Device and method for thermal control and space object

Abstract

Device (100) for thermal control of a space object (10), characterized by a thermal shielding element (110) which is designed to shield the space object (10) at least in sections from thermal radiation, and an actuator (120) which is coupled to the shielding element (110) and is designed to control the shielding element (110) as a result of the action of thermal radiation on the actuator, characterized in that the actuator (120) has a curved shape, in particular a spiral shape.

Description

[0001] The invention relates to a device for thermal control of a spacecraft. Furthermore, the invention relates to a spacecraft having such a device. Furthermore, the invention relates to a method for thermal control of a spacecraft.

[0002] Document DE 10 2021 102 331 A1 discloses a method for thermal control of a discrete thermal sector of a spacecraft. It proposes controlling the discrete thermal sector, which has thermal insulation and a heat leak, using an actuator. Heat can flow into and / or out of the thermal sector through the heat leak. The thermal control method described in the document therefore requires a heat leak that can be controlled by the actuator.

[0003] From the document RU 2 465 181 C2 a microstructural thermal management system for a spacecraft is known, comprising: a substrate fixed to the surface of the spacecraft or to a component attached to the spacecraft, shields moving under the action of the heat flow and regularly arranged above the substrate, made in the form of a matrix with elastically articulated cantilevers consisting of parallel trapezoidal inserts of monocrystalline silicon with the orientation and connected by polyimide interlayers consisting of a polyimide film, wherein the shields are made in the form of a matrix with elastically articulated cantilevers attached to the fastening elements of the substrate or to a fixed frame rigidly attached to the fastening elements of the substrate.

[0004] Document RU 2 725 947 C1 discloses a microsystem for thermal regulation of small spacecraft. It includes a silicon plate consisting of a fixed frame bonded to the surface of the spacecraft with an adhesive having a low thermal conductivity coefficient, as well as movable elements in the form of louvres with a metal coating with a high reflection coefficient applied to their outer surface, hinges connecting the louvres to the fixed frame and made of polyimide film with the same metal coating, bimorph actuators attached to the fixed frame by means of bases, and a flexible polyimide tape reinforced with silicon carriers, connecting the actuator legs to the louvres, and areas formed on the legs and bases of the bimorph actuators with high solar radiation absorption and low emissivity.wherein the movable elements are grounded to the body of the spacecraft through metallized connections and conductive holes formed in the fixed frame, wherein said movable elements, shaped as louvre flaps, are grounded to the body of the spacecraft, under which the surface of the spacecraft is photographed on the surface of the spacecraft.,

[0005] From the document CN 114644139 A1 a satellite assembly is known which comprises: a satellite arranged in a launch vehicle, a shield comprising a frame carrying a flexible insulating mat surrounding the satellite, and a method for manufacturing the satellite assembly.

[0006] The invention is based on the object of structurally and / or functionally improving a thermal control device mentioned above. Furthermore, the invention is based on the object of structurally and / or functionally improving a spacecraft with the aforementioned thermal control device and a thermal control method mentioned above.

[0007] The object is achieved by a device for thermal control of a component of a space object having the features of claim 1. Furthermore, the object is achieved by a space object having the features of claim 7. Furthermore, the object is achieved by a method for thermal control of a component of a space object having the features of claim 9. Advantageous embodiments and / or further developments are the subject of the subclaims / dependent claims.

[0008] The device and / or method can be used to control a temperature of a space object or at least a part thereof. The device and / or method can be used to maintain a temperature of the space object or the part thereof in a temperature range of approximately 200 to approximately 470 K, in particular of approximately 233 to approximately 323 K. The temperature range of approximately 200 to approximately 470 K can also be referred to as a conventional range in contrast to a cryogenic range and a high-temperature range. The temperature range of approximately 233 to approximately 323 K can be a temperature range for which one or more components of the space object, for example an electronic component or the like, were developed and qualified. In the present case, "controlling" refers in particular to control-related and / or feedback control.

[0009] The device or the spacecraft equipped therewith can be used in space. In particular, they can be used in or exposed to an external radiation field. In this context, "external radiation field" refers in particular to an area outside the spacecraft. The external radiation field can be outer space or the atmosphere of a celestial body. A high vacuum with low particle density can prevail in the external radiation field. The external radiation field can contain gases, cosmic dust, and elementary particles. The external radiation field can contain electric and magnetic fields, gravitational fields, and electromagnetic waves.In order to protect a system such as the space object in space and / or external radiation field from temperature influences, such as the effects of heat due to radiation or cooling, the space object can be provided at least in sections with a thermally effective paint which can absorb thermal energy less effectively or release it more effectively. The device can also use heating elements which continuously protect the space object or desired parts thereof from temperatures that are too low. If the space object is exposed to direct sunlight, the side of the space object facing the sun, e.g. at least one surface of the space object, can be exposed to high heat due to radiation, while a side of the space object facing away from the sun can be exposed to cold typical of space, e.g. due to shadows cast by the space object itself. Due to the movement of the space object in space orRelative to the sun, the direction of solar radiation and / or the orientation of the space object relative to, for example, the sun can change continuously, so that the sides, surfaces, etc. of the space object facing the sun can also change continuously. "Thermal radiation" can be understood as radiation that can cause the space object to heat up. "Thermal radiation" can, in particular, be electromagnetic radiation, such as that emitted by the sun.

[0010] The thermal shielding element can serve to thermally shield at least part of the space object, or at least a portion thereof. The shielding element can accordingly be understood to mean any element which, due to its structure and / or properties, such as material properties or the like, is designed to at least partially absorb and / or reflect radiation, in particular electromagnetic radiation, from, for example, the sun. The shielding element can be adjustable between a first size and a different, second size. The shielding element can have a mechanism, e.g., a folding mechanism, for variably changing its size. The shielding element can be designed to be actuated by means of the actuator as a function of the thermal radiation, e.g., as a function of the radiation intensity, the direction of incidence of the radiation, etc.The shielding element can be made, for example, from a textile, a plastic material, or the like, with radiation-absorbing and / or radiation-reflecting properties. The shielding element can have a reflective, in particular mirror-like, surface. The surface can, for example, be formed from or comprise a multilayer insulation foil. The device can have a plurality of shielding elements, each of which can be configured to shield an associated portion of the spacecraft.

[0011] The actuator can be used to actuate the thermal shielding element. In particular, the actuator can be used to selectively activate and deactivate the shielding element, wherein the activated shielding element is configured to shield the space object from radiation and the deactivated shielding element is at least largely radiation-permeable. The actuator can be designed as a passive device and / or a passive, possibly also as a purely mechanical, mechanism, wherein "passive" refers to the fact that the actuator does not require any electrical energy and / or electrical signal for its operation, actuation, control, or the like, and / or does not need to be actively controlled. The actuator can be coupled to the thermal shielding element. The actuator can have structural and / or functional properties that can be changed depending on radiation or irradiation and / or temperature.The actuator can be configured to actuate the thermal shielding element, in particular as a function of thermal radiation or irradiation onto the actuator.

[0012] The actuator can be configured to deform as a result of the action of thermal radiation. The thermal radiation can cause the actuator to heat up or, in the absence of thermal radiation, to cool down, which can cause a deformation of the actuator. The actuator can be configured to deform as a result of the action of thermal radiation between a first shape, in which the shielding element has a first surface, and a second shape, in which the shielding element has a second surface that is larger than the first surface. The actuator can have a first shape if the thermal radiation acting on the actuator is comparatively low or (virtually) zero, and a second shape if the thermal radiation acting on the actuator is comparatively high, higher, or high enough to cause a deformation of the actuator.

[0013] The actuator can be configured to selectively reduce or enlarge the area of ​​the shielding element depending on the effect of thermal radiation on the actuator. The actuator can be configured to have either a curved or a straightened shape depending on the effect of thermal radiation on the actuator. With the straightened shape, the actuator can expand the shielding element over a large area. The actuator can have a spiral shape or the like.

[0014] The actuator can, for example, comprise or be formed from a bimetal element. The bimetal element can be, for example, a metal strip with two adjacent layers of different metals with different thermal expansion coefficients, joined together, for example, by a material fit, a form fit, and / or a force fit. The actuator has a curved shape, e.g., a spiral shape.

[0015] The actuator and the shielding element can each be coupled to one another by one of their flat sides. The actuator can be arranged on a side of the shielding element facing away from the spacecraft or facing a potential radiation source, e.g., the sun.

[0016] The space object can be, for example, a satellite or a part thereof, a space robot or a part thereof, a spacecraft or a part thereof, a space station or a part thereof, etc. The device can be arranged, attached, etc., on an exterior of the space object. The space object can have several of the devices arranged around an exterior of the space object. The shielding elements of the several devices can also overlap when activated, e.g., when enlarged in area.

[0017] The method for thermal control of a space object can be carried out, for example, using the device described above. The method comprises arranging a thermal shielding element on an exterior of the space object such that the space object can be shielded from thermal radiation, at least in sections, by the shielding element. Furthermore, the method comprises coupling an actuator to the thermal shielding element such that the actuator controls the shielding element as a result of the action of thermal radiation on the actuator. The actuator has a curved shape, in particular a spiral shape.

[0018] In summary, and in other words, the invention thus results in, among other things, a device for thermal control of a space object. The shielding element is actuated by the actuator, i.e., by means of a passive mechanism. Due to its simple, passive design, this actuator is hardly or not at all susceptible to failure, thus achieving a long service life. Furthermore, the actuator allows for effective regulation of the radiation exposure or heat exposure and thus the temperature of the space object. In particular, the space object can be protected from heat exposure by the device. The actuator makes it possible to control the shielding element as needed, namely depending on the radiation and / or temperature.

[0019] The invention provides a space-qualified possibility for actively changing and adapting a component to thermal conditions in space and / or on celestial bodies.

[0020] In the following, embodiments of the invention are described in more detail with reference to figures, which show schematically and by way of example: Fig. 1 shows a side view of a space object with a thermal control device exposed to the radiation of a celestial body, Fig. 2 shows a front view of a space object with a thermal control device in which a thermal shielding element is at least substantially unactuated, Fig. 3 shows a front view of a space object with a device for thermal control, in which a thermal shielding element is actuated for at least partially shielding the space object, and Fig. 4 shows a sectional view of a space object with a plurality of thermal control devices, each of which has a thermal shielding element actuated to shield the space object at least in sections.

[0021] Fig. Figure 1 shows a space object 10, or a section thereof, with a thermal control device 100. The space object 10 is, by way of example, part of a robotic device that may be located in space. The space object 10 is exposed to thermal and / or thermally effective radiation, in particular electromagnetic radiation, of a celestial body S, which may be the sun.

[0022] The device 100 has at least one thermal shielding element 110. The shielding element 110 is configured to shield the space object 10 at least in sections from the thermal radiation of the celestial body S. The shielding element 110 has, for example, radiation-absorbing and / or radiation-reflecting properties. The shielding element 110 is configured to be changed in size by appropriate actuation, control, or the like in order to optionally shield a smaller section, no section at all, a larger section, or the entire space object 10.

[0023] The device 100 also has at least one actuator 120, which serves to actuate the shielding element 110. The actuator 120 is coupled to the shielding element 110. The actuator 120 is configured to control, activate, move, or the like the shielding element as a result of the action of thermal radiation on the actuator. The actuator 120 is arranged on a side of the shielding element facing the celestial body S and is thus exposed to more or less radiation from the space object 10 depending on the orientation and / or position of the space object 10 relative to the celestial body S. The actuator 120 here exemplarily has a bimetal or is formed from such a bimetal. The bimetal can be, for example, a metal strip with two layers of different metals with different thermal expansion coefficients that lie adjacent to one another and are joined together, for example, in a materially bonded, positively bonded, and / or non-positively bonded manner.Depending on the radiation acting on the actuator 120, a corresponding heat input occurs into the actuator 120, which consequently changes its shape due to its material properties. The radiation-, temperature-, and / or heat-dependent deformation of the actuator actuates the shielding element 110 accordingly.

[0024] Fig. 2 and Fig. 3 each show a front view of the space object 10 with the device 100 described above. In Fig. 2, the shielding element 120 is at least substantially inactive or deactivated, ie, it essentially does not shield the space object 10 from radiation. This is the case, for example, if at a given time this side of the space object 10 is at least essentially facing away from the celestial body S. As a result, correspondingly little or no radiation acts on the actuator 110, which thus has a shape with which the shielding element 120 has no shielding effect, e.g., folded. Fig. 3, the shielding element 110 is actuated by the actuator 120 and thus has a shielding effect on the space object 10. This is the case, for example, if at a given time this side of the space object 10 is at least substantially facing the celestial body S. As a result, radiation acts on the actuator 110, which thus has a Fig. 2, has a different shape with which the shielding element 120 has a shielding effect on the space object 10, e.g. is enlarged in area, spanned, etc.

[0025] Fig. 4 shows the space object 10 with several of the above-described devices 100. The devices 100 are arranged on an outer side of the space object 10 around it. Merely for better illustration, the respective shielding elements 110 are actuated by the respective actuator 110 of the respective device 100 here, e.g., stretched out over a large area, or the like. However, it should be noted that the respective shielding element 110, in particular its areal size, can vary depending on the radiation acting on the respective actuator 110, e.g., the radiation of the celestial body S (see Fig.1) can be changed in order to change the shielding effect of the respective shielding element 110. For example, depending on the orientation and / or position of the space object 10, more or fewer of the shielding elements 110 are activated simultaneously and / or with different strengths.

[0026] "May" refers in particular to optional features of the invention. Accordingly, there are also further developments and / or embodiments of the invention that additionally or alternatively comprise the respective feature(s).

[0027] If necessary, isolated features may also be selected from the combinations of features disclosed here and used in combination with other features to define the subject matter of the claim, dissolving any structural and / or functional connection that may exist between the features. Reference symbol 10 space object 100 device 110 umbrella element 120 Actuator S celestial bodies, e.g. sun

Claims

[1] Device (100) for thermal control of a space object (10), characterized by a thermal shielding element (110) which is designed to shield the space object (10) at least partially from thermal radiation, and an actuator (120) which is coupled to the shielding element (110) and is designed to control the shielding element (110) as a result of the action of thermal radiation on the actuator, characterized by that the actuator (120) has a curved shape, in particular a spiral shape. [2] Device (100) according to claim 1, characterized by that the actuator (120) is designed to deform as a result of the action of thermal radiation. [3] Device (100) according to claim 1 or 2, characterized byin that the actuator (120) is designed to deform as a result of the action of thermal radiation between a first shape in which the shielding element (110) has a first surface, and a second shape in which the shielding element (110) has a second surface which is larger than the first surface. [4] Device (100) according to at least one of the preceding claims, characterized by that the actuator (120) is designed to selectively reduce or enlarge the area of ​​the shielding element (110) depending on the effect of thermal radiation. [5] Device (100) according to at least one of the preceding claims, characterized by that the actuator (120) is designed to have either a curved or a straightened shape depending on the effect of thermal radiation and to span the shielding element (110) flatly with the straightened shape. [6] Device (100) according to at least one of the preceding claims, characterized by that the actuator (120) and the shielding element (110) are coupled to one another by one of their flat sides. [7] Space object (10), comprising at least one device (100) for thermal control of the space object (10) according to at least one of the preceding claims. [8] Space object (10) according to claim 7, characterized by that several of the devices (100) are arranged on an outer side of the space object (10) around it. [9] Method for thermal control of a space object (10), comprising: Arranging a thermal shielding element (110) on an outer side of the space object (10) such that the space object (10) can be shielded from thermal radiation at least in sections by the shielding element (110), and Coupling an actuator (120) to the thermal shielding element (110) such that the actuator (120) controls the shielding element (110) as a result of the action of thermal radiation on the actuator (120), characterized by , that the actuator (120) has a curved shape, in particular a spiral shape.

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