Systems and methods for bonding objects using energetic welding
Systems and methods for bonding objects using energetic welding are disclosed. A representative system includes a launch vehicle portion, one or more landing support elements positioned to support the launch vehicle portion when the launch vehicle portion lands on a landing surface, and a bonding device carried by at least one of the landing support elements and configured to form a bond between the bonding device and the landing surface when the launch vehicle portion is on the landing surface. The bond may include a weld. A further representative system includes a bonding device with an energetic material and an anchor element, wherein activating the energetic material deforms the anchor element onto a landing surface to form a weld between the bonding device and the landing surface. A representative method includes automatically bonding a portion of a launch vehicle to a landing surface in response to landing.
1. An aerospace system comprising:
a launch vehicle portion;
one or more landing support elements carried by the launch vehicle portion and positioned to support the launch vehicle portion when the launch vehicle portion lands on a landing surface; and
a bonding device carried by at least one of the landing support elements and configured to form a weld between the bonding device and the landing surface when the launch vehicle portion is on the landing surface.
2. The aerospace system of claim 1 , wherein the bonding device comprises:
a layer of metal material; and
an energetic material positioned to deform the layer of metal material onto the landing surface to weld the layer of metal material to the landing surface.
3. The aerospace system of claim 1 , wherein the bonding device comprises an anchor element and an energetic material carried by the anchor element, wherein activation of the energetic material welds the anchor element to the landing surface.
4. The aerospace system of claim 3 , wherein the anchor element comprises:
a plate portion having a first side positioned to face the landing support element and a second side opposite the first side and positioned to face the landing surface;
a ring portion positioned on the first side of the plate portion and forming a first cavity; and
a second cavity extending into the second side of the plate portion;
wherein the plate portion includes a layer of metal material positioned between the first cavity and the second cavity, the second cavity is positioned to form a gap between the landing surface and the layer of metal material when the launch vehicle portion is on the landing surface, and the energetic material is positioned in the first cavity.
5. The aerospace system of claim 4 , wherein the layer of metal material is configured to deform in response to activation of the energetic material, and wherein activating the energetic material causes the layer of metal material to weld to the landing surface.
6. The aerospace system of claim 4 , further comprising a foam material positioned in the gap.
7. The aerospace system of claim 3 , wherein the anchor element is releasably attached to the landing support element.
8. The aerospace system of claim 7 , wherein the anchor element is releasably attached to the landing support element via one or more releasable fasteners.
9. The aerospace system of claim 1 , further comprising the landing surface, wherein the landing surface comprises steel.
10. The aerospace system of claim 9 , further comprising a floating platform carrying the landing surface.
11. The aerospace system of claim 1 , wherein:
the launch vehicle portion is a booster stage of a launch vehicle comprising one or more upper stages;
the booster stage comprises one or more rocket engine exhaust nozzles positioned toward an aft end of the booster stage, and
the one or more landing support elements are positioned toward the aft end of the booster stage.
12. The aerospace system of claim 1 , further comprising a controller programmed with instructions that, when executed:
determine at least one of (a) whether the launch vehicle portion has touched down or (b) whether a propulsion system of the launch vehicle portion has been shut off; and
in response to the determination, activating an energetic material to weld the bonding device to the landing surface.
13. An aerospace system comprising a bonding device configured to form a weld between the bonding device and a landing surface, wherein the bonding device comprises:
an anchor element comprising a layer of metal material; and
an energetic material carried by the anchor element and positioned to deform the layer of metal material in response to activation of the energetic material, wherein activating the energetic material deforms the layer of metal material to form the weld.
14. The aerospace system of claim 13 , further comprising a landing support element positioned to support a portion of a launch vehicle on the landing surface, wherein the anchor element is carried by the landing support element.
15. The aerospace system of claim 14 , further comprising the portion of the launch vehicle.
16. The aerospace system of claim 13 , further comprising the landing surface.
17. The aerospace system of claim 13 , wherein the anchor element comprises:
a plate portion including the layer of metal material; and
a cavity extending into the plate portion and positioned to form a gap between the layer of metal material and the landing surface when the bonding device is positioned on the landing surface.
18. The aerospace system of claim 17 , further comprising a foam material positioned in the gap.
19. A method of operating an aerospace system, the method comprising:
landing a portion of a launch vehicle on a landing surface; and
after landing, securing the portion of the launch vehicle to the landing surface via a weld using a bonding device carried by the portion of the launch vehicle.
20. The method of claim 19 , wherein securing the portion of the launch vehicle to the landing surface comprises securing a landing support element to the landing surface, wherein the landing support element is carried by the portion of the launch vehicle and the landing support element carries the bonding device.
21. The method of claim 19 , wherein securing the portion of the launch vehicle to the landing surface comprises determining if the portion of the launch vehicle has made contact with the landing surface or whether a propulsion system of the portion of the launch vehicle has been shut off, and wherein using the bonding device comprises using the bonding device in response to the determination.
22. The method of claim 19 , further comprising removing the portion of the launch vehicle from the surface by separating the portion of the launch vehicle from at least part of the bonding device.
23. The method of claim 22 , further comprising supporting the portion of the launch vehicle in an upright orientation using one or more releasable restraints.
24. The method of claim 19 , wherein securing the portion of the launch vehicle to the landing surface comprises activating an energetic material and deforming a layer of metal material onto the landing surface to weld the layer of metal material to the landing surface.
25. The method of claim 24 , further comprising removing the portion of the launch vehicle from the surface by separating the portion of the launch vehicle from the layer of metal material.
26. The method of claim 24 , wherein securing the portion of the launch vehicle to the landing surface comprises determining if the portion of the launch vehicle has made contact with the landing surface or whether a propulsion system of the portion of the launch vehicle has been shut off, and wherein activating the energetic material comprises activating the energetic material in response to the determination.
27. An aerospace system comprising:
a portion of a launch vehicle;
one or more landing support elements carried by the portion of the launch vehicle and positioned to support the portion of the launch vehicle when the portion of the launch vehicle lands on a landing surface;
a bonding device carried by at least one of the landing support elements and configured to form a weld between the bonding device and the landing surface when the portion of the launch vehicle is on the landing surface, wherein the bonding device includes an anchor element and an energetic material; and
a controller programmed with instructions that, when executed, determine at least one of (a) whether the launch vehicle portion has touched down or (b) whether a propulsion system of the launch vehicle portion has been shut off, and in response to the determination, activating the energetic material;
wherein upon activation of the energetic material, the energetic material is positioned to deform at least a portion of the anchor element toward the landing surface to form the weld.
28. The aerospace system of claim 27 , wherein at least a portion of the anchor element is releasably attached to the at least one of the landing support elements.
29. The aerospace system of claim 27 , wherein the anchor element supports the energetic material, and wherein the anchor element comprises a layer of metal positioned to deform onto the landing surface in response to activation of the energetic material, to form the weld.
30. The aerospace system of claim 27 , further comprising a platform carrying the landing surface, wherein the platform is configured to float on a body of water.