be operated and used by using the general hexagonal screwdriver, and it is convenient to couple all the screws with the whole in the gap direction.

This invention proposes a method and system for predicting the drag contribution of automotive rear wing designs, belonging to the fields of automotive aerodynamics and artificial intelligence. The method includes: acquiring and preprocessing raw CFD flow field images to generate standardized binary images; extracting flow field depth and tilt angle features from the binary images, using them together as multi-source features characterizing the wake field structure; constructing a deep learning model, using the multi-source features as input, training the deep learning model, and outputting scalar parameters; inputting the flow field image of the automotive rear wing design to be predicted into the trained deep learning model, extracting multi-source features, and combining them with changes in target design parameters to quickly predict the drag contribution using a quadratic function. This invention significantly improves prediction efficiency and has strong generalization ability, providing accurate and efficient decision-making basis for automotive rear wing drag optimization design, and is suitable for rapid iteration and parameter scanning in automotive rear wing design.

This invention discloses a volute, a fan, a smart appliance, and a method for generating the volute profile. The volute's annular wall includes a volute tongue segment, a first helical segment, a second helical segment, a third helical segment, and a fourth helical segment connected sequentially. The first height boundary point of the volute is located between a first feature point and a first width boundary point. The second feature point is the first width boundary point. The third feature point is located between the second width boundary point and the second height boundary point of the volute. The fourth feature point is the second width boundary point. The first helical segment includes a first helical sub-segment and a second helical sub-segment. The profiles of the first helical sub-segment and the second helical segment have opposite helical directions. Using the embodiments disclosed in this invention, even in limited space, uniform airflow within the volute can be ensured, thereby improving the aerodynamic performance of the fan.

The invention relates to the technical field of aerospace transportation, in particular to a vertical take-off and landing single-stage injection repeatable heaven and earth back-and-forth carrying method which comprises the following steps: preparing for vertical boosting launching, and simultaneously finishing all preparations before rocket launching; the vertical boosting launching device releases stored energy and boosts the rocket to accelerate; after boosting launching is completed, the rocket engine is ignited to take off and leave the boosting device; the rocket continuously accelerates to the orbit injection speed and then enters a preset orbit; the rocket is adjusted to be in a tail windward configuration needed by reentry, and the rocket is decelerated to enter a reentry window; a rocket enters the atmosphere with the tail nozzle taper plug outsole as a windward side, and the thermal protection capacity of the taper plug outsole is enhanced through a regeneration cooling structure in the taper plug outsole structure. And the rocket vertically lands to the original boosting launching rack and waits for a re-launching task at the original position. According to the invention, by constructing an integrated vertical take-off and landing, single-stage orbit injection, orbit reentry and in-situ recovery process, high-frequency, low-cost and flight-based operation of a sky-ground back-and-forth carrying task is realized.