CN117104531A

CN117104531A - Lunar surface detector

Info

Publication number: CN117104531A
Application number: CN202310974159.2A
Authority: CN
Inventors: 张汉勋; 于喜河; 刘颖; 郭玉雪; 张伟; 乔志宏
Original assignee: Technology and Engineering Center for Space Utilization of CAS
Current assignee: Technology and Engineering Center for Space Utilization of CAS
Priority date: 2023-08-03
Filing date: 2023-08-03
Publication date: 2023-11-24

Abstract

The invention relates to a lunar surface detector which comprises a bearing shell and a heat source, wherein a moving mechanism is arranged in the bearing shell, an inlet and an outlet are formed in the side wall of the bearing shell, and a driving end of the moving mechanism is connected with the heat source and drives the heat source to enter and exit the bearing shell from the inlet and the outlet. According to the lunar surface detector, the moving mechanism is arranged, and the heat source is driven to enter and exit the bearing shell through the moving mechanism, so that the heat source can be positioned in the bearing shell or outside the bearing shell according to the requirements. Compared with the existing heat source utilization mode, the invention adopts the movement mechanism to drive the heat source to enter and exit the bearing shell so as to meet different requirements on the heat source, thereby being capable of effectively utilizing the heat source to generate heat during the month and the night, avoiding the over-high temperature in the bearing shell during the month and the day period and ensuring the effective heat dissipation during the month and the day period.

Description

Lunar surface detector

Technical Field

The invention relates to the technical field related to lunar exploration, in particular to a lunar surface detector.

Background

The moon surface has extremely high and low temperature environment besides high vacuum, 1/6g gravity acceleration, particle radiation, static electricity, moon dust and other environmental factors. The lunar surface temperature may be reduced to-180 ℃ or even lower during the night of up to about 15 earth days, and +120 ℃ or even higher during the day of up to about 15 earth days. The lunar rover is used as a carrier of various scientific detection instruments and application loads, and provides a proper working temperature environment for the payload loaded inside and outside the lunar rover while resisting the extreme environmental conditions, wherein the working temperature environment comprises the steps of solving the heat dissipation problem of the load equipment during the working period of the lunar daytime load and solving the heat preservation problem of the load during the dormant period of the lunar night load.

The existing lunar vehicles all adopt heat insulation measures to reduce heat exchange between the lunar vehicle and the surrounding environment, and good heat insulation measures can prevent excessive heat from the sun and the lunar surface from entering the lunar vehicle in the noon period and also prevent excessive heat from leaking out of the lunar vehicle in the low-temperature lunar night period. With the progress of science and technology and the appearance of new materials, more effective heat insulation measures can be adopted on lunar vehicles. The enhancement of the heat insulation effect is beneficial to reducing the pressure of heat input of the environment outside the lunar daytime on the lunar vehicle heat dissipation system and reducing the quantity value requirement of the lunar vehicle heat preservation system on heat sources such as isotopes in the lunar night.

In order to solve the problem of heat dissipation after load work, and also in order to ensure that the whole temperature of the lunar rover is still in the allowable range in the noon period, the lunar rover and part of load equipment outside the rover are provided with heat radiation radiating surfaces. Calculation analysis shows that the orientation and arrangement positions of the radiating surfaces are optimized, the influence of solar incident heat flow and lunar surface high temperature on the radiating capacity of the heat radiating surfaces can be effectively reduced, and the radiating capacity of the system is improved. However, the design of the lunar rover heat radiation surface solution also needs to consider how to realize the blocking problem of the heat radiation links during the month and the night, and avoid excessive heat from leaking from the links during the month and the night. Therefore, design optimization of the heat radiation radiating surface and layout position optimization of the radiating surface become an important content of lunar vehicle heat design consideration.

In the existing projects, the number of load devices carried by the lunar rover is limited, so that some lunar rovers adopt forced air circulation in a closed cavity to realize uniform temperature (the pressure-bearing requirement of the closed cavity can cause the increase of the weight and the volume of the system). However, as the number of loads loaded in a unit volume increases and the difference value of heat consumption between different loads increases, and factors such as rapid movement on a lunar surface and large change of surrounding heat environment caused by complex operation are also included, the temperature equalization design gradually becomes an important content of lunar vehicle heat design consideration, and the temperature equalization design is also beneficial to improving the universality and applicability of the system.

The problem of heat preservation energy utilization rate at night is also an important problem in the thermal design of lunar vehicles. In the past projects, an isotope heat source is generally adopted as an energy source for the month and night heat preservation. However, in order to solve the problems of self heat dissipation of the isotope heat source during the moon day/on-orbit flight period and unnecessary baking of the load equipment, the isotope heat source is generally installed outside the lunar rover, and part of the heat of the isotope heat source is introduced into the lunar rover during the moon night period through a thermal switch (a circulating fan or a two-phase gravity auxiliary loop and the like) and is isolated outside the lunar rover during the moon day period. This approach may cause some of the isotope heat source heat to dissipate outside the lunar rover during the night of the month, thereby reducing the utilization of the isotope heat source.

Therefore, the existing lunar rover scheme has the following technical problems: (1) the problem of low monthly and nocturnal utilization rate of the isotope heat source. In the existing projects, the isotope heat source is generally arranged outside the vehicle, and during the period of the moon, a considerable part of heat generated by the isotope heat source is discharged to the lunar surface outside the lunar vehicle and the cool black universe background in a heat radiation mode, and the part of heat is lost. (2) The isotope heat source utilization mode is complex, for example, a two-phase gravity auxiliary heat transfer system has the problem of low reliability caused by a valve, and also has the problem that the performance and the running state of the two-phase gravity auxiliary circulation system are sensitive to the initial vapor-liquid distribution condition, the position and the posture of a lunar rover, the heat source distribution characteristics, the external thermal environment parameters and the like of the system; for example, a pump circulation system has the problems of complex system constitution, active control, system reliability and the like. (3) The heat dissipation capacity, versatility and applicability of the existing systems need to be further improved. With more diversified lunar exploration and lunar application requirements, the quantity and the concentration of the payloads integrally loaded on the lunar rover are higher, the heat dissipation requirements brought by the work of load equipment are higher, and the reverse influence of various scientific exploration and technology application equipment on the lunar rover is larger. Therefore, the heat radiation capability, versatility and applicability of the lunar surface movement detector such as a lunar rover are to be improved. The measures in the aspect of thermal control comprise optimization of design and arrangement position of a radiating surface, optimization of a heat insulation structure, application of new materials, uniform temperature design of a lunar rover and the like, so that the lunar rover can adapt to large changes of a load working mode and changes of load composition (such as changing of load composition by astronauts), and adapt to internal heat and external heat environment changes caused by high-strength walking and working. Is suitable for more complex lunar environments and various scientific exploration and application environments (such as lunar dust deposition and pollution caused by drilling, and the like), and has better performance and longer service life.

Disclosure of Invention

The invention provides a general lunar surface detector scheme for energy conservation and heat preservation in midday period work/month and night in equatorial region for solving the technical problem of thermal control of the existing lunar vehicle. The scheme is suitable for the construction of heat control/structural systems of unmanned lunar surface detectors, manned lunar surface detectors, lunar bases and even other detectors/buildings which survive and work for a long time in a high vacuum environment and an extremely high and low temperature environment.

The technical scheme for solving the technical problems is as follows: the lunar surface detector comprises a bearing shell, a heat source and load equipment, wherein a moving mechanism is arranged in the bearing shell, an inlet and an outlet are formed in the side wall of the bearing shell, and a driving end of the moving mechanism is connected with the heat source and drives the heat source to enter and exit the bearing shell from the inlet and the outlet;

the top of the bearing shell is provided with an optical reflector and a solar sailboard, the solar sailboard is positioned at the outer side of the optical reflector, the optical reflector can be exposed when the solar sailboard is opened, and the optical reflector can be shielded when the solar sailboard is closed; the load device is disposed within the load bearing housing.

The beneficial effects of the invention are as follows: according to the lunar surface detector, the moving mechanism is arranged, and the heat source is driven to enter and exit the bearing shell through the moving mechanism, so that the heat source can be positioned in the bearing shell or outside the bearing shell according to the requirements. Specifically, except for the period of the month and night, the heat generated by the heat source is basically required to be discharged outwards in other periods, so that the heat source is prevented from entering the bearing shell as much as possible. The heat source is driven to be positioned outside the bearing shell through the movement mechanism until the heat source enters the lunar surface and enters the moon night, and the heat source outside the bearing shell discharges heat to the space in a heat radiation mode; when the moon is over night, the heat source can be driven into the bearing shell by the movement mechanism, and the heat source entering the bearing shell transmits the heat to instrument boards, equipment and the like arranged in the bearing shell in a radiation and heat conduction mode. Compared with the existing heat source utilization mode, the invention adopts the movement mechanism to drive the heat source to enter and exit the bearing shell so as to meet different requirements on the heat source, thereby being capable of effectively utilizing the heat source to generate heat during the month and the night, avoiding the over-high temperature in the bearing shell during the month and the day period and ensuring the effective heat dissipation during the month and the day period. The solar sailboard is matched with the optical reflector, and the optical reflector positioned at the top of the heat insulation shell is shared by the load built-in bearing shell during the daytime of the moon to radiate heat, so that the solar sailboard is opened; the load bearing shell is internally provided with a load sharing heat source to generate heat during the month and night, and the solar sailboard is folded at the moment; the solar sailboard at the top of the heat-insulating shell is opened and closed to solve the 'opposite' requirements of moon day heat dissipation and moon night heat preservation.

On the basis of the technical scheme, the invention can be improved as follows.

Further, a first heat insulation plate and a second heat insulation plate are respectively arranged on the inner side and the outer side of the heat source, and when the driving end of the movement mechanism drives the heat source to extend out of the bearing shell from the inlet and the outlet, the inlet and the outlet are blocked by the first heat insulation plate; when the driving end of the movement mechanism drives the heat source to retract from the inlet and the outlet to the inner side of the bearing shell, the second heat insulation plate seals the inlet and the outlet.

The beneficial effects of adopting the further scheme are as follows: by arranging the first heat insulating plate and the second heat insulating plate, when the heat source is positioned outside the bearing shell, the first heat insulating plate can be used for plugging the inlet and the outlet, so that the heat source is prevented from radiating heat to the bearing shell; when the heat source is positioned in the bearing shell, the inlet and the outlet can be plugged by the second heat insulation plate, so that the heat source is prevented from leaking out of the bearing shell. Because the lunar surface is a vacuum environment, even if a necessary movement gap exists between the bearing shell and the first heat insulation plate and the second heat insulation plate, the phenomenon that cold air/hot air on the ground is poured into the bearing shell can not occur, and the heat leakage caused by the movement gap is much smaller than that of other projects. Therefore, the heat-insulating plate is adopted to realize the heat leakage prevention and heat radiation prevention, and the heat utilization rate of the heat source can reach more than 90 percent.

Further, the first heat insulating plate and the second heat insulating plate are both aerogel plates.

The beneficial effects of adopting the further scheme are as follows: the aerogel plate is adopted for heat insulation, so that the heat insulation effect is better.

Further, the first heat insulation plate and the second heat insulation plate are both in a flat plate structure and are both arranged perpendicular to the driving direction of the movement mechanism; the first heat insulation plate is positioned at the inner side of the inlet and the outlet of the bearing shell, and the second heat insulation plate is positioned at the outer side of the inlet and the outlet of the bearing shell.

Further, a support is arranged on the outer side wall of the bearing shell, and one axial end of the support is cylindrical and is fixed around the inlet and the outlet.

The beneficial effects of adopting the further scheme are as follows: by arranging the support, the mechanical test of the rocket launching process and the lunar falling process can be safely carried out by the heat source. And when the heat source transfers around the ground and the moon, the heat source discharges the heat to the space in a heat radiation mode, so that the heat source is helped to safely experience the bracket for mechanical examination in the process of emission and moon falling, and the auxiliary heat dissipation effect can be achieved.

Further, the bearing shell comprises an outer insulating shell and an inner supporting shell, and the movement mechanism is arranged in an interlayer between the outer insulating shell and the inner supporting shell.

The beneficial effects of adopting the further scheme are as follows: the heat insulation outer shell is a heat insulation layer with complete envelope, and the supporting inner shell realizes structural support and meets the requirement of uniform temperature.

Further, the supporting inner shell comprises a honeycomb plate and a supporting frame, wherein frame rods of the supporting frame are arranged at edge positions of the honeycomb plate, and heat pipes are arranged on the honeycomb plate;

the heat insulation shell comprises an outer shell layer and a heat insulation layer, wherein the heat insulation layer is arranged on the inner side wall of the outer shell layer.

The beneficial effects of adopting the further scheme are as follows: the support frame can carry out effective structural support to the honeycomb panel, and the heat pipe can carry out effective water conservancy diversion to the heat source heat, satisfies the heat demand of each equipment in the bearing shell.

Further, the heat control system is respectively arranged in the bearing shell, is respectively connected with the heat source, the bearing shell and the load equipment, and establishes a heat channel between the load equipment and the heat source and the bearing shell.

The beneficial effects of adopting the further scheme are as follows: the thermal control system is used for establishing a thermal channel between the load equipment and the heat source and the bearing shell, so that the heat radiation capacity is increased, the heat insulation effect is good, the heat source utilization rate is improved, the load layout adjustment and the working mode adaptability are improved, and the working environment adaptability is improved.

Further, the load devices are multiple and are respectively arranged on the outer surface of the bearing shell or/and the interlayer of the bearing shell or/and the inner cavity of the bearing shell.

The lunar surface detector of the invention has the following characteristics: (1) The two-way heat insulation function under the high-temperature/low-temperature environment of the moon day and the night is wider in temperature resistant range and smaller in system heat leakage rate; (2) Layered heat insulation/partition temperature control, more reasonable heat control resource utilization and finer heat support for loads/mechanisms/astronauts; (3) The solar heat flow of high-intensity visible light and the infrared heat flow of high-intensity lunar surface can be shielded simultaneously, a large-scale low-temperature radiating surface is formed, and the high-intensity working/walking requirements in the midday period of the equatorial region are met; (4) The on/off function and the conveying/distributing management scheme of the isotope heat source heat are simple, effective and reliable, the demand of heat source heat dissipation to the environment in the daytime period is met, and the high-efficiency and on-demand utilization of the isotope heat source heat in the evening period are realized.

Drawings

FIG. 1 is a schematic diagram of an optical mirror according to the present invention;

FIG. 2 is a schematic view of the heat insulating housing of the present invention;

FIG. 3 is a schematic view of the configuration of the heat insulating housing of the present invention mated with an optical reflector;

FIG. 4 is a schematic view of the assembled structure of the bracket of the present invention on the heat insulating housing;

FIG. 5 is a schematic view of the assembly process of the motion mechanism, heat source, first heat shield and second heat shield of the present invention;

FIG. 6 is a schematic view of the structure of the invention after the assembly of the movement mechanism, heat source, first heat shield and second heat shield within the heat shield housing;

FIG. 7 is a schematic view of the structure of the moving mechanism, heat source, first heat shield and second heat shield of the present invention assembled and positioned in the bracket;

FIG. 8 is a schematic view of the assembly of the support inner housing, heat pipes and optical reflector of the present invention;

FIG. 9 is a schematic view of the assembly of the support frame with the support inner housing, heat pipes and optical mirrors of the present invention;

FIG. 10 is a schematic perspective view of a lunar surface detector according to the present invention;

FIG. 11 is a schematic diagram of the result of estimating the heat dissipation capacity of an optical reflector according to the present invention;

FIG. 12 is a diagram showing the evaluation result of the heat source leakage.

In the drawings, the list of components represented by the various numbers is as follows:

100. a heat source;

200. a movement mechanism;

300. a first heat shield; 301. a second heat shield;

401. a heat insulating housing; 402. supporting the inner shell; 403. an inlet and an outlet; 404. an optical mirror; 405. a solar sailboard; 406. a heat pipe; 407. a bracket; 408. an interlayer accommodating chamber; 409. a thermal insulation layer; 410. an outer shell layer; 411. and a supporting frame.

Detailed Description

The principles and features of the present invention are described below with reference to the drawings, the examples are illustrated for the purpose of illustrating the invention and are not to be construed as limiting the scope of the invention.

As shown in fig. 1 to 10, the lunar surface detector of the present embodiment includes a bearing shell, a heat source 100 and a load device, a movement mechanism 200 is disposed in the bearing shell, an inlet and an outlet 403 are formed on a side wall of the bearing shell, and a driving end of the movement mechanism 200 is connected with the heat source 100 and drives the heat source 100 to implement the movement of entering and exiting the bearing shell from the inlet and the outlet 403.

Specifically, the heat source 100 of the present embodiment may be an isotope heat source RHU.

As shown in fig. 1, 3, 4, 6 and 7, an optical mirror 404 and a solar panel 405 are disposed on the top of the carrying case in this embodiment, the solar panel 405 is located at the outer side of the optical mirror 404, the optical mirror 404 can be exposed when the solar panel 405 is opened, and the optical mirror 404 can be blocked when the solar panel 405 is closed. The solar sailboard is matched with the optical reflector, and the optical reflector positioned at the top of the heat insulation shell is shared by the load built-in bearing shell during the daytime of the moon to radiate heat, so that the solar sailboard is opened; the load bearing shell is internally provided with a load sharing heat source to generate heat during the month and night, and the solar sailboard is folded at the moment; the solar sailboard at the top of the heat-insulating shell is opened and closed to solve the 'opposite' requirements of moon day heat dissipation and moon night heat preservation. The optical reflector 404 is also called OSR, and is arranged on the top of the bearing shell, namely, the top facing surface of the highest point of the whole lunar surface detector, so that adverse effects of a high Wen Yue surface and a vehicle body (lunar surface detector) on a radiating surface are avoided to the greatest extent, and the heat radiation and radiating capability as large as possible can be formed on the lunar surface detector with limited dimensions.

As shown in fig. 5, in this embodiment, a first heat insulation board 300 and a second heat insulation board 301 are respectively disposed on the inner and outer sides of the heat source 100, and when the driving end of the movement mechanism 200 drives the heat source 100 to extend out of the bearing shell from the inlet/outlet 403, the first heat insulation board 300 seals the inlet/outlet 403; when the driving end of the moving mechanism 200 drives the heat source 100 to retract from the inlet/outlet 403 to the inner side of the bearing housing, the second heat insulation plate 301 seals the inlet/outlet 403. The first heat shield 300 may be fixed to the driving end of the moving mechanism 200 or may be installed on the heat source 100. By arranging the first heat insulating plate and the second heat insulating plate, when the heat source is positioned outside the bearing shell, the first heat insulating plate can be used for plugging the inlet and the outlet, so that the heat source is prevented from radiating heat to the bearing shell; when the heat source is positioned in the bearing shell, the inlet and the outlet can be plugged by the second heat insulation plate, so that the heat source is prevented from leaking out of the bearing shell. Because the lunar surface is a vacuum environment, even if a necessary movement gap exists between the bearing shell and the first heat insulation plate and the second heat insulation plate, the phenomenon that cold air/hot air on the ground is poured into the bearing shell can not occur, and the heat leakage caused by the movement gap is much smaller than that of other projects. Therefore, the heat-insulating plate is adopted to realize the heat leakage prevention and heat radiation prevention, and the heat utilization rate of the heat source can reach more than 90 percent.

An alternative to this embodiment is to use aerogel sheets for both the first heat shield 300 and the second heat shield 301. The aerogel plate is adopted for heat insulation, so that the heat insulation effect is better.

The shape of the heat insulation plate is not limited, and the inlet and the outlet can be blocked. For example, fig. 5 shows a heat insulating plate with a square structure so as to block and close an inlet and an outlet of the square structure.

As shown in fig. 5, in one embodiment of the present invention, the first heat insulation board 300 and the second heat insulation board 301 are both in a flat plate structure and are both arranged perpendicular to the driving direction of the movement mechanism 200; the first heat insulating plate 300 is positioned at the inner side of the inlet and outlet of the bearing shell, and the second heat insulating plate 301 is positioned at the outer side of the inlet and outlet 403 of the bearing shell.

As shown in fig. 4, 6 and 7, in a preferred embodiment of this embodiment, a bracket 407 is disposed on an outer sidewall of the bearing shell, and one axial end of the bracket 407 is fixed around the inlet/outlet 403. By arranging the support, the mechanical test of the rocket launching process and the lunar falling process can be safely carried out by the heat source. And when the heat source transfers around the ground and the moon, the heat source discharges the heat to the space in a heat radiation mode, so that the heat source is helped to safely experience the bracket for mechanical examination in the process of emission and moon falling, and the auxiliary heat dissipation effect can be achieved. The shape of the bracket can be set at will, for example, a square tubular structure can be adopted, a cylindrical structure can also be adopted, and the bracket can be matched with the shape of the inlet and the outlet. The support is provided with a lightening hole, so that the weight is reduced as much as possible, and the strength and the stability of the whole structure are not influenced.

Wherein, the movement mechanism 200 is combined with the heat source 100 to form an isotope heat source capable of entering and exiting, and is composed of an isotope heat source, an entering and exiting mechanism and a heat insulation plate (inner/outer). The isotope heat source is a heat source which can not stop when heating is started, the heat of the isotope heat source is used for realizing the heat preservation of the moon and the night during long moon and the heat of the isotope heat source is needed to be used for discharging unnecessary heat during long moon and day and on-orbit flight. Thus, the access mechanism and the heat shield (inside/outside) are designed. The in-out mechanism moves the heat source out of the lunar surface detector in a lunar day period and moves the heat source into the lunar surface detector in a lunar night period. After the moving-out/moving-in action is in place, the heat insulation plate (one of the inner part or the outer part) just plugs the entrance and exit hole, so that the requirements that the isotope heat source heat is sealed in the lunar surface detector during the night and shielded outside the lunar surface detector during the day are met. The support is used as an external support structure necessary when the isotope heat source is positioned outside the detector, and is provided with a locking/unlocking mechanism besides mechanical bearing and auxiliary heat radiation and heat dissipation functions so as to realize the mechanical locking of the isotope heat source externally arranged in the emission/on-orbit flight/month winding/month falling period; the motion assembly is driven by a motor, and after the moon-falling unlocking is completed, the isotope heat source and the heat insulation plate (inner/outer) integrated moving in/out function is realized; the inner radiation cavity of the isotope heat source is mainly used for absorbing heat of the high-temperature isotope heat source entering the cavity in a heat radiation mode, and damage of high temperature and radioactivity of the isotope heat source to load equipment is avoided. The heat absorbed by the internal radiation cavity is transmitted to each part of the lunar surface detector as required by a traditional heat pipe network, heat radiation, heat conduction and other modes with better lunar surface force/heat environment adaptability, so that the heat preservation requirements of the lunar surface detector in extremely cold and long lunar night time periods are met. The internal radiation cavity scheme provides a more reliable, simpler and effective isotope heat source heat utilization scheme than the existing project, and forms a similar switching effect of the on/off of the isotope heat source in the moon night together with the isotope heat source 'in/out' scheme, and the comprehensive utilization of the isotope heat source heat in the moon night period is realized on the isotope heat source heat utilization efficiency, so that the utilization efficiency is higher than that of the conventional project. The isotope heat source can be in and out and is positioned at the lower left position of the lunar surface detector. During the emission period, the on-orbit flight period of the running month and the month falling process, the isotope heat source is always positioned in the region of the isotope heat source bracket 407, and the locking/unlocking device in the locking state assists the isotope in-out mechanism to bear the mechanical environment of the emission/month falling stage. After the lunar surface detector falls to the lunar surface, the locking/unlocking device is unlocked, the isotope inlet and outlet mechanism is changed from a locking state to a freely movable state, and the isotope heat source is led into and out of the lunar surface detector through the inlet and outlet 403 shown in fig. 8.

As shown in fig. 6 to 10, the carrying case of the present embodiment includes an insulating outer case 401 and a supporting inner case 402, and the movement mechanism 200 is disposed in a sandwich between the insulating outer case 401 and the supporting inner case 402. The heat insulation outer shell is a heat insulation layer with complete envelope, and the supporting inner shell realizes structural support and meets the requirement of uniform temperature. Because the movement mechanism needs to keep warm in the evening and cannot withstand sun exposure and infrared baking of the evening, the movement mechanism needs to be arranged in an interlayer between the bearing shells. Since the insulating housing 401 is the primary barrier for the lunar surface detector to establish an internal and external temperature differential during the lunar day and night, and to maintain the internal temperature of the lunar surface detector at a level substantially within the temperature of a conventional satellite at all times, the installation of the movement mechanism in the interlayer ensures efficient operation of the movement mechanism. Besides, besides the moving mechanism for driving the heat source, the load driving mechanism can be arranged in the interlayer, the load driving mechanism can adopt a linear moving mechanism and can drive the load to enter and exit the lunar surface detector, and after the lunar surface detector is taken out of the shell, the free lunar surface space can be utilized to realize expansion or deformation, so that the utilization rate of the interlayer space can be improved, more loads or mechanisms can be arranged in the interlayer, the existing body of the load driving mechanism or load equipment can be utilized to automatically block the entrance and exit the hole, and further, the integrity of the heat insulation shell of the lunar surface detector is not damaged by the load driving mechanism and the load equipment in the working state, the storage state and even the transitional state, and the problem that heat at the entrance and exit hole is gushed in during the lunar day and runs off during the lunar night is avoided. The heat insulation shell 401 is not only an outermost heat insulation layer of the lunar surface detector, but also can form an enveloping and shielding effect on the optical reflector 404, and can effectively isolate infrared heat influence generated by the incandescent height Wen Yue facing the optical reflector 404. Therefore, it is the synergistic effect of the heat insulation housing 401 and the optical reflector 404, and the heat radiation surface with large scale and low Wen Gongyong can be formed under the clamping of the high-intensity solar visible light heat flow and the high-intensity infrared heat flow of the lunar surface (120 ℃) in the noon period of the near-equatorial region, so that the heat radiation requirement brought by the high-intensity work/walking of the detector at noon time can be met (fig. 10). The inlet and outlet mechanism is arranged in the interlayer, so that the effective work of the inlet and outlet mechanism can be ensured without damaging the thermal stability of the system. In addition to the access mechanism for driving the isotope heat source of the present embodiment, other types of access mechanisms may be disposed in the interlayer. All kinds of business turn over mechanisms all adopt linear motion mode action in the intermediate layer, accomplish complex actions such as expansion or rotation again after going out the intermediate layer to the moon surface space, can improve intermediate layer space utilization like this so that arrange more loads or mechanisms in the intermediate layer, also be convenient for utilize the model body of mechanism or load equipment to seal in and out the entrance to a cave mouth voluntarily, and then guarantee the integrality of the thermal-insulated envelope of lunar surface detector under operating condition and the storage state, avoid heat to gush into in the time of lunar day through the entrance to a cave mouth, the problem of loss during the night of moon.

The bearing shell of the embodiment comprises a heat insulation outer shell 401 and a supporting inner shell 402, which is equivalent to that the whole bearing shell is composed of a 3-layer structure of a multifunctional protection outer cover, a wide temperature area mechanism interlayer and a uniform temperature inner layer. The multifunctional protective outer cover (the heat insulation shell 401) can meet the requirements of moon night heat preservation/moon day heat insulation, dust prevention/static prevention/scrubbing resistance and the like of the moon surface detector; the wide temperature zone mechanism interlayer (interlayer between the heat insulation outer shell 401 and the support inner shell 402) and the uniform temperature inner layer (inside the support inner shell 402) can meet the requirements of stretching work of various mechanisms in the daytime and daytime period/folding heat preservation in the nighttime and the requirements of mechanical bearing and temperature control of the mechanisms and load equipment in the launching/on-track flight/moon falling/walking/drilling and other periods. The 3-layer structure scheme has the advantages of layered heat insulation and zonal temperature control. The layered heat insulation can effectively improve the heat insulation capacity, and meets the bidirectional heat insulation requirements of the past lunar exploration project which does not go through at the same time and is only encountered in the lunar day extremely high-temperature environment and the lunar night extremely low-temperature environment when the lunar exploration project is in lunar on the near-equatorial region; the partition temperature control can reduce the heat control resource requirement, is convenient for realizing that mechanism inlet and outlet interlayers do not damage the heat envelope integrity of the uniform temperature inner layer/the multifunctional protective outer cover, avoids the problems of moon sunlight and high Wen Yuebiao heat filling/moon low Wen Yue surface and heat leakage caused by cold and black space caused by leaving large-scale mechanism inlet and outlet holes, and further maintains the stability of the heat state of other load devices in the lunar surface detector. The interlayer of the wide temperature zone mechanism is arranged between the multifunctional protective outer cover and the uniform temperature inner layer, and is a concentrated arrangement zone of various inlet and outlet mechanisms. The interlayer of the wide temperature area mechanism and the multifunctional protective outer cover can meet the thermal integrity requirement that the entrance/exit detectors of various complex mechanisms do not damage the heat insulation envelope, prevent the environmental heat of the moon day period from being poured into/the heat of the moon night period detector from leaking, and realize the moon day stretching work of the mechanism and the heat preservation requirement of the moon night folding while not affecting the thermal state of other equipment. The interlayer temperature control adopts passive heat control measures such as heat insulation/heat conduction/heat radiation and the like, and does not consume active heat control resources. The temperature range is-120 ℃ to +90 ℃, which is better than the temperature range of-180 ℃ to +120 ℃ of the month surface where the multifunctional protective outer cover is positioned. The inner layer adopts passive heat control measures such as a common heat pipe network/coating and the like, is coupled with components such as a structural system frame/honeycomb plate and the like, is optimally designed, balances the temperature difference between high and low temperature equipment, balances the sunlight and shadow side temperature difference, and realizes heat capacity and heat sharing. The uniform temperature inner layer is more suitable for the load layout with high concentration and heat consumption and the lunar surface replacement requirement under the assistance of astronauts. The uniform temperature inner layer is used as a heat transfer bridge, a heat transfer channel between the load equipment and the top OSR heat radiation surface and between the load equipment and the isotope heat source inner radiation cavity is established, the top OSR heat radiation surface is utilized to realize moon day work and heat dissipation during moon day and night, and the isotope heat source entering the detector is utilized to realize moon night heat preservation during moon night. Under the condition of not consuming active heat control resources such as electric heating, the control requirement of the storage temperature range of-50 ℃ to +70 ℃ and the working temperature range of-20 ℃ to +50 ℃ is realized, and a necessary foundation is laid for the temperature control of load equipment working in a narrower temperature range. The layered heat insulation is adopted in the embodiment, so that the heat insulation capacity can be effectively improved, and the bidirectional heat insulation requirements of the past month detection project, which are not experienced at the same time, are met only in the month day extremely high-temperature environment and the month night extremely low-temperature environment which are met when the month is climbed in the near-equatorial region are met; the adoption of the partition temperature control can reduce the heat control resource requirement, is convenient for realizing that the mechanism inlet and outlet interlayer does not damage the heat envelope integrity of the uniform temperature inner layer/the multifunctional protective outer cover, avoids the problems of moon sunlight and high Wen Yuebiao heat filling/moon low Wen Yue surface and heat leakage caused by cold and black space caused by leaving a large-scale mechanism inlet and outlet hole, and further maintains the stability of the heat state of other load devices in the lunar surface detector.

The optical mirror 404, which is the common OSR heat radiating surface on top, has the greatest radiation viewing angle for a cool black sky after the closable/deployable solar array is deployed; the complete heat insulation envelope formed by the multifunctional protective outer cover and the heat insulation plate can shield infrared heat radiation of the OSR heat radiation surface on the opposite top of the high Wen Yue surface; the OSR affixed to the heat radiating surface of the overhead OSR also provides very high infrared heat radiation capability to the cool black sky while reflecting a substantial portion of the incident heat flow of visible sunlight. Therefore, the heat radiation surface of the overhead OSR has a good low-temperature state even in the midday time division near the equator, and can meet the working heat radiation requirement of the lunar surface detector with higher intensity in the midday time division of the lunar equatorial region. The heat generated by the equipment and a small amount of heat leakage from the environment are transferred to the heat radiation surface of the overhead OSR in a heat conduction and radiation mode through the interlayer of the wide temperature area mechanism, the inner radiation cavity of the isotope heat source and the heat pipe network. The solar sailboard capable of being closed/unfolded is closed at night and further covers the heat radiation surface of the top OSR; after finishing the moon work, all mechanisms are folded to the interlayer of the mechanism with wide temperature area, and the interlayer with good temperature condition is prepared to pass extremely cold moon night; the isotope heat source enters the lunar surface detector and provides heat preservation heat for the lunar surface detector in cold and night time periods. In the moon night mode, the multi-layer heat insulation material on the back of the solar sailboard, the multifunctional protective outer cover and the heat insulation board form a complete heat insulation envelope together, so that the heat leakage of the moon surface detector in the extremely cold moon night period is effectively reduced. The radiation cavity and the heat pipe network in the isotope heat source send the heat of the isotope heat source which enters the detector to each load device according to the requirement, thereby ensuring the safety of the lunar surface detector to pass extremely cold and long moon night.

Specifically, as shown in fig. 4 to 6, the movement mechanism 200 of the present embodiment may be a linear movement mechanism, such as a linear motor, a cylinder, a linear module, or a rotary in-out mechanism, such as a 90 ° tilting mechanism. An interlayer accommodating cavity 408 can be arranged in the heat insulating outer shell, an inlet and an outlet 403 are arranged at corresponding positions on the heat insulating outer shell 401 and the supporting inner shell 402, the moving mechanism 200 is arranged in the interlayer accommodating cavity 408, when the moving mechanism 200 is positioned in the interlayer accommodating cavity, the inlet and the outlet on the supporting inner shell 402 are blocked by the first heat insulating plate 300, and the inlet and the outlet on the heat insulating outer shell 401 are blocked by the second heat insulating plate 301. Whether a linear or inverted in-out isotope heat source is used, the port 403 must be plugged at the opening formed in the insulating envelope of the lunar surface detector.

As shown in fig. 8 and 9, the supporting inner case 402 of the present embodiment includes a honeycomb plate and a supporting frame 411, and frame bars of the supporting frame 411 are disposed at edge positions of the honeycomb plate, and heat pipes 406 are disposed on the honeycomb plate. The support frame can carry out effective structural support to the honeycomb panel, and the heat pipe can carry out effective water conservancy diversion to the heat source heat, satisfies the heat demand of each equipment in the bearing shell. The supporting inner shell 402 also adopts a double-layer structure, namely, the supporting frame 411 is used as an outer layer supporting structure, the honeycomb plate is matched with the heat pipe 406 to be used as an inner layer temperature equalizing structure, the load built-in load of the bearing shell is arranged on the honeycomb plate, the built-in load shares a shared optical reflector 404 (when the solar sailboard is opened) positioned at the top of the lunar surface detector during the lunar day, and the built-in load shares the heat generation of a heat source (when the solar sailboard is closed) during the lunar night. The honeycomb plate and heat pipe combined scheme can also adopt aluminum alloy metal plates as heat radiation plate surfaces to replace the heat radiation plate surfaces. The outer side walls of the bearing inner shell 402 (embedded heat pipe honeycomb plate) and the supporting frame 411 are provided with brackets 407 of isotope heat sources, and the brackets 407 are fixed around the inlet and outlet 403. Through setting up the support, can help isotope heat source safety to go through the mechanical test of rocket launching process and month process. And in the period of ground winding/ground month transferring/month winding, the bracket can also play a role in assisting heat dissipation. The shape of the bracket can be a square cylindrical structure or a cylindrical structure, and can be matched with the shape of the inlet and the outlet. The support is provided with a lightening hole, so that the weight is reduced as much as possible, the strength and stability of the whole structure are not affected, and the isotope heat source is convenient to rapidly install on the rocket launching tower when the isotope heat source is nearby to launch. The inner side walls of the bearing inner shell 402 (embedded heat pipe honeycomb plate) and the supporting frame 411 are provided with an interlayer containing cavity 408, the interlayer containing cavity is used as an isotope heat source inner radiation cavity and is formed by a high-temperature resistant and high-infrared-emissivity surface treated metal material, the interlayer containing cavity is used as a heat/radiation protection barrier between a high-temperature isotope heat source and normal-temperature load equipment, isotope heat source heat is collected in a heat radiation mode, heat is transmitted to the positions of the lunar surface detector according to needs in a contact surface heat conduction and heat transfer mode, a heat pipe network mode and the like, and the heat is used for lunar night heat preservation of the lunar surface detector.

In the month and day period after the month, the movement mechanism is responsible for countering the vibration generated by activities such as walking and drilling of the lunar surface detector and stabilizing the position of the isotope heat source in the region of the bracket 407. The bracket 407 and the outer shell 410 are made of metal materials, and can resist long-term high-temperature baking of the isotope heat source and assist the isotope heat source to complete heat radiation and heat dissipation. The multiple layers of insulating material 409 form a complete insulating envelope with the first insulating barrier 300, isolating the isotope heat source heat from the lunar surface detector during periods of external isotope heat source placement.

And in the month and night period after the month, the isotope motion mechanism is responsible for countering various mechanical disturbances possibly occurring in the month and night period and stabilizing the position of the isotope heat source in the radiation cavity in the isotope heat source. After the heat of the isotope heat source is collected by the radiation cavity in the isotope heat source in a heat radiation mode, the heat is transmitted to all positions of the lunar surface detector as required through modes of heat conduction and heat transfer of the contact surface, a heat pipe network and the like, and the lunar surface detector is used for heat preservation of the lunar night. The multiple layers of insulating material 409 form a complete insulating envelope with the second insulating barrier 301, enveloping the isotope heat source heat within the lunar surface detector during the isotope heat source build-in period.

Specifically, as shown in fig. 8, 4 side plates of the inner layer of the lunar surface detector all adopt a pre-buried heat pipe honeycomb plate scheme, 3 heat pipes are horizontally arranged on each honeycomb plate, and the 3 horizontally arranged heat pipes can establish a uniform temperature channel between load devices arranged on the single honeycomb plate. Further, in order to establish a thermal channel between the 4 side plates and the top OSR heat radiation surface, 4L-shaped bridging heat pipes are adopted, and the bridging heat pipes realize thermal coupling between the 4 side plates and the top OSR heat radiation surface.

Specifically, as shown in fig. 3, the heat insulation housing 401 includes a housing layer 410 and a heat insulation layer 409, and the heat insulation layer 409 is disposed on an inner sidewall of the housing layer 410. The outer shell layer 410 and the heat insulating layer 409 together form a heat insulating layer with complete envelope, the outer shell layer 410 is formed by a light thin shell structure which is positioned on the side surface and the bottom surface and integrates heat insulation, scratch resistance, static electricity prevention and dust prevention functions, the heat insulating layer 409 adopts a heat insulating material MLI, the heat insulating layer 409 is not only arranged on the inner side wall of the outer shell layer 410, but also is arranged on the back surface of the solar sailboard positioned on the top surface. The insulating housing 401 has a double-layer structure to meet the requirement of insulating the external extreme heat environment uniformly existing in the daytime and nighttime.

The insulating outer shell 401 is mounted in an insulating manner (with the insulating mat in the connection position) on a support frame 411 supporting the inner shell 402, i.e. on the basis that the insulating layer 409 has achieved insulation of the external extreme thermal environment on the heat radiating link, insulation of the external extreme thermal environment is also achieved on the heat conducting link. Not only is the heat insulation outer shell 401 of a double-layer structure adopted, but also the support inner shell of a double-layer structure is adopted, and an inner-outer double-layer structure design is adopted between the support inner shell and the heat insulation outer shell for bearing the weight of the shell, so that the load partition arrangement is realized while the outer heat insulation heat preservation/inner layer uniform temperature design is better realized, the requirement on heat control resources is reduced, and more load/more complex application requirements can be met.

The lunar surface detector of the embodiment further comprises a thermal control system, wherein the thermal control system is arranged in the bearing shell, is respectively connected with the heat source 100, the bearing shell and the load equipment, and establishes a thermal channel between the load equipment and the heat source 100 and the bearing shell. The thermal control system is specifically connected with the optical reflector and is used for controlling the temperature of the load equipment on the bearing shell.

As shown in fig. 10, a mobile device may be further disposed at a lower portion of the carrier shell of the lunar surface detector in this embodiment, so that the lunar surface detector can move on the lunar surface conveniently. The mobile device can select the roller commonly used by the existing lunar surface detector, and the like.

The outer surface of the heat insulation housing 401 may be provided with devices which do not need to keep warm for a month and night, and can also withstand solar irradiation during a long period of time and influence of infrared heat on the month and night, such as a high and low temperature resistant travelling mechanism, a solar sailboard, a sun/star sensor and the like which are used in the goddess project, which are uniformly distributed on the outer surface of the heat insulation housing 401, the devices which need to be mechanically carried are installed on the supporting inner housing 402 in a heat insulation manner, and the devices which do not need to be mechanically carried can be installed on the inner side wall of the heat insulation housing 401.

According to the lunar surface detector, the moving mechanism is arranged, and the heat source is driven to enter and exit the bearing shell through the moving mechanism, so that the heat source can be positioned in the bearing shell or outside the bearing shell according to the requirements. Specifically, except for the period of the month and night, the heat generated by the heat source is basically required to be discharged outwards in other periods, so that the heat source is prevented from entering the bearing shell as much as possible. The heat source is driven to be positioned outside the bearing shell through the movement mechanism until the heat source enters the lunar surface and enters the moon night, and the heat source outside the bearing shell discharges heat to the space in a heat radiation mode; when the moon is over night, the heat source can be driven into the bearing shell by the movement mechanism, and the heat source entering the bearing shell transmits the heat to instrument boards, equipment and the like arranged in the bearing shell in a radiation and heat conduction mode. Compared with the existing heat source utilization mode, the embodiment adopts the movement mechanism to drive the heat source to enter and exit the bearing shell to meet different requirements on the heat source, so that the heat source can be effectively utilized to generate heat during the month and the night, the over-high temperature in the bearing shell during the month and the day period is avoided, and the effective heat dissipation during the month and the day period is ensured.

When the lunar surface detector of the embodiment is used for carrying out lunar day heat dissipation, unlike a jade rabbit, the optical reflector is arranged on the upper and lower butt joint surfaces, and the optical reflector is arranged at the highest position right above the whole lunar surface detector and is arranged on the inner supporting shell of the bearing shell in a heat conduction mode, and meanwhile, the heat shielding of the high Wen Yue surface is realized by means of the outer contour formed by the heat insulation shell of the lunar surface detector. The optical reflector can effectively reflect sunlight in a visible light wave band, the heat insulation shell shields hot infrared radiation from the lunar surface and the outer surface of the detector, and the high-altitude optical reflector has a view almost not shielded on a cold black universe background, so that the lunar surface detector of the embodiment has better radiation heat-dissipation capability, and particularly, when the solar altitude angle is lower in the morning and afternoon. When the lunar surface detector of the embodiment is used for carrying out lunar night heat preservation, heat generated by the heat source is basically required to be discharged outwards in other periods except for the lunar night period, and the heat is prevented from entering the space in the bearing shell as much as possible. The heat source is present outside the lunar surface detector from the emission stage until the lunar surface enters the night. The support arranged on the lunar surface detector helps the heat source to safely go through the mechanical test of the rocket launching process and the lunar falling process.

Compared with the existing lunar surface detector, the lunar surface detector has the advantages of increased heat radiation capacity, good heat insulation effect, improved heat source utilization rate, load layout adjustment, improved working mode adaptability and improved working environment adaptability. The lunar surface detector, such as a lunar vehicle, can meet the requirements of load cluster lunar day work and lunar night heat preservation on the lunar surface detector, can adapt to high heat dissipation requirements caused by load quantity increase and power density increase, and can adapt to heat influence caused by load composition adjustment/working mode change or internal and external heat flow change caused by rapid movement/complex operation of the lunar surface detector. The lunar surface detector of the embodiment can meet the maximum utilization requirement of the heat source during the moon night, avoid the invalid waste of precious energy, ensure that the heat source can normally dissipate heat during the moon day, and have no adverse heat effect on the detector working at high temperature. The lunar surface detector of the embodiment can be better suitable for lunar high vacuum, 1/6g gravity acceleration, particle radiation, static electricity and lunar dust environments; the device is suitable for long-term working requirements (such as dust pollution caused by long-time drilling and the like) of the moon vehicle under high-strength motorized walking or special load high-strength/variable mode/strong pollution.

The heat dissipation capacity of the top OSR heat radiation surface of the lunar surface detector of this embodiment is estimated, and the evaluation software: thermal Desktop model V5.7, and the estimation method is a lumped parameter-finite difference method. The estimation results are shown in fig. 11, wherein in fig. 11, the abscissa represents the time of day of month, the ordinate represents the temperature of the heat radiation surface of the overhead OSR, the broken line represents the temperature change curve under the 300W heat consumption condition, and the solid line represents the temperature change curve under the 0W heat consumption condition. As can be seen from fig. 11, under the combined action of the direct heat flow of the nearly vertically poured sunlight and the infrared heat flow of the glorious lunar surface, the top OSR heat radiation surface of the lunar surface detector of the embodiment achieves the goal of dissipating the working heat consumption of the 300W load device at the scale of 1.8 square meters.

Evaluation of heat source leakage amount of lunar surface detector of this embodiment as shown in fig. 12, evaluation software: thermal Desktop model V5.7, and the estimation method is a lumped parameter-finite difference method. The estimation results are shown in fig. 12, in which the abscissa represents the month and night time, the ordinate represents the heat leak amount, and the solid line represents the heat leak condition of the system throughout the month and night from evening to dawn. As can be seen from fig. 12, the amount of heat leakage is large at the initial time because the system is still in a high temperature state, but then as the temperature decreases, the amount of heat leakage of the system gradually decreases and balances at a lower magnitude, 4W.

The embodiment is based on the unprecedented requirements of bidirectional heat insulation in the extreme high-temperature environment of the moon day and the extreme low-temperature environment of the moon night in the near-equatorial region, the requirements of high-strength walking/working heat dissipation in noon of the moon day, and the requirements of meeting higher index requirements under severe resource constraint conditions, such as the requirements of high-efficiency utilization of isotope heat source heat, the requirements of multi-class complex mechanism moon day stretching work/moon night gathering heat preservation, the requirements of general layout/high-concentration work of multi-class load products and the like, and is given after iterative demonstration and detailed analysis. The system can be used for the development of a thermal control/structure subsystem of an unmanned lunar surface detector platform and a manned lunar surface detector platform in an extreme heat environment. Its advantages and features include:

(1) The layered heat insulation function realized by the design scheme of the multifunctional protective outer cover, the wide temperature area mechanism interlayer and the uniform temperature inner layer 3 layers provides stronger heat insulation capability than that of the traditional lunar surface detector. The stronger heat insulation capability is a necessary foundation for realizing the high-strength walking/working requirements of the lunar surface detector on the hot lunar surface in noon and inheriting the mature isotope heat source products to solve the heat insulation problem of the lunar surface detector with larger scale in extremely cold and long moon night; (2) The 'partition temperature control' function realized by the 'multifunctional protective outer cover + wide temperature area mechanism interlayer + uniform temperature inner layer' 3-layer structural design scheme can naturally form 3 temperature areas which are reversely distributed in extremely cold month and night and hot month and day time periods. On the basis of a naturally formed warm zone, a more suitable working heat environment and a rest/living environment are conveniently established for load equipment and lunar astronauts by using less heat control resource investment; (3) The design scheme of the wide temperature area mechanism interlayer is convenient for realizing the stretching work of various mechanisms during the moon day/the folding and heat preservation during the moon night; the mechanism does not damage the thermal integrity of the heat insulation envelope of the inner layer/the outer layer when in and out, avoids heat from being poured in/out through the inlet and outlet hole, and is beneficial to maintaining the thermal stability of other equipment; (4) The scheme of the 'in-out isotope heat source' utilizes the heat of the isotope heat source to the greatest extent during the night of the month, the utilization rate (more than 90 percent) is higher than that of the prior project, and the heat utilization mode adopts the traditional heat radiation and heat conduction mode, so that the method is more reliable, simple and effective than the prior project. "in and out" also solves the isolation and dissipation of unnecessary heat generation of isotope heat sources during on-orbit flight hours and during lunar daytime hours at the same time; (5) The layout scheme of the overhead public OSR heat radiation surface not only enables the heat radiation surface to have the maximum heat radiation visual angle for the cold and black sky so as to improve the heat radiation capacity of the heat radiation surface, but also comprehensively shields the adverse effect of the high-intensity infrared radiation heat flow of the hot lunar surface on the heat radiation capacity of the public heat radiation surface by utilizing the shielding effect of the shape outline of the lunar surface detector below the heat radiation surface. The public heat radiation surface top-setting scheme, the detector layering heat insulation scheme from outside to inside and the detector shape profile shielding Gao Wenyue surface scheme provided by the invention solve the problem of extreme heat control caused by high-intensity walking/working on the hot lunar surface in noon in the equatorial region together with the traditional OSR surface treatment measures with low visible light absorptivity/high infrared emissivity; (6) The 'uniform inner layer' establishes heat capacity and heat sharing among all load devices, and also establishes heat transfer channels among the lunar day time period, the public OSR heat radiation surface, the lunar night time period and the isotope heat source, so that the lunar day heat dissipation/lunar night heat preservation function is realized. Compared with the prior art adopting two-phase gravity auxiliary loop/closed chamber circulating fan and other schemes, the temperature equalization inner layer is composed of a traditional heat radiation cavity and a heat pipe network, and has the characteristics of simple structure, low cost, effective operation and high reliability.

In the prior solid detection and long-term survival task of the lunar surface in the lunar equatorial region of the moon, the lunar surface detector can resist double clamping of near-vertical pouring solar visible light heat flow and lunar surface (-120 ℃) high-intensity infrared radiation heat flow in a passive/no-energy consumption mode in the noon period, realize good heat insulation, form a large-scale low-temperature radiation surface and meet the heat dissipation requirement brought by higher-intensity work/walking of the detector at noon; according to the scheme, the heat insulation requirements of the lunar night detector with a larger scale (meaning more heat leakage) can be met by using the heat source with the same quantity in extremely cold and long lunar night time, and the heat insulation performance is better than that of the previous projects, the lunar night utilization efficiency of the isotope heat source is higher; the structural design and the thermal control measures adopted by the scheme are more suitable for the requirements of the lunar project on higher requirements on the performance, the load working strength, the load density and the mechanism complexity of a thermal control system, the requirements on lunar surface replacement assisted by astronauts and the like generated in the process of shifting from a scientific detection stage to a large-scale application stage and shifting from unmanned lunar surface to manned lunar surface. Compared with the existing projects, the scheme not only improves extreme thermal environment adaptability, but also improves the supporting capability for detection and application.

In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the present invention.

Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include at least one such feature. In the description of the present invention, the meaning of "plurality" means at least two, for example, two, three, etc., unless specifically defined otherwise.

In the present invention, unless explicitly specified and limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly, through intermediaries, or both, may be in communication with each other or in interaction with each other, unless expressly defined otherwise. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.

In the present invention, unless expressly stated or limited otherwise, a first feature "up" or "down" a second feature may be the first and second features in direct contact, or the first and second features in indirect contact via an intervening medium. Moreover, a first feature being "above," "over" and "on" a second feature may be a first feature being directly above or obliquely above the second feature, or simply indicating that the first feature is level higher than the second feature. The first feature being "under", "below" and "beneath" the second feature may be the first feature being directly under or obliquely below the second feature, or simply indicating that the first feature is less level than the second feature.

In the description of the present specification, a description referring to terms "one embodiment," "some embodiments," "examples," "specific examples," or "some examples," etc., means that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the present invention. In this specification, schematic representations of the above terms are not necessarily directed to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples. Furthermore, the different embodiments or examples described in this specification and the features of the different embodiments or examples may be combined and combined by those skilled in the art without contradiction.

While embodiments of the present invention have been shown and described above, it will be understood that the above embodiments are illustrative and not to be construed as limiting the invention, and that variations, modifications, alternatives and variations may be made to the above embodiments by one of ordinary skill in the art within the scope of the invention.

Claims

1. The lunar surface detector is characterized by comprising a bearing shell, a heat source and load equipment, wherein a moving mechanism is arranged in the bearing shell, an inlet and an outlet are formed in the side wall of the bearing shell, and a driving end of the moving mechanism is connected with the heat source and drives the heat source to enter and exit the bearing shell from the inlet and the outlet;

2. The lunar surface detector according to claim 1, wherein a first heat insulation plate and a second heat insulation plate are respectively arranged on the inner side and the outer side of the heat source, and when the driving end of the movement mechanism drives the heat source to extend out of the bearing shell from the inlet and the outlet, the inlet and the outlet are blocked by the first heat insulation plate; when the driving end of the movement mechanism drives the heat source to retract from the inlet and the outlet to the inner side of the bearing shell, the second heat insulation plate seals the inlet and the outlet.

3. The lunar surface detector of claim 2 wherein the first and second heat shields are aerogel plates.

4. The lunar surface detector according to claim 2, wherein the first heat insulating plate and the second heat insulating plate are both in a flat plate-like structure and are both arranged perpendicular to the driving direction of the movement mechanism; the first heat insulation plate is positioned at the inner side of the inlet and the outlet of the bearing shell, and the second heat insulation plate is positioned at the outer side of the inlet and the outlet of the bearing shell.

5. The lunar surface detector according to claim 1, wherein a bracket is arranged on the outer side wall of the bearing shell, and one axial end of the bracket is fixed around the inlet and the outlet.

6. The lunar surface detector of claim 1 wherein the carrier shell comprises an outer insulating shell and an inner supporting shell, and the movement mechanism is disposed in an interlayer between the outer insulating shell and the inner supporting shell.

7. The lunar surface detector of claim 6 wherein the inner support shell comprises a honeycomb plate and a support frame, wherein the frame bars of the support frame are arranged at the edge positions of the honeycomb plate, and the honeycomb plate is provided with heat pipes;

8. The lunar surface detector of claim 1 further comprising a thermal control system disposed within the load bearing housing, the thermal control system being coupled to the heat source, the load bearing housing, and the load bearing device, respectively, and establishing a thermal path between the load bearing device and the heat source and the load bearing housing.

9. A lunar surface detector according to claim 1, wherein the load device is a plurality of load devices and is disposed on the outer surface of the carrier shell or/and in the sandwich of the carrier shell or/and in the inner cavity of the carrier shell, respectively.