A solid-liquid spherical lunar probe that can flexibly move and roll on the lunar surface

Abstract

A solid-liquid spherical lunar flight probe that can flexibly move and roll on the lunar surface includes a bottom shell, a partition, a top cover, and a nozzle shell; the bottom shell is hemispherical, a partition is provided inside the bottom shell, a liquid oxidant tank is provided below the partition, a solid fuel tank is provided above the partition, an upper plane of the solid fuel tank is hinged to an electric push rod, and the telescopic end of the electric push rod passes through the hole on the nozzle shell and is hinged to the top cover; the outer surface of the top cover is a spherical surface, and has a common center of circle with the bottom shell; wherein the electric push rod is extended and retracted by receiving control instructions to adjust the relative position of the top cover, thereby changing the jet thrust in all directions to control the attitude of the aircraft. The present invention adopts a self-pressurized solid-liquid propulsion method, has a simple structure, designs the flight probe into a spherical shape, allows rolling, and has a low center of gravity. By adjusting the center of gravity, it can automatically adjust to a take-off attitude on the lunar surface, thereby improving reliability.

Description

Technical Field

[0001] The invention relates to the field of aerospace exploration, and in particular to a solid-liquid spherical lunar flying probe which can flexibly move and roll on the lunar surface. Background Art

[0002] The moon is the closest planet to the earth, and it contains rich resources and energy as well as a special environment. The exploration of the moon is an important part in the field of aerospace. However, at present, lunar rovers are widely used in lunar exploration, which have the disadvantages of slow movement and long time. The lunar exploration is far away from the lunar surface and cannot be directly sampled and analyzed. Therefore, it is necessary to carry out flight exploration on the lunar surface. The gravity on the moon is small, and the aircraft is easy to take off and land. The tumbling spherical aircraft can cope with the mountainous environment on the moon. Therefore, it is feasible to carry out flight exploration on the lunar surface. Since there is no air on the moon, the working conditions of the aircraft on the earth cannot be met on the moon. The only feasible flight power is the rocket engine. For conventional rockets, high-efficiency combustion and propulsion often mean high pressure and temperature, and the achievable combustion chamber pressure is determined by the throat area, the pressure of the fuel tank or the pressure of the fuel pump. The mainstream boosting methods include pump boosting, and high-pressure gas boosting can be used for space propulsion, but these methods often have defects such as complex structure, occupied volume, and large additional mass. Therefore, we use solid-liquid rocket propulsion; traditional landers are designed to have feet with landing capabilities, but in the case of slopes or overturning, it is difficult to adjust the aircraft if the posture is incorrect, so the shape and internal layout of the aircraft should be designed reasonably. Summary of the invention

[0003] The purpose of the present invention is to solve the above-mentioned problems in the prior art and to provide a solid-liquid spherical lunar flying probe that can flexibly move and roll on the lunar surface. It adopts a self-pressurized solid-liquid propulsion method and has a simple structure. The flying probe is designed to be spherical, allowing rolling. The center of gravity is arranged at a low position. By adjusting the center of gravity, it can adjust itself to a take-off posture on the lunar surface, thereby improving reliability.

[0004] In order to achieve the above object, the present invention adopts the following technical scheme:

[0005] A solid-liquid spherical lunar flying probe that can flexibly move and roll on the lunar surface, including a bottom shell, a partition, a top cover, a nozzle shell and an electrical push rod;

[0006] The bottom shell is hemispherical, a partition is provided inside the bottom shell, a liquid oxidant tank is provided below the partition, a solid fuel tank is provided above the partition, the upper plane of the solid fuel tank is hinged to the electric push rod, the telescopic end of the electric push rod passes through the hole on the nozzle shell and is hinged to the top cover; the outer surface of the top cover is a spherical surface, and has a common center with the bottom shell; wherein the electric push rod is extended and retracted by receiving a control instruction to adjust the relative position of the top cover, thereby changing the jet thrust in each direction to control the attitude of the aircraft;

[0007] The solid fuel tank comprises an outer shell, a middle shell and an inner shell which are arranged in sequence, the bottom of the middle shell is provided with a base, and the top is provided with a top seat; two groups of microchannels are formed between the outer shell and the middle shell, which are respectively an air inlet microchannel and an air outlet microchannel; the interior of the inner shell is filled with fuel, and gaps are provided between the inner shell and the base of the middle shell, and between the base of the middle shell and the wall of the middle shell, and the gaps are connected with the air outlet microchannels; openings are provided at the upper and lower parts of the inner shell; a nozzle throat is provided at the middle part of the nozzle shell, the nozzle throat is connected with the upper opening of the inner shell, and the lower opening of the inner shell is connected with the gap; an empty interlayer is provided around the nozzle throat, and the interlayer is connected with the two groups of microchannels; an opening connected with the air inlet microchannel is provided on the partition plate, so that the oxidant flows from the liquid oxidant tank into the air inlet microchannel.

[0008] The partition is welded to the inner wall of the bottom shell, and the solid fuel bin is welded to the partition.

[0009] The electric push rods are provided in three groups.

[0010] The articulation adopts a spherical articulation.

[0011] The top cover is provided with a top and a bottom, a hollow area is formed between the top and the bottom, and the bottom forms a drainage cone.

[0012] Compared with the prior art, the technical solution of the present invention has the following beneficial effects:

[0013] The present invention discloses a lunar flight probe based on solid-liquid rocket propulsion, which is spherical, can be flexibly lifted and lowered, can fly horizontally in all directions, and can adjust its attitude according to human instructions and automatic control. Its characteristics are: it adopts a spherical shape, can roll on the uneven lunar surface, and will not terminate the mission due to tipping; the center of gravity is located at a lower position, so that the aircraft can automatically return to its attitude on the lunar surface like a tumbler when there is no propulsion; because the propulsion device is a solid-liquid rocket with adjustable flow and self-reheating installed inside the probe, the aircraft can be lifted and lowered freely; and the nozzle of the solid-liquid rocket is annular and supported and adjusted by three electrical push rods, which are extended and retracted according to human instructions and automatic control to adjust the relative position of the top cover and the base, adjust the shape of the spray ring, and cause differences in the thrust of the aircraft in all directions, so that the aircraft can be finely adjusted in attitude, thereby realizing the horizontal propulsion of the aircraft in all directions. After landing on the moon, its center of gravity can keep it in the required takeoff posture; the liquid oxidant (H2O2 or other suitable liquid oxidant) is heated up by regeneration and vaporized by relying on the zero pressure environment outside, so that its saturated vapor pressure is stabilized at the high-efficiency combustion pressure and the liquid oxidant is pushed into the combustion chamber to react with the solid fuel to achieve the purpose of propulsion. The oxidant flow rate is adjusted to control the thrust and achieve ascent and descent. The flying lunar exploration has a wider detection range, faster movement speed, and is almost unaffected by the lunar surface terrain. This project will be an important part of the future construction of the lunar base. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 It is a schematic diagram of the overall structure of the present invention;

[0015] Figure 2 It is a schematic diagram of the cross-sectional structure of the present invention;

[0016] Figure 3 Schematic diagram of the overall structure of the bottom shell;

[0017] Figure 4 is a schematic diagram of the cross-sectional structure of the bottom shell;

[0018] Figure 5 is a three-dimensional cross-sectional schematic diagram of a nozzle shell;

[0019] Figure 6 is a cross-sectional schematic diagram of the nozzle shell;

[0020] Figure 7 is a schematic diagram of the structure of the top cover;

[0021] Figure 8 This is a schematic diagram of the overall structure of the solid fuel bunker;

[0022] Fig. 9 It is a schematic diagram of the cross-sectional structure of a solid fuel bunker;

[0023] Fig.10 for Fig. 9 Enlarged view of part A in the middle;

[0024] Fig.11 Schematic diagram of the flow direction of the oxidant and the flow direction of the gas after combustion. DETAILED DESCRIPTION

[0025] In order to make the technical problems, technical solutions and beneficial effects to be solved by the present invention clearer and more understandable, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments.

[0026] like Figures 1 to 10 As shown, the solid-liquid spherical lunar flying probe of this embodiment can flexibly move and roll on the lunar surface, including a bottom shell, a partition, a top cover, a nozzle shell and an electric push rod;

[0027] The bottom shell is hemispherical, a partition is provided inside the bottom shell, a liquid oxidant tank is provided below the partition, a solid fuel tank is provided above the partition, the upper plane of the solid fuel tank is hinged to the electric push rod, the telescopic end of the electric push rod passes through the hole on the nozzle shell and is hinged to the top cover; the outer surface of the top cover is a spherical surface, and has a common center with the bottom shell; wherein the electric push rod is extended and retracted by receiving a control instruction to adjust the relative position of the top cover, thereby changing the jet thrust in each direction to control the attitude of the aircraft;

[0028] The solid fuel bin includes an outer shell, a middle shell and an inner shell arranged in sequence, wherein the bottom of the middle shell is provided with a base and the top is provided with a top seat; two groups of microchannels are formed between the outer shell and the middle shell, which are respectively an air inlet microchannel and an air outlet microchannel; the inner shell serves as the shell of the combustion chamber and is filled with fuel; the inner shell and the base of the middle shell, as well as the base of the middle shell and the wall of the middle shell are provided with gaps, which are connected to the air outlet microchannel; the upper and lower parts of the inner shell are provided with openings; the middle part of the nozzle shell is provided with a nozzle throat, which is connected to the upper opening of the inner shell, and the lower opening of the inner shell is connected to the gap; an empty interlayer is provided around the nozzle throat, which is connected to the two groups of microchannels; the bottom shell is provided with an opening connected to the air inlet microchannel so that the oxidant can flow into the air inlet microchannel. In this embodiment, a regulating valve can be provided at the interlayer of the nozzle throat to regulate the flow of the oxidant.

[0029] The partition is welded to the inner wall of the bottom shell; the solid fuel tank is welded to the partition and filled with solid fuel, wherein the solid fuel is required to be able to spontaneously burn quickly with the vaporized oxidant. The nozzle shell is welded to the bottom shell and there must be no air leakage or loose welding. The required scientific detection instruments and gyroscopes are installed before loading the nozzle shell.

[0030] The electric push rods are provided with three groups, and correspondingly, three holes of appropriate size are opened on the nozzle shell to allow the electric push rods to pass through and reserve lateral movement space for the electric push rods when they are extended and retracted. The arrangement of the internal instruments and counterweights in this embodiment should make the center of gravity of the aircraft on the symmetry axis, and make the center of gravity of the aircraft still below the center of the sphere when the fuel is about to be exhausted.

[0031] The articulation adopts a spherical articulation, so that no friction and stress between different parts will be generated during control.

[0032] The top cover is provided with a top and a bottom, a hollow area is formed between the top and the bottom, and a guide cone is formed at the bottom to form a Prandtl-Meyer flow to prevent the gas from directly impacting the top cover and causing power loss.

[0033] The lunar probe of this embodiment adopts the method of self-reheating and self-pressurization. Fig.11 , oxidant flows from: the hole on the partition of the liquid oxidant compartment of the bottom shell → the air inlet micro-channel of the solid fuel compartment → the interlayer of the nozzle throat → the air outlet micro-channel of the solid fuel compartment → enters the cavity outside the inner liner of the solid fuel compartment through the gap between the base of the middle shell and the wall of the middle shell → enters the combustion chamber through the gap between the base of the middle shell and the inner liner. The vaporized oxidant reacts with the fuel in the combustion chamber to generate combustion gas, which is then ejected from the nozzle throat.

[0034] When the aircraft first starts to operate, the liquid oxidizer vaporizes in the liquid oxidizer bin due to the low pressure and flows into the air intake microchannel; after running for a period of time, the pressure in the liquid oxidizer bin, microchannel, combustion chamber, etc. increases. After the liquid oxidizer passes through the air intake microchannel, it absorbs heat in the interlayer of the nozzle throat before heating and vaporizing, and the pressure is increased, and the purpose of cooling the nozzle shell is achieved; the vaporized oxidizer then flows back to the bottom of the solid fuel bin along the air outlet microchannel, and then released into the combustion chamber. This structure allows the oxidizer to recover heat and increase pressure by itself to improve thermal efficiency, and cool the solid fuel bin, especially its liner, to prevent thermal damage to the structure. The oxidizer will not flow back or high and low temperature oxidizers will not mix. Related components need to be made of high temperature resistant materials.

[0035] The oxidizer is heated and vaporized by the nozzle shell wall (or vaporized by itself in the liquid oxidizer compartment due to low pressure at the beginning of startup) and then reacts with the fuel in the combustion chamber and burns by itself. The gas is accelerated through the nozzle throat and then accelerated and reversed through the spray ring composed of the top cover and the nozzle shell; the electric push rod is controlled to fine-tune the direction of the top cover to change the shape of the spray ring, bringing about thrust differences in different directions to change the attitude of the aircraft, so that it can fly level, etc.

Claims

1. A solid-liquid spherical lunar flying probe that can flexibly move and roll on the lunar surface, characterized by: It includes a bottom shell, a partition, a top cover, a nozzle shell and an electric push rod; The bottom shell is hemispherical, a partition is provided inside the bottom shell, a liquid oxidant tank is provided below the partition, a solid fuel tank is provided above the partition, the upper plane of the solid fuel tank is hinged to the electric push rod, the telescopic end of the electric push rod passes through the hole on the nozzle shell and is hinged to the top cover; the outer surface of the top cover is a spherical surface, and has a common center with the bottom shell; wherein the electric push rod is extended and retracted by receiving a control instruction to adjust the relative position of the top cover, thereby changing the jet thrust in each direction to control the attitude of the aircraft; The solid fuel tank comprises an outer shell, a middle shell and an inner shell which are arranged in sequence, the bottom of the middle shell is provided with a base, and the top is provided with a top seat; two groups of microchannels are formed between the outer shell and the middle shell, which are respectively an air inlet microchannel and an air outlet microchannel; the interior of the inner shell is filled with fuel, and gaps are provided between the inner shell and the base of the middle shell, and between the base of the middle shell and the wall of the middle shell, and the gaps are connected with the air outlet microchannels; openings are provided at the upper and lower parts of the inner shell; a nozzle throat is provided at the middle part of the nozzle shell, the nozzle throat is connected with the upper opening of the inner shell, and the lower opening of the inner shell is connected with the gap; an empty interlayer is provided around the nozzle throat, and the interlayer is connected with the two groups of microchannels; an opening connected with the air inlet microchannel is provided on the partition plate, so that the oxidant flows from the liquid oxidant tank into the air inlet microchannel.

2. The solid-liquid spherical lunar flying probe capable of flexibly moving and rolling on the lunar surface as claimed in claim 1, characterized in that: The partition is welded to the inner wall of the bottom shell, and the solid fuel bin is welded to the partition.

3. The solid-liquid spherical lunar flying probe capable of flexibly moving and rolling on the lunar surface as claimed in claim 1, characterized in that: The electric push rods are provided in three groups.

4. The solid-liquid spherical lunar flying probe capable of flexibly moving and rolling on the lunar surface as claimed in claim 1, characterized in that: The articulation adopts a spherical articulation.

5. The solid-liquid spherical lunar flying probe capable of flexibly moving and rolling on the lunar surface as claimed in claim 1, characterized in that: The top cover is provided with a top and a bottom, a hollow area is formed between the top and the bottom, and the bottom forms a drainage cone.

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