Valves for transferring materials to spacecraft and associated systems and methods

Abstract

Valves and associated systems and methods for transferring materials to spacecraft are disclosed. A representative system includes a valve device configured to be carried by a spacecraft (e.g., as part of a coupler for joining with another spacecraft). The valve device can include: a body; a bore extending along a longitudinal axis of the body, the bore having a tapered interior surface; and one or more tapered seal retention elements positioned in the body and movable along the longitudinal axis. The tapers of the one or more seal retention elements can correspond to the tapered interior surface of the body, such that one or more seal elements carried by the one or more seal retention elements can form seal interfaces with the tapered interior surface. The one or more seal retention elements are movable to selectively open and close the valve (e.g., via a probe carried by another spacecraft).

Description

VALVES FOR TRANSFERRING MATERIALS TO SPACECRAFT ANDASSOCIATED SYSTEMS AND METHODSCROSS-REFERENCE TO RELATED APPLICATION(S)

[0001] The present application claims priority to U.S. Provisional Patent Application No. 63 / 572,127, filed March 29, 2024, and which is incorporated herein by reference in its entirety.TECHNICAL FIELD

[0002] The present disclosure is directed generally to material transfer interfaces for spacecraft, and associated systems and methods. More particularly, the present disclosure is directed to valves for transferring materials to and from spacecraft, and associated systems and methods.BACKGROUND

[0003] Existing space systems have several drawbacks. For example, launch vehicles may have limited volume and mass capacities. Spacecraft, such as space vehicles, 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. 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 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.

[0004] Refueling a satellite is difficult or impossible with many existing systems. For example, many existing docking systems and procedures are complicated, and two satellites or other types of spacecraft may have incompatible docking systems or no docking systems. Existing docking systems may be difficult or impossible to use autonomously. Existing docking systems may not simultaneously provide adequate docking capabilities and material transfer interfaces (e.g., for filling and / or draining). Some existing systems also include valves with a large amount of components that tend to increase weight and / or difficulty and cost in manufacturing and assembly.

[0005] Existing valves for transferring materials in space also suffer from several drawbacks. For example, many existing valves have a large number of components or moving parts that increase risk of failure. Additionally, many existing valves cannot withstand repeated use with corrosive fluids or extremely hot or cold fluids without leaking. Leakage is a critical problem in a space environment where waste or loss can be expensive and highly inefficient.BRIEF DESCRIPTION OF THE DRAWINGS

[0006] Figure l is a partially-schematic, isometric illustration of two spacecraft preparing to couple and transfer material in accordance with embodiments of the present technology.

[0007] Figures 2A-2D are partially-schematic, cross-sectional illustrations of portions of couplers for connecting two spacecraft, in various stages of a connection sequence, in accordance with embodiments of the present technology.

[0008] Figure 3 is a partially-schematic, isometric illustration of a coupler configured to be carried by a spacecraft and configured to mate with another coupler carried by another spacecraft, in accordance with embodiments of the present technology.

[0009] Figure 4 illustrates an exploded perspective view of the coupler shown in Figure 3.

[0010] Figure 5A illustrates a partially-schematic cross-sectional view of a valve device configured in accordance with embodiments of the present technology.

[0011] Figure 5B illustrates a detailed view of a portion of the valve device shown in Figure 5A.

[0012] Figure 5C illustrates a partially-schematic exploded view of the valve device shown in Figure 5A.

[0013] Figure 5D illustrates a partially-schematic cross-sectional view of selected components of the valve device shown in Figure 5A.

[0014] Figure 5E illustrates a detailed side view of a first movable seal retention element for a valve device, configured in accordance with embodiments of the present technology.

[0015] Figure 5F illustrates a detailed side view of a second movable seal retention element for a valve device, configured in accordance with embodiments of the present technology.

[0016] Figure 6A illustrates a partially-schematic cross-sectional view of portions of the valve device shown in Figure 5A, in a pre-mated or closed state, in accordance with embodiments of the present technology.

[0017] Figure 6B illustrates a partially-schematic cross-sectional view of the portions of the valve device shown in Figure 6A, in a mated or open state, to illustrate a fluid flow path through the valve device in accordance with embodiments of the present technology.DETAILED DESCRIPTION

[0018] Several embodiments of the present technology are directed to systems and methods for transferring materials (e.g., liquids, gases, solids, and / or other materials) in space and / or on a planetary and / or lunar surface. In particular, several embodiments of the present technology are directed to valves for transferring materials to and from spacecraft and associated systems and methods.

[0019] A representative system includes a first coupler configured to be carried by a first spacecraft, and a first valve device carried by the first coupler. The system further includes a second coupler configured to be carried by a second spacecraft, and a second valve device carried by the second coupler. The first valve device includes a movable probe that is insertable into the second valve device when the second coupler is connected to the first coupler (e.g., using latch arms or another suitable mechanism). Couplers that may carry or implement embodiments of the present technology can include, for example and without limitation, couplers described in U.S. Patent No. 12,195,204 (corresponding to U.S. Patent Application No. 17 / 864,251) and / or in U.S. Patent No. 12,187,466 (corresponding to U.S. Patent Application No. 17 / 211,547), each of which is incorporated herein by reference. Other couplers may carry or implement embodiments of the present technology, and / or valve devices disclosed herein may be implemented independently of couplers or in other suitable implementations.

[0020] Many specific details of some embodiments of the present technology are set forth in the following description and in Figures 1-6B to provide a thorough understanding of these embodiments. Well-known structures, systems, and methods that are often associated with aerospace vehicles, couplers, valves, or other structures for transferring materials may not be shown or described in detail herein to avoid unnecessarily obscuring some significant aspects of the disclosure. Moreover, although the following disclosure sets forth some embodiments of the technology, other embodiments of the technology can have different configurations and / ordifferent components than those described herein. As such, the technology can include embodiments with additional elements, and / or without several of the elements described below with reference to the figures.

[0021] The terminology used below is to be interpreted in its broadest reasonable manner, even though it is being used in conjunction with a detailed description of certain examples of embodiments of the technology. Indeed, certain terms may even be emphasized below; however, any terminology intended to be interpreted in any restricted manner will be overtly and specifically defined as such in this Detailed Description.

[0022] The accompanying figures depict embodiments of the present technology and are not intended to be limiting of its scope. The sizes of various depicted elements are not necessarily drawn to scale, and these various elements may be arbitrarily enlarged in the figures to improve legibility. Component details may be abstracted in the figures to exclude details such as positions of components, and certain precise connections between such components, when such details are unnecessary for a complete understanding of how to make and use the present technology. Many of the details, dimensions, angles and / or other features shown in the figures are merely illustrative of particular embodiments of the present technology. Accordingly, other embodiments can have other details, dimensions, angles, and / or features without departing from the spirit or scope of the present disclosure. In general, identical reference numbers in the figures identify at least generally similar (e.g., identical) elements.

[0023] Reference is made herein to “space.” Space includes orbital space near or around the Earth, the Moon, and / or another planetary body. A person of ordinary skill in the art will also recognize that embodiments of the present technology can be implemented near other planetary or lunar surfaces, or on a surface (e.g., on Earth). Reference is also made herein to fuel and propellant. A person of ordinary skill in the art will understand that the terms fuel and propellant can be used interchangeably when referring to a substance for powering and / or propelling a spacecraft and can include oxidizers that function as propellant when combined with fuels. A person of ordinary skill in the art will also understand that when reference is made to transferring a fuel or propellant, corresponding embodiments can be used to transfer other materials, such as a pressurant, water, coolant, waste, and / or other materials that can be transferred between two spacecraft and / or two containers. In addition, a person of ordinary skill in the art will understand that a spacecraft can include any human-made object in space. Several embodiments of the present technology can also be implemented in a terrestrial application onland (e.g., in automobiles or other ground-based vehicles), sea (e.g., in boats, submarines, etc.), and / or in an atmosphere (e.g., in aircraft, dirigibles, etc.), and / or in applications not necessarily involving vehicles (e.g., stationary containers).

[0024] The present disclosure describes systems and / or devices, including material transfer interfaces, configured to facilitate transferring materials (such as fluids, including fuel, propellant, and / or other liquid or gaseous materials) between containers (such as containers carried by spacecraft) in an extraterrestrial environment, such as in space, or on extraterrestrial bodies such as moons, planets, and / or asteroids, and / or on Earth or within Earth's atmosphere. The present technology also includes coupling systems for connecting spacecraft to each other, such as in a rendezvous and / or docking maneuver. Accordingly, embodiments of the present technology provide spacecraft with the capability to refuel and extend their useful life and / or to expel waste materials, among other advantages. Although some embodiments are directed to autonomous material transfer activities, activities performed by systems and / or spacecraft disclosed herein can be semi-autonomous or non-autonomous, and can include assistance by robots, artificial intelligence, and / or humans.A. System Overview

[0025] Figure 1 is a partially-schematic, isometric illustration of a first spacecraft 101 positioned to dock with a second spacecraft 201 to transfer materials between the two spacecraft 101, 201.

[0026] In a particular embodiment, the first spacecraft 101 is or includes a service vehicle, for example, a space tug, or a fuel transfer vehicle. The second spacecraft 201 can be or include a satellite or another spacecraft to which materials are delivered, and / or from which materials are received. To transfer materials between the two spacecraft, each spacecraft includes a portion of an overall transfer interface system 100. Accordingly, the first spacecraft 101 can include a first coupler 150, and the second spacecraft 201 can include a second coupler 162. In many instances, fluids are transferred between the first spacecraft 101 and the second spacecraft 201. For example, and as described above, suitable fluids can include propulsion fluids transferred from the first spacecraft 101 to the second spacecraft 201 to enable the second spacecraft 201 to carry out further missions. Accordingly, the first coupler 150 can include a first valve device 155, and the second coupler 162 can include a second valve device 220. When the two couplers 150, 162 are connected, the two valve devices 155, 220 can transfer fluids and / or other materials between the two spacecraft 101, 201. Further details of representativesystems for coupling the spacecraft and, specifically, transferring fluids between the spacecraft, are described below.

[0027] The transfer interface system 100 can include a controller system 103 that, with or without human assistance, directs the operation of coupling the two spacecraft 101, 201, and / or transferring materials between the two spacecraft. The controller system 103 can accordingly include a first controller 102 carried by the first spacecraft 101, and a second controller 202 carried by the second spacecraft 201. The controller system 103 can further include an off-board controller 104 that is carried by neither the first spacecraft 101 nor the second spacecraft 201 but is instead located externally. For example, the off-board controller 104 can be carried or positioned on Earth.

[0028] Figures 2A-2D are partially-schematic, cross-sectional, simplified illustrations of portions of the first coupler 150 (carried by the first spacecraft 101 shown in Figure 1), in various stages of a connection sequence with the second coupler 162 (carried by the second spacecraft 201, also shown in Figure 1) in accordance with embodiments of the present technology.

[0029] Beginning with Figure 2A, in some embodiments, the first coupler 150 can include one or more latch arms 151 (e.g., four; two are shown in Figure 2A) that are configured to be received in corresponding arm receivers 211 carried by the second coupler 162. The process for connecting the two couplers 150, 162 can include a “soft latch” process, and a “hard latch” process. The soft latch process positions the two couplers 150, 162 close to each other, but with tolerance for at least some movement by either spacecraft (see Figure 2C, described in further detail below). The hard latch process eliminates or at least significantly reduces / minimizes relative movement between the two spacecraft (see Figure 2D, described in further detail below). In the hard latch configuration, the two couplers 150, 162 are engaged to begin a fluid transfer process.

[0030] Next, in Figure 2B, the latch arms 151 begin to pivot toward the arm receivers 211, as indicated by two arrows A. Next, in Figure 2C, the two latch arms 151 are received in the corresponding arm receivers 211, to place the two couplers 150, 162 in the soft latch configuration. In this configuration, each coupler 150, 162 can move slightly with respect to the other, but the latch arms 151 prevent either coupler from completely disengaging from the other.

[0031] Once the latch arms 151 have completed the soft latch maneuver, the latch arms 151 move downwardly, toward the first coupler 150, as indicated by two arrows B. Figure 2D shows the latch arms 151 moved to a full downward position, preventing further motion betweenthe first coupler 150 and the second coupler 162 in the hard latch configuration. At this point, the two couplers 150, 162 are sufficiently latched to each other to begin a fluid transfer process. Generally reversing the process shown in Figures 2A-2D decouples the couplers 150, 162.

[0032] In some embodiments, the first coupler 150 may be generally similar to, or have several features of, the “first coupler 150” described in U.S. Patent No. 12,195,204 (previously incorporated by reference herein), such as the latch arms and the movement thereof.

[0033] The foregoing latching / coupling process and couplers are for example context only. Accordingly, other embodiments of the present technology can include other couplers and / or other methods of coupling, and valve devices disclosed herein can be used in other couplers and / or methods of coupling.B. Valve Operation - First Spacecraft

[0034] Before providing additional detail regarding the second valve device 220 (see Figure 1), general functionality of a first valve device 155 of the first spacecraft 101 will now be described for the purpose of providing examples of valve devices that can engage or otherwise work with the second valve device 220. With reference again to Figure 1, the first valve device 155 associated with the first coupler 150 can include a probe element that extends from the first coupler 150 to enter a portion of the second coupler 162 (specifically, to enter the second valve device 220 of the second coupler 162). The probe element can include passageways or otherwise be configured to conduct material between the first coupler 150 and the second coupler 162 when the probe element of the first valve device 155 is engaged with the second valve device 220 of the second coupler 162. For example, briefly referring to Figures 6A and 6B, which are described in additional detail below, a probe 600 is shown schematically as being engaged within a second valve device (labeled “310” in Figures 6A and 6B). Accordingly, the probe 600 in Figures 6A and 6B is an example of a suitable probe element of the first valve device 155.

[0035] In some embodiments, for example, the first coupler 150 may include elements and / or functionality of the “first valve device 160” and / or the “probe 163” described in U.S. Patent No. 12,195,204 (see, e.g., Figures 9-14), such as the elements for opening and closing the “first valve device 160” (e.g., elements to move the “probe 163” relative to the “valve housing 191”). Accordingly, systems configured in accordance with embodiments of the present technology can include the first valve device described in U.S. Patent No. 12,195,204, along with the second valve devices described in further detail below.

[0036] In general, embodiments of the present technology may include or be implemented with suitable couplers having a probe that extends and retracts for fluidly engaging or disengaging a valve in the second coupler 162 of the present technology.C. Second Coupler and Valve Operation - Second Spacecraft

[0037] Figure 3 illustrates a perspective view of at least part of a second coupler 300 configured in accordance with embodiments of the present technology. The second coupler 300 and its valves described below can be implemented as the second coupler 162 described above in connection with Figures 1-2C, and / or it can be implemented in other systems. In Figure 3, the second coupler 300 is shown upside-down relative to the illustrations of the second coupler 162 described above. The second coupler 300 can include a body or housing 305 carrying one or more second valve devices 310. In the embodiment shown in Figure 3, the housing 305 carries two second valve devices 310, corresponding to two first valve devices carried by the first spacecraft. Each second valve device 310 can include a first port 315 and a second port 320 that can be in fluid communication when the second valve device 310 is open, and which are isolated from fluid communication with each other when the second valve device 310 is closed. The housing 305 can include arm receivers 211 to receive latch arms 151 of a first coupler 150 for docking / latching as described above with regard to Figures 1-2C.

[0038] Figure 4 illustrates an exploded perspective view of the second coupler 300 shown in Figure 3. In some embodiments, the housing 305 includes one or more recesses 400 for receiving corresponding bodies 405 of the second valve devices 310. Each body 405 of the second valve devices 310 can be fixed to the housing 305, e.g., via one or more fasteners 410 passing through a flange 412 or other portion of the body 405 and engaging one or more surfaces inside the one or more recesses 400. In some embodiments, the housing 305 can include a cover 415 with openings or through-holes 420 for portions of the bodies 405 to pass through (e.g., to facilitate access to the second ports 320 from outside of the housing 305). The cover 415 can be fixed to the remainder of the housing 305 via one or more additional fasteners 425. In general, embodiments of the present technology can include any suitable housing, body, enclosure, and / or support structure for supporting the second valve devices 310 in a manner suitable for the second valve devices 310 to receive corresponding probes from the first valve devices.

[0039] Figure 5A illustrates a partially-schematic cross-sectional view of one of the second valve devices 310, configured in accordance with embodiments of the present technology. Figure 5B illustrates a detailed view of a portion of Figure 5 A. Figure 5C illustratesa partially-schematic exploded view of one of the second valve devices 310, configured in accordance with embodiments of the present technology. Figure 5D illustrates a partially- schematic cross-sectional view of selected components of one of the second valve devices 310 (i.e., omitting some of the components shown in Figure 5A), for additional clarity and context of several components of the second valve device 310, in accordance with embodiments of the present technology. In Figures 5A, 5B, and 5C, the second valve device 310 is in a closed configuration, such that there is not a fluid connection between the first port 315 and the second port 320.

[0040] With reference to each of Figures 5A, 5B, 5C, and 5D, the second valve device 310 can include the body 405, which can be generally hollow with a main bore 406 extending therethrough. The body 405 can include the first port 315 and the second port 320. In some embodiments, the body 405 can include a body cap 500. In some embodiments, the body cap 500 is separate from, but attached to, the body 405 (e.g., by welding or another suitable mode of attachment). In some embodiments, the body cap 500 and the body 405 may be formed as a unitary / integral structure. In some embodiments, the body cap 500 can include the first port 315. In some embodiments, the body cap 500 includes a tubular extension portion 505 extending axially away from the body 405, with the first port 315 being positioned at a terminal end 507 of the tubular extension portion 505, although the tubular extension portion 505 is optional and may be omitted, such that the first port 315 can be an opening directly adjacent to the main bore 406. In some embodiments, the first port 315 (e.g., at the terminal end 507 of the tubular extension portion 505 or directly adjacent to the main bore 406) can include and / or carry a fitting 510 for connecting the valve device 310 to plumbing associated with the second spacecraft 201 (e.g., plumbing associated with connections to a fluid reservoir acting as a fluid source and / or a fluid sink).

[0041] With specific reference to Figure 5D, the body 405 and body cap 500 (with optional tubular extension portion 505) form a fluid flow path 515 (shown schematically as a dashed line) between the first port 315 and the second port 320 and / or between the first port 315 and a probe positioned in the second port 320 as explained in further detail below. The fluid flow path 515 can be selectively obstructed by other components of the second valve device 310, such as the components shown in Figures 5A, 5B, and 5C. For convenience in description and illustration, the dashed line in Figure 5D is also labeled X to represent the central longitudinal axis of the second valve device 310. In some embodiments, the main bore 406 can taper from a wider portion at the first port 320 to a narrower portion, in addition to a taper from a wider portion forreceiving the first movable seal retention element 520 to the narrower portion. The taper from the first port 320 may help guide or align a probe entering the main body 405.

[0042] Representative components that selectively obstruct or open the fluid flow path 515 are shown in Figures 5 A, 5B, and 5C. For example, in some embodiments, the second valve device 310 can include a first movable seal retention element 520, a second movable seal retention element 525, a biasing element 530 (e.g., a compression spring biased toward expansion), a first seal element 535 carried by the first movable seal retention element 520, and / or a second seal element 540 carried by the second movable seal retention element 525, one or more of which (such as all) can be aligned coaxially along the longitudinal axis X.

[0043] Operation of the components that selectively obstruct or open the fluid flow path 515 can be understood with observation of at least Figures 5 A and 5B. With continuing reference to at least Figures 5A and 5B, in operation, a probe (e.g., a hollow and / or tubular probe having its own fluid flow pathway, such as the probe described above in Section B for the first coupler 150) may enter the second port 320 and push on the second movable seal retention element 525, which in turn pushes the first movable seal retention element 520 against the biasing force (e.g., spring force) of the biasing element 530, causing the second movable seal retention element 525 and the first movable seal retention element 520 to move axially by a distance D (see Figure 5B) between the first movable seal retention element 520 and a travel-limiting element associated with the body 405, such as the body cap 500, thereby separating each of the first seal element 535 and the second seal element 540 from an interior wall 545 of the body 405 and allowing fluid to pass between the interior wall 545 of the body 405 and the components inside the body 405 (e.g., the first movable seal retention element 520, the second movable seal retention element 525, the first seal element 535, and / or the second seal element 540), through the body cap 500, and through the first port 315. The interior wall 545 forms an outer boundary of the fluid flow path 515 as it passes by and / or through the moving components within the body 405. Operation of the components of the valve device 310 is further explained below with regard to additional illustrations in Figures 6A and 6B.

[0044] With continued reference to at least Figure 5B, the first and second seal elements 535, 540 may be in the form of O-rings, such as O-rings composed of an elastomeric compound (e.g., ethylene propylene diene monomer or “EPDM,” which is compatible with corrosive fluids such as hydrazine). In the illustrated embodiment, the first and second seal elements 535, 540 form independent redundant seals between their corresponding retention elements 520, 525. Forexample, even if fluid were to breach one of the seals 535, 540, the other seal 535, 540 remains capable of blocking the flow. In some embodiments, as explained in additional detail below with regard to Figures 5E and 5F, one or both of the seal retention elements 520, 525 can include tapered surfaces for engaging tapered surfaces within the main bore 406, such as a tapered portion of the interior wall 545 of the body 405. The seal interfaces formed by the seal elements 535, 540 and one or both of the movable seal retention elements 520, 525 against the surface of the interior wall 545 of the body 405 can be canted relative to the longitudinal axis X (see Figure 5D), for example, by an angle between 20 degrees and 30 degrees relative to a line parallel to the longitudinal axis X (e.g., 22 degrees ± 1 degree), or another suitable angle.

[0045] Figure 5E illustrates a detailed side view of the first movable seal retention element520 configured in accordance with embodiments of the present technology. With reference to Figures 5B and 5E together, in some embodiments, the first movable seal retention element 520 can include a cylindrical body portion 550, a radially inwardly tapering orifice portion 553, a radially inwardly tapering seal retention portion 555, and a cup portion 560 having a radially extending flange 563, such that the seal retention portion 555 can, in some embodiments, form a circumferential notch 564 (which may have a trapezoidal shape). In some embodiments, a radially inward side 564a of the circumferential notch 564 can optionally be parallel to the interior wall 545 of the body 405 adjacent to the first seal element 535. In some embodiments, a distance D2 between the radially extending flange 563 and the body portion 550 is greater than a width or thickness (e.g., cross-sectional diameter) of the seal element 535, which allows the seal element 535 to deform into the seal retention portion 555 when the valve device 310 is closed to form an adequate seal resisting (e.g., preventing) flow past the first seal element 535.

[0046] Referring again to Figure 5B, the cylindrical body portion 550 can include a longitudinally aligned interior bore 557 for receiving at least part of the biasing element 530. At an end of the longitudinally aligned bore 557, the first movable seal retention element 520 can include one or more (e.g., a plurality of) fluid flow channels 559 in fluid connection with the bore 557 and with orifices 561 distributed around a perimeter of the orifice portion 553. The bore 557 is also in fluid communication with the body cap 500 and / or the first port 315 (e.g., via the tubular extension portion 505). The interior wall 545 can generally obstruct the orifices 561 when the valve device 310 is closed, and the orifices 561 may be unobstructed when the valve device 310 is opened (i.e., when the orifices 561 are moved away from the interior wall 545). The tapering geometry of the tapering orifice portion 553 and the seal retention portion 555facilitates opening the fluid flow path 515 when the first movable seal retention element 520 moves away from the second port 320.

[0047] Figure 5F illustrates a detailed side view of the second movable seal retention element 525 configured in accordance with embodiments of the present technology. With reference to Figures 5B and 5F together, in some embodiments, the second movable seal retention element 525 can include a cylindrical base portion 565, a seal retention portion 567 that tapers inwardly from its first end 567a as it extends from the cylindrical base portion 565 (the first end 567a can be wider than the cylindrical base portion 565), and a flange portion 569 that tapers inwardly from its first end 569a as it extends from the seal retention portion 567 (the first end 569a can be wider than a second end 567b of the seal retention portion 567), such that the second movable seal retention element may have a staggered shape.

[0048] With reference again to Figure 5B, in some embodiments, the cylindrical base portion 565 can be positionable to seat inside the cup portion 560 of the first movable seal retention element 525, such that part of the flange 563 of the first movable seal retention element 525, along with the seal retention portion 567, form a boundary for the second seal element 540. The seal retention portion 567 of the second movable seal retention element 525, along with the edge of the flange 563 of the first movable seal retention element 520, can form another notch 571 (e.g., a circumferential notch, which can have a trapezoidal cross-sectional shape) for the second seal element 540, in which a radially inward side 571a of notch 571 is optionally parallel to the interior wall 545 adjacent to the second seal element 540. In some embodiments, a distance D3 between the radially extending flange 563 and the inwardly tapered flange portion 569 is greater than a width or thickness (e.g., cross-sectional diameter) of the second seal element 540, which allows the second seal element 540 to deform into the seal retention portion 567 when the valve device 310 is closed, to form an adequate seal resisting (e.g., preventing) flow past the second seal element 540.

[0049] The tapered or canted geometry of the seal retention portions 555, 567 and the circumferential recesses / notches 564, 571 they form to receive the seals 535, 540, along with a corresponding tapered geometry of the interior wall 545, forms the redundant seal interfaces between the seals 535, 540 and the interior wall 545, which open when the retention elements 520, 525 move away from the second port 320. The matching or complementary geometries of the seal retention portions 555, 567 and the interior wall 545 can also be characterized as concentric conical shapes having parallel sides.

[0050] In some embodiments, optionally, the second seal retention element 525 can include an interior bore 570. Optionally, another biasing element (e.g., a compression spring, not shown in Figure 5B, but which is visible in Figures 6A and 6B as the biasing element 605) can be positioned in the bore 570 between the first and second movable seal retention elements 520, 525, to bias them away from each other, e.g., to further improve the seal interface between the second seal element 540 and the interior wall 545. However, in some embodiments, the interior bore 570 and the additional biasing element therein can be omitted. In some embodiments, when the seal retention elements 520, 525 are two separate elements, they can facilitate interstitial pressure relief if the bore 570 is pressurized. However, in some other embodiments, the retention elements 520, 525 can be attached together or integral with each other, forming a single retention element carrying both seal elements 535, 540.

[0051] In some embodiments, one or more components, such as the seal elements 535, 540, can be lubricated using suitable materials, such as KRYTOX brand lubricant available from The Chemours Company FC, LLC, or another lubricant suitable for corrosive environments and / or environments with extreme temperatures. Aside from the seal elements 535, 540, components of the second valve device 310 may be made of one or more metal materials, such as alloys suitable for corrosive fluids, extreme temperatures, and precision manufacturing processes. Although several parts are described and illustrated as being cylindrical relative to the longitudinal axis X, in some embodiments, components may have other cross-sectional shapes. In some embodiments, one or more surfaces of elements of the technology can include conductive surfaces or coatings to resist accumulation of a static charge.D. Combined Valve Operation - First and Second Spacecraft

[0052] Figure 6A illustrates a partially-schematic cross-sectional view of portions of the valve device shown in Figure 5A, in a pre-mated or closed state, in accordance with embodiments of the present technology. Figure 6B illustrates a partially-schematic cross- sectional view of the portions of the valve device shown in Figure 6A, in a mated or open state, to illustrate a fluid / material flow path through the valve device in accordance with embodiments of the present technology. A dotted pattern in Figures 6A and 6B illustrates the presence of fluid / material. As understood from the foregoing description, when the valve is open (see Figure 6A), fluid may flow between the first port 315 (see Figure 5 A) and the second port 320. In some embodiments that implement a probe to open the valve, as described in further detail below,when the valve is open, fluid may pass between the first port 315 (see Figure 5 A) and the probe within the second port 320.

[0053] With reference to Figure 6 A, in the pre-mated state, a spacecraft having the second valve device 310 may already have some fluid (e.g., propellant or fuel) onboard. For example, the spacecraft having the second valve device 310 may be a satellite that requires refueling but which may still have at least some fuel remaining onboard, or which was already fueled or refueled. However, in some circumstances, the second valve device 310 may be empty when in the pre-mated state. The dotted pattern of fluid in Figure 6A representing some fluid onboard is helpful to illustrate functionality of the seals that resist (e.g., prevent) the fluid from leaking out of the second valve device 310 when it is not engaged with another valve device. Because the bore 557 is in fluid communication with the first port 315 (see Figures 5A and 5B), fluid may already be in the bore 557, around the biasing element 530 and in the fluid flow channels 559, up to the first seal element 535. The first seal element 535 is positioned and configured to block fluid from passing beyond the seal interface it forms with the interior wall 545 of the body 405 when the second valve device 310 is in the closed configuration generally shown in Figure 6A. However, if the fluid flows past the first seal element 535, the redundant second seal element 540 is also positioned and configured to block fluid flow past the sealing interface that the second seal element 540 forms with the interior wall 545 of the body 405. In the pre-mated state, the seal retention elements 520, 525 are biased toward positions that close the valve (i.e., the closed valve configuration) due to fluid pressure and / or force from the biasing element 530 (and the optional additional biasing element 605 in the interior bore 570 of the second seal retention element 525). In some embodiments, in the premated / closed state, the second valve device 310 can seal against up to 400 psig without leaking. In other embodiments, other pressures can be accommodated.

[0054] With reference to Figure 6B, in the mated state, the probe 600 (e.g., from the first spacecraft 101 or the first coupler 150) entering the second port 320 (see also, Figure 5 A) can press the seal retention elements 520, 525 against the fluid pressure and / or against the force from the biasing element 530 (e.g., as far as the distance D), to move the seal retention elements 520, 525, which opens the seal interfaces previously formed by the seal elements 535, 540. In the open configuration, there is a gap 610 adjacent to the interior wall 545 through which the fluid can flow, e.g., from the probe 600, through the gap 610, into the orifices 561 (see Figure 5E), through the channels 559, into the bore 557, through the body cap 500, and through the first port 315 (see Figure 5 A). In some embodiments, flow may be bidirectional such that opening thevalve in the mated state can permit fluid to flow from the bore 557 into the probe 600 (e.g., via orifices in the probe 600). In some embodiments, the probe 600 can include its own seal elements 615 (e.g., two, for redundancy) to seal against the main bore 406 to resist or prevent fluid from leaking past the probe 600, such that the fluid can exit the body 405 via the second port 320 only through the probe 600. Such flow can be controlled with suitable pumps or other devices connected to the corresponding valve devices.E. Examples

[0055] Several aspects of the present technology are set forth in the following examples. Embodiments of the present technology may include more or different features than those listed in the examples, they may omit one or more features from the examples, and / or features in some examples may be combined with features in other examples. The examples do not limit the scope of the embodiments of the present technology.1. A fluid transfer system for transferring a fluid between a first spacecraft and a second spacecraft, the system comprising: a first coupler configured to be carried by the first spacecraft, wherein the first coupler is configured to engage a second coupler carried by the second spacecraft; and a valve device carried by the first coupler, wherein the valve device comprises: a body having a first port and a second port; one or more movable seal retention elements positioned in the body and aligned coaxially with the body; and a biasing element aligned coaxially with the body and positioned between the one or more movable seal retention elements and the body; wherein — the first port is configured to receive a probe carried by the second coupler, and when the first port receives the probe, the probe moves the one or more movable seal retention elements from a first position in which the valve device resists fluid flow past the one or more movable seal retention elements to a second position in which first port is in fluid communication with the second port and / or the probe.2. The fluid transfer system of example 1, further comprising the probe.3. The fluid transfer system of example 1 or example 2, further comprising the second coupler.4. The fluid transfer system of any one of examples 1-3 wherein the body comprises a main bore having one or more tapered interior surfaces.5. The fluid transfer system of example 4 wherein the one or more movable seal retention elements comprise one or more tapered surfaces, and wherein the one or more movable seal retention elements form canted seal interfaces with a first tapered interior surface of the one or more tapered interior surfaces of the body when the one or more movable seal retention elements are in the first position.6. The fluid transfer system of any one of examples 1-5 wherein the body includes a body cap carrying the first port.7. The fluid transfer system of example 6 wherein the body cap includes a tubular extension portion, and wherein the first port is positioned at a terminal end of the tubular extension portion.8. The fluid transfer system of any one of examples 1-7 wherein the one or more movable seal retention elements comprise: a first movable seal retention element positioned in the body and movable coaxially within the body; and a second movable seal retention element positioned in the body, movable coaxially within the body, and positioned adjacent to the first movable seal retention element.9. The fluid transfer system of example 8 wherein the second movable seal retention element comprises a portion positionable within a cup portion of the first movable seal retention element.10. The fluid transfer system of any one of examples 1-9 wherein the one or more movable seal retention elements carry a first seal element and a second seal element.11. The fluid transfer system of any one of examples 1-10 wherein the one or more movable seal retention elements comprise an interior bore in fluid communication with the first port.12. The fluid transfer system of example 11 wherein the biasing element comprises a compression spring positioned in the interior bore of the one or more movable seal retention elements.13. The fluid transfer system of example 11 or example 12 wherein the one or more movable seal retention elements comprise one or more fluid flow channels in fluid communication with the interior bore, wherein the one or more fluid flow channels are in fluid communication with the second port when the one or more movable seal retention elements are in the second position.14. A valve device compri sing : a body having a first end and a second end; a bore extending through the body from the first end and the second end, wherein the bore includes a tapered portion forming a tapered surface; and one or more movable seal retention elements positioned in the bore, wherein the one or more movable seal retention elements carry one or more seal elements positionable between; wherein — the one or more movable seal retention elements are movable along a longitudinal axis of the valve device concentrically relative to the body; the one or more movable seal retention elements comprise a tapered portion having a tapered shape at least partially corresponding to the tapered portion of the bore, and wherein the one or more movable seal retention elements and the one or more seal elements form a canted seal interface with the tapered surface of the bore, and further wherein the canted seal interface is oriented at an oblique angle relative to the longitudinal axis; and the one or more movable seal retention elements are movable between a closed position in which the one or more seal elements prevent fluid fromflowing from the first end of the body to the second end of the body, and an open position in which a gap is positioned between the one or more seal elements and the tapered portion of the bore, wherein the gap is configured to form a fluid flow pathway.15. The valve device of example 14 wherein the one or more movable seal retention elements comprise: a first movable seal retention element; and a second movable seal retention element positioned adjacent to the first movable seal retention element or at least partially positioned within a cup portion of the first movable seal retention element.16. The valve device of example 15 wherein: the one or more seal elements comprises a first seal element and a second seal element; the first movable seal retention element comprises a circumferential notch, wherein the first seal element is at least partially positioned in the circumferential notch; and the second movable seal retention element carries the second seal element.17. A method of transferring a fluid from a first spacecraft to a second spacecraft or from a first container to a second container, the method comprising operating a valve device, wherein operating the valve device comprises: receiving, in a bore within a body of the valve device, a probe element; and moving, with the probe element, one or more seal retention elements from a first position to a second position within the bore, wherein the second position opens a fluid flow pathway through the body between a first port and a second port or between the first port and the probe element.18. The method of example 17 wherein: the one or more seal retention elements comprise one or more tapered surfaces; the bore comprises a corresponding tapered surface; each tapered surface of the one or more tapered surfaces carries an O-ring; and moving the one or more seal retention elements comprises moving the one or more tapered surfaces of the one or more seal retention elements away from thecorresponding tapered surface of the bore, wherein a gap between each O-ring and the tapered surface of the bore forms at least part of the fluid flow pathway.19. The method of example 17 or example 18, further comprising biasing the one or more seal retention elements toward the first position.20. The method of any one of examples 17-19, further comprising causing fluid to flow through the probe element, through an interior bore of at least one of the one or more seal retention elements, and through a port of the valve device to transfer fluid from the first spacecraft to the second spacecraft or from the first container to the second container.21. A fluid transfer system for spacecraft, the system comprising: a first coupler configured to be carried by a first spacecraft; a first valve device carried by the first coupler and comprising a movable probe; a second coupler configured to be carried by a second spacecraft; and a second valve device carried by the second coupler, wherein the second valve device includes a first port and a second port that are in fluid communication with each other when the second valve device is open, and which are isolated from fluid communication when the second valve device is closed, the second valve device comprising: a body including the second port and having a tapered interior surface; a body cap including the first port, the body cap being attached to the body; a first movable seal retention element positioned in the body and carrying a first seal element in a tapered seal retention portion; a second movable seal retention element positioned in the body and carrying a second seal element in a tapered seal retention portion; and a biasing element positioned between the first movable seal retention element and the body cap; wherein the body is configured to receive the movable probe, wherein the movable probe pushes the seal retention elements to open a fluid flow pathway through the second valve device; wherein: one or more (such as both) of the seal retention elements and / or the seal elements form canted seal interfaces against the tapered interior surface of the bodywhen the second valve device is closed (e.g., the canted seal interfaces are oriented at an oblique angle relative to a longitudinal axis of the valve device)22. A valve device comprising: a body having a first end and comprising a port, the body having a tapered interior surface; and a movable seal retention element positioned in the body, the movable seal retention element comprising a tapered portion having a concentric tapered shape corresponding to the tapered interior surface, wherein the movable seal retention element is movable along a longitudinal axis of the valve device concentrically relative to the body, wherein the movable seal retention element forms a canted seal interface with the tapered interior surface that is oriented at an oblique angle relative to the longitudinal axis, wherein the movable seal retention element is movable between a closed position in which the movable seal retention element seals against the tapered interior surface, and an open position in which there is a gap forming a fluid flow pathway between the movable seal retention element and the tapered interior surface.23. The valve device of example 22, wherein the movable seal retention element carries a seal element, wherein the seal element forms the seal interface with the tapered interior surface.24. The valve device of example 22, further comprising a second movable seal retention element in contact with the first movable seal element and movable between open and closed positions, wherein the second movable seal retention element comprises a tapered shape corresponding to the tapered interior surface.25. The valve device of example 24, wherein the second movable seal retention element carries a seal element to form another seal interface with the tapered interior surface.26. A method of transferring a fluid from one spacecraft to another or from one container to another, the method comprising operating a valve device, wherein operating the valve device comprises: receiving, in a body of the valve device, a probe element; and moving, with the probe element, one or more seal retention elements from a first position to a second position within the body to open a fluid flow pathway through the body between a first port and a second port; wherein: moving the one or more seal retention elements comprises moving one or more tapered seal retention elements having tapered surfaces that selectively contact a tapered interior surface of the body, wherein the tapered surfaces and one or more seal elements carried by the seal retention elements form canted seal interfaces that are oriented at an oblique angle relative to a longitudinal axis of the valve device.27. A system, valve, mechanism, component, and / or device as disclosed herein.28. A method of operating a system, valve, mechanism, component, and / or device as disclosed herein.29. A controller programmed with instructions that, when executed, carry out a method disclosed herein.F. Conclusion

[0056] As used herein, the term “and / or” when used in the phrase “A and / or B” means “A, or B, or both A and B.” A similar manner of interpretation applies to the term "and / or" when used in a list of more than two terms. The word “or” in reference to a list of two or more items covers all of the following interpretations of the word: any of the items in the list, all of the items in the list, and any combination of the items in the list. As used herein, the terms “about,” and “approximately,” and the like refer to values within 10% of the stated value. As used herein, the terms “connected,” “coupled,” “attached,” or any variant thereof means any connection, coupling, or attachment, either direct or indirect, between two or more elements. Additionally, the words “herein,” “above,” "below," and words of similar import, when used in this application, refer to this application as a whole and not to any particular portions of this application. Where the context permits, singular or plural terms may also include the plural orsingular term, respectively. Numerical adjectives including “first” and “second,” or the like, as used in the present disclosure, do not convey hierarchy or specific features or functions. Rather, such numerical adjectives are intended to aid the reader in distinguishing between elements which may have similar nomenclature, but which may differ in position, orientation, or structure. Accordingly, such numerical adjectives may be used differently in the claims. To the extent any materials incorporated herein by reference conflict with the present disclosure, the present disclosure controls.

[0057] From the foregoing, it will be appreciated that some embodiments of the present technology have been described herein for purposes of illustration, but various modifications can be made without deviating from the disclosed technology. For example, the valves and / or actuators and / or the coupler of the first spacecraft can have configurations different than those expressly described. The transferred fluids can be liquids and / or gases, can include fluids other than propellants, and / or can be transferred in either direction between the spacecraft.

[0058] Further, while advantages associated with some embodiments of the technology have been described in the context of those embodiments, some embodiments may also exhibit said advantages, and not all embodiments need necessarily exhibit such advantages to fall within the scope of the present technology. Accordingly, the present disclosure and associated technology can encompass other embodiments not expressly described or shown herein.

Claims

CLAIMSI / We claim:

1. A fluid transfer system for transferring a fluid between a first spacecraft and a second spacecraft, the system comprising: a first coupler configured to be carried by the first spacecraft, wherein the first coupler is configured to engage a second coupler carried by the second spacecraft; and a valve device carried by the first coupler, wherein the valve device comprises: a body having a first port and a second port; one or more movable seal retention elements positioned in the body and aligned coaxially with the body; and a biasing element aligned coaxially with the body and positioned between the one or more movable seal retention elements and the body; wherein — the first port is configured to receive a probe carried by the second coupler, and when the first port receives the probe, the probe moves the one or more movable seal retention elements from a first position in which the valve device resists fluid flow past the one or more movable seal retention elements to a second position in which first port is in fluid communication with the second port and / or the probe.

2. The fluid transfer system of claim 1, further comprising the probe.

3. The fluid transfer system of claim 2, further comprising the second coupler.

4. The fluid transfer system of claim 1 wherein the body comprises a main bore having one or more tapered interior surfaces.

5. The fluid transfer system of claim 4 wherein the one or more movable seal retention elements comprise one or more tapered surfaces, and wherein the one or more movable seal retention elements form canted seal interfaces with a first tapered interior surface of the oneor more tapered interior surfaces of the body when the one or more movable seal retention elements are in the first position.

6. The fluid transfer system of claim 1 wherein the body includes a body cap carrying the first port.

7. The fluid transfer system of claim 6 wherein the body cap includes a tubular extension portion, and wherein the first port is positioned at a terminal end of the tubular extension portion.

8. The fluid transfer system of claim 1 wherein the one or more movable seal retention elements comprise: a first movable seal retention element positioned in the body and movable coaxially within the body; and a second movable seal retention element positioned in the body, movable coaxially within the body, and positioned adjacent to the first movable seal retention element.

9. The fluid transfer system of claim 8 wherein the second movable seal retention element comprises a portion positionable within a cup portion of the first movable seal retention element.

10. The fluid transfer system of claim 1 wherein the one or more movable seal retention elements carry a first seal element and a second seal element.

11. The fluid transfer system of claim 1 wherein the one or more movable seal retention elements comprise an interior bore in fluid communication with the first port.

12. The fluid transfer system of claim 11 wherein the biasing element comprises a compression spring positioned in the interior bore of the one or more movable seal retention elements.

13. The fluid transfer system of claim 11 wherein the one or more movable seal retention elements comprise one or more fluid flow channels in fluid communication with the interior bore, wherein the one or more fluid flow channels are in fluid communication with the second port when the one or more movable seal retention elements are in the second position.

14. A valve device compri sing : a body having a first end and a second end; a bore extending through the body from the first end and the second end, wherein the bore includes a tapered portion forming a tapered surface; and one or more movable seal retention elements positioned in the bore, wherein the one or more movable seal retention elements carry one or more seal elements positionable between; wherein — the one or more movable seal retention elements are movable along a longitudinal axis of the valve device concentrically relative to the body; the one or more movable seal retention elements comprise a tapered portion having a tapered shape at least partially corresponding to the tapered portion of the bore, and wherein the one or more movable seal retention elements and the one or more seal elements form a canted seal interface with the tapered surface of the bore, and further wherein the canted seal interface is oriented at an oblique angle relative to the longitudinal axis; and the one or more movable seal retention elements are movable between a closed position in which the one or more seal elements prevent fluid from flowing from the first end of the body to the second end of the body, and an open position in which a gap is positioned between the one or more seal elements and the tapered portion of the bore, wherein the gap is configured to form a fluid flow pathway.

15. The valve device of claim 14 wherein the one or more movable seal retention elements comprise: a first movable seal retention element; anda second movable seal retention element positioned adjacent to the first movable seal retention element or at least partially positioned within a cup portion of the first movable seal retention element.

16. The valve device of claim 15 wherein: the one or more seal elements comprises a first seal element and a second seal element; the first movable seal retention element comprises a circumferential notch, wherein the first seal element is at least partially positioned in the circumferential notch; and the second movable seal retention element carries the second seal element.

17. A method of transferring a fluid from a first spacecraft to a second spacecraft or from a first container to a second container, the method comprising operating a valve device, wherein operating the valve device comprises: receiving, in a bore within a body of the valve device, a probe element; and moving, with the probe element, one or more seal retention elements from a first position to a second position within the bore, wherein the second position opens a fluid flow pathway through the body between a first port and a second port or between the first port and the probe element.

18. The method of claim 17 wherein: the one or more seal retention elements comprise one or more tapered surfaces; the bore comprises a corresponding tapered surface; each tapered surface of the one or more tapered surfaces carries an O-ring; and moving the one or more seal retention elements comprises moving the one or more tapered surfaces of the one or more seal retention elements away from the corresponding tapered surface of the bore, wherein a gap between each O-ring and the tapered surface of the bore forms at least part of the fluid flow pathway.

19. The method of claim 17, further comprising biasing the one or more seal retention elements toward the first position.

20. The method of claim 17, further comprising causing fluid to flow through the probe element, through an interior bore of at least one of the one or more seal retention elements,and through a port of the valve device to transfer fluid from the first spacecraft to the second spacecraft or from the first container to the second container.

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