Space vehicle with cooling system

Abstract

To provide a space vehicle with one or more heat-producing components, and with a closed loop cooling system configured to remove heat generated by the one or more heat-producing components.SOLUTION: The closed loop cooling system comprises a coolant passageway defining a closed loop, a coolant located within the coolant passageway, the coolant having a static pressure of 100 pounds or less per square inch and being in a single liquid phase through the coolant passageway, and one or more pumps configured to move the coolant through the coolant passageway. The closed loop cooling system further comprises a first heat exchange component disposed along the coolant passageway, the first heat exchange component configured to transfer heat from the heat-producing components to the coolant, and a second heat exchange component disposed along the coolant passageway, the second heat exchange component configured to remove heat from the coolant.SELECTED DRAWING: Figure 4

Description

[Technical field]

[0001] The present disclosure relates to space vehicles, and more particularly, to space vehicles with closed-loop cooling systems. [Background technology]

[0002] Space vehicles include various components that generate heat. For example, a satellite may include a payload, such as an imaging system or an antenna array, that generates heat during operation. To maintain the components within a desired operating temperature range, the space vehicle may include a cooling system that removes heat generated by the heat-generating components. Some cooling systems for space vehicles employ passive mechanisms to dissipate heat (e.g., heat pipes and heat spreaders). However, passive cooling systems impose an upper limit on heat dissipation, constraining the power of the payload and, therefore, the design of the space vehicle. For example, some passive cooling systems may limit the power of the payload components to less than 20 Watts and the power density to less than 40 Watt / in2.

[0003] Some cooling systems for space vehicles employ ammonia as a coolant. However, ammonia is toxic and can create compatibility issues with other materials. For example, in the presence of water or hydroxides, ammonia can corrode aluminum, which is commonly used in space vehicle components. Additionally, ammonia is processed at high pressure (e.g., 400 psi) in some cooling systems. High pressure can cause a high risk of leakage, which can reduce cooling performance and therefore component performance, and in some scenarios can cause serious failure of the pumped fluid cooling system. Ammonia-based cooling systems can also exhibit significant performance degradation at temperatures above 80° C. These and other issues combine to make the storage, distribution, and use of ammonia-based coolants in space vehicles cumbersome and hazardous, limiting space vehicle designs.

[0004] Thus, in view of the above, challenges exist in cooling space vehicle components. Summary of the Invention

[0005] To address the above problems, a space vehicle is provided according to one aspect of the disclosure. In this aspect, the space vehicle includes one or more heat-generating components and a closed-loop cooling system configured to remove heat generated by the one or more heat-generating components. The closed-loop cooling system includes a coolant passageway defining a closed loop, a coolant located within the coolant passageway having a static pressure of 100 pounds per square inch or less and in a single liquid phase throughout the coolant passageway, and one or more pumps configured to move the coolant through the coolant passageway. The closed-loop cooling system further includes a first heat exchange component disposed along the coolant passageway, the first heat exchange component configured to transfer heat from the heat-generating components to the coolant, and a second heat exchange component disposed along the coolant passageway, the second heat exchange component configured to remove heat from the coolant.

[0006] Another aspect of the disclosure relates to a space vehicle comprising one or more heat generating components and a closed-loop cooling system configured to remove heat generated by the one or more heat generating components. In this aspect, the closed-loop cooling system comprises a coolant passageway defining a closed loop, a hydrocarbon coolant located within the coolant passageway, the hydrocarbon coolant being in a single liquid phase throughout the coolant passageway, and one or more pumps configured to move the hydrocarbon coolant through the coolant passageway. The closed-loop cooling system further comprises a first heat exchange component disposed along the coolant passageway, the first heat exchange component configured to transfer heat from the heat generating components of the payload to the hydrocarbon coolant, and a second heat exchange component disposed along the coolant passageway, the second heat exchange component configured to remove heat from the hydrocarbon coolant.

[0007] Yet another aspect of the present disclosure relates to a space vehicle including a payload including one or more heat generating components, and a vehicle platform including a closed-loop cooling system configured to remove heat generated by the one or more heat generating components of the payload. In this aspect, the closed-loop cooling system includes a coolant passageway defining a closed loop, the coolant passageway including a platform coolant passageway portion and a payload coolant passageway portion, a coolant located within the coolant passageway, and one or more pumps configured to move the coolant through the coolant passageway. The closed-loop cooling system further includes a first heat exchange component disposed along the payload coolant passageway portion, the first heat exchange component configured to transfer heat from the heat generating components of the payload to the coolant, a quick disconnect fitting connecting the platform coolant passageway portion to the payload passageway portion, and a second heat exchange component disposed along the platform coolant passageway portion, the second heat exchange component configured to remove heat from the coolant.

[0008] Yet another aspect of the present disclosure relates to a space vehicle comprising a payload including one or more heat-generating components, and a closed-loop cooling system configured to remove heat generated by the one or more heat-generating components of the payload, wherein the closed-loop cooling system comprises a coolant passageway defining a closed loop, a coolant located within the coolant passageway, one or more pumps configured to move the coolant through the coolant passageway, and one or more additively manufactured heat exchange components located along the coolant passageway.

[0009] The above-described features, functions, and advantages may be realized individually in various embodiments or may be combined in yet other embodiments, and further details of these features, functions, and advantages may be understood with reference to the following description and drawings. [Brief description of the drawings]

[0010] [Figure 1] 1 illustrates an exemplary space vehicle with a cooling system, according to one embodiment of the present disclosure. [Diagram 2] 1 illustrates an exemplary space vehicle with a cooling system according to another embodiment of the present disclosure. [Diagram 3] 1 illustrates a schematic diagram of an exemplary cooling system for a space vehicle, in accordance with one embodiment of the present disclosure. [Figure 4] 1 illustrates an exemplary additively manufactured heat exchange component, according to one embodiment of the present disclosure. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0011] In view of the above discussion, embodiments are disclosed that relate to a space vehicle with a closed-loop cooling system. Briefly, one exemplary cooling system includes a coolant passageway defining a closed loop, a single-phase liquid coolant located within the coolant passageway, and one or more pumps configured to move the coolant through the coolant passageway. A first heat exchange component disposed along the coolant passageway transfers heat from a heat-generating component (e.g., a component of the space vehicle payload) to the coolant, and a second heat exchange component disposed along the coolant passageway removes heat from the coolant, thereby exhausting heat from the space vehicle. In some embodiments, the single-phase liquid coolant has a static pressure of 100 pounds per square inch absolute (psia) (e.g., in some embodiments, a minimum of 4 psia). The pressure at this state may help reduce the risk of coolant leakage when compared to high pressure cooling systems and may facilitate manufacturing and filling of the cooling system at ambient pressure. In some embodiments, quick disconnect fittings are used to connect the platform and payload portions of the cooling system, further helping to simplify manufacturing, integration, and testing. In contrast to passive cooling structures that, in some embodiments, may limit payload component power to less than 20 Watts and power densities to less than 40 Watts / in2, the cooling systems disclosed herein, in some embodiments, may increase thermal management capabilities to allow payload component power up to 150 Watts, power densities of 200 Watts / in2 or more, and operating temperatures up to 150° C. under a variety of conditions.

[0012] In some embodiments, the coolant comprises a hydrocarbon-based liquid, such liquid comprising one or more C8-C15 alkanes, alkenes, alkynes, and / or aromatics. In more specific embodiments, the coolant comprises a mixture of C8-C15 isoalkanes having freezing and boiling points selected such that the coolant remains in a single liquid phase throughout the operating temperature and pressure range. Such coolants may also be selected to have a sufficiently high thermal conductivity (e.g., 0.08 to 0.2 W / mK) and a sufficiently high specific heat (e.g., 1.5 to 3.0 kJ / kg-K) to enable the cooling system to dissipate relatively large amounts of heat at a suitably high density for the desired application, supporting higher power and more complex payloads. In some embodiments, the coolant may dissipate relatively large amounts of heat while being pumped at temperatures up to 100° C., and in other embodiments up to 150° C. In contrast, ammonia-based coolants may exhibit a significant decrease in performance at temperatures above 80° C. Additionally, because hydrocarbon coolants do not oxidize, such coolants may reduce the potential for corrosion to platform and payload cooling system components compared to using coolants such as ammonia and water. In some embodiments, such coolants may serve as suitable lubricants and coolants for pumps that circulate the coolant. Such coolants are also dielectrics, allowing for pumping in electronic devices. Additionally, such coolants may exhibit acceptable levels of hydrogen production when exposed to radiation similar to that encountered in space.

[0013] FIG. 1 illustrates an exemplary space vehicle with a cooling system according to an embodiment of the present disclosure. In this embodiment, the space vehicle takes the form of a satellite 100 carrying a payload 102 including heat-generating components. In some embodiments, the payload 102 may include a transmit and receive antenna array for communication. Additionally, in some embodiments, the payload 102 may include an imaging system (e.g., a radar imaging system, an optical imaging system, a microwave imaging system, and / or an infrared imaging system). Other examples of heat-generating components that may be incorporated into the satellite and / or payload include sensor systems (e.g., for measuring operational aspects of the satellite 100) and computer systems (e.g., for controlling the operation of the satellite 100). As used herein, the term "space vehicle" refers to both actively driven and passively moving space vehicles.

[0014] FIG. 2 illustrates another example of a space vehicle with a cooling system according to an embodiment of the present disclosure. The exemplary space vehicle takes the form of a rover 200 that may be used to explore the surface of extraterrestrial bodies. The rover 200 may include any of a wide variety of heat-generating components, including, but not limited to, image sensing and analysis components, chemical sensors and analysis components, radiation detectors and analysis components, mechanical systems, optical and radio frequency communication systems, and inter-satellite links. The space vehicles of FIGS. 1 and 2 are presented for illustrative purposes, and the exemplary cooling systems described herein may be implemented in any suitable space vehicle to cool any suitable heat-generating components, whether the components are part of a payload or platform portion of the space vehicle. Additionally, examples of space vehicles include crewed and non-crewed spacecraft.

[0015] 3 illustrates generally an example closed-loop cooling system 300 for a space vehicle, such as the example space vehicle described above. The illustrated cooling system 300 comprises a payload portion 301 integrated with a payload including heat-generating components, and a platform portion 302 coupled to the payload portion 301, the platform portion 302 including the active components of the cooling system 300, such as a pump for circulating a coolant.

[0016] The cooling system 300 includes coolant passages 303 that form a continuous closed loop through which coolant flows. The passages 303 include fill / drain valves 304 through which coolant may be supplied to and exhausted from the passages 303. To remove heat from the heat-generating components of the payload, the payload portion 301 of the cooling system 300 includes a number of heat exchange components, such as cold plates 306, that are in thermal communication with the heat-generating components of the payload. The cold plates 306 transfer heat from the heat-generating components to the liquid-phase coolant circulating through the payload portion 301 of the cooling system 300. As described in more detail below, the coolant remains in a liquid phase throughout its circulation through the passages 303 and is therefore referred to herein as a single-phase liquid coolant, in contrast to coolants that remove heat through a phase change process (e.g., an evaporation / condensation process).

[0017] Cold plates 306 and / or other heat exchanging components may be provided along the coolant passages 303 in any suitable number and arrangement. In the embodiment shown, the cold plates 306 are arranged in two parallel groups. In the first group 308, the parallel coolant passage segments 309 each include two or more cold plates 306 and share a common inlet 310A and a common outlet 312A. In the second group 314, the parallel coolant passage segments 309 each include two or more cold plates 306 and share a common inlet 310B and a common outlet 312B. In this embodiment, the cold plates 306 in the first group 308 transfer heat from a first heat generating component to the coolant in the passages 303, and the cold plates 306 in the second group 314 transfer heat from a second heat generating component to the coolant in the passages. With inlets 310 and outlets 312 arranged in parallel with each other, groups 308 and 314 allow the first and second heat generating components to be cooled in parallel with each other. Furthermore, the parallel arrangement of groups 308 and 314 may reduce the coolant pressure drop across payload portion 301. In other embodiments, the cold plates may be arranged in series rather than partially or completely in parallel. Furthermore, the multiple segments may each be provided with one or more cold plates, with two or more segments sharing common inlets and / or outlets. Alternatively or additionally, one or more of the multiple segments may have dedicated inlets and / or outlets that are not shared with other segments.

[0018] In some embodiments, the cold plates 306 remove heat generated by a payload including an antenna array. In such embodiments, the cold plates 306 in the first group 308 may cool a transmitter antenna array, while the cold plates 306 in the second group 314 may cool a transceiver array. In other embodiments, the cold plates 306 may be configured to remove heat from any other suitable heat-generating components of a space vehicle payload or platform. Additionally, the cooling system may implement any suitable arrangement and number of cold plates other than those shown in the illustrated embodiment.

[0019] In some embodiments, the payload portion 301 is coupled to the platform portion 302 via quick disconnect (QD) fittings 320. In the embodiment shown, four QD fittings are used to couple the payload portion 301 and the platform portion 302. A first QD fitting 320A couples an inlet 310A of the first group 308 to the platform portion 302, a second QD fitting 320B couples an outlet 312A of the first group 308 to the platform portion 302, a third QD fitting 320C couples an inlet 310B of the second group 314 to the platform portion 302, and a fourth QD fitting 320D couples an outlet 312B of the second group 314 to the platform portion 302. In other embodiments, any other suitable number of QD fittings can be used to connect the payload and platform portion 301 and platform portion 302 based on the number and arrangement of cold plates and components to be cooled.

[0020] The use of QD fittings 320 to couple the payload portion 301 and the platform portion 302 of the cooling system 300 may enable various advantages in the manufacturing, testing, and deployment of the cooling system 300. For example, the QD fittings 320 allow the payload and the platform portion 301 and the platform portion 302 to be easily coupled together without being individually tested, manipulated, and then performing a welding or other permanent coupling process. This allows for improved manufacturing and testing efficiency for cooling systems where the portions cannot be quickly disconnected and connected. Additionally, the quick connection / disconnection via the QD fittings 320 allows the payload and the platform portion 301 and the platform portion 302 to be moved separately during manufacturing and transportation.

[0021] The parallel flows of coolant from cold plate 306 join at junction 322. From junction 322, the flows pass through accumulator 324. Accumulator 324 is partially filled with coolant and controls the pressure of the coolant in passageway 303. Accumulator 324 may compensate for changes in the volume of the coolant (e.g., due to changes in the density and / or temperature of the coolant) as well as leakage of coolant from system 300. Accumulator 324 may take any suitable shape (e.g., that of a bellows-type accumulator). Additionally, accumulator 324 may be filled according to its configuration along passageway 303 or may be pre-filled with one or more gases (e.g., helium, argon, and / or nitrogen). It will be understood that the term "single-phase liquid coolant" used to describe the coolant in passage 303 does not exclude some vapor pressure of the coolant in accumulator 324 and / or elsewhere in the closed loop, but rather means that cooling system 300 does not use a phase change process as the primary mechanism of heat transfer.

[0022] From the accumulator 324, the coolant flows to a pump stage 325 configured to circulate the coolant through the passageway 303. The illustrated pump stage 325 includes a branch 326, where the coolant passageway 303 splits into a first segment 328 and a second segment 330 arranged in parallel with the first segment 328. The first segment 328 includes a first filter 332A, a first pump 334A, and a first check valve 336A. Similarly, the second segment 330 includes a second filter 332B, a second pump 334B, and a second check valve 336B. The filter 332 separates particulates from the coolant, thereby providing filtered coolant to the pump 334. Particulates may arise during operation of the cooling system 300 (e.g., from operation of the pump 334 and erosion of surfaces of the passageway 303) and also from manufacturing processes, for example. Separating particulates from the coolant may, for example, help reduce further erosion and protect bearings (e.g., hydrodynamic bearings) of the pump 334. Any suitable filter may be used. As an example, each filter 332 may include an absolute filter rating of 10 to 25 microns with a maximum AC dust capacity of 1 gram or higher. Furthermore, any suitable filter arrangement may be used. As another example, a single filter may be provided upstream of the pump 334.

[0023] The pumps of the cooling system 300 may operate alone or together in various embodiments. In some embodiments, one pump is intended to operate at a time, with the other pumps being provided as backup pumps in case the operating pump experiences performance issues. Pump operation may be monitored via any suitable sensor or sensors, including but not limited to thermistors and / or pressure sensors. In other embodiments, the cooling system may include any other suitable number and arrangement of pumps, such as three or more pumps (which may or may not be redundant) or a single pump. When multiple pumps are employed, the pumps may be arranged in parallel (as shown) or in series. Additionally, any suitable type of pump (e.g., centrifugal pumps in some embodiments) may be used and may be controlled via any suitable control scheme, including but not limited to closed loop rotational speed control (e.g., based on output from one or more Hall effect sensors). A check valve 336 allows unidirectional flow of coolant in the downstream direction, thus preventing backflow of coolant to the inactive pump.

[0024] Pump stage 325 increases the pressure of the filtered coolant. As one illustrative example, pump stage 325 may receive coolant pressurized to approximately 4 to 50 psi and output coolant at a pressure of 14 to 100 psi. The coolant flow downstream of check valve 336 proceeds to a junction 338 where first segment 328 and second segment 330 of coolant passage 303 meet.

[0025] From junction 338, the coolant flow splits into parallel segments 340A and 340B that pass through first and second heat rejection cold plates (HRCPs) 342A and 342B, respectively. In some embodiments, HRCPs 342 include brazed aluminum cold plates. In other embodiments, HRCPs 342 may take any other suitable form (e.g., additive manufacturing forms). In the embodiment shown, each HRCP 342 is coupled to a number of heat pipes (e.g., heat pipes 344) to transfer heat from the HRCP. HRCPs 342 and heat pipes 344 represent one example of a heat exchange component, and other embodiments may employ any other suitable heat exchange components, including, but not limited to, other heat radiators and spreaders. Additionally, system 300 may implement any suitable number of HRCPs 342 and heat pipes 344. For example, in other embodiments, the outputs from segment 328 and segment 330 may be combined to flow to a single HRCP, multiple HRCPs arranged in series, or three or more parallel segments, each with one or more HRCPs.

[0026] As the coolant passes through the HRCPs 342, heat contained in the coolant is transferred to the HRCPs 342 and to the heat pipes 344, thereby extracting it from the system 300. In this manner, heat generated by the heat-generating components of the payload section 301 is removed from the system 300. After passing through the HRCPs 342, the flow proceeds to a junction 346 where the outflows of each HRCP 342 join. Here, the cooled coolant is again supplied to the cold plate 306 within the payload section 301.

[0027] As mentioned above, the fluid used as the coolant remains in a single liquid phase throughout passage 303, thereby removing heat from heat generating components and extracting heat from the space vehicle without utilizing a phase change as the primary heat transfer process. In some embodiments, the coolant is configured to be in liquid phase within a temperature range of -80° C. to 150° C. As mentioned above, the single-phase liquid coolant may contain a vapor pressure at a higher temperature than the liquid phase (e.g., in an accumulator).

[0028] In some embodiments, the coolant circulates at a relatively low pressure (e.g., as low as 4 psi in some embodiments), such as a pressure of 100 psi or less. Use of such low coolant pressures can reduce the possibility of coolant leakage from the passages 303 (e.g., at seals and joints in the passages 303). Additionally, the coolant can be liquid at atmospheric pressure (e.g., 1 atmosphere) and room temperature (e.g., 25° C.). This can facilitate filling of the passages 303 and testing of the system 300 during manufacturing without the equipment that would otherwise be used to achieve and maintain higher coolant pressures.

[0029] Additionally, the lower coolant pressure may reduce material and / or structural requirements imposed on the heat exchange components that conduct the coolant. For example, the lower coolant pressure and dielectric properties may allow the coolant to flow in contact with the electronic device. Another example of such a reduced requirement is that the lower coolant pressure may allow additively manufactured components to be used in the system 300. FIG. 4 illustrates a schematic of an exemplary additively manufactured cold plate 400 that may be used as the cold plate 306 or HRCP 342. FIG. 4 also illustrates a schematic of a coolant passage 402 formed within the cold plate 400. The passage 402 represents the passage 303 of FIG. 3 in an embodiment in which the cold plate 400 represents one of the cold plate 306 or HRCP 342.

[0030] Cold plate 400 includes multiple layers, two examples of which are shown at 404, that are deposited sequentially to form cold plate 400. Using high pressure coolant can pose a risk of separating the layers of the brazed assembly or of fracturing or rupturing the additively manufactured cold plate, whereas the lower pressure of the coolant used in the embodiments disclosed herein may pose less risk of degrading the integrity of the additively manufactured part or other layered structure.

[0031] As discussed above, the disclosed exemplary cooling system may utilize a single-phase hydrocarbon coolant. Any suitable hydrocarbon coolant may be used. In some embodiments, the coolant includes a mixture of one or more C8-C15 alkanes (n-alkanes or isoalkanes), alkenes, alkynes, and / or aromatic compounds. In more specific embodiments, the coolant may include a mixture of C8-C15 isoalkanes. In another more specific embodiment, the coolant may include one or more C10-C13 hydrocarbons, including one or more C10-C13 isoalkanes. Such hydrocarbon compounds may be relatively inexpensive compared to other coolants (e.g., fluorocarbon coolants). In still other embodiments, any other suitable hydrocarbon coolant may be used. The hydrocarbon coolant may be selected to have a suitably low freezing point (e.g., about -85°C at normal operating pressures) and a suitably high boiling point (e.g., 150°C at normal operating pressures) to remain in the liquid phase throughout the coolant passages.

[0032] Any suitable operating pressure may be used. In some embodiments, an operating pressure in the range of 4 to 100 psi, or in the range of 20 to 75 psi may be used. As mentioned above, using a relatively low operating pressure may reduce the possibility of coolant leakage and allow for the use of additively manufactured components along the coolant passages. Such hydrocarbon molecules are also larger than ammonia molecules or other lighter molecular weight molecules used as coolants. This may reduce the rate of coolant leakage through any small openings. Still further, the hydrocarbon coolant may function as a lubricant for one or more bearings of the pump 334. Alternatively or additionally, the hydrocarbon coolant may be used to cool the motor and / or other components within the pump 334. Other properties that may be used to select a coolant include thermal conductivity, specific heat, and viscosity (e.g., 0.2 to 30 cP) within the operating temperature and pressure range.

[0033] In some embodiments, the pump 334 may be isolated via one or more structures that reduce the transmission of vibrations from the pump 334 to other components in the system 300. As an example, the pump 334 may be mounted to a support that is isolated from other structures in the cooling system 300 via a damping structure that absorbs vibrations resulting from the operation of the pump 334.

[0034] System 300 may include various sensor devices for monitoring the operation of components therein. In some embodiments, sensor outputs may be transmitted to another location, for example, as part of telemetry provided by space vehicle mounted system 300. By way of example, system 300 may include one or more potentiometers (e.g., for sensing the volume of fluid in accumulator 324), one or more ammeters (e.g., for monitoring the operation of pump 334 via current), one or more Hall effect sensors (e.g., for controlling the operation of pump 334), one or more temperature sensors (e.g., at the inlet of pump 334, the inlet of HRCP 342, and / or the outlet of HRCP 342), one or more pressure transducers (e.g., at the inlet and / or outlet of pump 334 to sense the pressure of the coolant), one or more flow rate sensors, and / or one or more thermistors.

[0035] Active cooling enabled by the pumped flow of coolant within system 300 may increase the dissipation of heat generated by the payload as compared to cooling systems that passively cool the payload. System 300 therefore supports cooling of higher power payloads at higher power densities and allows the use of more complex payload configurations. Furthermore, by supporting variations in the number, arrangement, and type of components, system 300 supports a wide variety of space vehicle implementations.

[0036] Another embodiment provides a space vehicle comprising one or more heat generating components and a closed loop cooling system configured to remove heat generated by the one or more heat generating components, the closed loop cooling system comprising a coolant passage defining a closed loop, a coolant located within the coolant passage having a static pressure of 100 pounds per square inch or less and in a single liquid phase through the coolant passage, one or more pumps configured to move the coolant through the coolant passage, a first heat exchange component disposed along the coolant passage configured to transfer heat from the heat generating components to the coolant, and a second heat exchange component disposed along the coolant passage configured to remove heat from the coolant. In such an embodiment, the coolant may alternatively or additionally include a hydrocarbon. In such an embodiment, the coolant may alternatively or additionally include one or more C10-C13 isoalkanes, and the coolant may be configured to be in a liquid phase of -80 degrees Celsius to 150 degrees Celsius at a pressure of at least 4 to 100 pounds per square inch. In such an embodiment, the space vehicle may include a satellite. In such an embodiment, the satellite may include a platform to which a payload including heat generating components is coupled. The coolant passageway may include a platform portion and a payload portion coupled together by a quick disconnect fitting. In such an embodiment, the one or more pumps may include a first pump and a second pump arranged in parallel along parallel coolant passageway segments. In such an embodiment, the space vehicle may alternatively or additionally include a first check valve downstream of the first pump and upstream of a junction where the parallel coolant passageway segments meet, and a second check valve downstream of the second pump and upstream of the junction. In such an embodiment, the space vehicle may alternatively or additionally include a first filter located upstream of the first pump and a second filter located upstream of the second pump. In such an embodiment, each pump of the one or more pumps may alternatively or additionally include one or more bearings, and the coolant may be a lubricant for the one or more bearings.In such embodiments, one or more of the first heat exchange component and the second heat exchange component may include an additively manufactured structure or other layered structure.

[0037] Another embodiment provides a space vehicle comprising one or more heat generating components and a closed loop cooling system configured to remove heat generated by the one or more heat generating components, the closed loop cooling system comprising a coolant passage defining a closed loop, a hydrocarbon coolant located within the coolant passage, the hydrocarbon coolant being in a single liquid phase through the coolant passage, one or more pumps configured to move the hydrocarbon coolant through the coolant passage, a first heat exchange component disposed along the coolant passage configured to transfer heat from a heat generating component of the payload to the hydrocarbon coolant, and a second heat exchange component disposed along the coolant passage configured to remove heat from the hydrocarbon coolant. In such an embodiment, the hydrocarbon coolant may alternatively or additionally comprise one or more C8-C15 isoalkanes. In such an embodiment, each pump of the one or more pumps may comprise one or more bearings, and the hydrocarbon coolant may be a lubricant for the one or more bearings. In such an embodiment, the space vehicle may comprise a satellite. In such an embodiment, the satellite may comprise a platform to which a payload including a heat generating component is coupled. The coolant passage may include a platform portion and a payload portion coupled together by a quick disconnect fitting. In such an embodiment, one or more of the first heat exchange component and the second heat exchange component may have an additively manufactured structure. In such an embodiment, the coolant may alternatively or additionally include a static pressure of 100 pounds per square inch or less. In such an embodiment, the one or more pumps may alternatively or additionally include a first pump and a second pump arranged in parallel along the parallel coolant passage segments. In such an embodiment, the space vehicle may alternatively or additionally include a first check valve downstream of the first pump and upstream of a junction where the parallel coolant passage segments meet, and a second check valve downstream of the second pump and upstream of the junction. In such an embodiment, the space vehicle may alternatively or additionally include a first filter located upstream of the first pump, and a second filter located upstream of the second pump.

[0038] Another embodiment provides a space vehicle comprising a vehicle platform including a payload including one or more heat generating components and a closed loop cooling system configured to remove heat generated by the one or more heat generating components of the payload, the closed loop cooling system comprising a coolant passage defining a closed loop, a coolant passage including a platform coolant passage portion and a payload coolant passage portion, a coolant located within the coolant passage, one or more pumps configured to move the coolant through the coolant passage, a first heat exchange component disposed along the payload coolant passage portion, the first heat exchange component configured to transfer heat from the heat generating components of the payload to the coolant, a quick disconnect fitting connecting the platform coolant passage portion to the payload coolant passage portion, and a second heat exchange component disposed along the platform coolant passage portion, the second heat exchange component configured to remove heat from the coolant. In such an embodiment, the coolant may have a static pressure of 100 pounds per square inch or less. In such an embodiment, the payload coolant passage portion may comprise a plurality of segments arranged in parallel. In such examples, the space vehicle may alternatively or additionally include a satellite, and the first payload heat source may be configured to be cooled by the first payload coolant passage segment and the second payload heat source may be configured to be cooled by the second payload coolant passage segment. In such examples, one or more of the first heat exchange component and the second heat exchange component may include an additively manufactured structure.

[0039] Another embodiment provides a space vehicle comprising a payload including one or more heat generating components and a closed-loop cooling system configured to remove heat generated by the one or more heat generating components of the payload, the closed-loop cooling system comprising a coolant passage defining a closed loop, a coolant located within the coolant passage, one or more pumps configured to move the coolant through the coolant passage, and one or more additively manufactured heat exchange components located along the coolant passage. In such embodiments, the coolant may include a static pressure of 100 pounds per square inch or less. In such embodiments, the coolant may alternatively or additionally be in a single liquid phase throughout the closed-loop cooling system. In such embodiments, the coolant may alternatively or additionally be in a liquid phase. In such embodiments, the one or more additively manufactured heat exchange components may include an aluminum cold plate. Furthermore, the present disclosure includes embodiments according to the following clauses:

[0040] Clause 1 A space vehicle (100), one or more heat generating components (102); a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102), comprising: a coolant passage (303) defining a closed loop; a coolant located within said coolant passages (303), said coolant having a static pressure of 100 pounds per square inch or less and in a single liquid phase throughout said coolant passages (303); one or more pumps (334) configured to move the coolant through the coolant passages (303); a first heat exchange element (306) disposed along the coolant passage (303), the first heat exchange element (306) configured to transfer heat from the heat generating component (102) to the coolant; and a second heat exchange element (342) disposed along the coolant passage (303), the second heat exchange element (342) configured to remove heat from the coolant; A closed loop cooling system (300) comprising: A space vehicle (100).

[0041] Clause 2 2. The space vehicle (100) of claim 1, wherein the coolant comprises a hydrocarbon.

[0042] Clause 3 3. The space vehicle (100) of claim 2, wherein the coolant comprises one or more C10-C13 isoalkanes and is configured to be in a liquid phase at a temperature between -80 degrees Celsius and 150 degrees Celsius at a pressure of at least 4 to 100 pounds per square inch.

[0043] Clause 4 A space vehicle (100) as described in any one of clauses 1 to 3, wherein the space vehicle (100) comprises an artificial satellite (100).

[0044] Clause 5 A space vehicle (100) as described in any one of clauses 1 to 4, wherein the coolant passage (303) comprises a platform portion (302) and a payload portion (301) connected together by a quick disconnect fitting (320).

[0045] Clause 6 A space vehicle (100) as described in any one of clauses 1 to 5, wherein the one or more pumps (334) comprise a first pump (334A) and a second pump (334B) arranged in parallel along parallel coolant passage segments (328, 330).

[0046] Clause 7 The space vehicle (100) of clause 6, further comprising a first check valve (336A) downstream of the first pump (334A) and upstream of a junction (338) where the parallel coolant passage segments (328, 330) meet, and a second check valve (336B) downstream of the second pump (334B) and upstream of the junction (338).

[0047] Clause 8 8. The space vehicle (100) of clause 6 or 7, further comprising a first filter (332A) located upstream of the first pump (334A) and a second filter (332B) located upstream of the second pump (334B).

[0048] Clause 9 9. The space vehicle (100) of any one of clauses 1 to 8, wherein each pump (334A, 334B) of the one or more pumps (334) comprises one or more bearings, and the coolant is a lubricant for the one or more bearings.

[0049] Clause 10 A space vehicle (100) as described in any one of clauses 1 to 9, wherein one or more of the first heat exchange component (306) and the second heat exchange component (342) comprise an additively manufactured structure (400) or other layered structure (404).

[0050] Clause 11 A space vehicle (100), one or more heat generating components (102); a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102), comprising: a coolant passage (303) defining a closed loop; a hydrocarbon coolant located within said coolant passage (303), said hydrocarbon coolant being in a single liquid phase throughout said coolant passage (303); one or more pumps (334) configured to move the hydrocarbon coolant through the coolant passages (303); a first heat exchange element (306) disposed along the coolant passage (303), the first heat exchange element (306) configured to transfer heat from the heat generating component (102) of a payload (102) to the hydrocarbon coolant; and a second heat exchange component (342) disposed along the coolant passage (303), the second heat exchange component (342) configured to remove heat from the hydrocarbon coolant; A closed loop cooling system (300) comprising: A space vehicle (100).

[0051] Clause 12 12. The space vehicle (100) of claim 11, wherein the hydrocarbon coolant comprises one or more C8-C15 isoalkanes.

[0052] Clause 13 13. The space vehicle (100) of clause 11 or 12, wherein each pump (334A, 334B) of the one or more pumps (334) comprises one or more bearings, and the hydrocarbon coolant is a lubricant for the one or more bearings.

[0053] Clause 14. A space vehicle (100) as described in any one of clauses 11 to 13, wherein the space vehicle (100) comprises a satellite (100).

[0054] Clause 15 15. A space vehicle (100) as described in any one of clauses 11 to 14, wherein the coolant passage (303) comprises a platform portion (302) and a payload portion (301) connected together by a quick disconnect fitting (320).

[0055] Clause 16 A space vehicle (100) as described in any one of clauses 11 to 15, wherein one or more of the first heat exchange component (306) and the second heat exchange component (342) include an additively manufactured structure (400).

[0056] Clause 17 17. The space vehicle (100) of any one of clauses 11 to 16, wherein the coolant has a static pressure of 100 pounds per square inch or less.

[0057] Clause 18 18. A space vehicle (100) as described in any one of clauses 11 to 17, wherein the one or more pumps (334) comprise a first pump (334A) and a second pump (334B) arranged in parallel along parallel coolant passage segments (328, 330).

[0058] Clause 19 19. The space vehicle (100) of claim 18, further comprising a first check valve (336A) downstream of the first pump (334A) and upstream of a junction (338) where the parallel coolant passage segments (328, 330) meet, and a second check valve (336B) downstream of the second pump (334B) and upstream of the junction (338).

[0059] Clause 20 20. The space vehicle (100) of clause 18 or 19, further comprising a first filter (332A) located upstream of the first pump (334A) and a second filter (332B) located upstream of the second pump (334B).

[0060] Clause 21 A space vehicle (100), a payload (102) including one or more heat-generating components (102); 1. A vehicle platform comprising a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102) of the payload (102), the closed-loop cooling system (300) comprising: a coolant passage (303) defining a closed loop, the coolant passage (303) including a platform coolant passage portion (302) and a payload coolant passage portion (301); A coolant located within the coolant passage (303); one or more pumps (334) configured to move the coolant through the coolant passages (303); a first heat exchange component (306) disposed along the payload coolant passage portion (301), the first heat exchange component (306) configured to transfer heat from the heat generating component (102) of the payload (102) to the coolant; a quick disconnect fitting (320) connecting the platform coolant passage portion (302) to the payload coolant passage portion (301); and a second heat exchange component (342) disposed along the platform coolant passage portion (302), the second heat exchange component (342) configured to remove heat from the coolant; A vehicle platform equipped with A space vehicle (100).

[0061] Clause 22 22. The space vehicle (100) of claim 21, wherein the coolant has a static pressure of 100 pounds per square inch or less.

[0062] Clause 23 23. A space vehicle (100) as described in clause 21 or 22, wherein the payload coolant passage portion (301) comprises a plurality of segments (309) arranged in parallel.

[0063] Clause 24 A space vehicle (100) as described in any one of clauses 21 to 23, wherein the space vehicle (100) includes a satellite (100), a first payload heat source configured to be cooled by a first payload coolant path segment (309), and a second payload heat source configured to be cooled by a second payload coolant path segment (309).

[0064] Clause 25 A space vehicle (100) as described in any one of clauses 21 to 24, wherein one or more of the first heat exchange component (306) and the second heat exchange component (342) comprise an additively manufactured structure (400).

[0065] Clause 26 A space vehicle (100), a payload (102) including one or more heat-generating components (102); a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102) of the payload (102), comprising: a coolant passage (303) defining a closed loop; A coolant located within the coolant passage (303); one or more pumps (334) configured to move the coolant through the coolant passages (303); and a closed loop cooling system (300) including one or more additively manufactured heat exchange components (306) positioned along the coolant passage; A space vehicle (100).

[0066] Clause 27 27. The space vehicle (100) of claim 26, wherein the coolant has a static pressure of 100 pounds per square inch or less.

[0067] Clause 28 28. A space vehicle (100) according to any one of clauses 26 to 27, wherein the coolant is in a single liquid phase throughout the closed loop cooling system (300).

[0068] Clause 29 29. A space vehicle (100) according to any one of clauses 26 to 28, wherein the coolant is in a liquid phase.

[0069] Clause 30 30. The space vehicle (100) of any one of clauses 26 to 29, wherein the one or more additively manufactured heat exchange components (306) include an aluminum cold plate (306).

[0070] The present disclosure includes all novel and non-obvious combinations and subcombinations of the various features and techniques disclosed herein. The various features and techniques disclosed herein are not necessarily required for all embodiments of the present disclosure. Moreover, the various features and techniques disclosed herein may define patentable subject matter apart from the disclosed embodiments and may find utility in other embodiments not expressly disclosed herein.

Claims

1. A space vehicle (100), one or more heat generating components (102); a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102), comprising: a coolant passage (303) defining a closed loop, the coolant passage (303) including a platform coolant passage portion (302) and a payload coolant passage portion (301); a coolant located within said coolant passages (303), said coolant having a static pressure of 100 pounds per square inch or less and in a single liquid phase throughout said coolant passages (303); one or more pumps (334) configured to move the coolant through the coolant passages (303); a first heat exchange component (306) disposed along the coolant passage (303), the first heat exchange component (306) configured to transfer heat from the heat generating component (102) to the coolant; a quick disconnect fitting (320) connecting the platform coolant passage portion (302) to the payload coolant passage portion (301); and a second heat exchange element (342) disposed along the coolant passage (303), the second heat exchange element (342) configured to remove heat from the coolant; A closed loop cooling system (300) comprising: Equipped with the one or more heat-generating components (102) include a first heat-generating component and a second heat-generating component; The quick disconnect fitting (320) comprises: a first QD fitting connecting a first group of inlets of the first heat exchange component (306) that transfers heat from the first heat generating component to the coolant to the platform coolant passage portion (302); a second QD fitting connecting the first group of outlets to the platform coolant passage portion (302); a third QD fitting connecting a second group of inlets of the first heat exchange component (306) that transfers heat from the second heat generating component to the coolant to the platform coolant passage portion (302); and a fourth QD fitting connecting the second group of outlets to the platform coolant passage portion.

2. 2. The space vehicle (100) of claim 1, wherein the one or more pumps (334) comprise a first pump (334A) and a second pump (334B) arranged in parallel along parallel coolant passage segments (328, 330).

3. 3. The space vehicle (100) of claim 1 or 2, wherein one or more of the first heat exchange component (306) and the second heat exchange component (342) comprise an additively manufactured structure (400) or other layered structure (404).

4. A space vehicle (100), one or more heat generating components (102); a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102), comprising: a coolant passage (303) defining a closed loop, the coolant passage (303) including a platform coolant passage portion (302) and a payload coolant passage portion (301); a hydrocarbon coolant located within said coolant passage (303), said hydrocarbon coolant being in a single liquid phase throughout said coolant passage (303); one or more pumps (334) configured to move the hydrocarbon coolant through the coolant passages (303); a first heat exchange component (306) disposed along the coolant passage (303), the first heat exchange component (306) configured to transfer heat from the heat generating component (102) of the payload (102) to the hydrocarbon coolant; a quick disconnect fitting (320) connecting the platform coolant passage portion (302) to the payload coolant passage portion (301); and a second heat exchange component (342) disposed along the coolant passage (303), the second heat exchange component (342) configured to remove heat from the hydrocarbon coolant; A closed loop cooling system (300) comprising: Equipped with the one or more heat-generating components (102) include a first heat-generating component and a second heat-generating component; The quick disconnect fitting (320) comprises: a first QD fitting connecting a first group of inlets of the first heat exchange component (306) that transfers heat from the first heat generating component to the hydrocarbon coolant to the platform coolant passage portion (302); a second QD fitting connecting the first group of outlets to the platform coolant passage portion (302); a third QD fitting connecting a second group of inlets of the first heat exchange component (306) that transfers heat from the second heat generating component to the hydrocarbon coolant to the platform coolant passage portion (302); and a fourth QD fitting connecting the second group of outlets to the platform coolant passage portion.

5. 5. The space vehicle (100) of claim 4, wherein each pump (334A, 334B) of the one or more pumps (334) comprises one or more bearings, and the hydrocarbon coolant is a lubricant for the one or more bearings.

6. The one or more pumps (334) include a first pump (334A) and a second pump (334B) arranged in parallel along parallel coolant passage segments (328, 330); 6. The space vehicle (100) of claim 4 or 5, further comprising a first check valve (336A) downstream of the first pump (334A) and upstream of a junction (338) where parallel coolant passage segments (328, 330) meet, and a second check valve (336B) downstream of the second pump (334B) and upstream of the junction (338).

7. A space vehicle (100), a payload (102) including one or more heat-generating components (102); 1. A vehicle platform comprising a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102) of the payload (102), the closed-loop cooling system (300) comprising: a coolant passage (303) defining a closed loop, the coolant passage (303) including a platform coolant passage portion (302) and a payload coolant passage portion (301); A coolant located within the coolant passage (303); one or more pumps (334) configured to move the coolant through the coolant passages (303); a first heat exchange component (306) disposed along the payload coolant passage portion (301), the first heat exchange component (306) configured to transfer heat from the heat-generating component (102) of the payload (102) to the coolant; a quick disconnect fitting (320) connecting the platform coolant passage portion (302) to the payload coolant passage portion (301); and a second heat exchange component (342) disposed along the platform coolant passage portion (302), the second heat exchange component (342) configured to remove heat from the coolant; A vehicle platform equipped with Equipped with the one or more heat-generating components (102) include a first heat-generating component and a second heat-generating component; The quick disconnect fitting (320) comprises: a first QD fitting connecting a first group of inlets of the first heat exchange component (306) that transfers heat from the first heat generating component to the coolant to the platform coolant passage portion (302); a second QD fitting connecting the first group of outlets to the platform coolant passage portion (302); a third QD fitting connecting a second group of inlets of the first heat exchange component (306) that transfers heat from the second heat generating component to the coolant to the platform coolant passage portion (302); and a fourth QD fitting connecting the second group of outlets to the platform coolant passage portion.

8. 8. The space vehicle (100) of claim 7, wherein the space vehicle (100) includes a satellite (100), a first payload heat source configured to be cooled by a first payload coolant path segment (309), and a second payload heat source configured to be cooled by a second payload coolant path segment (309).

9. A space vehicle (100), a payload (102) including one or more heat-generating components (102); a closed-loop cooling system (300) configured to remove heat generated by the one or more heat-generating components (102) of the payload (102), comprising: a coolant passage (303) defining a closed loop, the coolant passage (303) including a platform coolant passage portion (302) and a payload coolant passage portion (301); A coolant located within the coolant passage (303); one or more pumps (334) configured to move the coolant through the coolant passages (303); one or more additively manufactured heat exchange components (306) located along the coolant passages; and a quick disconnect fitting (320) connecting said platform coolant passage portion (302) to said payload coolant passage portion (301); A closed loop cooling system (300) comprising: Equipped with the one or more heat-generating components (102) include a first heat-generating component and a second heat-generating component; The quick disconnect fitting (320) comprises: a first QD fitting connecting a first group of inlets of the heat exchange components (306) that transfer heat from the first heat generating components to the coolant to the platform coolant passage portion (302); a second QD fitting connecting the first group of outlets to the platform coolant passage portion (302); a third QD fitting connecting a second group of inlets of the heat exchange components (306) that transfer heat from the second heat generating components to the coolant to the platform coolant passage portion (302); and a fourth QD fitting connecting the second group of outlets to the platform coolant passage portion.

10. The space vehicle (100) of claim 9, wherein the coolant is in a single liquid phase throughout the closed-loop cooling system (300).

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