Satellite assembly and apparatus for transporting a satellite into space

Abstract

A satellite assembly and apparatus for transporting a satellite into space are disclosed. The satellite assembly includes a satellite and a shroud. The satellite is stowed in a launch vehicle and the shroud includes a frame that supports a flexible blanket that encloses the satellite.

Description

BACKGROUND

[0001] Spacecraft must endure extreme temperatures, beginning with the intense thermal conditions at launch. Typically, launch vehicles include a payload fairing to protect the carried payload, such as a satellite, from dynamic pressure and aerodynamic heating during launch. The bulky fairing can limit the space and weight available to the payload, and in some cases, the payload can need to endure bending loads or vibrations from the connected fairing. There is a need for a lightweight and compact thermal protection device. SUMMARY

[0002] The present disclosure provides systems, devices, and methods related to a thermally insulated enclosure for a satellite. In some examples, a satellite assembly can include a satellite and a shroud. The satellite can be stowed in a launch vehicle and the shroud can include a frame supporting a flexible blanket that encloses the satellite.

[0003] In some examples, a device for carrying a satellite into space can include a launch vehicle and a thermally insulated shroud. The shroud can include a frame and a flexible material supported by the frame. The shroud can also be connected to the launch vehicle and configured for containing the satellite during a launch phase.

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

[0005] Features, functions, and advantages can be independently implemented or combined in various examples of the present disclosure, further details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF DRAWINGS

[0006] FIG. 1 is a schematic view of an example satellite launched and deployed from a launch vehicle.

[0007] FIG. 2 is a block diagram of the satellite of FIG. 1

[0008] FIG. 3 is an isometric view of an example thermally insulated shroud according to aspects of the present disclosure, mounted to a launch vehicle payload adapter and enclosing a satellite assembly.

[0009] FIG. 4 is a top view of the thermally insulated shroud and satellite assembly of FIG. 3

[0010] FIG. 5 is a side view of the thermally insulated shroud and satellite assembly of FIG. 3 ​​isometric view of the thermal shield and satellite assembly in the stowed position.

[0011] FIG. 6 is FIG. 3 isometric view of the thermal shield and satellite assembly in the deployed position with the door in the closed position.

[0012] FIG. 7 is FIG. 3 isometric view of the thermal shield and satellite assembly in the deployed position with the door in the open position.

[0013] FIG. 8 is FIG. 3 detail view of the upper corner of the door of the thermal shield.

[0014] FIG. 9 is FIG. 3 detail view of the door actuator and upper tab of the thermal shield and satellite assembly.

[0015] FIG. 10 is FIG. 3 detail view of the door release and lower tab of the thermal shield and satellite assembly.

[0016] FIG. 11 is FIG. 3 detail view of the extended release and pivotable corner bracket of the thermal shield.

[0017] FIG. 12 is a cross-sectional detail view of the vertical strut of the frame of the thermal shield of FIG. 3 in the stowed position.

[0018] FIG. 13 is a cross-sectional detail view of the vertical strut of FIG. 12 in the deployed position.

[0019] FIG. 14 is a cross-sectional detail view of the ratchet lock of the side strut of the door of the thermal shield of FIG. 3

[0020] FIG. 15 is a flowchart describing the steps of an exemplary method of launching a satellite into space according to the present teachings. DETAILED DESCRIPTION

[0021] ​Various aspects and examples of thermally insulated enclosures having an expandable framework and related methods are described below and illustrated in the associated drawings. Unless otherwise specified, a thermally insulated enclosure and / or various components thereof according to the present teachings can but need not include at least one of the structures, components, functions, and / or variations described, shown, and / or combined herein. Moreover, unless specifically excluded, process steps, structures, components, functions, and / or variations described, shown, and / or combined herein as examples of the present teachings can be interchanged freely without departing from the scope of the present teachings, including being interchanged among the disclosed examples. The description of the following various examples is merely exemplary in nature and is in no way intended to limit the disclosure, its application, or uses.

[0022] This DETAILED DESCRIPTION includes the following sections: (1) Overview; (2) Examples, Components, and Alternatives; (3) Exemplary Combinations and Additional Examples; (4) Advantages, Features, and Benefits; and (5) Conclusion. The Examples, Components, and Alternatives section is further divided into subsections A through C, each of which is labeled accordingly.

[0023] SUMMARY

[0024] Generally, an expandable thermally insulated enclosure according to the present teachings can include a framework that supports a flexible thermal insulation material. A shroud can be configured to house one or more satellites and thermally protect the satellites during launch. The shroud can include a door for covering an opening, which is framed by a top frame element, a bottom frame element, and two side frame elements. The frame elements can also be described as top struts, bottom struts, and opposing side struts. The door can open to allow deployment of the one or more satellites.

[0025] The shroud can have two or more trapezoidal sides and two or more expandable sides that expand from a rectangle to a trapezoid. The shroud can also have a proximal end and a distal end, the distal end including an opening and a door. The distal end can expand from a stowed configuration to a deployed configuration. The two side frame elements can telescope between a stowed position and a deployed position to expand the size of the opening. Each side frame element can include a passive actuator, such as a spring, to urge expansion of the distal end. The door can include opposing frame members, each frame member capable of telescoping parallel to the pair of side frame elements.

[0026] At least one of the top frame element and the bottom frame element can engage one or more housed satellites in the stowed configuration to limit lateral movement of the distal end of the shroud. The lateral restriction can be released when the shroud expands to the deployed configuration.

[0027] Examples, Components, and Alternatives

[0028] The following sections describe selected aspects of exemplary insulated enclosures and related systems and / or methods. The examples in these sections are intended to be illustrative and should not be construed as limiting the overall scope of the disclosure. Each section can include one or more distinct examples, and / or contextual or related information, functionality, and / or structure.

[0029] A . Exemplary Satellites and Related Methods

[0030] Examples disclosed herein can be described in the context of an exemplary satellite launch method 80 (see FIG. 1 ) and an exemplary satellite 100 (see FIG. 2 ). In the present example, the method 80 includes three phases: a launch phase 20, a deployment phase 40, and an operations phase 60. The launch phase 20 can include transporting the satellite 100 (alternatively, 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 can include regions beyond the Karman line. The deployment phase 40 can include separating the satellite 100 from the launch vehicle 124 once a desired position, trajectory, and / or orbit has been achieved. The operations phase 60 can include preparing the satellite 100 for operations, such as establishing communication with a controller on the planetary body 120, extending solar panels or instrument arms, and / or maneuvering to a desired orientation relative to the planetary body. In some examples, the method can also include design, production, and / or commissioning phases.

[0031] Each process of the method 80 can be conducted or performed by a system integrator, a third party, and / or an operator (e.g., a consumer). For the purposes of this description, a system integrator can include, without limitation, any number of aircraft manufacturers and prime system subcontractors; a third party can include, without limitation, any number of vendors, subcontractors, and suppliers; and an operator can be an airline, a leasing company, a military organization, a service organization, etc.

[0032] As shown in FIG. 2 , the satellite 100 can include a bus 102 with 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 structure 108, a propulsion system 110, a power system 112, a thermal management system 114, a radiation shielding system 116, and a communication system 118. Each system can include various subsystems, such as controllers, processors, actuators, effectors, motors, generators, etc., depending on the functionality involved. Any number of other systems can be included. Although an unmanned artificial satellite example is shown, the principles disclosed herein can be applied to other aerospace vehicles and technologies, such as launch vehicles, space stations, manned spacecraft, and / or interstellar probes.

[0033] The devices and methods shown or described herein can be employed during any one or more of the stages of the satellite launch method 80. For example, the thermally insulating enclosure can protect the enclosed satellite 100 from thermal conditions during the launch stage 20. Also, one or more instances of a device, method, or combination thereof can be utilized during the deployment stage 40, for example, by expanding and / or opening the thermally insulating enclosure to provide clearance for the satellite to be deployed. Similarly, one or more instances of a device or method implementation, or a combination thereof, can be utilized to return the thermally insulating enclosure to an enclosing and / or stowed configuration, for example, when the satellite 100 is in the operational stage 60.

[0034] B. Exemplary Insulation Enclosure

[0035] As FIG. 3 to FIG. 14 shown, this section describes an exemplary thermally insulating shroud 200. The thermally insulating shroud 200 is an example of an expandable thermally insulating enclosure as described above. The thermally insulating shroud can be used in a launch vehicle to enclose and protect a payload. In FIG. 3 the thermally insulating shroud 200 is depicted as mounted to a launch vehicle payload adapter 410 and enclosing a pair of stacked satellites 412 as part of a satellite assembly 402. The pair of satellites can also be described as a satellite stack and / or a plurality of satellites.

[0036] The satellite stack 412 includes a distal satellite 413 and a proximal satellite 415 and is connected to the payload adapter 410 by a mounting plate 432. The thermally insulating shroud 200 is connected to the payload adapter 410 by the mounting plate 432 and can be described as being supported by the satellite stack.

[0037] In this example, the payload adapter 410 is a ring-shaped structure, such as an Evolutionary Secondary Payload Adapter (ESPA) produced by Moog Inc. The payload adapter 410 includes six mounting points 414 that are arranged symmetrically around the ring-shaped structure. In FIG. 3 the plurality of shrouds 430 including the shroud 200 are shown connected to the mounting plate at two of the mounting points 414. In many examples, the thermally insulating shroud, satellites, and / or other payload devices can be mounted symmetrically about the payload adapter 410 in order to balance the loads transferred to the payload adapter.

[0038] The payload adapter 410 is part of a launch vehicle, such as the launch vehicle 124 described above, having a launch axis 416. The launch vehicle can also be described as part of the satellite assembly 402. In this example, the ring-shaped structure of the payload adapter 410 has a central axis 418 that is parallel to the launch axis 416. The launch axis can also be described as a launch direction, a longitudinal axis of the launch vehicle, a z-axis, or a vertical axis. Directions that are perpendicular to the launch axis can be described as lateral, longitudinal, and / or horizontal.

[0039] Prior to launch, the launch axis can be aligned with the vertical direction defined by the gravitational reference frame. During launch, as the rocket follows a non-linear launch trajectory, the launch axis can rotate relative to the gravitational reference frame. Accordingly, for clarity in the following description, directional terms and descriptors such as "up," "down," "top," "bottom," and the like should be understood relative to the vertical direction defined by the launch axis.

[0040] Referring again to FIG. 3 , the thermal shroud 200 includes a rigid frame 210 and a flexible wall material 212. The shroud is connected to the mounting plate 432 at a proximal end 214. At a distal end 216, the shroud includes a door 218. The thermal shroud is expandable to allow for the maximum volume of the satellite 412 in the launch vehicle, also providing sufficient clearance for satellite safe deployment. The expandable shroud can provide greater volume for the satellite compared to using separate thermal protection and dynamic clearance.

[0041] The thermal shroud 200 can be constructed according to the limitations of the selected launch vehicle, payload adapter, and other payloads or operational equipment housed in the launch vehicle. More specifically, the thermal shroud can expand in one or more directions that are limited to be removed or reduced during payload deployment. The thermal shroud can expand one or more openings to allow for unobstructed passage of the deployed satellite.

[0042] In the present example, the payload adapter 410 is a secondary payload adapter, and a primary payload can be mounted vertically above the thermal shroud 200. Accordingly, the vertical extent of the shroud can be limited during launch, but a vertical clearance can become available after the primary payload is deployed. Thus, the thermal shroud 200 has a vertical expansion direction 420. The lateral extent of the shroud is not limited, so the shroud does not expand laterally. In the present example, the satellite 412 is configured to deploy radially outward from the payload adapter 410, so the door 218 is disposed at the distal end 216 of the thermal shroud 200, and the distal end of the shroud expands.

[0043] The thermal shroud 200 can be stowed during launch, as shown in FIG. 5 When the satellite 412 is to be deployed, the distal end 216 can expand vertically, as shown in FIG. 3 and 6 The door 218 can open, as shown in FIG. 7 As the shroud expands, the left side 220 and the right side 222 of the shroud can transition from a rectangular shape to a trapezoidal shape. The door 218 can transition from a rectangular shape to a square shape. The top side 224 and the bottom side 226 of the thermal shroud 200 can not be affected by the expansion and remain trapezoidal.

[0044] The specific shape of the shroud sides can depend on the size and shape of the satellite being enclosed. In the depicted example, the shroud is configured for two cubic satellites. Generally, when the thermal shroud 200 is expanded, the top side 224 and the bottom side 226, as well as the proximal end 214, can remain constant in area, while each of the left side 220 and the right side 222, as well as the distal end 216, expand. This expansion can allow for the maximum volume of the satellites 412, while limiting the complexity and number of moving parts required for the thermal shroud 200.

[0045] FIG. 4 is a view of the top side 224 of the thermal shroud 200 and the satellite stack 412 parallel to the vertical axis. The shroud can be described as having a longitudinal axis 228 and a transverse axis 230. The longitudinal axis 228 can also be described as the long axis of the thermal shroud 200. The left side 220 and the right side 222 are opposite along the transverse axis and can be described as lateral sides. The mounting plate 432 is opposite the door 218 along the longitudinal axis.

[0046] The proximal end 214 of the thermal shroud 200 includes four base arms 274 that connect the shroud to the mounting plate 432. In this example, 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 shroud to a payload adapter.

[0047] The inner surface of the mounting plate 432 is configured to connect to the satellites 413, 415 by a separation system. The mounting plate 432 can form part of the load path of both the satellites and the shroud to the launch vehicle, and can be designed to withstand any resulting bending moments and / or vibration loads. For example, the mounting plate can be made of the same material as the primary structure of the satellites and / or payload adapter, such as an aluminum alloy.

[0048] In addition to the base arms 274, the frame 210 can include a combination of composite tubes and additively manufactured brackets, sleeves, and other connecting components. Hollow composite tubes can be lightweight but strong enough to support the weight of the frame and attached flexible wall material 212. The connecting components can be additively manufactured from any suitably strong and lightweight material, such as plastic or an aluminum alloy. Additive manufacturing can allow for inexpensive production of custom components that enable the pivoting or other motions associated with expansion of the thermal shroud, and / or integration of functional components such as latches.

[0049] The flexible wall material 212 can include any lightweight and sufficiently thermally insulating material that can be folded, pleated, or otherwise stowed. For example, the material can include thermal blankets or space blankets. More specifically, the material can include foil-coated plastic sheets or films. In this example, the flexible wall material includes a single layer of thermal blankets. In some examples, the flexible wall material can include multiple layers and / or a combination of multiple insulating materials.

[0050] The flexible wall material 212 can be bonded and / or otherwise attached to the frame 210 along some or all of the edges of the material. On the top side 224 and the bottom side 226, the flexible wall material can be stretched or flattened between the longitudinal struts 234 of the frame 210. The flexible wall material can extend under the cross-ties 236. On the left side 220 and the right side 222, the flexible wall material can be pleated or folded to include additional material. The flexible wall material can be unrolled as the left and right sides of the thermal shield 200 are expanded.

[0051] As noted above, the top side 224 is trapezoidal in shape to provide a good lateral clearance for deployment of the satellite 412. The top side can be described as having a proximal width 238 and a distal width 240 between the longitudinal struts 234, as measured parallel to the lateral axis 230. The distal width can be twice as large as the proximal width for a selected lateral clearance for satellite deployment. The thermal shield 200 can be described as having a length 242, measured parallel to the longitudinal axis 228, between the base arm 274 and the door 218. The length 242 can be the same for each side 220, 222, 224, 226.

[0052] The proximal width 238 and the length 242 can depend on the size and geometry of the satellite 412. That is, the shield dimensions can be set to closely match the size of one or more encased satellites. For example, the thermal shield 200 can be configured to encase a single satellite, in which case the length 242 can be half of the illustrated example, but the proximal width 238 and the distal width 240 can be the same as in the illustrated example. The material, size, number, and / or location of the composite tubes that make up the frame 210 can similarly be varied according to the shield dimensions and / or design to minimize weight but maintain structural strength.

[0053] FIG. 5 is an isometric view of the thermal shield 200 in the stowed position 244, with the door 218 in the closed position 246. In FIG. 6 , the shield is depicted in the expanded position 248, with the door still in the closed position. In FIG. 7 , the thermal shield 200 is depicted in the expanded position, with the door 218 in the open position 250.

[0054] As FIG. 5 to FIG. 7As shown, the frame 210 includes four longitudinal struts 234 that extend from the base arm 274 to the opening 252. The opening is defined between two vertical struts 254, a lower cross strut 256, and an upper cross bar 258. The opening 252 can also be described as being framed by the vertical struts, the lower cross strut, and the upper cross bar. The door 218 includes a frame 260 and a pleated or folded flexible wall material 212. The door frame is constructed from a hinged bar 262 that is connected to a latch bar 264 by two side struts 266. A support bar 268 extends laterally between the side struts and can restrain the flexible wall material 212, thereby controlling any tendency of the material to billow.

[0055] The top side 224 of the thermal shield 200 includes a cross brace 236 and the flexible wall material 212 that extend between two of the longitudinal struts 234. Similar to the support bar 268, the cross brace 236 can restrain the flexible wall material 212 and control any tendency of the material to billow. The cross brace 236 can also provide structural reinforcement to the frame 210. The bottom side 226, which is noted but not depicted, similarly includes a cross brace and the flexible wall material between two of the longitudinal struts 234.

[0056] Each of the lateral sides 220, 222 includes the pleated or folded flexible wall material 212 and three vertical telescoping bars 270 that extend between the upper longitudinal strut 234 and the lower longitudinal strut 234. Similar to the support bar 268 and the cross brace 236, the vertical telescoping bars can restrain the flexible wall material 212, thereby controlling any tendency of the material to billow, particularly during the expansion and deployment of the lateral sides of the flexible wall material.

[0057] Each longitudinal strut 234 is connected at a proximal end and a distal end by a pivotable gusset 272. At the proximal end, the gusset pivotably connects the longitudinal strut to the base arm 274. At the distal end, at the corner of the frame of the opening 252, the gusset pivotably connects the longitudinal strut to either the upper cross bar 258 or the lower cross strut 256. The following references FIG. 11 The pivotable gusset 272 is further described.

[0058] The thermal shield 200 also includes three latches and a restraint system. A door latch 276 connects the latch bar 264 of the door 218 to the lower cross strut 256, as further described below with reference to FIG. 10 Each vertical strut 254 is connected to one of the lower longitudinal struts 234 by an expansion latch 278, as further described below with reference to FIG. 11 The upper cross bar 258 and the lower cross strut 256 are restrained relative to the satellite 412 by a restraint system 280 that includes two interlocking tab structures, as further described below with reference to FIG. 9 and 10 The restraint system 280 is further described.

[0059] In some examples, the thermal shield 200 can include additional struts, poles, or bars as needed to achieve the desired structural properties of the frame 210. In some examples, the shield can omit one or more of the structural members described in the present example. For example, one or both lateral sides can include additional longitudinal struts, or can include only one vertical telescoping pole. Latches, tabs, brackets, and / or other connection structures can be included, omitted, and / or otherwise positioned to facilitate expansion of the shield and opening of the door 218.

[0060] Referring again to FIG. 5 In the closed position 246, the opening 252 is covered by the door 218, blocking the exit of the satellite 412 and thermally insulating the opening. The frame 260 of the door is oriented such that the lateral struts 266 are both proximate to and parallel with the vertical struts 254, and the latch poles 264 are both proximate to and parallel with the lower lateral struts 256. The support poles 268 and the flexible wall material 212 extend through the opening 252.

[0061] When the thermal shield 200 is in the stowed position 244, the vertical struts 254, the lateral struts 266, and the vertical telescoping poles 270 are all retracted. The vertical struts, lateral struts, and vertical telescoping poles can be described as each having a retracted position 282. The lateral sides 220, 222, the opening 252, and the door 218 are all rectangular. The expansion latches 278 are both engaged, and the tab structures of the restraint system 280 are engaged with the satellite 412. When in the stowed position, the thermal shield 200 also occupies a minimum volume.

[0062] When the satellite 412 has been fully installed and connected within the thermal shield, the thermal shield 200 can be placed in the stowed position 244 by an operator, such as a payload specialist. The shield can remain in the stowed position throughout the launch process until the satellite 412 is ready to be deployed. At this time, the expansion latches 278 can be released, triggering expansion of the vertical struts 254, as described below with reference to FIG. 12 and FIG. 13 are further described.

[0063] Turning to FIG. 6 The thermal shield 200 is shown in the expanded position 284. The door 218 is still in the closed position 246. The vertical struts 254 have fully expanded, driving corresponding expansion of the lateral struts 266 and the vertical telescoping poles 270. The vertical struts, lateral struts, and vertical telescoping poles can be described as each having an expanded position 284. The lengths of the vertical telescoping poles differ in the expanded position 284. In other words, the distance by which the poles expand increases from the proximal end 214 to the distal end 216 as the distal end expands to form a trapezoidal shape of the expanded lateral side. The vertical struts 254 expand a greater distance than any of the vertical telescoping poles 270, and the lateral struts 266 expand the same distance as the vertical struts.

[0064] In the extended position 248, the opening 252 and the door 218 have a square shape. The side pillars 266 of the door 218 are locked in the extended position 284, as described below. FIG. 14 Further described. The tripod 272 pivots from the stowed position to the extended position 248 to accommodate changes in the angle between the longitudinal strut 234 and the base arm 274, the upper transverse bar 258, or the lower transverse strut 256. The extension of the vertical strut 254 moves the upper transverse bar 258 and the lower transverse strut 256 away from the satellite 412, thereby separating the restraint system 280 from the satellite.

[0065] Once the thermal shield 200 has been fully extended to the deployed position 248, the latch 276 is released to allow the door 218 to open. The thermal shield may be held in the deployed position only briefly before the deployment of the outermost or farthest satellite 413 in satellite 412, with the door 218 in the closed position 246. In some instances, such as if the innermost or nearest satellite 415 in satellite 415 will be deployed in a different orbit than the farthest satellite, the door may be reclosed after the farthest satellite is deployed, and the thermal shield 200 may be held in the deployed position 248 with the door in the closed position 246 until the nearest satellite is ready for deployment.

[0066] In this example, the heat shield 200 can only be manually retracted from the deployed position 248 to the retracted position 244. In other words, the heat shield may retract back to the retracted position, neither remotely nor automatically, after launch. In some examples, one or more other elements of the vertical strut 254 and / or frame 210 may include motorized actuators to allow for remote retraction of the shield.

[0067] like FIG. 7 As shown, door 218 rotates about hinge rod 262 to open position 250. In this example, the door rotates 100 degrees to ensure that the open door does not obstruct satellite deployment. Typically, the door can rotate at least 90 degrees. Once door 218 is fully open to open position 250, the separation system of the far-side satellite 413 can be actuated to push the satellite out of opening 252 in a direction parallel to the longitudinal axis of the thermal shield 200. As described above, near-side satellite 415 can then be deployed, or door 218 can be closed and reopened for deployment of the near-side satellite.

[0068] like FIG. 8 and FIG. 9 As shown, hinge rod 262 is supported by multiple bearings 286 mounted in the housing to the upper transverse rod 258 of frame 210. The opening and closing of door 218 is achieved by rotating hinge rod 262 via linear actuator 288 and a pair of torsion springs 290. FIG. 9 As shown, the linear actuator 288 is positioned approximately at the center point of the hinge rod 262. Torsion springs 290 are located at the left and right ends of the hinge rod. FIG. 8The left spring is shown in FIG.

[0069] Linear actuator 288 is connected to hinge rod 262 by a link 292 that is configured to convert linear motion of the actuator to rotational motion. The linear actuator can be connected to the control system of the launch vehicle to trigger opening of door 218. In the present example, linear actuator 288 is a wax actuator. In general, any effective lightweight linear or rotational actuator can be used.

[0070] Torsion spring 290 biases hinge rod 262 against the action of linear actuator 288 and link 292. That is, the torsion spring is configured to urge door 218 closed. Torsion spring 290 can also be described as providing a return force and / or keeping the door closed. Linear actuator 288 can exert enough force to overcome the bias of torsion spring 290. In the present example, this pair of torsion springs exerts a rotational force of 5 inch-pounds. In general, any strength of spring can be used to keep the door in the closed position during maneuvering of the launch vehicle.

[0071] A pair of rotational stops 294 are also mounted to hinge rod 262, one on either side of the hinge rod. FIG. 8 Each rotational stop extends radially outward from the hinge rod to engage a corresponding limit switch 296 in upper crossbar 258. Rotational stops 294 can rotate with hinge rod 262 through a selected range of rotation of door 218, thereby engaging limit switches at the ends of the range of rotation. Engagement between rotational stops 294 and limit switches 296 can both prevent further rotation of door 218 and generate an electrical signal to confirm that the door has reached the open position.

[0072] FIG. 10 Door latch 276 is shown in FIG. 2. As described above, the door latch keeps door 218 in the closed position. More specifically, door latch 276 can keep the door closed throughout the launch process until the shroud is extended to the deployed position. Release of door latch 276 can allow the door to be opened by the linear actuator.

[0073] Door latch 276 includes a latch puller 298 having a pin 300. The latch puller is mounted to lower cross strut 256. Pin 300 engages a hole 302 in a bracket mounted on latch rod 264 of door 218. Latch puller 298 can be low-impact and fast-acting to facilitate smooth and combined release of door 218.

[0074] FIG. 9 And FIG. 10 Restraint system 280 is also shown in FIGS. 2 and 3. The system includes an upper tab 304 and a lower tab 306. Upper tab is mounted to upper crossbar 258, and lower tab is mounted to lower cross strut 256. Each tab 304, 306 has a rounded trapezoidal shape and extends inward beyond opening 252. Restraint system 280 also includes an upper receiving bracket 308 and a lower receiving bracket 310.

[0075] Two receiving brackets 308, 310 are mounted to adjacent portions of the distal satellite 413. Each bracket includes a flat mounting plate and a curved raised lip that matches the corresponding tab 304, 306. The raised lip can be described as forming a recess to receive the tab. When the tab is received by the corresponding bracket, the flat inner surface of the tab can be proximate to, but spaced apart from or in contact with, the mounting plate of the bracket. The outer curved edge of the tab can be proximate to, but spaced apart from, the raised lip of the bracket.

[0076] In the present example, the brackets 308, 310 are mounted to a wall plate 422 of the housing of the distal satellite 413. The wall plate 422 can be described as a front plate of the distal satellite and is disposed adjacent to the opening 252. In general, the brackets 308, 310 can be mounted to any suitable structure of the one or more surrounding satellites adjacent to the opening.

[0077] The upper tab 304 and the upper receiving bracket 308 can be described as an engagement structure. Similarly, the lower tab 306 and the lower receiving bracket 310 can be described as an engagement structure. In the present example, the restraint system 280 includes two engagement structures. In general, the system can include any number of engagement structures or arrangements of engagement structures suitable for the desired restraint of the shroud.

[0078] When the insulated shroud 200 is in the stowed position 244 as shown in FIG. 5 , FIG. 9 and FIG. 10 , each tab 304, 306 is received by the respective bracket 308, 310. In the stowed position 244, the tabs 304, 306 can be described as engaging the brackets 308, 310. When the tabs engage the brackets, the restraint system 280 can restrain lateral and vertical movement of the distal end 216 of the insulated 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.

[0079] Restraining lateral movement of the distal end of the insulated shroud 200 can stabilize the shroud against launch forces and vibration loads. The distal end of the insulated shroud can also be described as being supported by the satellite. The restraint system 280 can allow the frame 210 to be less rigid, and thus lighter in weight.

[0080] When the insulated shroud 200 is extended to the deployed position 248 as shown in FIG. 6 and FIG. 7As shown, tabs 304, 306 are retracted from brackets 308, 310. As vertical struts 254 expand, upper cross strut 258 and lower cross strut 256 move away from distal satellite 413. As a result, upper tab 304 and lower tab 306 are pulled away from wall panel 422 and brackets 308, 310. These tabs are pulled away from wall panel 422 so that deployment of satellite 412 is not impeded by restraint system 280. Restraint on lateral movement of the distal end of the shroud is also released.

[0081] FIG. 11 is a detailed view of one of the plurality of pivotable gimbals 272, specifically the gimbals connecting the left side of longitudinal strut 234, lower cross strut 256, and vertical strut 254. Gimbals 272 fixedly connect lower member 312 of the lower cross strut and the vertical strut. The gimbals pivotably connect the lower cross strut and the vertical strut to longitudinal strut 234.

[0082] Gimbals 272 include an elbow sleeve portion 316 that surrounds a lateral end of lower cross strut 256 and is fastened to a bottom end of lower member 312. A curved flange 318 extends longitudinally from sleeve portion 316 toward longitudinal strut 234. Gimbals 272 also include a diverging sleeve portion 320 that surrounds an end of longitudinal strut 234 and an end of cross brace 236. Diverging sleeve portion 320 includes two fingers 322 that extend on either side of flange 318. Fingers 322, flange 318, and a bolt that extends laterally through these two components together can form a pivotable connection.

[0083] In the present example, gimbals 272 are fabricated additively. More specifically, the brackets are made of an aluminum alloy direct metal laser sintering (DMLS). Additive fabrication of the gimbals and other such components of thermal protection shield 200 can allow for rapid and inexpensive production of complex geometries. Such geometries can enable desired structural connections and functional movements with minimal material. In general, any effective method of fabrication can be used.

[0084] FIG. 11 One of the expansion latches 278 is also shown in FIG. 11 to FIG. 13 Vertical struts 254 and expansion latches 278 at the left side 220 of the thermal protection shield are depicted in and described below, but it will be appreciated that the vertical struts and expansion latches at the right side of the thermal protection shield are configured accordingly. Release of both expansion latches can be coordinated by the control system of the launch vehicle to achieve symmetrical expansion of the thermal protection shield.

[0085] Expansion latches 278 include a latch 284 and a latch 286, similar to latches 276 FIG. 10The pin 300 of the puller engages a hole of a bracket 326 fixed to the upper member 314 of the vertical strut 254. The puller 298 is mounted to the sleeve portion 316 of the corner bracket 272 and is fixed relative to the lower member 312 of the vertical strut. Thus, the engagement of the pin 300 with the bracket 326 fixes the upper member 314 relative to the lower member 312, thereby preventing expansion of the vertical strut 254.

[0086] The upper member 314 and the lower member 312 of the vertical strut 254 are shown in greater detail in FIG. 12 and FIG. 13 . In FIG. 12 , the vertical strut is shown in a collapsed position 282. In FIG. 13 , the vertical strut 254 is shown in an expanded position 284. In the collapsed position 282, most of the lower member 312 is received in the upper member 314, while in the expanded position 284, only an upper portion of the lower member is received in the upper member.

[0087] 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 apply a bias at all times, but expansion of the vertical strut 254 can be triggered by releasing an expansion latch. A drive rod 330 is disposed within the upper member 314 and the lower member 312, with a first end of the rod fixed at a top end of the upper member 314 proximate the upper crossbar 258. A second end 331 of the drive rod 330 is fixed to a spring 332 at a bottom end of the lower member 312. The spring urges the drive rod 330 upward away from the lower crossbar 256, causing the upper member 314 and the lower member 312 to telescope and cause the vertical strut 254 to expand.

[0088] The spring 332 and the attached second end 331 of the drive rod 330 are enclosed in a damper housing 334 filled with a fluid 336. The second end 331 and the damper housing 334 can be described as functioning as a piston and cylinder. The second end completely blocks the internal passage of the damper housing 334, but includes an orifice that allows passage of the fluid 336. The orifice size can be precisely set to control the rate of expansion of the vertical strut 254. This controlled expansion can provide a smooth, low-impact deployment of the thermal shield.

[0089] The second end 331 further includes a check valve for controlled compression of the actuator 328. During satellite loading and launch preparation, a technician or other user can manually collapse the vertical strut 254 from the expanded position 284 to the collapsed position 282. The check valve can regulate the rate of vertical strut collapse to prevent the shock or damage from a too-rapid collapse of the thermal shield.

[0090] 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 shield is subjected to extreme temperatures, pressure changes, and vibrations associated with launch and space environments. In the present example, the fluid 336 is silicone oil. In general, the fluid can be selected according to desired damping characteristics. The spring coefficient of the spring 332, the number and size of the orifices of the second end 331, and the inner diameter of the damper housing 334 can be selected to achieve a desired expansion rate of the vertical strut 254.

[0091] In the present example, the vertical strut 254 expands approximately 6 inches. This creates a 3-inch gap at the upper and lower edges of the satellite 412, as shown in FIG. 6 and FIG. 7 The satellites 412 are each approximately 20 square inches, so a 6-inch expansion results in an approximately 15% increase in volume. Without expansion of the thermal shield 200, the satellites 412 would need to be reduced by a corresponding amount. In other words, the thermal shield 200 enables larger satellites to be designed for a given available volume in a launch vehicle, rather than needing to allow for separate shields and dynamic gaps. In the present example, the thermal shield 200 allows the satellites to be increased by approximately 15%.

[0092] FIG. 14 is a cross-sectional view of one side strut 266 of the door 218 in the expanded position 284. The other side strut can be understood to be correspondingly configured. The side strut 266 includes an outer member 338 that partially encloses an inner member 340. As shown in FIG. 5 , the outer member 338 is fixed to the hinged bar 262 and the inner member 340 is fixed to the latching bar 264. The two members are free to slide relative to one another, and the side strut 266 can expand as the hinged and latching bars are pulled apart due to expansion of the vertical strut 254. That is, expansion of the side strut 266 can be driven by expansion of the vertical strut 254.

[0093] Referring again to FIG. 14 , a locking bracket 342 is disposed on the side strut 266 with the inner member 340 received in the outer member 338. An upper portion of the bracket is received between the inner and outer members, and a lower portion of the bracket surrounds the inner member 340. The locking bracket 342 includes serrations 344 on an inner surface adjacent the inner member 340. In the present example, the serrations are divided into three circumferential portions divided by three portions of smooth surface.

[0094] The inner member 340 includes respective flexible tabs 346. In the present example, the inner member includes three flexible tabs corresponding to the three serrated portions of the locking bracket 342. As the side strut 266 expands, the flexible tabs 346 can slide over the serrations 344. The flexible tabs in turn can prevent return motion of the inner member 340 relative to the locking bracket 342, thereby preventing contraction of the side strut 266. This locking of the side strut 266 can avoid contraction of the door 218 as the door is opened to the open position 250 FIG. 7 ).

[0095] For manual contraction of the side strut 266, the lower portion of the locking bracket 342 can be rotatable. A user can rotate the lower portion of the bracket approximately 60 degrees so that the flexible tabs 346 engage the smooth surface between the portions of the serrations 344. Return motion of the inner member 340 and contraction of the side strut 266 is in turn possible. Rotating the lower portion of the bracket back can prepare the side strut for expansion.

[0096] The inner member 340 also includes a stop flange 348 extending radially outward from the inner member. Contact between the flange 348 and the uppermost edge of the locking bracket 342 can prevent further motion of the inner member 340 and expansion of the side strut 266. That is, the flange 348 can limit expansion of the side strut.

[0097] C. Exemplary Methods

[0098] This section describes steps of an exemplary method for transporting a satellite into space; see FIG. 15 Aspects of the thermally insulated enclosure described above can be used in the method steps described below. Where appropriate, reference can be made to components and systems that can be used in carrying out each step. These references are for illustration and are not intended to limit the possible ways of carrying out any particular step of the method.

[0099] FIG. 15 is a flowchart showing steps performed in an exemplary method and can not recite the entire process or all steps of the method. While various steps of the method 500 are described below and depicted in FIG. 15 , the steps do not have to be performed in their entirety, and in some cases can be performed simultaneously or in a different order than shown.

[0100] At step 510, the method includes installing a thermally insulated shroud to a launch vehicle. The shroud can include a rigid frame and a flexible thermal insulation material. For example, the shroud can include a plurality of hollow composite tubes connected by a scaffold that is additively manufactured and a thermal blanket material that includes layers of foil deposited on a thin, flexible plastic sheet.

[0101] Bolting the base portion of the shroud and / or otherwise fastening, joining, or attaching the shroud to the payload adapter, mounting plate, and / or satellite assembly of the launch vehicle. For example, step 510 can include fastening the base plate of the shroud to a mounting plate that is bolted to an annular secondary payload adapter such that the longitudinal axis of the shroud extends radially outward from the annulus.

[0102] Step 512 includes loading a satellite into the shroud. Loading the satellite can include inserting the satellite through the opening of the shroud and mounting the satellite to the support structure. The satellite can be mounted to the base portion of the shroud, the mounting plate, and / or the payload adapter of the launch vehicle. In some examples, loading the satellite into the shroud can include encasing a satellite or satellite assembly that has already been mounted to the launch vehicle with the shroud.

[0103] In some examples, step 512 can include loading multiple satellites into the shroud. In such examples, the satellites can be mounted sequentially. One or more loaded satellites can be mounted indirectly to the support structure through another satellite or multiple satellites. Launch preparations for one or more satellites can be performed and / or completed prior to continuing the method, and the next steps of the method can limit further physical access to the satellites.

[0104] Step 514 includes closing the door of the shroud. Closing the door can include allowing a biasing spring to cause rotation of the door about a hinge or hinge member such that the door blocks the opening through which the satellite was inserted. The step can also include securing or latching the door in the closed position. For example, a pin of a low-impact puller can engage a latch of the door.

[0105] Step 516 includes retracting the expandable struts of the shroud to a stowed position. The rigid frame and the door of the shroud can include a plurality of telescoping members that act as the expandable struts and allow the shroud to expand and retract along at least one axis. For example, the shroud can expand along an axis that is parallel to a launch axis of the launch vehicle. Retracting the expandable struts can include engaging one or more latches to hold the struts in the stowed position.

[0106] Two or more of the telescoping members can include actuators for driving expansion of the shroud. Step 516 can include compression, deactivation, and / or reversal of the actuators. For example, the step can include retracting a fluid-damped passive spring actuator. In such examples, retraction of the actuator can be regulated by a check valve to limit the rate of retraction. Step 516 can be performed manually by a user or by a payload specialist such as a launch.

[0107] Step 518 includes engaging the frame of the shroud with the satellite. The frame and the satellite can include corresponding structures configured to engage as the expandable struts are retracted in step 516. For example, tabs can be secured to upper and lower members that frame an opening of the shroud. As the shroud is retracted, recesses or brackets on the satellite adjacent the opening can receive the tabs. Engagement between the frame and the satellite can limit or prevent lateral movement of the thermal shroud.

[0108] Step 520 includes launching the vehicle into space. Launching the vehicle can include carrying the thermal shroud and the loaded satellite into space. This step can also include positioning the launch vehicle for deployment of one or more satellites. For example, positioning the launch vehicle can include placing the vehicle in a desired orbit of the satellite.

[0109] At step 522, the method includes expanding the expandable struts of the shroud to a deployed position. Expanding the struts can include releasing one or more latches engaged in step 516 to allow expansion. Expanding the struts can also include engaging or activating active actuators, or allowing passive actuators to actuate. For example, this step can include allowing a spring bias of a fluid-damped passive spring actuator to expand the two struts at a controlled rate. Expandable struts that do not include actuators can expand in response to actuated struts. In some instances, expanding the struts can include engaging ratchet locks of one or more expandable struts to prevent retraction back to a stowed position.

[0110] Step 524 includes separating the frame from the satellite. Expansion of the expandable struts can separate the frame and corresponding structures on the satellite. For example, as the members expand away from the satellite, tabs secured to the upper and lower members can retract from recesses or brackets on the satellite. Separating the frame from the satellite can leave an unobstructed path for the satellite through the opening.

[0111] At step 526, the method includes opening the door. Opening the door can include releasing latches engaged in step 514. The door can be opened using actuators. For example, a paraffin linear actuator connected to a hinge member of the door through a linkage can rotate the hinge member to open the door. The door can open at least 90 degrees or more to provide an unobstructed exit for the loaded one or more satellites.

[0112] Step 528 includes deploying one or more satellites. Deployment can include actuating a separation system to provide a separation pulse out of the opening of the shroud and away from the launch vehicle. In instances where multiple satellites are loaded into the shroud, the satellites can be deployed sequentially. In such instances, the method can include repeating step 514 to close the door, maneuvering the launch vehicle for deployment of additional satellites, and repeating step 526 to open the door again before deployment of the next satellite.

[0113] Further example and non-exclusive examples in accordance with the present disclosure are described in the following paragraphs, including embodiments in accordance with the following:

[0114] In an example in accordance with the present disclosure, a satellite assembly 402 includes a satellite 100, 413, 415 stowed in a launch vehicle 124, a shroud 200 including a frame 210 supporting a flexible thermal blanket 212 that encloses the satellite.

[0115] Optionally, in the satellite assembly of the preceding paragraph, wherein the shroud 200 has a proximal end 214 and a distal end 216, the distal end is expandable.

[0116] Optionally, in the satellite assembly of one of the preceding paragraphs, the distal end 216 of the shroud 200 includes a door 218 that expands and opens when the satellite 100, 413, 415 is deployed.

[0117] Optionally, in the satellite assembly of one of the preceding paragraphs, the door 218 is configured to close after the satellite 100, 413, 415 is deployed.

[0118] Optionally, in the satellite assembly of one of the preceding paragraphs, the shroud 200 has trapezoidal sides 224, 226.

[0119] Optionally, in the satellite assembly of one of the preceding paragraphs, the shroud 200 has a stowed position 244 and a deployed position 248, the satellite 100, 413, 415 limiting lateral movement of the shroud when the shroud is in the stowed position and releasing the lateral limitation when the shroud expands to the deployed position.

[0120] Optionally, in the satellite assembly of one of the preceding paragraphs, the shroud 200 has a proximal end 214 and a distal end 216, the distal end having a door 218 covering an opening 252, the opening being defined by a top frame element 258, a bottom frame element 256, and two side frame elements 254, the side frame elements being able to telescope between a stowed position 282 and a deployed position 284 for expanding the size of the opening.

[0121] Optionally, in the satellite assembly of one of the preceding paragraphs, the satellite 100, 413, 415 engages at least one of the top frame element and the bottom frame element 256, 258 when the side frame elements are in the stowed position 282, thereby limiting lateral movement of the shroud 200.

[0122] In another example in accordance with the present disclosure, an apparatus 402 for transporting a satellite into space includes a launch vehicle 124 and a thermal shroud 200 including a frame 210 and a flexible wall material 212 supported by the frame, the shroud being connected to the launch vehicle and configured for containing a satellite 100, 413, 415 during a launch phase 20, 520.

[0123] Optionally, in the apparatus of the preceding paragraph, the shroud 200 is configured to house a plurality of stacked satellites 412.

[0124] Optionally, in the apparatus of one of the preceding paragraphs, further comprising a ring structure 410 connected to the launch vehicle 124, the ring structure having a central axis 418 parallel to a launch axis 416 of the launch vehicle, wherein the shroud 200 is mounted on the ring structure.

[0125] Optionally, in the apparatus of one of the preceding paragraphs, the shroud 200 has a long axis 228 perpendicular to the launch axis 416.

[0126] Optionally, in the apparatus of one of the preceding paragraphs, the shroud 200 has a proximal end 214 and a distal end 216, the distal end being expandable.

[0127] Optionally, in the apparatus of one of the preceding paragraphs, the distal end 216 is expandable only in a direction 420 parallel to the launch axis 416 of the launch vehicle 124.

[0128] In another example in accordance with the present disclosure, an assembly 402 for transporting satellites into space, comprising: a ring structure 410 having a central axis 418 parallel to a launch direction 416; and a plurality of shrouds 430 extending radially outward from the ring structure, each shroud 200 comprising a frame 210 supporting a flexible wall material 212, having a proximal end 214 connected to the ring structure, and having a distal end 216 comprising a door 218 for allowing deployment of a satellite 100, 413, 415 into space 122.

[0129] Optionally, in the assembly of the preceding paragraph, the distal end 216 of each shroud 200 is expandable from a stowed configuration 244 to a deployed configuration 248.

[0130] Optionally, in the assembly of one of the preceding paragraphs, the distal end 216 of each shroud 200 is expandable only in a direction 420 parallel to the launch direction 416.

[0131] Optionally, in the assembly of one of the preceding paragraphs, each shroud 200 has a top side 224, a bottom side 226, and a pair of lateral sides 220, 222, wherein each of the top side, the bottom side, and the proximal end 214 remains constant in area as each of the pair of lateral sides and the distal end 216 expands.

[0132] Optionally, in the assembly of one of the preceding paragraphs, the distal end 216 of each shroud 200 has a rectangular opening 252 framed by a top strut 258, a bottom strut 256, and a pair of opposing side struts 254, each side strut comprising a spring 332 for urging expansion of the distal end into a deployed configuration 248.

[0133] Optionally, in the assembly of one of the preceding paragraphs, the door 218 has a pair of opposing frame members 266, each frame member being able to telescope parallel to the pair of opposing side struts 254.

[0134] The different examples of expandable thermal shrouds described herein provide several advantages over known solutions for thermal protection of satellites during launch. For example, the example examples described herein allow for the use of lightweight thermal insulation materials.

[0135] Further, among other benefits, the example examples described herein maximize the available internal volume.

[0136] Further, among other benefits, the example examples described herein enable a larger satellite for a given available volume in a launch vehicle.

[0137] Further, among other benefits, the example examples described herein allow for protection of multiple connected satellites.

[0138] Further, among other benefits, the example examples described herein allow for distal support and stabilization from the satellite.

[0139] Further, among other benefits, the example examples described herein allow for controlled low-impact expansion.

[0140] No known system or device can perform these functions, particularly for satellites mounted to a secondary payload adapter. Accordingly, the example examples described herein are particularly useful for micro-satellites. However, not all of the examples described herein provide the same advantages or the same degree of advantages.

[0141] The disclosure set forth above can include a plurality of different examples that each have individual utility. While each of these has been disclosed in its preferred form, the particular examples disclosed herein are not to be construed as limiting as many variations are possible. Just as the parts are used within this disclosure, such parts are only for organizational purposes. The subject matter of this disclosure includes all novel and nonobvious combinations and subcombinations of the various elements, features, functions and / or properties disclosed herein. The following claims particularly point out certain combinations and subcombinations that are regarded as novel and nonobvious. Other combinations and subcombinations can be claimed in applications claiming priority from this application or a related application. Such claims, whether broader, narrower, equal, or different, are also regarded as included within the subject matter of the present disclosure.

Claims

1. A satellite assembly (402), wherein, The satellite assembly comprises: a satellite (100, 413, 415) stowed in a launch vehicle (124), a shroud (200) comprising a frame (210) supporting a flexible thermal blanket (212) surrounding the satellite, wherein the shroud (200) has a proximal end (214) and a distal end (216) having a door (218) covering an opening (252) built from a top frame element (258), a bottom frame element (256) and two side frame elements (254) which are retractable between a stowed position (282) and a deployed position (284) to enlarge the size for the opening.

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

3. The satellite assembly of claim 1 or 2, wherein, The shroud (200) has the stowed position (244) and the deployed position (248), the satellite (100, 413, 415) restricting lateral movement of the shroud when the shroud is in the stowed position and releasing lateral restriction when the shroud is expanded into the deployed position.

4. The satellite assembly of claim 1, wherein, When the side frame elements are in the stowed position (282), the satellite (100, 413, 415) engages at least one of the top frame element and the bottom frame element (256, 258) restricting lateral movement of the shroud (200).

5. An apparatus (402) for transporting a satellite into space, the apparatus comprising: a launch vehicle (124), a thermally insulated shroud (200) comprising a frame (210) and a flexible wall material (212) supported by the frame, the shroud being connected to the launch vehicle and configured to house a satellite (100, 413, 415) during a launch phase (20, 520), wherein the shroud (200) has a proximal end (214) and a distal end (216) having a door (218) covering an opening (252) built from a top frame element (258), a bottom frame element (256) and two side frame elements (254) which are retractable between a stowed position (282) and a deployed position (284) to enlarge the size for the opening.

6. The apparatus of claim 5, wherein, The shroud (200) is configured to house a plurality of stacked satellites (412).

7. The apparatus of claim 5 or 6, further comprising a ring structure (410) connected to the launch vehicle (124), the ring structure having a central axis (418) parallel to a launch axis (416) of the launch vehicle, wherein, The shroud (200) is mounted on the ring structure, wherein the shroud (200) has a long axis (228) perpendicular to the launch axis (416).

8. The apparatus of claim 5 or 6, wherein, The distal end is expandable in a direction (420) parallel to a launch axis (416) of the launch vehicle (124).

9. An apparatus (402) for transporting a satellite into space, the apparatus comprising: a ring structure (410) having a central axis (418) parallel to a launch direction (416), a plurality of shrouds (430) extending radially outward from the ring structure, each shroud (200) comprising a frame (210) supporting a flexible wall material (212), each shroud having a proximal end (214) connected to the ring structure and having a distal end (216) comprising an opening (252) and a door (218) for covering the opening (252) and allowing deployment of a satellite (100, 413, 415) into space (122), wherein the opening (252) is built from a top frame element (258), a bottom frame element (256) and two side frame elements (254) that are telescopable between a stowed position (282) and a deployed position (284) to enlarge the size for the opening.

10. The apparatus of claim 9, wherein, The distal end (216) of each shroud (200) is expandable from a stowed configuration (244) to a deployed configuration (248).

11. The apparatus of claim 10, wherein, The distal end (216) of each shroud (200) is expandable only in a direction (420) parallel to the launch direction (416).

12. The apparatus of any one of claims 9-11, wherein, Each shroud (200) has a top side (224), a bottom side (226) and a pair of lateral sides (220, 222), wherein each of the top side, the bottom side and the proximal end (214) remains constant in area when each of the pair of lateral sides and the distal end (216) is expanded.

13. The apparatus of claim 10 or 11, wherein, The opening (252) is a rectangular opening built from a top strut, a bottom strut and a pair of opposing side struts, each side strut comprising a spring (332) for urging the distal end to expand into a deployed configuration (248).

14. The apparatus of claim 13, wherein, The door (218) has a pair of opposing frame members (266), each frame member being telescopable parallel to the pair of opposing side struts (254).

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