CN117360803A - lander - Google Patents
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- CN117360803A CN117360803A CN202311345182.1A CN202311345182A CN117360803A CN 117360803 A CN117360803 A CN 117360803A CN 202311345182 A CN202311345182 A CN 202311345182A CN 117360803 A CN117360803 A CN 117360803A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/62—Systems for re-entry into the earth's atmosphere; Retarding or landing devices
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Abstract
本申请涉及航天技术领域，尤其是涉及一种着陆器，着陆器包括主体部、冷气喷射组件和多个喷射发动机，冷气喷射组件包括冷却高压气源和环射器，环射器设置于主体部在第一方向上的一端，多个喷射发动机均设置于主体部的环射器所在的一侧，且多个喷射发动机围绕环射器的周向均布，喷射发动机的喷射口朝向环射器在的一侧设置。环射器设置有围绕环射器设置至少一周的喷口，冷却高压气源与环射器连通，以使冷却气体能够在环射器的喷射作用下，达到预定速度喷出形成包裹主体部的冷却气膜。根据本申请提供的着陆器，冷却气膜对主体部进行隔热保护。减少主体部的外侧隔热材料，减小了着陆器的无效质量占比，降低主体部的包覆难度。
This application relates to the field of aerospace technology, and in particular to a lander. The lander includes a main body, a cold air injection assembly and a plurality of jet engines. The cold air injection assembly includes a cooling high-pressure air source and an circulator. The circulator is disposed on the main body. At one end in the first direction, a plurality of jet engines are disposed on the side of the main body where the circulator is located, and the plurality of jet engines are evenly distributed around the circumference of the circulator, and the injection ports of the jet engines face the circulator. Set on one side. The circulator is provided with a nozzle that is arranged around the circulator for at least one week, and the cooling high-pressure air source is connected with the circulator, so that the cooling gas can be ejected at a predetermined speed under the injection action of the circulator to form a cooling package for the main body. air film. According to the lander provided by this application, the cooling air film thermally insulates and protects the main body. Reducing the outer insulation material of the main body reduces the proportion of ineffective mass of the lander and reduces the difficulty of covering the main body.
Description
Technical Field
The application relates to the technical field of aerospace, in particular to a lander.
Background
Today's landers typically require ignition of the engine during landing so that the engine is pushed in the opposite direction (reverse direction pushing here is understood to mean that the engine is injecting air towards the landing floor so that the engine can be pushed in a direction away from the landing floor) to slow down the lander until the lander is lowered to a certain height before turning off the engine to make the lander land smoothly. As the distance of the lander from the landing ground decreases, particularly for multi-engine landers, the plume field becomes more complex, making the thermal environment near the lander harsh. As the multiple engine lander approaches the landing ground, the engine center creates a recirculation zone, the aerodynamic heat flow impinging on the lander bottom, the surface of which is thus dramatically elevated, resulting in difficult thermal protection.
The heat protection of the existing lander is generally carried out by adopting a heat insulation material with lower heat conductivity to cover the protected position, and the method has a simple structure and is widely applied to the heat protection of spacecrafts. However, on one hand, the external parts of the existing landers are often required to be loaded with loads with different functions, so that the outer walls of the landers can be provided with irregularly-shaped bulges or depressions, and complex surfaces (such as bulges, depressions and the like) are required to be coated independently in a manner of coating by adopting a heat protection material, so that the complexity is increased and the quality of coating materials is increased; on the other hand, as the requirements of the space exploration task are higher, the landing process of the lander is required to be more stable, the requirements of the shutdown height of the engine are lower, the thermal environment at the bottom of the lander is more severe, thicker thermal protection materials are required to be coated for ensuring the safety, the invalid mass of the lander is increased, the effective mass is reduced, and the advancement of the spacecraft and the economy of the space exploration task are reduced.
Disclosure of Invention
The purpose of the present application is to provide a lander, so as to solve the problem that the existing landers in the prior art are mostly irregularly shaped to a certain extent, and the lander is coated by adopting a thermal protection material, so that complex surfaces (such as surface protrusions and surface depressions) need to be coated separately, and the complexity is increased and the quality of coating materials is increased; in addition, as the requirements of the space exploration task are higher and higher, the thermal environment at the bottom of the lander is worse, thicker thermal protection materials need to be coated for ensuring the safety, the invalid mass of the lander is increased, the effective mass is reduced, and the technical problems of the advancement of the spacecraft and the economy of the space exploration task are solved.
According to a first aspect of the present application, there is provided a lander comprising a main body, a cold air injection assembly and a plurality of injection engines, wherein the cold air injection assembly comprises a cooling high-pressure air source and a ring injector, the cooling high-pressure air source is arranged in the main body, the ring injector is arranged at one end of the main body in a first direction, the injection engines are all arranged at one side of the main body where the ring injector is located, the injection engines are circumferentially and uniformly distributed around the ring injector, and an injection port of the injection engine is arranged towards one side of the ring injector opposite to one end of the main body where the ring injector is located;
the annular ejector is provided with a nozzle, the nozzle surrounds the annular ejector for at least one circle, the cooling high-pressure air source is communicated with the annular ejector, so that cooling air in the cooling high-pressure air source can be sprayed out from the nozzle at a preset speed under the spraying action of the annular ejector, and a cooling air film wrapping the bottom of the main body part is formed.
Preferably, the annular injector comprises a first disc part and a second disc part which are coaxially overlapped with each other, the axes of the first disc part and the second disc part extend along the first direction, and the nozzle is an annular gap formed between the first disc part and the second disc part;
in the radial direction of the annular injector and in the direction from the center of the annular injector to the edge of the annular injector, the distance of the nozzle in the first direction is gradually reduced and then gradually increased.
Preferably, the side of the first disk facing away from the second disk is planar, and the thickness of the first disk in the radial direction of the annular emitter and in a direction from the center of the annular emitter to the edge of the annular emitter increases and decreases.
Preferably, the side of the second disk facing away from the first disk is planar, and the thickness of the first disk in the radial direction of the annular emitter and in a direction from the center of the annular emitter toward the edge of the annular emitter increases and decreases.
Preferably, the first disk portion is provided on a side of the second disk portion facing the main body portion;
the annular injector further comprises a communicating pipe, a connecting column and a connecting rib plate, wherein the communicating pipe and the connecting column extend along the first direction, one end of the communicating pipe is connected with the first disk part and communicated with the nozzle, and the other end of the communicating pipe is connected with the main body part and communicated with the cooling high-pressure air source;
one end of the connecting column is connected with the second disc part, at least part of the connecting column extends into the communicating pipe, and the connecting rib plate is arranged between the communicating pipe and the connecting column and is connected with the communicating pipe and the connecting column.
Preferably, the minimum distance from the nozzle to the main body is 0.1m to 0.2m.
Preferably, the cold air injection assembly further comprises:
the control valve is arranged between the annular injector and the cooling high-pressure air source to control the communication between the annular injector and the cooling high-pressure air source;
a filter disposed between the control valve and the cooling high-pressure gas source to filter the cooling gas flowing out from the cooling high-pressure gas source;
and the pressure control part is arranged between the filter and the control valve so as to control the air pressure of the cooling air flowing out from the cooling high-pressure air source.
Preferably, the predetermined speed is supersonic.
Preferably, the cooling gas is an inert gas or nitrogen;
the cooling gas is in a gaseous or liquid state when the cooling gas is within the source of cooling high pressure gas.
Preferably, the engine further comprises a plurality of landing legs, the landing legs are arranged on the side of the main body part where the annular injector is located, the landing legs are uniformly distributed around the circumference of the annular injector, and the number of the landing legs arranged between every two adjacent injection engines is the same.
Compared with the prior art, the beneficial effects of this application are:
the lander provided by the application can be arranged on the side of the main body facing the landing ground by arranging the annular jet on the side of the main body facing the jet port of the jet engine, namely, during landing/lifting of the lander. The high-pressure cooling gas can be sprayed from the spray nozzle around the annular injector at a preset speed to form a cooling gas film capable of wrapping the bottom of the main body by taking the annular injector as the center, and the backflow of the gas flow emitted by the jet engine can be blocked by the cooling gas film, as shown in fig. 4 and 5, which are temperature distribution simulation diagrams of whether the annular injector is opened or not under a preset environment state (the specification and the size of the lander, the output power of the jet engine, the environment where the lander is located, the speed of the lander and the like can be understood as the same under the preset environment state). Comparing fig. 4 and fig. 5, the ambient temperature around the main body portion after the annular injector is opened is significantly reduced, so as to further illustrate that the cooling air film formed by the injection of the annular injector can effectively perform heat insulation protection on the main body portion. The outer side of the main body part is reduced or even avoided from being coated with heat insulation materials, the invalid mass ratio of the lander is effectively reduced, and the economy of the lander is improved. And compared with the coating of the heat insulating material, the cooling air film can be quickly and effectively adapted to and attached to the surface of the main body part, and the coating difficulty of the main body part is reduced.
In order to make the above objects, features and advantages of the present application more comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic diagram of an axial structure of a lander according to an embodiment of the present disclosure;
FIG. 2 is a schematic view of a cut structure of the annular injector according to the embodiment of the present application;
FIG. 3 is a schematic diagram illustrating connection of a cold air injection assembly according to an embodiment of the present disclosure;
FIG. 4 is a simulated graph of temperature distribution for a lander in a predetermined state and with the injector closed, according to an embodiment of the present disclosure;
fig. 5 is a temperature distribution simulation diagram of a lander provided in an embodiment of the present application in a predetermined environmental state and with the ring injector turned on.
Reference numerals:
1-a cold air injection assembly; 11-cooling a high-pressure air source; 12-ring injector; 121-a first disc portion; 122-a second disc portion; 123-spout; 124-communicating tube; 125-connecting columns; 126-connecting rib plates; 13-a control valve; 14-a filter; 15-a pressure control part; 2-a main body; 3-injection engines; 4-landing legs.
F1-first direction.
Detailed Description
The following description of the embodiments of the present application will be made apparent and fully in view of the accompanying drawings, in which some, but not all embodiments of the invention are shown.
The components of the embodiments of the present application, as generally described and illustrated in the figures herein, may be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, as provided in the accompanying drawings, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application.
All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present disclosure.
In the description of the present application, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of description of the present application and to simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.
Landers according to some embodiments of the present application are described below with reference to fig. 1-5.
Referring to fig. 1 to 5, an embodiment of the first aspect of the present application provides a lander, which includes a main body 2, a cold air injection assembly 1 and a plurality of injection engines 3, wherein the cold air injection assembly 1 includes a cooling high-pressure air source 11 and an annular injector 12, the cooling high-pressure air source 11 is disposed in the main body 2, the annular injector 12 is disposed at one end of the main body 2 in a first direction F1, the plurality of injection engines 3 are all disposed at one side of the main body 2 where the annular injector 12 is located, and the plurality of injection engines 3 are uniformly distributed around a circumference of the annular injector 12, with respect to one end of the main body 2 facing away from the annular injector 12, and injection ports of the injection engines 3 are disposed toward one side of the annular injector 12. The annular injector 12 is provided with a nozzle 123, the nozzle 123 is arranged around the annular injector 12 for at least one circle, and the cooling high-pressure air source 11 is communicated with the annular injector 12, so that the cooling air in the cooling high-pressure air source 11 can be sprayed out from the nozzle 123 at a preset speed under the spraying action of the annular injector 12, and a cooling air film wrapping the bottom of the main body part 2 is formed.
According to the above-described technical feature, the lander 12 can be provided on the side of the main body 2 facing the landing ground by providing the ring injector 12 on the side of the main body 2 toward which the injection port of the injection engine 3 faces, that is, during landing/lifting of the lander. And is communicated with the cooling high-pressure air source 11 through the annular injector 12, so that the high-pressure cooling air can be sprayed from the spray nozzles 123 around the annular injector 12 at a predetermined speed, so that the high-pressure cooling air can be sprayed around the annular injector 12 to form a cooling air film capable of wrapping the bottom of the main body, and the backflow of the air flow emitted by the jet engine 3 can be blocked by the cooling air film, as shown in fig. 4 and 5, which are temperature distribution simulation diagrams of whether the annular injector 12 is opened or not in a predetermined environment state (the specification size of the lander, the output power of the jet engine 3, the environment where the lander is located, the speed of the lander, and the like can be understood as the same in the predetermined environment state). In comparison with fig. 4 and 5, the ambient temperature around the main body 2 drops significantly after the annular injector 12 is turned on, and further, it is explained that the cooling air film formed by the injection of the annular injector 12 can effectively insulate and protect the main body 2. The outer side of the main body part 2 is reduced or even avoided from being coated with heat insulation materials, so that the invalid mass ratio of the lander is effectively reduced, and the economy of the lander is improved. And, for using the thermal insulation material cladding, the cooling air film can adapt to and laminate the surface of main part 2 fast effectively, has reduced the cladding degree of difficulty of main part 2.
Referring to fig. 1 and 2, an example of the first direction F1 is shown in F1. Preferably, the first direction F1 may be the direction of gravity of the planet in which the landing device is located. In other words, the above-mentioned annulus 12 may be located at the bottom of the main body 2 when the landing gear is in the landing/lifting state, so as to block the air flow bouncing from the landing ground to the landing gear.
Preferably, as shown in fig. 1, the number of the annular ejectors 12 may be 1, and the annular ejectors 12 may be coaxially disposed with the main body 2, that is, the annular ejectors 12 may be disposed at a bottom center position of the main body 2, so as to ensure that the main body 2 is uniformly coated in all directions, and ensure uniform coverage of the cooling air film.
The number of the annular injectors 12 is not limited to 1, and may be plural, for example, 2, 3, 4, … …, or more, as long as it is possible to ensure that the cooling air films emitted from the annular injectors 12 do not interfere with each other or that the impact interference between the cooling air films emitted from the annular injectors 12 does not affect the protection of the main body 2.
Preferably, as shown in fig. 2, the annular injector 12 may include a first disk portion 121 and a second disk portion 122 coaxially disposed on top of each other, wherein axes of both the first disk portion 121 and the second disk portion 122 extend in the first direction F1, such that an annular gap formed between both the first disk portion 121 and the second disk portion 122 serves as the above-described nozzle 123.
It should be noted that, although only an example in which two disc-shaped members of the first disc portion 121 and the second disc portion 122 form an annular gap is shown, the annular gap is not limited thereto, and the annular injector 12 may further include three, four or more disc-shaped members coaxially and stacked along the first direction F1, and the annular gap may be formed between two adjacent disc-shaped members.
Preferably, as shown in fig. 2, in the radial direction of the annular injector 12 and in the direction from the center of the annular injector 12 toward the edge of the annular injector 12, the distance of the nozzle 123 in the first direction F1 is gradually decreased and then gradually increased, so that a laval nozzle, which is gradually narrowed and then gradually widened, is formed in the direction from the center to the edge of the nozzle 123, so that the flow rate of the cooling gas injected through the annular injector 12 can reach supersonic speed, in other words, the above predetermined speed can be supersonic speed. And further effectively improve the coverage area of the cooling air film and the stability of the cooling air film, and ensure the protection effect of the cooling air film on the main body part 2.
Preferably, as shown in fig. 2, the side of the first disk portion 121 facing away from the second disk portion 122 is a plane, and in the radial direction of the annular injector 12 and in the direction from the center of the annular injector 12 toward the edge of the annular injector 12, the thickness of the first disk portion 121 in the first direction F1 increases and decreases gradually, so that the nozzle 123 forms the above-mentioned laval nozzle (i.e., the first disk portion 121 is a disk of unequal thickness).
Alternatively, as an example not shown in the drawings, both sides of the second disk portion 122 in the first direction F1 may be flat, that is, the second disk portion 122 may be a disk of equal thickness.
Preferably, as shown in fig. 2, the side of the second disk portion 122 facing away from the first disk portion 121 is a plane, and in the radial direction of the annular injector 12 and in the direction from the center of the annular injector 12 toward the edge of the annular injector 12, the thickness of the first disk portion 121 in the first direction F1 increases and decreases gradually, so that the nozzle 123 forms the above-mentioned laval nozzle (i.e., the second disk portion 122 is a disk of unequal thickness).
Alternatively, as an example not shown in the drawings, both sides of the first disk portion 121 in the first direction F1 may be flat, that is, the first disk portion 121 may be a disk of equal thickness.
Preferably, as shown in fig. 2, the first disc portion 121 and the second disc portion 122 are discs with different thicknesses, and the thickest part of the first disc portion 121 in the first direction F1 and the thickest part of the second disc portion 122 in the first direction F1 are opposite to each other in the first direction F1, so that on one hand, consistency of variation trend of the first disc and the second disc in a direction from the center of the annular injector 12 to the edge of the annular injector 12 is ensured, and effectiveness of the laval nozzle is ensured; on the other hand, the stability at the narrow mouth of the laval nozzle (i.e., the thickest part of the first disk part 121 in the first direction F1 or the thickest part of the second disk part 122 in the first direction F1) is effectively improved.
Preferably, as shown in fig. 2, the first disk portion 121 is provided on a side of the second disk portion 122 facing the main body portion 2. The annular injector 12 may further include a communicating pipe 124, a connecting column 125, and a connecting rib 126, where the communicating pipe 124 and the connecting column 125 extend along the first direction F1, one end of the communicating pipe 124 is connected to the first disk portion 121 and communicates with the nozzle 123, and the other end of the communicating pipe 124 is connected to the main body portion 2 and communicates with the cooling high-pressure air source 11. One end of the connection column 125 is connected to the second tray 122, and at least part of the connection column 125 extends into the connection pipe 124, and the connection rib 126 is provided between the connection pipe 124 and the connection column 125 and connects the connection pipe 124 and the connection column 125, so that, on the one hand, communication between the annular injector 12 and the cooling high-pressure gas source 11 and fixation of the annular injector 12 and the main body 2 can be achieved through the connection pipe 124; on the other hand, the part of the connecting column 125 stretches into the communicating pipe 124 to be connected with the communicating pipe 124 through the connecting rib plate 126, so that the influence of the connecting rib plate 126 on the nozzle 123 is effectively reduced, and the package integrity of the cooling air film is further improved.
Preferably, the average diameter of the main body 2 may be 10 to 20 times the diameter of the annular injector 12 to ensure the effect of covering the cooling film. Taking the diameter of the annular injector 12 as an example, the average diameter of the main body 2 may be 1m to 2m.
Preferably, the minimum distance from the nozzle 123 to the main body 2 may be 0.1m to 0.2m, so as to ensure that the cooling air film sprayed by the annular injector 12 can cover all the protrusions provided on the main body 2.
In an embodiment, preferably, as shown in fig. 3, the cold air injection assembly 1 may further include a control valve 13, and the control valve 13 is disposed between the annular burner 12 and the cooling high pressure air source 11 to control communication of the annular burner 12 with the cooling high pressure air source 11. Alternatively, the control valve 13 may be a solenoid valve, which may be communicatively connected to the control system of the lander.
Preferably, as shown in fig. 3, the cold air injection assembly 1 may further include a filter 14, and the filter 14 may be disposed between the control valve 13 and the high pressure cooling air supply 11 to filter the cooling air flowing from the high pressure cooling air supply 11, so as to prevent the cooling air supply from being blocked by impurities in the cooling air supply.
Preferably, as shown in fig. 3, the cold air injection assembly 1 may further include a pressure control part 15, where the pressure control part 15 is disposed between the filter 14 and the control valve 13 to control the air pressure of the cooling air flowing from the cooling high-pressure air source 11, so as to ensure the air pressure consistency of the cooling air input to the annular injector 12, and further ensure the continuous stability of the cooling air film. Alternatively, the air pressure portion may be a pressure reducing valve, taking a lunar lander (i.e., a lander for lunar landing) as an example, and the pressure reducing valve may control the air pressure of the cooling gas to be greater than or equal to 1MPa, so as to ensure that the cooling gas ejected through the annular injector 12 can form a stable cooling gas film in a low air pressure environment of the lunar, and ensure the protection effect of the cooling gas film.
Alternatively, the cooling gas may be an inert gas, such as helium, neon, argon, krypton, xenon.
Preferably, the cooling gas may also be nitrogen to enhance the economics of the lander.
Preferably, the above-described cooling high-pressure gas source 11 may be a gas container (e.g., a gas cylinder) or a cooling gas generator.
Preferably, when the cooling gas is in the cooling high-pressure gas source 11, the cooling gas may be in a gaseous state to ensure the output stability of the cooling gas.
Alternatively, when the cooling gas is in the high-pressure cooling gas source 11, the cooling gas may be in a liquid state to increase the storage amount of the cooling gas for cooling the high-pressure cooling gas source 11.
In an embodiment, as shown in fig. 1, the lander may further include a plurality of landing legs 4, the landing legs 4 are disposed on the side of the annular injector 12 of the main body 2, the plurality of landing legs 4 are uniformly distributed around the circumference of the annular injector 12, and the number of landing legs 4 disposed between every two adjacent injection engines 3 is the same.
As shown in fig. 1, the above-described example in which the number of the injection engines 3 and the number of the landing legs 4 are 4, and 1 landing leg 4 is provided between every adjacent two injection engines 3 is shown, however, the present invention is not limited thereto, and the number of the injection engines 3 and the landing legs 4 may be adjusted depending on actual demands.
On the basis of the features described above, description will be made taking the lander shown in fig. 1 to 5 as an example, and the workflow of the lander will be specifically described below.
1. The landing process and the self-landing ground lifting process of the lander are simulated according to the setting of the environmental parameters (for example, the landing of the moon, the setting of the environmental parameters according to the use environment of the moon, that is, the gravitational acceleration of the moon, the atmospheric pressure of the moon, and the like) to determine the safety height, that is, the highest height at which the lander needs to be protected, in other words, the safety height, which is the position at which the injection engine 3 is turned on, and the control valve 13 is set to be turned on when the lander is lower than the safety height, so that the cold air injection assembly 1 injects the cooling gas to protect the main body 2.
2. The landing time required by the landing process of the lander from the safe height to the landing is determined according to the planned landing track (if the landing is required to return, the take-off time required by the landing device to rise to the safe height is increased at the same time), a certain margin is added on the basis to determine the pressure and the volume of a high-pressure air source, the optimal pressure behind a relief valve is selected according to the protection effect, for example, a lunar surface lander (i.e. a lander for lunar landing), and the relief valve controls the air pressure of cooling air to be greater than or equal to 1MPa, so that the protection effect is optimal.
3. During landing of the landing gear, both the injection engine 3 and the control valve 13 are opened when the landing gear is lowered to a safe height. When the lander decelerates to a safe landing speed, the injection engine 3 is closed and the control valve 13 is closed.
4. During the ascent of the lander, after opening the control valve 13, the injection engine 3 is opened, the lander is pushed to rise until reaching the safe height, and the control valve 13 is closed.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the corresponding technical solutions from the scope of the technical solutions of the embodiments of the present application.
Claims (10)
1. The lander is characterized by comprising a main body part, a cold air injection assembly and a plurality of injection engines, wherein the cold air injection assembly comprises a cooling high-pressure air source and a ring injector, the cooling high-pressure air source is arranged in the main body part, the ring injector is arranged at one end of the main body part in a first direction, the injection engines are all arranged at one side of the main body part where the ring injector is located, the injection engines are uniformly distributed around the circumference of the ring injector, and an injection port of the injection engine is arranged towards one side of the ring injector opposite to one end of the main body part where the ring injector is located;
the annular ejector is provided with a nozzle, the nozzle surrounds the annular ejector for at least one circle, the cooling high-pressure air source is communicated with the annular ejector, so that cooling air in the cooling high-pressure air source can be sprayed out from the nozzle at a preset speed under the spraying action of the annular ejector, and a cooling air film wrapping the bottom of the main body part is formed.
2. The lander of claim 1, wherein the annulus includes a first disk portion and a second disk portion coaxially disposed over one another, axes of both the first disk portion and the second disk portion extending in the first direction, the spout being an annular gap formed between both the first disk portion and the second disk portion;
in the radial direction of the annular injector and in the direction from the center of the annular injector to the edge of the annular injector, the distance of the nozzle in the first direction is gradually reduced and then gradually increased.
3. The lander of claim 2 wherein the landing member is configured to engage in a landing process,
the side surface of the first disc part, which is opposite to the second disc part, is a plane, and the thickness of the first disc part in the first direction is gradually increased and then gradually decreased in the radial direction of the annular syringe and in the direction from the center of the annular syringe to the edge of the annular syringe.
4. A lander as claimed in claim 2 or 3, wherein,
the side surface of the second disc part, which is opposite to the first disc part, is a plane, and the thickness of the first disc part in the first direction is gradually increased and then gradually decreased in the radial direction of the annular syringe and in the direction from the center of the annular syringe to the edge of the annular syringe.
5. The lander of claim 2, wherein the first disk portion is disposed on a side of the second disk portion facing the main body portion;
the annular injector further comprises a communicating pipe, a connecting column and a connecting rib plate, wherein the communicating pipe and the connecting column extend along the first direction, one end of the communicating pipe is connected with the first disk part and communicated with the nozzle, and the other end of the communicating pipe is connected with the main body part and communicated with the cooling high-pressure air source;
one end of the connecting column is connected with the second disc part, at least part of the connecting column extends into the communicating pipe, and the connecting rib plate is arranged between the communicating pipe and the connecting column and is connected with the communicating pipe and the connecting column.
6. The lander of claim 2 wherein the minimum distance of the spout to the body portion is 0.1m to 0.2m.
7. The lander of claim 5, wherein the cold gas jet assembly further comprises:
the control valve is arranged between the annular injector and the cooling high-pressure air source to control the communication between the annular injector and the cooling high-pressure air source;
a filter disposed between the control valve and the cooling high-pressure gas source to filter the cooling gas flowing out from the cooling high-pressure gas source;
and the pressure control part is arranged between the filter and the control valve so as to control the air pressure of the cooling air flowing out from the cooling high-pressure air source.
8. The lander of claim 1 wherein the predetermined speed is supersonic.
9. The lander of claim 1, wherein the cooling gas is an inert gas or nitrogen;
the cooling gas is in a gaseous or liquid state when the cooling gas is within the source of cooling high pressure gas.
10. The lander of claim 1 further comprising a plurality of landing legs disposed on a side of the body portion where the annulus is located, the plurality of landing legs being evenly distributed around a circumference of the annulus, and the number of landing legs disposed between each adjacent two of the jet engines being the same.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117963174A (en) * | 2024-03-28 | 2024-05-03 | 江苏深蓝航天有限公司 | Aircraft landing buffer device, aircraft landing control system and aircraft |
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