Thermally-enhanced and deployable structures
An apparatus includes a structure configured to receive thermal energy and to reject the thermal energy into an external environment. The structure includes a lid and a body. The structure also includes (i) multiple inline and interconnected thermomechanical regions and (ii) one or more oscillating heat pipes embedded in at least some of the thermomechanical regions. Different portions of at least one of the lid and the body form the thermomechanical regions. The one or more oscillating heat pipes are configured to transfer the thermal energy between different ones of the thermomechanical regions. At least one of the thermomechanical regions includes one or more shape-memory materials configured to cause a shape of the structure to change. Each of the one or more oscillating heat pipes includes at least one channel in the structure.
1. A system comprising:
a flight vehicle;
one or more deployable panels, each deployable panel comprising multiple solar collectors disposed on the deployable panel; and
one or more shape-changeable hinges coupled to the one or more deployable panels and the flight vehicle;
wherein each of the one or more shape-changeable hinges comprises:
a lid;
a body;
one or more morphable regions forming a first portion of the lid and the body, the one or more morphable regions comprising one or more shape-memory materials configured to cause a shape of the hinge to change;
one or more adiabatic regions disposed adjacent to the one or more morphable regions and forming a second portion of the lid and the body, wherein the one or more adiabatic regions are coated with one or more insulative materials;
one or more heat pipes embedded in the one or more morphable regions and the one or more adiabatic regions, the one or more heat pipes configured to receive thermal energy from the solar collectors and transfer the thermal energy at least partially along a length of the hinge, the one or more heat pipes having a shape formed by one or more first indentations formed in an inner surface of the lid and one or more second indentations formed in an inner surface of the body, the one or more first indentations and the one or more second indentations aligning with each other to form the one or more heat pipes; and
wherein only the one or more morphable regions include the one or more shape-memory materials and the one or more adiabatic regions are formed from one or more other materials having high thermal conductivity.
2. The system of claim 1 , wherein the one or more shape-changeable hinges are configured to:
permit the one or more deployable panels to be folded against the flight vehicle; and
unfold the one or more deployable panels to deploy the one or more deployable panels extending away from the flight vehicle.
3. The system of claim 1 , wherein the system comprises multiple deployable panels and multiple hinges.
4. The system of claim 3 , wherein the hinges are configured to:
permit the deployable panels to be folded upon each other; and
unfold the deployable panels to deploy the deployable panels extending away from the flight vehicle, the deployed panels having a larger exposed surface area than the folded panels.
5. The system of claim 1 , wherein the one or more morphable regions are configured to change shape.
6. The system of claim 5 , wherein each hinge further comprises:
one or more heat input regions configured to receive the thermal energy; and
one or more heat rejection regions configured to reject the thermal energy.
7. The system of claim 6 , wherein the one or more adiabatic regions are configured to provide structural support or reinforcement while at least substantially preventing heat transfer to and from an external environment.
8. The system of claim 1 , wherein the one or more heat pipes form an oscillating pattern within the one or more shape-memory materials.
9. The system of claim 1 , wherein, for each hinge, a bond line interface between the body of the hinge and the lid of the hinge is aligned with a neutral axis of the hinge.
10. The system of claim 9 , wherein, for each hinge, the neutral axis of the hinge equally divides a vertical thickness of the hinge.
11. The system of claim 1 , wherein the flight vehicle comprises a satellite.
12. A method comprising:
receiving thermal energy at one or more shape-changeable hinges coupled to a flight vehicle and one or more deployable panels, each of the one or more deployable panels comprising multiple solar collectors disposed on the deployable panel, each of the one or more shape-changeable hinges comprising:
a lid;
a body;
one or more morphable regions forming a first portion of the lid and the body, the one or more morphable regions comprising one or more shape-memory materials configured to cause a shape of the hinge to change;
one or more adiabatic regions disposed adjacent to the one or more morphable regions and forming a second portion of the lid and the body, wherein the one or more adiabatic regions are coated with one or more insulative materials; and
one or more heat pipes embedded in the one or more morphable regions and the one or more adiatabic regions, the one or more heat pipes configured to receive thermal energy from the solar collectors and transfer the thermal energy at least partially along a length of the hinge, the one or more heat pipes having a shape formed by one or more first indentations formed in an inner surface of the lid and one or more second indentations formed in an inner surface of the body, the one or more first indentations and the one or more second indentations aligning with each other to form the one or more heat pipes;
transferring the thermal energy between different ones of the regions using the one or more heat pipes; and
rejecting the thermal energy from the one or more shape-changeable hinges into an external environment;
wherein only the one or more morphable regions include the one or more shape-memory materials and the one or more adiabatic regions are formed from one or more other materials having high thermal conductivity.
13. A method comprising:
receiving thermal energy atone or more shape-changeable hinges coupled to one or more deployable panels and a flight vehicle, each of the one or more deployable panels comprising multiple solar collectors disposed on the deployable panel, each of the one or more shape-changeable hinges comprising:
a lid;
a body;
one or more morphable regions forming a first portion of the lid and the body, the one or more morphable regions comprising one or more shape-memory materials configured to cause a shape of the hinge to change;
one or more adiabatic regions disposed adjacent to the one or more morphable regions and forming a second portion of the lid and the body, wherein the one or more adiabatic regions are coated with one or more insulative materials; and
one or more heat pipes embedded in the one or more morphable regions and the one or more adiabatic regions, the one or more heat pipes configured to receive thermal energy from the solar collectors and transfer the thermal energy at least partially along a length of the hinge, the one or more heat pipes having a shape formed by one or more first indentations formed in an inner surface of the lid and one or more second indentations formed in an inner surface of the body, the one or more first indentations and the one or more second indentations aligning with each other to form the one or more heat pipes;
transferring the thermal energy at least partially along a length of each of the one or more shape-changeable hinges using the one or more heat pipes; and
changing a shape of at least one of the one or more shape-changeable hinges using the one or more shape-memory materials in the at least one shape-changeable hinge;
wherein only the one or more morphable regions include the one or more shape-memory materials and the one or more adiabatic regions are formed from one or more other materials having high thermal conductivity.
14. The method of claim 13 , further comprising:
folding the one or more deployable panels against the flight vehicle using the one or more shape-changeable hinges; and
unfolding the one or more deployable panels using the one or more shape-changeable hinges to deploy the one or more deployable panels extending away from the flight vehicle.
15. The method of claim 13 , wherein:
the one or more deployable panels comprise multiple deployable panels; and
the one or more shape-changeable hinges comprise multiple shape-changeable hinges.
16. The method of claim 15 , further comprising:
folding the deployable panels upon each other using the multiple shape-changeable hinges; and
unfolding the deployable panels using the multiple shape-changeable hinges to deploy the deployable panels extending away from the flight vehicle, the deployed panels having a larger exposed surface area than the folded panels.
17. The method of claim 13 , wherein the one or more morphable regions are configured to change shape.
18. The method of claim 17 , wherein each hinge further comprises:
one or more heat input regions configured to receive the thermal energy; and
one or more heat rejection regions configured to reject the thermal energy.
19. The method of claim 18 , wherein the one or more adiabatic regions are configured to provide structural support or reinforcement while at least substantially preventing heat transfer to and from an external environment.
20. The method of claim 13 , wherein the one or more heat pipes form an oscillating pattern within the one or more shape-memory materials.
21. The method of claim 13 , wherein, for each hinge, a bond line interface between the body of the hinge and the lid of the hinge is aligned with a neutral axis of the hinge.