Satellite heat shield

Abstract

To provide a system, apparatus and method for a satellite thermal enclosure.SOLUTION: A satellite assembly is disclosed, including a satellite and a shroud. The satellite is stowed in a launch vehicle, and the shroud 200 includes a frame 210 supporting a flexible thermal blanket 212 enclosing the satellite.SELECTED DRAWING: Figure 3

Description

Background Art

[0001] Spacecrafts must withstand extreme temperatures, starting from the intense heat conditions during launch. Typically, the launch vehicle includes a payload fairing to protect the payload being transported, such as a satellite, from the dynamic pressure and aerodynamic heating during launch. The heavy and bulky fairing can limit the space and weight available for the payload. In some cases, the payload may need to withstand bending loads or vibrations from the attached fairing. There is a need for low-weight and low-profile thermal protection.

Summary of the Invention

[0002] The present disclosure provides systems, devices, and methods related to a heat protection container for a satellite. In some embodiments, a satellite assembly may include a satellite and a shroud. The satellite may be housed within a launch vehicle, and the shroud may include a frame supporting a flexible thermal blanket that encloses the satellite.

[0003] In some embodiments, a device for transporting a satellite into space may include a launch vehicle and a thermal shroud. The shroud may include a frame and a flexible material supported by the frame. The shroud may also be connected to the launch vehicle and configured to house the satellite during the launch phase.

[0004] In some embodiments, an assembly for transporting a satellite into space may include a ring structure and a plurality of shrouds extending radially outward from the ring structure. The ring structure may have a central axis parallel to the launch direction. Each shroud may include a frame supporting a flexible wall material. Each shroud may also have a proximal end connected to the ring structure and a distal end including a door that allows the satellite to deploy into space.

[0005] Features, functions, and advantages may be realized individually in various embodiments of this disclosure, or they may be combined in yet another embodiment, further details of which can be understood by referring to the following description and drawings. [Brief explanation of the drawing]

[0006] [Figure 1] This is a schematic diagram of an example artificial satellite being launched and deployed from its launch vehicle. [Figure 2] Figure 1 is a block diagram of the artificial satellite. [Figure 3] This is an isometric view of an exemplary thermal shroud, attached to a payload adapter of a launch vehicle and enclosing a satellite assembly, according to an aspect of the present disclosure. [Figure 4] Figure 3 is a top view of the thermal shroud and satellite assembly. [Figure 5] Figure 3 is an isometric view of the thermal shroud and satellite assembly in their stowed positions. [Figure 6] Figure 3 shows isometric views of the thermal shroud and satellite assembly in the deployed position with the door closed. [Figure 7] Figure 3 is an isometric view of the thermal shroud and satellite assembly in their deployed positions with the doors open. [Figure 8] Figure 3 is a detailed view of the upper corner of the door on the heat shroud. [Figure 9] Figure 3 shows a detailed view of the thermal shroud, the door actuator, and the upper tab of the satellite assembly. [Figure 10] Figure 3 is a detailed view of the thermal shroud and the door opening and lower tab of the satellite assembly. [Figure 11] Figure 3 is a detailed view of the expandable and retractable corner brackets of the thermal shroud. [Figure 12] This is a detailed cross-sectional view of the vertical support column of the thermal shroud frame shown in Figure 3, which is in a stowed position. [Figure 13] This is a detailed cross-sectional view of the vertical support column in Figure 12, in its deployed position. [Figure 14] Figure 3 is a detailed cross-sectional view of the ratchet lock on the side support post of the door of the heat shroud. [Figure 15] This flowchart illustrates the steps of an exemplary method for transporting a satellite into space, as taught in this instruction. [Modes for carrying out the invention]

[0007] Various aspects and examples of thermal insulation containers with expandable frames and related methods are described below and shown in the relevant drawings. Unless otherwise specified, the thermal insulation containers and / or various components thereof according to this teaching may include, but are not required to include, at least one of the structures, components, functions, and / or modifications described, illustrated, and / or incorporated herein. Furthermore, unless otherwise specifically excluded, the process steps, structures, components, functions, and / or modifications described, illustrated, and / or incorporated herein in connection with this teaching may be included in other similar devices and methods, but are interchangeable among the disclosed embodiments. The following descriptions of various embodiments are essentially illustrative and are not intended to limit the disclosure, its uses, or applications. In addition, the benefits provided by the embodiments described below are essentially illustrative, and not all embodiments will provide the same or comparable benefits.

[0008] This detailed description includes the following sections that immediately follow: (1) Overview, (2) Examples, Components, and Alternatives, (3) Exemplary Combinations and Further Examples, (4) Advantages, Features, and Benefits, and (5) Conclusion. The sections on Examples, Components, and Alternatives are further divided into subsections A through C, each of which is correspondingly labeled.

[0009] overview In general, the expandable thermal enclosure according to this teaching may include a frame supporting a flexible thermal insulation material. The shroud may be configured to house one or more satellites and to thermally protect the satellites during launch. The shroud may include a door to cover an opening assembled by an upper frame element, a lower frame element, and two side frame elements. The frame elements may also be described as an upper strut, a lower strut, and side struts on both sides. The door may be opened to allow the deployment of one or more satellites.

[0010] The shroud may have two or more trapezoidal sides and two or more expandable sides. The two or more expandable sides expand from rectangular to trapezoidal. The shroud may also have a proximal end portion and a distal end portion. The distal end portion includes an opening and a door. The distal end portion may be expandable from a retracted configuration to an deployed configuration. Two side frame elements can extend and retract between a retracted position and an deployed position to expand the size of the opening. Each side frame element may include a passive actuator, such as a spring, to facilitate the extension of the distal end portion. The door may include frame members on both sides. Each frame member can extend and retract parallel to the pair of side frame elements.

[0011] At least one of the upper and lower frame elements may engage with one or more housed satellites in a retracted configuration to restrain lateral movement of the distal end portion of the shroud. When the shroud extends into a deployed configuration, the lateral restraint may be released.

[0012] Examples, components, and alternatives The following sections describe selected embodiments of exemplary heat-insulating containers and related systems and / or methods. The examples in these sections are illustrative and should not be construed as limiting the entire scope of this disclosure. Each section may contain one or more individual inventions and / or information, functions, and / or structures derived from or related to the context.

[0013] Exemplary satellite and related methods The embodiments disclosed herein may be described in the context of an exemplary satellite launch method 80 (see Figure 1) and an exemplary satellite 100 (see Figure 2). In this embodiment, method 80 comprises three phases: a launch phase 20, a deployment phase 40, and an operation phase 60. The launch phase 20 may include transporting the satellite 100 (or alternatively, the spacecraft 100) from a planetary body 120, such as Earth, to outer space 122 using a launch vehicle 124. In the context of Earth, outer space may include the region beyond the Karman line. The deployment phase 40 may include separating the satellite 100 from the launch vehicle 124 once a desired position, trajectory, and / or orbit has been reached. The operation phase 60 may include preparing the satellite 100 for operation, such as establishing communication with a controller on the planetary body 120, extending solar panels or equipment arms, and / or maneuvering to a desired orientation relative to the planetary body. In some embodiments, the method may further include design, manufacturing, and / or operation phases.

[0014] Each process of Method 80 may be performed or carried out by a system integrator, a third party, and / or an operator (e.g., a customer). For the purposes of this specification, a system integrator may include, but is not limited to, any number of aerospace manufacturers and major system subcontractors; a third party may include, but is not limited to, any number of vendors, subcontractors, and suppliers; and an operator may be an airline, leasing company, military organization, service organization, etc.

[0015] As shown in FIG. 2, the satellite 100 may include a bus 102 having a plurality of satellite systems, a payload 104, and a separation system 106. Examples of the plurality of systems include one or more of a primary structural portion 108, a propulsion system 110, an electrical power system 112, a thermal management system 114, a radiation shielding system 116, and a communication system 118. Each system may include various subsystems, such as a controller, a processor, an actuator, an effector, a motor, a generator, etc., depending on the functions included. Any number of other systems may also be included. Although an example of an unmanned satellite is shown, the principles described herein may be applied to aerospace vehicles and aerospace technologies, such as launch vehicles, space stations, manned spacecraft, and / or interstellar probes.

[0016] The devices and methods illustrated or described herein may be employed during any one or more of the stages of the satellite launch method 80. For example, the heat shield container may protect the enclosed satellite 100 from the thermal conditions during the launch phase 20. Also, one or more embodiments of the devices, methods, or combinations thereof may be utilized during the deployment phase 40, for example, by expanding and / or opening the heat shield container to provide a gap for the satellite to be deployed. Similarly, one or more embodiments of the implementation of the devices or methods or combinations thereof may be utilized, for example, but not limited to, while the satellite 100 is in the operational phase 60, to return the heat shield container to a closed and / or enclosed configuration.

[0017] Exemplary heat-resistant container As shown in FIGS. 3-14, this section describes an exemplary thermal shroud 200. The thermal shroud 200 is, as described above, an example of an expandable heat shield. The thermal shroud can be used within a launch vehicle to enclose and protect a payload. In FIG. 3, a thermal shroud 200 attached to a payload adapter 410 of a launch vehicle and enclosing a pair of aligned satellites 412 as part of a satellite assembly 402 is depicted. The pair of satellites may also be described as a stack of satellites and / or a plurality of satellites.

[0018] The stack of satellites 412 includes a distal satellite 413 and a proximal satellite 415 and is coupled to the payload adapter 410 by an attachment plate 432. The thermal shroud 200 can be described as being coupled to the payload adapter 410 via the attachment plate 432 and supported by the stack of satellites.

[0019] In this example, the payload adapter 410 is a ring structure such as an evolved secondary payload adapter (ESPA) manufactured by Moog, Inc., and the payload adapter 410 includes six attachment points 414 symmetrically disposed around the ring structure. In FIG. 3, a plurality of shrouds 430 including the shroud 200 are shown coupled to the attachment plate at two of the attachment points 414. In many examples, the thermal shroud, satellite, and / or other payload equipment can be attached symmetrically around the payload adapter 410 to balance the loads transmitted to the payload adapter.

[0020] The payload adapter 410 is a part of the launch vehicle, such as the launch vehicle 124 described above. The launch vehicle has a launch axis 416. The launch vehicle may also be described as a part of the satellite assembly 402. In this embodiment, the ring structure of the payload adapter 410 has a central axis 418 parallel to the launch axis 416. The launch axis may also be described as the launch direction, the longitudinal axis of the launch vehicle, the z-axis, or the vertical axis. The direction perpendicular to the launch axis may be described as lateral, longitudinal, and / or horizontal.

[0021] Prior to launch, the launch axis may be aligned vertically as defined by the gravity coordinate system. During launch, the launch axis may rotate relative to the gravity coordinate system as the transporter follows a nonlinear launch trajectory. Therefore, for clarity in the following explanation, directional terms and descriptive words such as "up," "down," "upper," and "lower" should be understood in relation to the vertical direction defined by the launch axis.

[0022] Referring again to Figure 3, the thermal shroud 200 includes a rigid frame 210 and a flexible wall material 212. The shroud is connected to a mounting plate 432 at its proximal end 214. At its distal end 216, the shroud includes a door 218. The thermal shroud allows for maximum space for the satellite 412 within the launch vehicle, but is expandable to provide sufficient clearance for the satellite to be safely deployed. An expandable shroud may allow for greater space for the satellite than one using separate thermal protection and dynamic clearance.

[0023] The thermal shroud 200 may be configured in accordance with the constraints of the selected launch vehicle, payload adapter, and other payloads or operational equipment housed within the launch vehicle. More specifically, the thermal shroud may be expandable in one or more directions. Restrictions in those directions are removed or relaxed during the payload deployment process. The thermal shroud may expand one or more openings to allow the unobstructed passage of the deployed satellite.

[0024] In this embodiment, the payload adapter 410 is an adapter for a secondary payload, and the primary payload can be mounted vertically on the thermal shroud 200. Therefore, the vertical extent of the shroud may be suppressed during launch, but after the deployment of the primary payload, vertical space may become available. Thus, the thermal shroud 200 has a vertical extension 420. Since the lateral extent of the shroud is not suppressed, the shroud does not extend laterally. In this embodiment, the satellite 412 is configured to deploy radially outward from the payload adapter 410, so the door 218 is located at the distal end 216 of the thermal shroud 200, and the distal end of the shroud extends.

[0025] As shown in Figure 5, the thermal shroud 200 can be retracted during launch. As shown in Figures 3 and 6, the distal end 216 can be extended vertically when the satellite 412 is to be deployed. As shown in Figure 7, the door 218 can be opened. The left and right sides 220 and 222 of the shroud can transition from rectangular to trapezoidal as the shroud expands. The door 218 can transition from rectangular to square. The upper and lower sides 224 and 226 of the thermal shroud 200 may remain trapezoidal and are not affected by the expansion.

[0026] The specific shape of the shroud can depend on the size and shape of the satellite being enclosed. In one embodiment depicted, the shroud is configured for two cubic satellites. Generally, when the thermal shroud 200 expands, the upper and lower sides 224 and the proximal end 214 may remain at a constant area. On the other hand, the left side 220 and the right side 222 and the distal end 216 expand. Such expansion allows for maximum space for the satellite 412, while limiting the complexity and number of moving parts required for the thermal shroud 200.

[0027] Figure 4 is a view perpendicular to the vertical axis of the thermal shroud 200 and the upper side 224 of the satellite stack 412. The shroud may be depicted as having a longitudinal axis 228 and a lateral axis 230. The longitudinal axis 228 may also be described as the long axis of the thermal shroud 200. The left side 220 and the right side 222 are on either side along the lateral axis and may be described as sides. The mounting plate 432 is on the opposite side of the door 218 along the longitudinal axis.

[0028] The proximal end 214 of the thermal shroud 200 includes four base arms 274, which connect the shroud to a mounting plate 432. In this embodiment, the base arms are bolted to the four corners of the mounting plate. The mounting plate 432 includes an outer surface configured to connect the satellite stack and the shroud to a payload adapter.

[0029] The inner surface of the mounting plate 432 is configured to be connected to the satellites 413 and 415 by a separation system. The mounting plate 432 may form part of the load path for both the satellites and the shroud to the launch vehicle and may be designed to withstand any resulting bending moments and / or vibration loads. For example, the mounting plate may be manufactured from the same material as the primary structure of the satellites and / or payload adapter, such as an aluminum alloy.

[0030] In addition to the base arm 274, the frame 210 may include a combination of composite tubing and additively manufactured brackets, sleeves, and other connecting components. The hollow composite material may be lightweight but strong enough to support the weight of the frame and the attached flexible wall material 212. The connecting components may be additively manufactured from any adequately strong and lightweight material, such as plastic or aluminum alloy. Additive manufacturing can enable the inexpensive production of custom components that allow pivoting or other movements associated with the expansion of the thermal shroud and / or the integration of functional components such as latches.

[0031] The flexible wall material 212 may include any lightweight and sufficiently insulating material that can be folded, pleated, or otherwise stored away. For example, the material may include a thermal blanket or a space blanket. More specifically, the material may include a foil-coated plastic sheet or film. In this embodiment, the flexible wall material includes a single layer of thermal blanket. In some embodiments, the flexible wall material may include multiple layers and / or combinations of multiple insulating materials.

[0032] The flexible wall material 212 may be joined and / or otherwise bonded to the frame 210 along part or all of its edges. On the upper side 224 and lower side 226, the flexible wall material may be stretched or extended flat between the longitudinal studs 234 of the frame 210. The flexible wall material may extend under the cross braces 236. On the left side 220 and right side 222, the flexible wall material may be pleated or folded to include additional material. The flexible wall material may be spread out when the left and right sides of the thermal shroud 200 expand.

[0033] As described above, the upper surface 224 has a trapezoidal shape to provide a good clearance for the deployment of the satellite 412. The upper surface is described as having a proximal width 238 and a distal width 240 between the longitudinal supports 234 when measured parallel to the lateral axis 230. The distal width may be greater than the proximal width by twice the lateral clearance selected for the deployment of the satellite. The thermal shroud 200 may be described as having a length 242 between the base arm 274 and the door 218 when measured parallel to the longitudinal axis 228. The length 242 may be the same for all sides 220, 222, 224, and 226.

[0034] The proximal width 238 and length 242 may depend on the size and geometric dimensions of the satellite 412. That is, the shroud may be sized to precisely fit the dimensions of one or more satellites to be enclosed. For example, the thermal shroud 200 may be configured to enclose a single satellite. In that case, the length 242 may be half that of the illustrated embodiment, but the proximal width 238 and distal width 240 may be the same as those of the illustrated embodiment. The material, size, number, and / or position of the composite tubes forming the frame 210 may also be modified according to the size and / or design of the shroud to minimize weight while maintaining structural strength.

[0035] Figure 5 is an isometric view of the thermal shroud 200 in its retracted position 244, with the door 218 in the closed position 246. Figure 6 shows the shroud in the deployed position 248. The door is still in the closed position. Figure 7 shows the thermal shroud 200 in the deployed position. The door 218 is in the open position 250.

[0036] As shown in Figures 5 to 7, the frame 210 includes four longitudinal posts 234 extending from the base arm 274 to the opening 252. The opening is defined between two vertical posts 254, a lower post 256, and an upper post 258. The opening 252 may also be described as being assembled by the vertical posts, the lower post, and the upper post. The door 218 includes a frame 260 and a pleated or folded flexible wall material 212. The door frame consists of a hinge rod 262 connected to a latch rod 264 by two posts 266. A brace rod 268 may extend laterally between the side posts to restrain the flexible wall material 212 and control any tendency of the material to undulate.

[0037] The upper side 224 of the thermal shroud 200 includes a cross brace 236 and flexible wall material 212 extending between the two upper longitudinal studs 234. Similar to the brace rods 268, the cross brace 236 may restrain the flexible wall material 212 and control any tendency of the material to undulate. The cross brace 236 may also provide structural reinforcement to the frame 210. The lower side 226, shown but not depicted, similarly includes a cross brace and flexible wall material between the two lower longitudinal studs 234.

[0038] Sides 220 and 222 each include pleated or folded flexible wall material 212 extending between the upper and lower longitudinal supports 234 and three vertical telescopic rods 270. The vertical telescopic rods, as well as the brace rods 268 and cross braces 236, may restrain the flexible wall material 212 and control any tendency for the material to undulate, particularly during side expansion and spreading of the flexible wall material.

[0039] Each of the longitudinal support columns 234 is connected to its proximal and distal ends by pivotable corner brackets 272. At the proximal end, the bracket pivotably connects the longitudinal support column to the base arm 274. At the distal end, the bracket pivotably connects the longitudinal support column to either the upper bar 258 or the lower support column 256 at the corner of the frame of the opening 252. The pivotable corner brackets 272 will be further described below with reference to Figure 11.

[0040] The thermal shroud 200 further includes three latch and restraint systems. As will be further described below with reference to Figure 10, a door latch 276 connects the latch rod 264 of the door 218 to the lower support 256. As will be further described below with reference to Figure 11, each vertical support 254 is connected to the lower of the longitudinal supports 234 by an extension latch 278. As will be further described with reference to Figures 9 and 10, the upper bar 258 and the lower support 256 are restrained against the satellite 412 by a restraint system 280 which includes two engagement tab structures.

[0041] In some embodiments, the thermal shroud 200 may include additional struts, rods, or bars as required to achieve the desired structural characteristics of the frame 210. In some embodiments, the shroud may omit one or more of the structural members described in this embodiment. For example, one or both sides may include additional struts, or only one vertical telescopic rod. To facilitate the expansion of the shroud and the opening of the door 218, latches, tabs, brackets, and / or other connecting structures may be included, omitted, and / or otherwise arranged.

[0042] Referring again to Figure 5, the opening 252 is covered by a door 218 in the closed position 246, the door 218 blocking the exit of the satellite 412 and insulating the opening. The door frame 260 is oriented such that the side supports 266 are close to and parallel to the vertical supports 254, and the latch rod 264 is close to and parallel to the lower supports 256. The brace rod 268 and flexible wall material 212 extend across the opening 252.

[0043] The vertical supports 254, the side supports 266, and the vertical telescopic rods 270 are all retracted when the thermal shroud 200 is in the retracted position 244. The vertical supports, side supports, and vertical telescopic rods may each be described as having a retracted position 282. The sides 220, 222, the opening 252, and the door 218 are all rectangular. Both extension latches 278 are engaged, and the tab structure of the restraint system 280 engages with the satellite 412. The thermal shroud 200 also occupies minimal space when in the retracted position.

[0044] The thermal shroud 200 may be positioned in a retracted position 244 by a worker, such as a payload specialist, when the satellite 412 is fully mounted and connected inside the thermal shroud. The shroud may remain in the retracted position throughout the launch until the satellite 412 is ready to be deployed. At that point, as will be further described with reference to Figures 12 and 13 below, the expansion latch 278 may be released, triggering the expansion of the vertical support 254.

[0045] Referring back to Figure 6, the thermal shroud 200 is shown in the deployed position 284. The door 218 is still in the closed position 246. The vertical support 254 is fully extended and drives the corresponding extensions of the lateral support 266 and the vertical telescopic rod 270. The vertical support, lateral support, and vertical telescopic rod may each be described as having an extended position 284. The length of the vertical telescopic rod differs at the extended position 284. In other words, the distance the rod extends increases from the proximal end 214 to the distal end 216 as the distal end extends to form a trapezoidal shape of the extended side. The vertical support 254 extends a longer distance than either of the vertical telescopic rods 270, and the lateral support 266 extends the same distance as the vertical support.

[0046] In the deployed position 248, the opening 252 and the door 218 have a square shape. As will be further explained with reference to Figure 14 below, the side support 266 of the door 218 is locked in the extended position 284. Corner brackets 272 slide from the retracted position to the deployed position 248 to accommodate changes in angle between the longitudinal support 234 and the base plate arm 274 and the upper bar 258 or the lower support 256. The extension of the vertical support 254 moves the upper bar 258 and the lower support 256 away from the satellite 412, thereby disengaging the restraint system 280 from the satellite.

[0047] When the thermal shroud 200 is fully extended to the deployed position 248, the door latch 276 is released to allow the door 218 to open. For a very short time prior to the deployment of the outermost or farthest satellite 413 of the satellites 412, the thermal shroud may remain in the deployed position where the door 218 is in the closed position 246. In some embodiments, if the innermost or nearest satellite 415 of the satellites is deployed to a different orbit than the farthest satellite, the door may be closed again after the farthest satellite has been deployed, and the thermal shroud 200 may remain in the deployed position 248 where the door is in the closed position 246 until the nearest satellite is ready to be deployed.

[0048] In this embodiment, the thermal shroud 200 can only be manually retracted from the deployed position 248 to the retracted position 244. In other words, the thermal shroud may not retract to the retracted position remotely or automatically after launch. In some embodiments, one or more other elements of the vertical support 254 and / or frame 210 may include an electric actuator to enable remote retraction of the shroud.

[0049] As shown in Figure 7, the door 218 rotates around the hinge rod 262 to an open position 250. In this embodiment, the door rotates up to 100 degrees to ensure that it does not obstruct the deployment of the satellites. Generally, the door can rotate at least 90 degrees. When the door 218 is fully open to the open position 250, the separation system for the distal satellite 413 can be activated to push the satellite out of the opening 252 in a direction parallel to the longitudinal axis of the thermal shroud 200. As described above, the proximal satellite 415 may then be deployed, or the door 218 may be closed and reopened for the deployment of the proximal satellite.

[0050] As shown in Figures 8 and 9, the hinge rod 262 is supported by multiple bearings 286 in a housing attached to the upper bar 258 of the frame 210. The opening and closing of the door 218 is brought about by the rotation of the hinge rod 262 by a linear actuator 288 and a pair of torsion springs 290. As shown in Figure 9, the linear actuator 288 is positioned approximately at the center point of the hinge rod 262. The torsion springs 290 are positioned at the left and right ends of the hinge rod, using the left spring shown in Figure 8.

[0051] The linear actuator 288 is connected to the hinge rod 262 by a linkage 292. The linkage 292 is configured to convert the linear motion of the actuator into rotational motion. The linear actuator may be connected to the launch vehicle's control system to induce the opening of the door 218. In this embodiment, the linear actuator 288 is a paraffin actuator. In general, any effective lightweight linear or rotary actuator may be used.

[0052] The torsion spring 290 biases the hinge rod 262 in response to the action of the linear actuator 288 and linkage 292. That is, the torsion spring is configured to prompt the door 218 to close. The torsion spring 290 may also be described as providing a return force and / or holding the door in the closed position. The linear actuator 288 can apply a force sufficient to overcome the bias of the torsion spring 290. In this embodiment, a pair of torsion springs apply a rotational force of 5 inch-pounds. Generally, any strength of the spring can be used to keep the door closed during the operation of the launch vehicle.

[0053] A pair of rotation stops 294 are also attached to the hinge rod 262. One of the rotation stops 294 is shown in Figure 8. Each rotation stop extends radially outward from the hinge rod to engage with a corresponding limit switch 296 in the upper bar 258. The rotation stops 294 may rotate with the hinge rod 262 through a selected range of rotation of the door 218 and engage with the limit switch at the end of the range of rotation. The engagement of the rotation stops 294 with the limit switch 296 prevents further rotation of the door 218 and can generate an electrical signal to confirm that the door has reached the open position.

[0054] Figure 10 shows the door latch 276. As described above, the door latch holds the door 218 in the closed position. More specifically, the door latch 276 may hold the door closed throughout the launch until the shroud extends to the deployed position. Releasing the door latch 276 may allow the door to be opened by a linear actuator.

[0055] The door latch 276 includes a pin puller 298 having a pin 300. The pin puller is mounted on the lower post 256. The pin 300 engages with an opening 302 in a bracket mounted on the latch rod 264 of the door 218. The pin puller 298 can operate with low impact and at high speed to facilitate the smooth and steady release of the door 218.

[0056] The restraint system 280 is also shown in Figures 9 and 10. The system includes an upper tab 304 and a lower tab 306. The upper tab is attached to the upper bar 258, and the lower tab is attached to the lower support column 256. Each tab 304, 306 has a rounded trapezoidal shape and extends inward across the opening 252. The restraint system 280 further includes an upper receiving bracket 308 and a lower receiving bracket 310.

[0057] Both receiving brackets 308, 310 are attached to adjacent portions of the distal satellite 413. Each bracket includes a flat mounting plate and a curved raised lip to accommodate the corresponding tabs 304, 306. The raised lip can be described as forming a recess for receiving the tabs. When a tab is received by the corresponding bracket, the flat inner surface of the tab may be close to but away from the mounting plate of the bracket, or may be in contact with the plate. The outer curved edge of the tab may be close to but away from the raised lip of the bracket.

[0058] In this embodiment, brackets 308 and 310 are attached to the wall panel 422 of the housing of the distal satellite 413. The wall panel 422 may be described as the front panel of the distal satellite and is located near the opening 252. Generally, brackets 308 and 310 may be attached to any suitable structure of one or more enclosed satellites near the opening.

[0059] The upper tab 304 and the upper receiving bracket 308 may be described as engaging structures. Similarly, the lower tab 306 and the lower receiving bracket 310 may be described as engaging structures. In this embodiment, the restraint system 280 includes two engaging structures. In general, the system may include any number or arrangement of engaging structures suitable for the desired restraint of the shroud.

[0060] As shown in Figures 5, 9, and 10, when the thermal shroud 200 is in its retracted position 244, each of the tabs 304, 306 is received by the corresponding brackets 308, 310. The tabs 304, 306 can be described as engaging with the brackets 308, 310 in the retracted position 244. When the tabs engage with the brackets, the restraint system 280 can restrain both lateral and vertical movement of the distal end 216 of the thermal shroud 200. More specifically, contact between the tabs and the raised lips of the brackets can limit or prevent movement of the frame 210 relative to the satellite 412.

[0061] By suppressing the lateral movement of the distal end of the thermal shroud 200, the shroud can be stabilized despite the intense forces and vibration loads of launch. The distal end of the thermal shroud can also be described as being supported by the satellite. The suppression system 280 may allow the frame 210 to be less rigid and, accordingly, lighter.

[0062] As shown in Figures 6 and 7, when the thermal shroud 200 extends to the deployed position 248, the tabs 304 and 306 retract from the brackets 308 and 310. When the vertical support 254 extends, the upper bar 258 and lower support 256 move away from the satellite 413. The upper tab 304 and lower tab 306 are therefore pulled away from the wall panel 422 and the brackets 308 and 310. The tabs are pulled away from the wall panel 422 without obstruction. Thereafter, the deployment of the satellite 412 is not hindered by the restraint system 280. The restraint on the lateral movement of the distal end of the shroud is also released.

[0063] Figure 11 is a detailed view of one of the pivotable corner brackets 272. Specifically, it is a bracket that connects the longitudinal support 234, the lower support 256, and one of the left-side vertical supports 254. The corner bracket 272 permanently connects the lower support and the lower member 312 of the vertical support. The corner bracket pivotably connects the lower support and the vertical support to the longitudinal support 234.

[0064] The corner bracket 272 includes an elbow-shaped sleeve portion 316. It surrounds the lateral end of the lower support 256 and is fixed to the lower end of the lower member 312. A curved flange 318 extends longitudinally from the sleeve portion 316 toward the longitudinal support 234. The corner bracket 272 further includes a branched sleeve portion 320. It surrounds the end of the longitudinal support 234 and the end of the cross brace 236. The sleeve portion 320 includes two fingers 322. They extend on both sides of the flange 318. The fingers 322, the flange 318, and bolts extending laterally through these two components form a pivotable connection.

[0065] In this embodiment, the corner bracket 272 is manufactured by additive manufacturing. More specifically, the bracket is manufactured by direct metal laser sintering (DMLS) of an aluminum alloy. Additive manufacturing of the corner bracket and other such components of the thermal shroud 200 can enable the rapid and inexpensive production of complex geometric dimensions. Such geometric dimensions can enable desired structural connections and functional movement with minimal material. In general, any effective method of manufacturing can be used.

[0066] One of the expansion latches 278 is also shown in Figure 11. The vertical support 254 and expansion latch 278 on the left side 220 of the thermal shroud are depicted in Figures 11 to 13 and described below. However, the vertical support and expansion latch on the right side of the thermal shroud can be understood to be configured in a corresponding manner. The release of the two expansion latches may be coordinated by the launch vehicle's control system to achieve symmetrical expansion of the thermal shroud.

[0067] The expansion latch 278 includes a pin puller 298, as shown in the door latch 276 (Figure 10). The pin 300 of the pin puller engages with an opening in a bracket 326 fixed to the upper member 314 of the vertical post 254. The pin puller 298 is attached to the sleeve portion 316 of the corner bracket 272 and fixed to the lower member 312 of the vertical post. The engagement of the pin 300 with the bracket 326 thus fixes the upper member 314 to the lower member 312 and prevents the vertical post 254 from expanding.

[0068] The upper member 314 and lower member 312 of the vertical support 254 are shown more clearly in Figures 12 and 13. In Figure 12, the vertical support is shown in a retracted position 282. In Figure 13, the vertical support 254 is shown in an extended position 284. In the retracted position 282, most of the lower member 312 is contained within the upper member 314, whereas in the extended position 284, only the upper portion of the lower member is contained within the upper member.

[0069] The relative motion of the upper member 314 and the lower member 312 is driven by a fluid-damped passive actuator 328. The actuator can be constantly biased, but the extension of the vertical column 254 can be induced by the release of an extension latch. A drive rod 330 is positioned inside the upper member 314 and the lower member 312, with its first end fixed to the upper end of the upper member 314 near the upper bar 258. The second end 331 of the drive rod 330 is fixed to a spring 332 at the lower end of the lower member 312. The spring causes the drive rod 330 to move upward away from the lower column 256, resulting in the extension of the upper member 314 and the lower member 312, and consequently, the extension of the vertical column 254.

[0070] The second end 331, to which the spring 332 and drive rod 330 are attached, is enclosed within a damper housing 334 filled with fluid 336. The second end 331 and damper housing 334 can be described as acting as a piston and cylinder. The second end includes an orifice that completely obstructs passage inside the damper housing 334 but allows passage of fluid 336. The orifice can be precisely sized to control the speed of expansion of the vertical support 254. Such controlled expansion can provide a smooth, low-impact deployment of the thermal shroud.

[0071] The second end 331 further includes a check valve for controlled compression of the actuator 328. The vertical support 254 can be manually retracted from an extended position 284 to a retracted position 282 by a technician or other user during satellite loading and launch preparation. The check valve can regulate the rate at which the vertical support retracts to prevent shock or damage from excessively rapid retraction of the thermal shroud.

[0072] The upper end of the damper housing 334 includes a redundant O-ring seal to prevent leakage of the fluid 336, even when the thermal shroud is subjected to extreme temperature, pressure changes, and vibrations associated with launch and the space environment. In this embodiment, the fluid 336 is silicone oil. Generally, the fluid may be selected according to desired damping characteristics. The spring constant of the spring 332, the number and size of the orifices of the second end 331, and the internal damper of the damper housing 334 may be selected to achieve a desired speed of extension of the vertical strut 254.

[0073] In this embodiment, the vertical support 254 extends by approximately 6 inches. As shown in Figures 6 and 7, this results in a 3-inch gap at the upper and lower edges of the satellite 412. Each satellite 412 is approximately 20 inches square. Therefore, the 6-inch extension results in an increase of approximately 15% in space. Without the extension of the thermal shroud 200, the satellite 412 might need to be smaller by a corresponding amount. In other words, the thermal shroud 200 allows for the design of a larger satellite for a given available space within the launch vehicle, rather than requiring a separate shroud and dynamic gap. In this embodiment, the thermal shroud 200 allows for a satellite that is approximately 15% larger.

[0074] Figure 14 is a cross-sectional view of one of the side posts 266 of a door 218 in an extended position 284. The other side posts can be understood to be configured accordingly. The side post 266 includes an outer member 338 that partially encloses an inner member 340. As shown in Figure 5, the outer member 338 is fixed to a hinge rod 262 and the inner member 340 is fixed to a latch rod 264. The two members may slide freely relative to each other, and the side post 266 may extend when the hinge rod and latch rod are pulled apart by the extension of the vertical post 254. That is, the extension of the side post 266 may be driven by the extension of the vertical post 254.

[0075] Referring again to Figure 14, the lock bracket 342 is positioned on the side support 266. In this case, the inner member 340 is received within the outer member 338. The upper portion of the bracket is received between the inner and outer members, and the lower portion of the bracket surrounds the inner member 340. The lock bracket 342 includes sawtooth teeth 344 on its inner surface near the inner member 340. In this embodiment, the sawtooth teeth are divided into three circumferential sections, each divided by three sections of smooth surface.

[0076] The inner member 340 includes corresponding flexible tabs 346. In this embodiment, the inner member includes three flexible tabs corresponding to three sawtooth sections of the lock bracket 342. When the side post 266 extends, the flexible tabs 346 can slide over the sawtooth 344. The flexible tabs may then prevent the inner member 340 from moving back relative to the lock bracket 342, thereby preventing the side post 266 from retracting. Such locking of the side post 266 can prevent the door 218 from retracting when the door is opened to the open position 250 (Figure 7).

[0077] During manual retraction of the side support 266, the lower portion of the lock bracket 342 may be rotatable. The user may rotate the lower portion of the bracket by approximately 60 degrees. This causes the flexible tab 346 to engage with the smooth surface between the serrated teeth 344. The inner member 340 can then be returned to its original position and the side support 266 to be retracted. By rotating the lower portion of the bracket back, the side support is ready to be extended.

[0078] The inner member 340 further includes a stop flange 348 extending radially outward from the inner member. Contact between the flange 348 and the uppermost edge of the lock bracket 342 can prevent further movement of the inner member 340 and further expansion of the side support 266. In other words, the flange 348 can limit the expansion of the side support.

[0079] Exemplary Method This section describes the steps of an exemplary method for transporting a satellite into space, with reference to Figure 15. The above-described embodiments of the heat-insulating container may be used in the method steps described below. Where appropriate, references may be given to components and systems that may be used in performing each step. These references are illustrative and are not intended to limit the possible ways in which any particular step of this method can be performed.

[0080] Figure 15 is a flowchart illustrating the steps performed in an exemplary manner and does not enumerate the complete process or all steps of the method. While various steps of Method 500 are described later and shown in Figure 15, not all steps necessarily need to be performed, and in some cases they may be performed simultaneously or in an order different from that shown.

[0081] Step 510 includes attaching a thermal shroud to a launch vehicle. The shroud may include a rigid frame and a flexible thermal insulation material. For example, the shroud may include a plurality of hollow composite tubes connected by laminated brackets and a thermal blanket material including a foil layer placed on a thin flexible plastic sheet.

[0082] Attaching the shroud may involve fastening, joining, or attaching the base portion of the shroud to the payload adapter of the launch vehicle, to a mounting plate, and / or to the satellite assembly by bolting and / or other means. For example, step 510 may involve fastening the base plate of the shroud to a mounting plate that is bolted to a ring-shaped secondary payload adapter, thereby causing the longitudinal axis of the shroud to extend radially outward from the ring.

[0083] Step 512 includes loading the satellite into the shroud. Loading the satellite includes inserting the satellite through an opening in the shroud and attaching the satellite to a support structure. The satellite may be attached to the base portion of the shroud, to a mounting plate, and / or to the payload adapter of the launch vehicle. In some embodiments, loading the satellite into the shroud may include enclosing a satellite or satellite assembly that is already attached to the launch vehicle with the shroud.

[0084] In some embodiments, step 512 may include loading multiple satellites into a shroud. In such embodiments, the satellites may be mounted in sequence. One or more loaded satellites may be indirectly attached to the support structure via one or more other satellites. Preparation of one or more satellites for launch may be carried out and / or completed before the method proceeds. Subsequent steps of the method may restrict further physical access to the satellites.

[0085] Step 514 includes closing the shroud door. Closing the door may include allowing a biasing spring to cause the door to rotate around the hinge or hinge member, thereby covering the opening into which the satellite is inserted. The step may further include fixing or latching the door in the closed position. For example, a low-impact pin puller may engage with the door latch.

[0086] Step 516 includes retracting the expandable struts of the shroud into a retracted position. The rigid frame and doors of the shroud may include a plurality of expandable members that act as expandable struts, enabling the shroud to expand and contract along at least one axis. For example, the shroud may be expandable along an axis parallel to the launch axis of the launch vehicle. Retracting the expandable struts may include engaging one or more latches to hold the struts in a retracted position.

[0087] Two or more of the expansion members may include actuators for driving the expansion of the shroud. Step 516 may include compressing, deactivating, and / or reversing the actuators. For example, the step may include compressing a fluid-damped passive spring actuator. In such an embodiment, the compression of the actuator may be controlled by a check valve to limit the rate of compression. Step 516 may be performed manually by the user or the launch payload specialist.

[0088] Step 518 includes engaging the shroud frame with the satellite. The frame and shroud may include corresponding structures configured to engage when the expandable struts in step 516 are retracted. For example, tabs may be fixed to the upper and lower members that assemble the opening of the shroud. When the shroud is retracted, recesses or brackets on the loaded satellite near the opening may receive the tabs. The engagement of the frame with the satellite may restrict or prevent lateral movement of the thermal shroud.

[0089] Step 520 includes launching the transporter into space. Launching the transporter may include carrying the thermal shroud and loaded satellites into space. The step may further include positioning the launch transporter for the deployment of one or more of the satellites. For example, positioning the launch transporter may include placing the transporter in a desired orbit for the satellites.

[0090] Step 522 includes extending the expandable struts of the shroud to the deployed position. Extending the struts may include releasing one or more latches engaged in step 516 to enable extension. Extending the struts may further include engaging or activating an active actuator or enabling action by a passive actuator. For example, the step may include the spring biasing of a fluid-damped passive spring actuator enabling two of the struts to extend at a controlled speed. Expandable struts without actuators may extend in accordance with the activated strut. In some embodiments, extending the struts may include engaging one or more ratchet locks on the expandable struts to prevent them from retracting back to their retracted position.

[0091] Step 524 includes disengaging the frame from the satellite. Extending the expandable struts may disengage the corresponding structures on the frame from the satellite. For example, tabs fixed to the upper and lower members may retract from recesses or brackets on the satellite as the members extend away from the satellite. Disengaging the frame from the satellite may leave an unobstructed and unhindered path through the opening for the satellite.

[0092] Step 526 includes opening the door. Opening the door may include releasing the latch engaged in step 514. The door may be opened using an actuator. For example, a paraffin linear actuator connected to the door's hinge member by a linkage may rotate the hinge member to open the door. The door may be opened at least 90 degrees or more to provide an obstruction-free exit for one or more loaded satellites.

[0093] Step 528 includes deploying one or more satellites. Deployment may include activating a separation system to provide a separation shock outward through the opening of the shroud so as to move away from the launch vehicle. In embodiments where multiple satellites are loaded into the shroud, the satellites may be deployed in sequence. In such embodiments, the method may include repeating step 514 to close the door, maneuvering the launch vehicle for the deployment of further satellites, and repeating step 526 to reopen the door before deploying the next satellite.

[0094] Further exemplary and non-exclusive embodiments of this disclosure are described in the following paragraphs, including embodiments as defined below.

[0095] In one embodiment of the present disclosure, the satellite assembly (402) comprises a shroud (200) including satellites (100, 413, 415) housed within a launch vehicle (124), and a frame (210) supporting a flexible thermal blanket (212) enclosing the satellites.

[0096] Optionally, in the satellite assembly of the previous paragraph, the shroud (200) has a proximal end portion (214) and a distal end portion (216), the distal end portion being expandable.

[0097] Optionally, in one of the satellite assemblies in the preceding paragraph, the distal end portion (216) of the shroud (200) includes a door (218) that expands and opens when the satellites (100, 413, 415) are deployed.

[0098] Optionally, in one of the satellite assemblies in the preceding paragraph, the door (218) is configured to close after the satellites (100, 413, 415) have been deployed.

[0099] Optionally, in one of the satellite assemblies from the previous paragraph, the shroud (200) has trapezoidal sides (224, 226).

[0100] Optionally, in one of the satellite assemblies in the preceding paragraph, the shroud (200) has a retracted position (244) and an extended position (248), and the satellite (100, 413, 415) restricts the lateral movement of the shroud when it is in the retracted position and releases the lateral restriction when the shroud is extended to the extended position.

[0101] Optionally, in one of the satellite assemblies from the preceding paragraph, the shroud (200) has a proximal end portion (214) and a distal end portion (216), the distal end portion having a door (218) that covers an opening (252) assembled by an upper frame element (258), a lower frame element (256), and two side frame elements (254), the side frame elements being extendable between a retracted position (282) and an extended position (284) to expand the size of the opening.

[0102] Optionally, in one of the satellite assemblies in the preceding paragraph, when the side frame element is in the retracted position (282), the satellite (100, 413, 415) engages with at least one of the upper frame element (256) and the lower frame element (258) to restrain the lateral movement of the shroud (200).

[0103] In another embodiment of the present disclosure, a device (402) for transporting a satellite into space comprises a launch vehicle (124) and a thermal shroud (200) including a frame (210) and a flexible wall material (212) supported by the frame, wherein the shroud is connected to the launch vehicle and configured to house the satellite (100, 413, 415) during the launch phase (20, 520).

[0104] Optionally, in the apparatus of the previous paragraph, the shroud (200) is configured to accommodate a plurality of stacked satellites (412).

[0105] Optionally, one of the devices in the preceding paragraph further comprises a ring structure (410) connected to the launch vehicle (124), the ring structure having a central axis (418) parallel to the launch axis (416) of the launch vehicle, and the shroud (200) being mounted on the ring structure.

[0106] Optionally, in one of the devices described in the previous paragraph, the shroud (200) has a major axis (228) perpendicular to the launch axis (416).

[0107] Optionally, in one of the devices described in the previous paragraph, the shroud (200) has a proximal end portion (214) and a distal end portion (216), the distal end portion being expandable.

[0108] Optionally, in one of the devices described in the previous paragraph, the distal end portion (216) is extendable only in a direction (420) parallel to the launch axis (416) of the launch vehicle (124).

[0109] In another embodiment of the present disclosure, an assembly (402) for transporting a satellite into space comprises a ring structure (410) having a central axis (418) parallel to the launch direction (416), and a plurality of shrouds (430) extending radially outward from the ring structure, each shroud (200) including a frame (210) supporting a flexible wall material (212), having a proximal end (214) connected to the ring structure, and a distal end (216) including a door (218) for enabling the deployment of the satellites (100, 413, 415) into space (122).

[0110] Optionally, in the assembly of the previous paragraph, the distal end (216) of each shroud (200) is expandable from a retracted configuration (244) to an deployed configuration (248).

[0111] Optionally, in one of the assemblies from the previous paragraph, the distal end (216) of each shroud (200) is extendable only in a direction (420) parallel to the launch direction (416).

[0112] Optionally, in one assembly of the preceding paragraph, each shroud (200) has an upper side (224), a lower side (226), and a pair of sides (220, 222), and each of the upper side, the lower side, and the proximal end (214) maintains a constant area when the pair of sides and the distal end (216) are extended.

[0113] Optionally, in one assembly of the preceding paragraph, the distal end (216) of each shroud (200) has a rectangular opening (252) assembled by an upper support (258), a lower support (256), and a pair of side supports (254), each side support including a spring (332) to encourage the distal end to expand into an unfolded configuration (248).

[0114] Optionally, in one assembly from the previous paragraph, the door (218) has a pair of side frame members (266), each frame member being extendable and retractable parallel to the pair of side support columns (254).

[0115] The different embodiments of expandable thermal insulation vessels described herein offer several advantages over known solutions for thermally protecting satellites during launch. For example, the exemplary embodiments described herein allow for the use of lightweight thermal insulation materials.

[0116] Furthermore, among other benefits, the exemplary embodiments described herein maximize available interior space.

[0117] Furthermore, among other benefits, the exemplary embodiments described herein enable larger satellites for a given available space within a launch vehicle.

[0118] Furthermore, among other benefits, the exemplary embodiments described herein enable the protection of multiple linked satellites.

[0119] Furthermore, among other benefits, the exemplary embodiments described herein enable distal support and stability from artificial satellites.

[0120] Furthermore, among other benefits, the exemplary embodiments described herein enable controlled, low-impact expansion.

[0121] No known systems or devices are capable of performing these functions, particularly for satellites mounted on secondary payload adapters. Therefore, the exemplary embodiments described herein are particularly useful for microsatellites. However, not all embodiments described herein offer the same or similar advantages.

[0122] The above disclosures may encompass multiple individual embodiments, each with its own unique utility. While each of these disclosures is disclosed in one or more preferred forms, the specific embodiments disclosed and illustrated herein should not be taken restrictively, as numerous modifications are possible. Section headings, as used within this disclosure, are for structural purposes only. The subject matter of this disclosure includes all novel and non-obvious combinations and partial combinations of the various elements, features, functions, and / or characteristics described herein. The following claims specifically refer to certain combinations and partial combinations that are considered novel and non-obvious. Other combinations and partial combinations of features, functions, elements, and / or characteristics may be claimed in an application claiming priority from this application or a related application. Furthermore, such claims, whether broader, narrower, equal to, or different from the original claims, are considered to be within the scope of the subject matter of this disclosure.

Claims

1. The artificial satellites (100, 413, 415) housed within the launch vehicle (124), The system includes a shroud (200) which includes a frame (210) that supports a flexible thermal blanket (212) enclosing the artificial satellite, A satellite assembly (402) comprising a shroud (200) having a distal end portion (216), the distal end portion (216) having a door (218) covering an expandable opening (252), the distal end portion (216) having a frame element of the frame (210) of the shroud (200), the frame element being expandable and contractible between a retracted position (282) and an extended position (284).

2. The satellite assembly according to claim 1, wherein the shroud (200) has trapezoidal sides (224, 226).

3. The satellite assembly according to claim 1 or 2, wherein the shroud (200) has a retracted position (244) and an extended position (248), and the satellite (100, 413, 415) restricts the lateral movement of the shroud (200) when the shroud (200) is in the retracted position and releases the lateral restriction when the shroud (200) is extended to the extended position.

4. The satellite assembly according to any one of claims 1 to 3, wherein the opening (252) is assembled by an upper frame element (258), a lower frame element (256), and two side frame elements (254), the side frame elements (254) being expandable and retractable between a retracted position (282) and an deployed position (284) to expand the size of the opening (252).

5. The satellite assembly according to claim 4, wherein when the side frame element (254) is in the retracted position (282), the satellite (100, 413, 415) engages with at least one of the upper frame element (256) and the lower frame element (258) to suppress the lateral movement of the shroud (200).

6. The satellite assembly according to any one of claims 1 to 5, wherein the shroud (200) is configured to accommodate a plurality of stacked satellites (412).

7. The satellite assembly according to any one of claims 1 to 6, further comprising a ring structure (410) having a central axis (418) parallel to the launch direction (416), wherein the shroud (200) is one of a plurality of shrouds (430) extending radially outward from the ring structure (410).

8. The satellite assembly according to any one of claims 1 to 7, wherein the distal end portion (216) of the shroud (200) is extendable only in a direction (420) parallel to the launch axis (416) of the launch vehicle (124).

9. The satellite assembly according to any one of claims 1 to 8, wherein the shroud (200) has an upper side (224), a lower side (226), and a pair of sides (220, 222), and each of the upper side (224) and the lower side (226) maintains a constant area when each of the pair of sides (220, 222) and the distal end portion (216) expands.

10. An assembly (402) for transporting an artificial satellite into space, A ring structure (410) having a central axis (418) parallel to the launch direction (416), The ring structure comprises a plurality of shrouds (430) extending radially outward from the ring structure, Each of the shrouds (200) includes a frame (210) that supports a flexible wall material (212), has a proximal end (214) connected to the ring structure (410), and has a distal end (216) opposite to the proximal end (214) along the long axis (228) of the shroud (200), The distal end (216) of each of the shrouds (200) includes a door (218) to allow the satellites (100, 413, 415) to be deployed radially outward into space (122), Each of the shrouds (200) has an upper side (224), a lower side (226), and a pair of sides (220, 222), and each of the upper side (224), the lower side (226), and the proximal end (214) maintains a constant area when each of the pair of sides (220, 222) and the distal end (216) expands. assembly.

11. The assembly according to claim 10, wherein the distal end (216) of each of the shrouds (200) is expandable from a retracted configuration (244) to an deployed configuration (248).

12. The assembly according to claim 11, wherein the distal end (216) of each shroud (200) is expandable only in a direction (420) parallel to the launch direction (416).

13. The assembly according to any one of claims 10 to 12, wherein the distal end (216) of each of the shrouds (200) has a rectangular opening (252) assembled by an upper support (258), a lower support (256), and a pair of side supports (254), and each of the side supports (254) includes a spring (332) for prompting the distal end (216) to expand into an unfolded configuration (248).

14. The assembly according to claim 13, wherein the door (218) has a pair of side frame members (266), each of which frame members (266) is extendable and retractable parallel to the pair of side support columns (254).

15. The assembly according to any one of claims 10 to 14, wherein the upper surface (224) and the lower surface (226) of each of the shrouds (200) are trapezoidal.

16. The assembly according to any one of claims 10 to 15, wherein the long axis (228) of each of the shrouds (200) is perpendicular to the central axis (418) of the ring structure (410).

17. The assembly according to any one of claims 10 to 16, wherein the distal end (216) of each of the shrouds (220) has a frame element of the frame of the shroud (200), the frame element being extendable between a retracted position (282) and an extended position (284).

18. An assembly (402) for transporting an artificial satellite into space, A ring structure (410) having a central axis (418) parallel to the launch direction (416), The ring structure comprises a plurality of shrouds (430) extending radially outward from the ring structure, Each of the shrouds (200) includes a frame (210) that supports a flexible wall material (212), has a proximal end (214) connected to the ring structure, and has a distal end (216) opposite to the proximal end (214) along the long axis (228) of the shroud (200), The distal end (216) of each of the shrouds (200) includes a door (218) to allow the satellites (100, 413, 415) to be deployed radially outward into space (122), Each of the shrouds (200) has a rectangular opening (252) at its distal end (216) which is assembled by an upper support (258), a lower support (256), and a pair of side supports (254), and each side support (254) includes a spring (332) to encourage the distal end (216) to expand into an unfolded configuration (248).

Images