Space probe with optimized thermal management and method for thermal management of such a probe

Abstract

The invention relates to a space probe (2) with optimized thermal management for operation in extreme environments as encountered on the moon, the space probe comprising a chassis (4) to receive probe components, four wheels (10) attached to the chassis and a mobile body (14) assembled on the chassis, the mobile body comprising a wheel shield (16) movable between an open position in which the wheels are exposed and a closed position in which the wheels are covered, and an access hatch (18) movable between an open position in which at least some components of the probe are exposed and a closed position in which at least some components of the probe are received inside the body. The body is movable relative to the chassis between a high rolling position in which the body is elevated relative to the wheels and a low receiving position in which the body is lowered relative to the wheels to increase the receptiveness of the probe components so as to limit heat losses.

Description

Background Technology

[0001] This invention relates to the general field of space probes designed to operate in extreme environments such as those encountered on the Moon. More specifically, this invention relates to a space probe with optimized thermal management.

[0002] Space probes (also known as planetary probes) are mobile exploration vehicles that can carry astronauts or move autonomously and are designed to travel on the surface of celestial bodies or planets (such as the Moon or Mars) beyond Earth in order to collect samples, analyze them, or take pictures of the surface of the celestial bodies.

[0003] Typically, a detector consists of a chassis mounted on wheels that supports various components, including an engine, navigation system, communication system, sampling and unloading tools, a location for receiving samples acquired by the tools, a battery for powering the engine and the device, and solar panels for recharging the battery.

[0004] The use of probes is particularly attractive for exploring regions that are difficult to access and / or subjected to extreme conditions. For example, as part of lunar exploration, the South Pole is of particular interest to scientists because of the water ice present in its permanently shadowed craters. However, in these polar regions, solar radiation is always at a low angle, and the undulating terrain creates areas that are permanently shadowed (especially at the bottom of craters) and where temperatures remain below 0°C. Therefore, probes exploring these polar regions must withstand temperatures ranging from -240°C. Extreme temperature variations up to +130℃.

[0005] Under such extreme conditions, it is especially important to ensure that detector components do not deteriorate, particularly when the temperature becomes very low. This can be achieved by incorporating a thermal energy storage device into the probe, allowing energy generated by the solar panels during the lunar day to be stored for heating components during the lunar night (when the solar panels are not in use). However, given the limited availability of solar energy at the poles (solar radiation is always at a low angle), the thermal energy storage device may be insufficient, and thermal management of the probe and its components becomes a practical problem. Summary of the Invention

[0006] Therefore, the main objective of this invention is to overcome these drawbacks by proposing a space probe architecture that enables it to withstand very large temperature variations that it may encounter, especially at the lunar poles.

[0007] According to the present invention, this objective is achieved by a space probe with optimized thermal management, designed for operation in extreme environments such as those encountered on the Moon, the space probe comprising:

[0008] - Chassis, which houses the detector's components, including the engine, battery, navigation system, communication system, sampling and unloading tools, location for receiving the load, and internal thermal energy storage device;

[0009] - At least four wheels, which are attached to the chassis; and

[0010] - The main body of the mobile unit, which is assembled on the chassis and includes:

[0011] o Wheel guards, these wheel guards can move between an open position and a closed position. In the open position, the wheel guards... The wheel well is exposed when the wheel well is in the closed position; in the closed position, the wheel well covers the wheel well.

[0012] The entry hatches are movable between an open position and a closed position. In the open position, at least some components of the probe are exposed; in the closed position, at least some components of the probe are retracted into the main body.

[0013] - The main body can move between a high rolling position and a low retracted position relative to the chassis. In the high rolling position, the main body is raised relative to the wheels to allow the detector to roll. In the low retracted position, the main body is lowered relative to the wheels to increase the retractability of the components or detector in order to limit heat loss.

[0014] In particular, the detector according to the invention is characterized by a movable chassis, and the detector can be controlled to be placed in a low-retractable position, in which all components of the detector are housed within the main body. This low-retractable position is particularly suitable for the static phase of the detector during lunar nights when temperatures are at their lowest. In fact, when the main body is in this low-retractable position, the detector's internal thermal energy storage device allows the detector components to be heated while limiting external [heat / temperature]. Heat loss. The detector's components are protected to withstand the extreme conditions during detector operation.

[0015] Preferably, the wheels are attached to the chassis via a suspension equipped with a wheel retraction mechanism.

[0016] The wheel well guards are also preferably provided with solar panels on their inner surface for recharging the battery and / or for use with detectors. Power supply for components.

[0017] More preferably, the main entrance hatch is equipped with solar panels on its outer surface for recharging the battery and / or for detection. The components of the device are powered.

[0018] The detector may also include solar panels that can deploy when the detector is in a static position to power the battery. Recharge.

[0019] Internal thermal energy storage devices can be thermal, mechanical, chemical, electrical, and / or gaseous, and include batteries, fuel cells, and other energy sources. The pool itself includes a heat transfer fluid buffer tank containing a phase change liquid, as well as heat pipes and / or heat transfer fluid circulation loops for energy transfer.

[0020] Another object of the present invention is a method for thermal management of a space probe as defined above, wherein:

[0021] - During the roll phase of the probe, the main body is moved to a high roll position, where the protective panels are in the open position and the hatch is in the... Close the location; and

[0022] - During the static rest phase of the probe, the main body is placed in a low-retraction position, with the protective panels and hatches closed to limit heat loss.

[0023] The method may also include moving the main body to a high roll position during the static operation phase of the detector, wherein the protective panels and hatches are moved to the open position to enable the sampling and unloading tools to be put into operation. Attached Figure Description

[0024] Referring to the accompanying drawings, other features and advantages of the invention will become apparent from the description given below, the drawings illustrating, in a manner that is by no means limited to, Limiting exemplary embodiments. In the accompanying drawings:

[0025] - Figure 1 This is a perspective view of a space probe in its rolling configuration provided by the present invention;

[0026] - Figure 2 It is a configuration in a static phase (e.g., during a moonlit night). Figure 1 A perspective view of the detector;

[0027] - Figure 3 It is in the manipulation configuration Figure 1 A perspective view of the detector. Detailed Implementation

[0028] This invention relates to a space probe (or planetary probe) designed to encounter, for example, planets on the Moon. Operating in extreme environments, particularly in the polar regions of the Moon.

[0029] like Figures 1 to 3As shown, the detector 2 includes a chassis 4 that houses multiple components, including, in particular: a motor, a battery, a navigation system, a communication system, and a sampling and unloading tool 6. Figure 3 Position 8 for receiving load () Figure 3 ),internal Thermal energy storage devices, etc.

[0030] These various components are well known to those skilled in the art and will not be described in detail here. In particular, the internal thermal energy storage device can be thermal, mechanical, chemical, electrical, or / and gaseous, and includes batteries, fuel cells, and other components that themselves comprise... A heat transfer fluid buffer tank for phase change liquids, and heat pipes and / or heat transfer fluid circulation loops for energy transfer.

[0031] Of course, the detector chassis 4 can carry other components required for the detector mission.

[0032] The detector 2 also includes at least four wheels 10, which are attached to the chassis 4 by means of a suspension 12. For example, the wheels 10 are deformable, non-pneumatic, load-bearing wheels as described in EP 4,331,867.

[0033] According to the invention, the detector 2 further includes a movable body 14, which is assembled on the chassis 4 and particularly includes wheel guards. Panel 16 and entry hatch 18.

[0034] More specifically, the wheel guard 16 is a door hinged to the main body 14 at the wheel arch, and the wheel guard 16 is movable between an open position and a closed position. In the open position, the wheel guard 16 exposes the wheel 10 (e.g., Figure 1 and Figure 3 As shown), in the closed position, the car Wheel guard plate 16 covers wheel 10 (e.g.) Figure 2 (As shown).

[0035] The access hatch 18 is also a door hinged to the main body 14 at its central portion. Therefore, these access hatches 18 are movable between an open position and a closed position, in which at least some components of the detector 2 are exposed (e.g., Figure 3 As shown), in the closed position, at least some components of detector 2 are housed within the main body 14 (e.g., Figure 1 and Figure 2 (As shown).

[0036] Still according to the invention, the main body 14 is also movable relative to the chassis 4 between a high rolling position and a low retracted position. In the high rolling position, the main body 14 is raised relative to the wheel 10 so that the detector 2 can roll (e.g., ...). Figure 1 and Figure 3 As shown), in the low-retracted position, the main body 14 is lowered relative to the wheel 10 to increase the retractability of the detector 2 components in order to limit heat loss (e.g., Figure 2 (As shown).

[0037] More specifically, when the main body 14 is in its low storage position ( Figure 2 When the detector is in contact with the ground, the clearance between the detector and the ground is approximately zero (body 14 contacts the ground S). By moving the wheel guard plate 16 and the access door 18 to their respective closed positions, the detector located inside body 14... The components of Device 2 are completely stored away.

[0038] Therefore, in this storage location of probe 2 (which is activated, for example, during the lunar night of a lunar mission), the thermal energy storage device is also... It can be activated to heat the sensitive detector components, thus enabling them to withstand the extreme conditions of a lunar night.

[0039] Conversely, when detector 2 needs to move (e.g.) Figure 1 As shown), the main body 14 moves to its high rolling position, and the wheel guard 16 is in the open position (the access door 18 is in the closed position to protect the components of the detector 2).

[0040] Furthermore, when detector 2 needs to operate without moving (e.g., for sampling - such as...) Figure 3 (As shown), the main body 14 remains in its high roll position, with the wheel guards 16 in the open position. The access hatch 18 moves to the closed position to approach the sampling area. And uninstallation tool 6.

[0041] To facilitate the movement of the detector 2 to its retracted position, the detector wheel 10 is attached to the chassis 4 via a suspension 12, which advantageously includes a wheel retraction mechanism (not shown). This mechanism can act on the suspension 12 to orient the wheel 10 toward the ground. Disc 4 is retracted so that wheel 10 no longer protrudes from detector body 14.

[0042] Also advantageously, the wheel guard 16 is provided with solar panels 20 on its inner surface, which are used to recharge the battery and / or power the components of the detector 2 (when the wheel guard 16 is in the open position, these solar panels 20 are exposed to the sun). radiation).

[0043] exist Figure 1 In the example shown, probe 2 is configured to explore the lunar polar regions where solar radiation is consistently at a low angle, and is set to... The wheel guard 16 with its solar panel 20 is positioned substantially vertically when in the open position in order to capture the most solar radiation.

[0044] Similarly, the entry hatch 18 in the main body 14 advantageously includes solar panels 20 on its outer surface to recharge the batteries and / or power the components of the detector 2 (these solar panels 20 are exposed to the sun when the entry hatch 18 is in the closed position). radiation; Figure 1 and Figure 2 ).

[0045] In another advantageous arrangement not shown in the figure, detector 2 may also include solar panels that can be deployed when detector 2 is in a static position to recharge the battery.

Claims

1. A space probe (2) with optimized thermal management, the space probe (2) being used to operate in extreme environments such as those encountered on the Moon, the space probe (2) comprising: The chassis (4) houses the components of the detector (2), including an engine, a battery, a navigation system, a communication system, a sampling and unloading tool (6), a location (8) for receiving a load, and an internal thermal energy storage device. At least four wheels (10) are attached to the chassis (4); and The active body (14) is assembled on the chassis (4) and includes: A wheel guard (16) is movable between an open position and a closed position, wherein in the open position the wheel guard (16) exposes the wheel (10), and in the closed position the wheel guard (16) covers the wheel (10). The entry hatch (18) is movable between an open position and a closed position, in which at least some components of the detector (2) are exposed, and in the closed position, at least some components of the detector (2) are housed inside the main body (14). The main body (14) is movable relative to the chassis (4) between a high rolling position and a low retractable position. In the high rolling position, the main body (14) is raised relative to the wheel (10) so that the detector (2) can roll. In the low retractable position, the main body (14) is lowered relative to the wheel (10) to increase the retractability of the component or the detector (2) in order to limit heat loss.

2. The detector according to claim 1, wherein the wheel (10) is attached to the chassis (4) via a suspension (12) provided with a wheel retraction mechanism.

3. The detector according to any one of claims 1 and 2, wherein the wheel guard (16) is provided with a solar panel (20) on its inner surface, the solar panel (20) being used to recharge the battery and / or power components of the detector (2).

4. The detector according to any one of claims 1 to 3, wherein the entrance hatch (18) of the main body is provided with a solar panel (20) on its outer surface, the solar panel (20) being used to recharge the battery and / or power the components of the detector (2).

5. The detector according to any one of claims 1 to 4, wherein the detector (2) further comprises a solar panel capable of unfolding when the detector (2) is in a static position to recharge the battery.

6. The detector according to any one of claims 1 to 5, wherein the internal thermal energy storage device may be thermal, mechanical, chemical, electrical, or / and gaseous, and includes a battery, a fuel cell, a heat transfer fluid buffer tank comprising a phase change liquid, and a heat pipe and / or heat transfer fluid circulation loop for transferring energy.

7. A method for thermal management of a space probe according to any one of claims 1 to 6, wherein: During the rolling phase of the detector, the main body is moved to the high rolling position, wherein the guard plate is in the open position and the hatch is in the closed position; and During the static rest phase of the detector, the main body is placed in a low-retracted position, wherein the protective plate and the hatch are closed to limit heat loss.

8. The method of claim 7, further comprising, during the static operation phase of the detector, moving the body to the high roll position, wherein the guard plate and the hatch are moved to the open position to enable the sampling and unloading tool to be put into operation.

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