Multi-dimensional and multi-mode autonomous thermal control device and method for deep space probe under complex thermal environment

Abstract

The application relates to the field of spacecraft thermal control technology and provides a multi-dimensional and multi-mode autonomous thermal control device and method of a deep space probe under a complex thermal environment, which autonomously shields one to multiple surfaces of the whole satellite according to heat dissipation requirements of the probe, and then maintains thermal balance of the whole satellite under different states. The application adopts brand-new thinking, brand-new means and bold imagination to carry out spacecraft thermal control design, expands the function of a solar sail of the spacecraft, has the characteristic of light shielding, reduces sunlight irradiation on a heat dissipation surface to achieve the effect of enhancing heat dissipation, is like a sun umbrella maintaining the shade of a sheltered object, and solves the heat dissipation problem under a complex thermal control environment, such as long-distance flight under a complex deep space orbit.

Description

Technical Field

[0001] This invention relates to the field of spacecraft thermal control technology, specifically to a multi-dimensional, multi-mode autonomous thermal control device and method for deep space probes operating under complex thermal environments. Background Technology

[0002] The current traditional thermal control design concept at home and abroad is: based on the orbital characteristics of the probe, select a surface with stable external heat flow as the heat dissipation surface to dissipate the heat inside the satellite; in the case of complex thermal control environment, the thermal control technology usually adopts spacecraft vector control to keep the spacecraft's fixed heat dissipation surface from being exposed to light. When it is difficult for the spacecraft to maintain a fixed heat dissipation surface, deployable thermal radiators can be installed for heat dissipation.

[0003] However, current vector control thermal control schemes rely too heavily on attitude control systems, affecting the normal operation of other systems; deployable radiators increase the weight and complexity of the spacecraft platform. When deep space probes are very close to the sun, such as near Venus, solar radiation is very strong, and traditional thermal designs require significantly increased heat dissipation and protection, further increasing the weight and complexity of the spacecraft.

[0004] Existing technologies also offer numerous designs. For example, patent document CN104816839A discloses a modular thermal control device for a satellite platform. This patent divides the satellite thermal control subsystem into multiple modules, including a low-temperature index thermal control module, a high-temperature index thermal control module, and a payload thermal control module, improving the thermal control adaptability of the satellite platform. However, this design cannot meet the thermal control requirements of deep space probes in complex thermal environments. Another example is patent document CN108146660A, which discloses a spacecraft thermal control management system. This patent designs the spacecraft thermal control management system as multiple control units, configuring these units in various regions of the spacecraft according to their thermal control requirements. The onboard data management computer controls these multiple control units, providing a global perspective on the spacecraft's thermal control design and uniformly configuring thermal control resources, thus improving thermal control efficiency. However, this design also cannot meet the thermal control requirements of deep space exploration missions in complex thermal environments.

[0005] For example, the article "A Review of the Progress in the Construction of New Thermal Control Systems for Chinese Spacecraft" (Acta Aeronautica Sinica, July 2019) comprehensively reviews the latest research results and progress in the construction of new thermal control systems for Chinese spacecraft. Specifically, it includes: new thermal control systems built to meet the needs of different missions such as manned spaceflight and lunar exploration, as well as a number of new thermal control products represented by pump-driven single-phase fluid loops, gravity-driven two-phase fluid loops, loop heat pipes, and water sublimators. Another example is the patent document CN108387123A, which discloses a satellite thermal management system and its method, as well as a method for installing it into an integrated satellite. This patent designs a thermal control system in which a liquid is used as a medium, absorbs heat at high temperatures and turns into steam, the steam circulates to the heat dissipation point and releases heat and turns back into liquid, and the liquid circulates back to the high temperature point to continue absorbing heat. All of the above adopt heat dissipation technology with fluid as the carrier.

[0006] The paper "Deep Space Exploration's Impact on Spacecraft Thermal Control Technology" (Vol. 33, No. 2, Spacecraft Environmental Engineering) also introduces new developments in thermal control and heat protection technologies, mentioning that the Chang'e-3 rover used solar panels for shading to address the extreme high temperatures on the lunar surface. However, this technology differs from the application of this invention in several ways. The Chang'e-3 rover used solar panels for shading while operating on the lunar surface, while the probe used in this invention operates during spaceflight. Secondly, the solar panel adjustment angles differ; this invention can drive the solar panels to block sunlight from any surface of the probe, while the Chang'e-3 rover only needs to block sunlight from above. Finally, the heat dissipation logic differs; due to this invention, any surface of the probe can be used as a heat dissipation surface in the thermal control design, while the Chang'e-3 rover's thermal control subsystem lacks this design. Summary of the Invention

[0007] To address the shortcomings of existing technologies, the purpose of this invention is to provide a multi-dimensional, multi-mode autonomous thermal control device and method for deep space probes operating in complex thermal environments.

[0008] According to the present invention, a multi-dimensional and multi-mode autonomous thermal control method for deep space probes under complex thermal environments is provided. The method autonomously blocks one or more surfaces of the entire satellite according to the heat dissipation requirements of the probe, thereby maintaining the thermal balance of the entire satellite under different states.

[0009] Preferably, the method includes the following steps:

[0010] S1: The autonomous controller collects the temperature parameters of the probe's interior and heat dissipation surface, calculates the direction of the sun on the probe's orbit and the current position of the solar panel, and calculates the positional relationship between the solar panel and the heat dissipation surface.

[0011] S2: Calculate the required control quantities for the rotating and oscillating mechanisms through analysis and calculation;

[0012] S3: The autonomous controller outputs control signals to drive the solar panel to perform solar orientation tracking and capture in a specified mode, so that the substrate surface of the solar panel and the sunlight are kept within a set range of illumination angle, and the heat dissipation surface of the detector is not exposed to sunlight.

[0013] Preferably, when the illumination angle varies complexly from 0° to 180° in a high-inclination orbit, multi-dimensional solar panels are used to block sunlight and maintain the heat dissipation surface of the entire satellite for thermal control of the detector, so that the detector is kept in a temperature state within a set range.

[0014] Preferably, a solar panel is used for shading, and the solar panel adopts a 1+1 dimensional drive design or a 1+2 dimensional drive control to achieve shading of the entire satellite.

[0015] Preferably, a solar panel is used for shading, and the back of the solar panel is covered with multiple layers of heat insulation.

[0016] Preferably, depending on the illumination angle and the detector's heat dissipation requirements, the detector can use a single-wing or double-wing solar panel to shield the detector's heat dissipation surface.

[0017] A multi-dimensional, multi-mode autonomous thermal control device for deep space probes operating under complex thermal environments, according to the present invention, includes a solar panel and further comprises:

[0018] Multiple layers of thermal insulation are arranged on the back of the solar panel;

[0019] The rotating mechanism is located on the heat dissipation surface of the detector;

[0020] The connecting frame is connected to the solar panel at one end via a swing mechanism, and to the rotating mechanism at the other end.

[0021] An autonomous controller that controls the movements of the rotating and oscillating mechanisms.

[0022] Preferably, the solar panel is a biplane solar panel or a singleplane solar panel.

[0023] Preferably, based on the detector's orbit and the size of its heat dissipation surface, the detector autonomously controls the solar panels to shade the detector's heat dissipation surface through a mapping relationship. The shading mapping relationship between the detector's solar panels and the heat dissipation surface is derived from a surface mapping relationship, then a line mapping relationship, and finally a point mapping relationship, resulting in the following expression:

[0024]

[0025] Where: Δ=(x+Msinθcosγ) 2 +(y+Msinθcosa) 2O is the intersection of the center point of the solar panel substrate and the connecting frame, OP is the distance from any point on the solar panel substrate to point O, (x, y) are the coordinates of any point on the heat dissipation surface with the rotation mechanism as the origin, θ is the angle between the incident direction of sunlight and the heat dissipation surface, M is the length of the connecting frame, α is the angle between the light ray and the X-axis of the detector body, and γ is the angle between the light ray and the Z-axis of the detector body.

[0026] Preferably, the value of θ ranges from 0° to 180°.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] 1. This invention adopts a novel approach and bold concept to design thermal control for spacecraft, expanding the function of the spacecraft's solar panels to include shading properties. This reduces sunlight exposure to the heat dissipation surface, thereby enhancing heat dissipation, much like a parasol keeping the shaded object cool. This solves the heat dissipation problem in complex thermal control environments such as deep space orbits and long-distance flights (e.g., the Jupiter probe's journey from Earth to Venus and then to Jupiter).

[0029] 2. This invention solves the key challenges of thermal control for deep space exploration and high-inclination spacecraft without increasing or only slightly increasing additional weight and power consumption. The platform has good heat dissipation and improves the performance of the spacecraft.

[0030] 3. The solar panels in this invention can adopt a 1+1 dimensional drive design or a 1+2 dimensional drive control to achieve shielding of the entire satellite. The heat dissipation requirements of the spacecraft can be met by shielding one or more surfaces of the entire satellite to maintain the thermal balance of the entire satellite under different conditions.

[0031] 4. When the illumination angle changes complexly from 0° to 180° in a high-inclination orbit, this invention uses multi-dimensional solar panels to block sunlight and maintain the heat dissipation surface of the entire satellite for spacecraft thermal control, so that the spacecraft is in an ideal temperature state, reducing thermal deformation of the structure and improving the accuracy of the spacecraft's reference plane.

[0032] 5. In this invention, the back of the solar panel is covered with a multi-layer heat insulation medium for thermal control. When the solar panel is 1.5m away from the heat dissipation surface, it is shielded, which can effectively improve the heat dissipation capacity.

[0033] 6. Based on the spacecraft's orbit and the size of its heat dissipation surface, this invention allows the spacecraft to autonomously control the solar panels through a mapping relationship to shield the spacecraft's heat dissipation surface, reducing the amount of light irradiating the optical payload and improving the heat dissipation effect.

[0034] 7. Based on the illumination angle and the heat dissipation requirements of spacecraft, the present invention allows spacecraft to use single-wing or double-wing solar panels to shield the heat dissipation surface of the spacecraft, which has good versatility. Attached Figure Description

[0035] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0036] Figure 1 This invention provides a configuration diagram of a single-wing solar panel for a spacecraft.

[0037] Figure 2 This invention provides a configuration diagram of a spacecraft's biplane solar panel.

[0038] Figure 3 This is a schematic diagram of a 1+1 dimensional solar panel for a spacecraft provided by the present invention;

[0039] Figure 4 This is a schematic diagram of a 1+2 dimensional solar panel for a spacecraft provided by the present invention;

[0040] Figure 5 This invention provides a block diagram illustrating the principle of multidimensional autonomous multimode thermal control.

[0041] Figure 6 This is a diagram showing the mapping relationship between the solar panel and the heat dissipation surface provided by the present invention.

[0042] The diagram shows:

[0043] Solar Panel 1

[0044] Multi-layer thermal insulation 2

[0045] Rotating mechanism 3

[0046] Connector 4

[0047] Swinging mechanism 5

[0048] Heat dissipation surface 6

[0049] Sun Angle Gauge 7 Detailed Implementation

[0050] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0051] With the continuous development of my country's aerospace industry, the orbits and thermal environments of deep space probes are becoming increasingly complex, and correspondingly, the control systems and operating modes of spacecraft are also becoming more and more complex. In order to reduce the impact of the complexity of the thermal environment on spacecraft, this invention provides a multi-dimensional and multi-mode autonomous thermal control method for deep space probes under complex thermal environments. Based on the heat dissipation requirements of the probe, one or more surfaces of the entire satellite are autonomously shielded to maintain the thermal balance of the entire satellite under different states.

[0052] Specifically, the multi-dimensional, multi-mode autonomous thermal control method for deep space probes operating under complex thermal environments employs a closed-loop autonomous control scheme involving multi-information fusion, such as... Figure 5 As shown, it includes the following steps:

[0053] S1: The autonomous controller collects temperature parameters of the detector's interior and heat dissipation surface through temperature sensors, calculates the direction of the sun on the detector's orbit and the current position of the solar panel 1 through the solar angle meter 7, and calculates the positional relationship between the solar panel 1 and the heat dissipation surface 6.

[0054] S2: Calculate the required control quantities for the rotating mechanism 3 and the swinging mechanism 5 through analysis and calculation;

[0055] S3: The autonomous controller outputs control signals to drive the solar panel 1 to perform solar orientation tracking and capture in a specified mode, so that the substrate surface of the solar panel 1 and the sunlight maintain an illumination angle within a set range, and ensure that the heat dissipation surface 6 of the detector is not exposed to sunlight, thus having a highly efficient heat dissipation function.

[0056] Solar Panel 1 can adopt a 1+1 dimensional drive design to achieve full-plane shading, such as... Figure 3 As shown, the connecting frame 4 is connected to the base plate by a 1D swing mechanism 5, and the connecting frame 4 is connected to the spacecraft body by a 1D rotation mechanism 3. 1+2D drive control can also be used, such as... Figure 4 The 2D rotation mechanism consists of a 1D rotation mechanism and a 1D swing mechanism. The connecting frame 4 is connected to the base plate using a 1D swing mechanism 5, and the connecting frame 4 is connected to the spacecraft body using a 2D rotation mechanism 3. For example... Figure 4 As shown. The rotating mechanism 3 mainly realizes the regional shielding of the spacecraft by the solar panel 1, which is called the regional structure. It determines the working range of the solar panel substrate. The swing mechanism 5 reflects the directional requirements of the solar panel 1, which is called the directional structure. It determines the flexibility of the solar panel substrate.

[0057] In this invention, solar cells are attached to the front of the solar panel substrate to convert light energy into electrical energy, generating a certain amount of heat energy which is radiated from both the positive and negative sides of the panel. This affects the working efficiency of the heat dissipation surface 6. Therefore, a heat insulation layer 2 is covered or pasted on the back of the solar panel 1 to block heat radiation to the back of the solar array, thereby improving the radiation efficiency of the heat dissipation surface. When the distance between the solar panel 1 and the heat dissipation surface 11 is less than or equal to 1.5m, the heat insulation layer 2 is used to block the heat on the back of the solar panel 1, achieving a heat dissipation capacity better than 150W / m. 2 The effect is that the operating temperature of the solar panel substrate can reach 150 degrees Celsius, and the power conversion efficiency decreases by 5%.

[0058] Depending on the illumination angle and the heat dissipation requirements of the detector, the detector can use a single-wing or double-wing solar panel 1 to shield the heat dissipation surface 6 of the detector.

[0059] This invention also provides a multi-dimensional, multi-mode autonomous thermal control device for deep space probes operating in complex thermal environments, including a solar panel 1, a thermal insulation multilayer 2, a rotating mechanism 3, a connecting frame 4, a solar angle meter 7, and an autonomous controller. The solar angle meter 7 is mounted on the solar panel 1, and the thermal insulation multilayer 2 is arranged on the back of the solar panel 1. The thermal insulation multilayer 2 is used to isolate the heat received by the solar panel 1 and prevent the heat from being transferred to the heat dissipation surface 6 through the solar panel 1. The thermal insulation multilayer 2 can be made of materials that can block heat radiation to the back of the solar panel 1 in the prior art, which will not be described in detail here.

[0060] The rotating mechanism 3 is arranged on the heat dissipation surface 6 of the detector; one end of the connecting frame 4 is connected to the solar panel 1 through the swing mechanism 5, and the other end of the connecting frame 4 is driven to the rotating mechanism 3; the autonomous controller can control the movement of the rotating mechanism 3 and the swing mechanism 5.

[0061] Specifically, the solar panel 1 can be a biplane solar panel or a single-plane solar panel. The spacecraft uses a large single-plane solar panel 1, located on one side, acting like an umbrella to block all sunlight, allowing the spacecraft to operate in the shade. The spacecraft body and the solar panel substrate are connected by a connecting frame 4, and a drive mechanism achieves decoupled drive control, making any attitude maneuver of the spacecraft independent of the solar panel (independent of sunlight). All surfaces of the spacecraft can be used as heat dissipation surfaces 6, allowing the spacecraft to dissipate the maximum amount of heat, such as... Figure 1 As shown. The spacecraft can also employ biplane solar panels 1, mounted on the left and right sides of the spacecraft body respectively. Located on both sides of the spacecraft, these panels shield the heat dissipation surfaces 6 on both sides of the spacecraft from sunlight, maintaining a fixed heat dissipation surface 6. In this case, the spacecraft can dissipate a certain amount of heat, such as... Figure 2 As shown.

[0062] like Figure 1As shown, during the design process, the size and configuration of the single-wing solar panel 1 are related to the size of the heat dissipation surface 6, the direction of light change, and the distance between the solar panel 1 and the spacecraft. Figure 1 The swing mechanism 5 shown is used to control the swing direction of the solar panel substrate. In order to prevent the swing mechanism 5 from getting too hot, the swing mechanism 5 is installed below the solar panel substrate, at a distance of more than 10cm from the solar panel substrate. Figure 1 The rotating mechanism 3 shown can be a 1D rotating mechanism or a 2D rotating mechanism. Different driving mechanisms are selected depending on the range of the area that the solar panel substrate needs to operate in.

[0063] Based on the probe's orbit and the size of its heat dissipation surface, the probe autonomously controls the solar panel 1 to shade the probe's heat dissipation surface 6 through a mapping relationship. The mapping relationship between the solar panel 1 and the heat dissipation surface 6 is derived from a surface mapping relationship, leading to a line mapping relationship and then a point mapping relationship, ultimately resulting in the following equation:

[0064]

[0065] Where: Δ=(x+Msinθcosγ) 2 +(y+Msinθcosa) 2 O is the intersection of the center point of the solar panel substrate and the connecting frame 4, OP is the distance from any point on the solar panel substrate to point O, (x, y) are the coordinates of any point on the heat dissipation surface 6 with the rotation mechanism 3 as the origin, θ is the angle between the incident direction of sunlight and the heat dissipation surface 6, M is the length of the connecting frame 4, α is the angle between the light ray and the X-axis of the detector body, and γ is the angle between the light ray and the Z-axis of the detector body.

[0066] Furthermore, for spacecraft orbits with large inclinations, the illumination angle varies greatly, ranging from 0° to 180°. Combined with the effects of Earth's infrared radiation and albedo, the external heat flux on the spacecraft surface ranges from 200 to 1800 W / m². 2 The complex thermal environment of a spacecraft, characterized by variations in illumination angles (θ) from 0° to 180° in high-inclination orbits, can cause significant thermal deformation of the spacecraft's structure, hindering the operation of the platform and payloads. By employing multi-dimensional solar panels (1) to shield the spacecraft from sunlight and maintain a fixed heat dissipation surface (6) for the entire satellite, the spacecraft can be kept at an ideal temperature within a set range. This reduces structural thermal deformation and improves the accuracy of the spacecraft's reference plane.

[0067] The spacecraft uses solar panels 1 to block sunlight, reducing the amount of light hitting the optical payload, thus acting as a payload light shield.

[0068] The working process of the spacecraft multi-dimensional autonomous multi-mode thermal control provided by this invention is as follows:

[0069] First, the spacecraft collects the location and temperature of the star's heat dissipation surface 6;

[0070] Secondly, the spacecraft collects data on the celestial bodies' orbits and attitudes, as well as the sun's direction;

[0071] Next, the spacecraft collects the orientation of solar panel 1 and determines the status of the mechanism;

[0072] Fourth, the spacecraft calculates the azimuth and actuator control step size of the solar panel 1 that need to be driven.

[0073] Fifth, the spacecraft first controls the rotation mechanism 3 to position the solar panel 1 in the direction of the sun;

[0074] Sixth, the spacecraft re-controls the swing mechanism 5 to swing the solar panel 1 in the direction of blocking the heat dissipation surface 6;

[0075] Finally, the spacecraft repeats the first to sixth steps of the working process to complete autonomous closed-loop control, so that the solar panel 1 can maintain the temperature balance of the heat dissipation surface 6.

[0076] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0077] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A multi-dimensional, multi-mode autonomous thermal control method for deep space probes under complex thermal environments, characterized in that, Based on the heat dissipation requirements of the detector, one or more surfaces of the entire satellite are autonomously shielded to maintain the thermal balance of the entire satellite under different conditions. When the illumination angle changes complexly from 0° to 180° under a large inclination orbit, a multi-dimensional solar panel (1) is used to block sunlight and maintain the heat dissipation surface (6) of the whole satellite for thermal control of the detector, so that the detector is in a temperature state within a set range. The solar panel (1) adopts a 1+1 dimension drive design or a 1+2 dimension drive control to achieve the blocking of the whole satellite. Based on the spacecraft's orbit and the size of its heat dissipation surface, the spacecraft autonomously controls the solar panels (1) through a mapping relationship to shield the spacecraft's heat dissipation surface.

2. The multi-dimensional, multi-mode autonomous thermal control method for deep space probes under complex thermal environments according to claim 1, characterized in that, Includes the following steps: S1: The autonomous controller collects the temperature parameters inside the detector and the heat dissipation surface, calculates the direction of the sun on the detector in orbit and the current position of the solar panel (1), and calculates the positional relationship between the solar panel (1) and the heat dissipation surface (6); S2: Calculate the required control quantities for the rotating mechanism (3) and the swing mechanism (5) through analysis and calculation; S3: The autonomous controller outputs control quantity to drive the solar panel (1) to perform solar orientation tracking and capture in accordance with the specified mode, so that the substrate surface of the solar panel (1) and the sunlight maintain the illumination angle within the set range, and ensure that the heat dissipation surface (6) of the detector is not exposed to sunlight.

3. The multi-dimensional, multi-mode autonomous thermal control method for deep space probes under complex thermal environments according to claim 1, characterized in that, A solar panel (1) is used for shading, and the back of the solar panel (1) is covered with a heat-insulating multilayer (2).

4. The multi-dimensional, multi-mode autonomous thermal control method for deep space probes under complex thermal environments according to claim 1, characterized in that, Depending on the illumination angle and the heat dissipation requirements of the detector, the detector can use a single-wing or double-wing solar panel (1) to shield the heat dissipation surface (6) of the detector.

5. A multi-dimensional, multi-mode autonomous thermal control device for deep space probes operating under complex thermal environments, comprising a solar panel (1), characterized in that, The multi-dimensional, multi-mode autonomous thermal control method for deep space probes under complex thermal environments, as described in any one of claims 1 to 4, further includes: A heat-insulating multilayer (2) is arranged on the back of the solar panel (1); The rotating mechanism (3) is arranged on the heat dissipation surface (6) of the detector; The connecting frame (4) is connected to the solar panel (1) at one end via a swing mechanism (5), and driven to the rotating mechanism (3) at the other end. An autonomous controller controls the actions of the rotating mechanism (3) and the swinging mechanism (5).

6. The multi-dimensional, multi-mode autonomous thermal control device for deep space probes under complex thermal environments according to claim 5, characterized in that, The solar panel (1) is a biplane solar panel or a singleplane solar panel.

7. The multi-dimensional, multi-mode autonomous thermal control device for deep space probes under complex thermal environments according to claim 5, characterized in that, Based on the probe's orbit and the size of its heat dissipation surface, the probe autonomously controls the solar panel (1) to shade the probe's heat dissipation surface (6) through a mapping relationship. The shading mapping relationship between the probe's solar panel (1) and the heat dissipation surface (6) is derived from the surface mapping relationship to the line mapping relationship and then to the point mapping relationship, ultimately resulting in the following formula: in: O is the intersection of the center point of the solar panel substrate and the connecting frame (4), OP is the distance from any point on the solar panel substrate to point O, and (x, y) are the coordinates of any point on the heat dissipation surface (6) with the rotation mechanism (3) as the origin. Let M be the angle between the incident direction of sunlight and the heat dissipation surface (6), and M be the length of the connecting frame (4). Let be the angle between the ray and the X-axis of the detector body. The angle between the ray and the Z-axis of the detector body is denoted as .

8. The multi-dimensional, multi-mode autonomous thermal control device for deep space probes under complex thermal environments according to claim 7, characterized in that, The value range is 0° to 180°.

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