US-12617556-B2 - Material transfer interfaces for space vehicles, and associated systems and methods

Abstract

Material transfer interfaces for space vehicles, and associated systems and methods are disclosed. A representative system includes a first coupler configured to be carried by a first space vehicle, and a first valve device carried by the first coupler. The system further includes a second coupler configured to be carried by a second space vehicle and a second valve device carried by the second coupler. The first coupler includes rotatable and translatable latch arms positioned to engage with and connect to the second coupler. The first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler to transfer fluid between the first and second valve devices.

Inventors

• Alexander Deuitch
• Srinivasan A. Suresh
• Logan Fettes
• James Cho

Assignees

• Orbit Fab, Inc.

Dates

Publication Date

20260505

Application Date

20241031

Claims (20)

1. 1 . A fluid transfer system for space vehicles, the system comprising a first coupler and a first valve device carried by the first coupler, wherein the first coupler is configured to be carried by a first space vehicle, wherein the first coupler comprises a cam tube, a latch arm carrier, and latch arms, and wherein: the cam tube includes a cam slot; the latch arm carrier comprises a cam follower positioned in the cam slot; the latch arm carrier is translatable relative to the cam tube via relative motion between the cam follower and the cam slot; and the latch arms are pivotably connected to the latch arm carrier and moveable to engage a second coupler carried by a second space vehicle, wherein, when the latch arms are engaged with the second coupler, the first valve device is engageable with a second valve device associated with the second space vehicle to transfer fluid between the first space vehicle and the second space vehicle.
2. 2 . The system of claim 1 , further comprising a single motor coupled to all the latch arms.
3. 3 . The system of claim 2 , further comprising: a latch arm spring positioned to bias an individual latch arm toward a closed position; and a latch arm guide positioned to releasably hold the individual latch arm in the closed position.
4. 4 . The system of claim 1 wherein the first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler.
5. 5 . The system of claim 4 wherein: the probe of the first valve device is movable among at least three positions including a closed position, a check position and an open position; in the closed position, a fluid pathway through the first valve device is closed; in the open position, a fluid pathway through both the first and second valve devices is open; and in the check position, a fluid pathway is open through the first valve device, but not through the second valve device.
6. 6 . The system of claim 1 , further comprising an actuator operably coupled to the latch arms to move the latch arms between an open position and closed position, and a spring motor operably coupled to the latch arms to move the latch arms to either the open position or the closed position if the actuator fails.
7. 7 . The system of claim 1 , wherein: the cam slot extends circumferentially around at least a portion of the cam tube, and extends at least partially axially along at least part of a length of the cam tube; and the system further comprises an actuator operably coupled to the cam tube to rotate the cam tube.
8. 8 . The system of claim 1 , further comprising: a support tube positioned concentrically between the cam tube and the latch arm carrier; and a latch arm guide carried by the support tube; wherein when the latch arm carrier moves, the latch arm guide causes at least one of the latch arms to pivot.
9. 9 . The system of claim 1 wherein at least one of the first coupler or the second coupler includes a separator positioned to push the first and second couplers away from each other.
10. 10 . A fluid transfer system for space vehicles, the system comprising a first coupler and a first valve device carried by the first coupler, wherein the first coupler is configured to be carried by a first space vehicle, and wherein: the first coupler comprises a tube, a latch arm carrier, latch arms carried by the latch arm carrier, and a latch arm guide; the latch arms are movable and positionable to engage a second coupler carried by a second space vehicle, wherein when the latch arms are engaged with the second coupler, the first valve device is engageable with a second valve device associated with the second space vehicle to transfer fluid between the first space vehicle and the second space vehicle; the latch arm carrier is translatable relative to the tube and relative to the latch arm guide; at least one of the latch arms contacts the latch arm guide; and translation of the latch arm carrier causes the at least one of the latch arms to move relative to the latch arm guide, and contact between the at least one of the latch arms and the latch arm guide while the at least one of the latch arms moves relative to the latch arm guide causes the at least one of the latch arms to pivot.
11. 11 . The fluid transfer system of claim 10 wherein the first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler.
12. 12 . The fluid transfer system of claim 10 wherein the latch arm carrier is positioned within the tube.
13. 13 . The fluid transfer system of claim 10 wherein the tube is cam tube having a cam slot, the latch arm carrier has a cam follower, the cam follower is positionable in the cam slot, and rotation of the tube relative to the latch arm carrier causes the latch arm carrier to translate relative to the tube.
14. 14 . The fluid transfer system of claim 13 , further comprising a support tube positioned concentrically between the cam tube and the latch arm carrier, wherein the support tube carries the latch arm guide.
15. 15 . The fluid transfer system of claim 13 , wherein the latch arm guide comprises a roller configured to roll along a surface of the at least one of the latch arms when the at least one of the latch arms moves relative to the latch arm guide.
16. 16 . The fluid transfer system of claim 13 , further comprising an actuator operably coupled to the cam tube to rotate the cam tube.
17. 17 . The fluid transfer system of claim 16 wherein the cam tube carries a gear for coupling the actuator to the cam tube.
18. 18 . The fluid transfer system of claim 13 , further comprising a spring positioned to bias the at least one of the latch arms toward an open position or a closed position.
19. 19 . A fluid transfer system for space vehicles, comprising: a first coupler configured to be carried by a first space vehicle; a first valve device carried by the first coupler; a second coupler configured to be carried by a second space vehicle; and a second valve device carried by the second coupler; wherein: the first coupler includes rotatable and translatable latch arms positioned to engage with and connect to the second coupler, an actuator operably coupled to the latch arms to move the latch arms between an open position and a closed position, and a spring motor operably coupled to the latch arms to move the latch arms to an open position if the actuator fails; and the first valve device incudes a moveable probe that is insertable into the second valve device when the latch arms of the first coupler are connected to the second coupler to transfer fluid between the first and second valve devices.
20. 20 . The system of claim 19 , further comprising a latch arm guide, wherein: the first coupler comprises a tube and a latch arm carrier; the latch arms are movably attached to the latch arm carrier; the latch arm carrier is translatable relative to the tube and relative to the latch arm guide; and translation of the latch arm carrier relative to the tube causes at least one of the latch arms to move relative to the latch arm guide while contacting the latch arm guide, wherein movement of the at least one latch arms while contacting the latch arm guide causes the at least one of the latch arms to pivot.

Description

CROSS-REFERENCE TO RELATED APPLICATION(S) The present application is a continuation of U.S. patent application Ser. No. 17/864,251, filed on Jul. 13, 2022 (now U.S. Pat. No. 12,195,204), which claims priority to U.S. Provisional Patent Application No. 63/221,841, filed Jul. 14, 2021, each of which is incorporated herein by reference in its entirety. TECHNICAL FIELD The present disclosure is directed generally to material transfer interfaces for space vehicles, and associated systems and methods. BACKGROUND Existing space systems have several drawbacks. For example, launch vehicles may have limited volume and mass capacities. Spacecraft, such as satellites and/or other machines for traveling in space, are often launched to orbit with a limited quantity of fuel on board due to size and/or cost restrictions that must be balanced when designing the spacecraft for a particular mission. Accordingly, space missions may have limited lifetimes and/or utility due to limited fuel. Likewise, features and functions of spacecraft, such as the type and quantity of payload the spacecraft itself may carry, may be limited and/or compromised because the spacecraft may need to be launched full of all of the fuel it will need for its entire lifetime. Accordingly, there is a need for systems and methods to refuel spacecraft, especially spacecraft with long lifecycles intended to be on orbit for extended periods of time. Refueling a satellite is difficult or impossible with existing systems. For example, existing docking systems and procedures are complicated and two satellites or vehicles may have incompatible docking systems or no docking systems. Existing docking systems are also difficult or impossible to use autonomously. Existing docking systems also do not simultaneously provide adequate docking capabilities and material transfer interfaces (e.g., for filling and/or draining). Accordingly, there is a need for systems and methods for transferring materials in space that overcome the disadvantages of existing space systems. BRIEF DESCRIPTION OF THE DRAWINGS FIG. 1 is a partially schematic, isometric illustration of two space vehicles preparing to couple and transfer material in accordance with embodiments of the present technology. FIGS. 2A-2D are partially schematic, cross-sectional illustrations of a sequence for connecting two space vehicles in accordance with embodiments of the present technology. FIG. 3 is a partially schematic, isometric illustration of a first coupler used to couple a first space vehicle to a second space vehicle in accordance with embodiments of the present technology. FIGS. 4A-4D are partially schematic, cross-sectional illustrations of a sequence, similar to that shown in FIGS. 2A-2D, with further system details configured in accordance with embodiments of the present technology. FIG. 5 is a partially schematic side view of an arrangement for controlling the motion of a latch arm, in accordance with embodiments of the present technology. FIG. 6 is a partially schematic, partial cross-sectional exploded view of a plunger used to store energy when two space vehicles are coupled together. FIG. 7 is a partially schematic, exploded view of elements included in a first coupler configured in accordance with embodiments of the present technology. FIG. 8 is a partially schematic, cross-sectional view of a portion of the assembled elements of FIG. 7, configured to move coupler latch arms in accordance with embodiments of the present technology. FIG. 9 is a partially schematic, partially exploded illustration of elements included in a valve drive assembly configured in accordance with embodiments of the present technology. FIG. 10 is a partially schematic, isometric illustration of a valve device configured for a space vehicle in accordance with embodiments of the present technology. FIGS. 11A-11C are partially schematic, cross-sectional illustrations of an embodiment of the valve device shown in FIG. 10. FIG. 12 is a partially schematic, cross-sectional illustration of a valve device and driver arrangement for opening and closing the valve device, configured in accordance with embodiments of the present technology. FIGS. 13A and 13B illustrate an arrangement for locking a valve drive device in an open position, in accordance with embodiments of the present technology. FIG. 14 is a partially schematic, exploded illustration of a valve drive assembly positioned on a mounting flange, with a housing positioned to secure the device in accordance with embodiments of the present technology. FIG. 15 is a partially schematic, isometric illustration of a second coupler, configured to be carried by a second spacecraft, and configured to mate with a first coupler carried by a first spacecraft in accordance with embodiments of the present technology. FIG. 16 is a partially schematic, partially exploded illustration of the second coupler shown in FIG. 15. FIG. 17A illustrates a representative second valve device with valv