1. Field of the Invention
The present disclosure relates to thermal management systems, and more particularly to radiators for use in spacecraft.
2. Description of Related Art
Space vehicles commonly employ thermal management systems to control the temperature of vehicle components, such as the space vehicle's solar cells. Such thermal management systems typically use a pumped coolant loop to remove heat from the solar cells and transport that heat to the spacecraft radiators to radiate that heat to space. Such systems generally must meet cooling requirements across a variety of operating temperatures, and must comply with weight requirements.
Such conventional methods and systems have generally been considered satisfactory for their intended purposes. However, there is still a need in the art for improved thermal management systems. This disclosure provides a solution for this need.
A modular radiator panel includes a coolant tube, a saddle surrounding a first portion of the coolant tube and a radiative sheet mounted to the saddle. The radiative sheet surrounds a second portion of the coolant tube, such that the coolant tube is sandwiched between the radiative sheet and the saddle.
The radiative sheet can be substantially planar. The modular radiator panel can include an epoxy layer surrounding the coolant tube between the saddle and the radiative sheet. The modular radiator panel can include a micrometeroid and orbital debris (MMOD) protection sheet. The MMOD protection sheet can be mounted to a side of the radiative sheet opposite that of the coolant tube and the saddle with an epoxy having a thermal conductivity of 0.331 W/(m·K). The coolant tube can be mounted to the saddle with an epoxy having a thermal conductivity of 0.331 W/(m·K), and the saddle can be mounted to the radiative sheet with an epoxy having a thermal conductivity of 0.331 W/(m·K). The modular radiator panel can include a bracket mounted to a side of the saddle opposite that of the coolant tube and the radiative sheet. The bracket can include a saddle portion offset from the saddle.
A radiator includes a plurality of coolant tubes and saddles. Each saddle surrounds a first portion of a respective one of the coolant tubes. The radiator includes a plurality of radiative sheets. Each radiative sheet is mounted to a respective one of the saddles. Each radiative sheet surrounds a second portion of a respective one of the coolant tubes, similar to the radiative sheet described above.
It is contemplated that the radiative sheets, saddles and coolant tubes can be similar to those described above. The radiator can include a plurality of MMOD protection sheets mounted to a side of a respective one of the radiative sheets opposite that of the coolant tube and the saddle. The MMOD protection sheets are similar to the MMOD protection sheet described above. The radiator can include a bracket mounted to sides of each of the saddles opposite that of the coolant tubes and the radiative sheets, similar to the bracket described above.
These and other features of the systems and methods of the subject disclosure will become more readily apparent to those skilled in the art from the following detailed description of the preferred embodiments taken in conjunction with the drawings.
So that those skilled in the art to which the subject disclosure appertains will readily understand how to make and use the devices and methods of the subject disclosure without undue experimentation, preferred embodiments thereof will be described in detail herein below with reference to certain figures, wherein:
Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an exemplary embodiment of a radiator assembly in accordance with the disclosure is shown in
As shown in
With reference now to
Coolant tube 102 is sandwiched between saddle 104 and radiative sheet 108. An epoxy layer 112 surrounds coolant tube 102 between saddle 104 and radiative sheet 108. Epoxy layer 112 acts to mount coolant tube 102, saddle 104, and radiative sheet 108 together. In addition, epoxy layer 112 facilitates heat transfer between coolant tube 102 and saddle 104 and/or radiative sheet 108. The sandwiched configuration allows for maximum heat transfer between coolant tube 102 and radiative sheet 108. For example, heat can be transferred from coolant tube 102 through epoxy layer 112 to radiative sheet 108, and/or can be transferred from coolant tube 102 through epoxy layer 112 to saddle 104, and then to radiative sheet 108.
Those skilled in the art will readily appreciate that the material for epoxy layer 112 is selected based on its strength properties and heat transfer properties over a certain operating temperature range, for example −150 ° C. to +150 ° C., and can vary as needed for a given application. For example, it is contemplated that epoxy layer 112 can withstand an equivalent of approximately 40 G's quasi-static vibration without cracking, and/or without compromising the thermal conductivity between radiative sheet 108, coolant tube 102 and saddle 104. Epoxy layer 112 can include any of a variety of different epoxies, but generally has thermal conductivity between 0.25 and 3, for example, a thermal conductivity of 0.331 W/(m·K) at 10.0 KHz.
With continued reference to
Those skilled in the art will readily appreciate that radiator 100 can operate in temperatures ranging from −150 ° C. to +150 ° C. In addition, radiator 100 can be less than 12 pounds and provide over 1 square meter of heat rejection surface. Radiator 100 is configured to be operational after exposed to launch random vibration, for example an equivalent of approximately 40 G's quasi-static vibration. Those skilled in the art will readily appreciate that the combination of the stiffness across radiative sheet 108, saddle 104 and epoxy layer 112 and the attachment to bracket 116 allow for this vibration resistivity.
The methods and systems of the present disclosure, as described above and shown in the drawings, provide for radiators with superior properties including increased thermal conductivity, increased strength and reduced weight. While the apparatus and methods of the subject disclosure have been shown and described with reference to preferred embodiments, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the spirit and scope of the subject disclosure.
This invention was made with government support under Prime Contract No. NNN06AA01C, Sub-Contract No. 970634, awarded by the National Aeronautics and Space Administration. The government has certain rights in the invention.