Printed spacecraft separation system
A spacecraft coupling system includes an integral component that can be deformed and placed into a stable state that locks one component into a mating component, and can easily be released from the deformed state, decoupling the two components. The integral component may include a central ring, a plurality of leaf elements arranged at the perimeter of the component, and a plurality of fins that extend outward from the ring to the plurality of leaf elements. A rotation of the ring element while the component is held stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently force the leaf elements against surfaces on the mating component. To reduce cost and complexity, the integral component is a metal, such as titanium, that can be formed using an additive manufacturing process, commonly termed a 3-D printing process.
1. A method comprising:
using a single additive manufacturing process to produce:
a first element that includes:
a core element situated at a center of the first element;
a plurality of leaf elements arranged at a perimeter of the first element;
a plurality of fins that extend outward from the core element to the plurality of leaf elements; and
a second element that includes a plurality of receiving surface areas corresponding to each of the plurality of leaf elements;
wherein the first element is arranged such that a rotation of the core element while the first element is stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently force the leaf elements against the receiving surface areas.
2. The method of claim 1 , wherein the first and second elements comprise titanium.
3. The method of claim 1 , including providing a locking element that maintains the force on the leaf elements while in a mechanically stable state.
4. The method of claim 3 , including providing a release element that places the locking element in a mechanically unstable state, causing the locking element to release the force on the leaf elements, thereby decoupling the first and second elements.
5. The method of claim 4 , wherein the locking element includes a lever, and the release element places the locking element in the mechanically unstable state by rotating the lever.
6. The method of claim 5 , wherein the release element includes an electric motor.
7. The method of claim 1 , wherein each leaf element includes a non-planar surface facing its corresponding receiving surface area, and the corresponding receiving surface areas includes a complementary non-planar surface for receiving the leaf elements.
8. The method of claim 7 , wherein at least one of the non-planar surface or the complementary non-planar surface includes one or more grooves.
9. The method of claim 1 , wherein each of the first and second elements include features that facilitate coupling the first and second elements to two vehicles that are to be coupled together.
10. The method of claim 9 , including providing the two vehicles.
11. The method of claim 10 , wherein the two vehicles include a spacecraft delivery vehicle and a payload vehicle.
12. The method of claim 1 , including providing springs that urge the second element away from the first element when the force on the leaf elements is released.
13. The method of claim 12 , wherein the springs are segments of at least one of the first and second elements.
14. The method of claim 1 , including creating structures in at least one of the first and second elements that accommodate electrical components.
15. The method of claim 1 , including creating structures in at least one of the first and second elements that facilitate routing of electrical cables.
16. The method of claim 1 , including creating structures in at least one of the first and second elements that facilitate coupling of the first and second elements without urging the leaf elements toward the receiving surface areas.
17. The method of claim 1 , including creating structures in at least one of the first and second elements that facilitate testing of the connector assembly.
18. The method of claim 1 , including creating structures in at least one of the first and second elements that facilitate transport of the connector assembly.
19. A computer-readable non-transitory medium that includes a database that, when executed by an additive process machine, causes the additive process machine to produce:
a first element that includes:
a core element situated at a center of the first element;
a plurality of leaf elements arranged at a perimeter of the first element;
a plurality of fins that extend outward from the core element to the plurality of leaf elements; and
a second element that includes a plurality of receiving surface areas corresponding to each of the plurality of leaf elements;
wherein the first element is arranged such that a rotation of the core element while the first element is stationary causes the fins to urge the leaf elements toward the receiving surface areas and to subsequently force the leaf elements against the receiving surface areas.