Space vehicle with paraglider re-entry capability and related systems and methods - Patents.com

Abstract

A space vehicle with paraglider re-entry capability and related systems and methods are disclosed. An exemplary system includes a reusable space vehicle, a foldable, deployable and retractable re-entry heat shield mounted on the space vehicle, and foldable, deployable and retractable flexible paraglider wings also mounted on the space vehicle. Thus, the space vehicle can perform repeated space-based missions and can be refurbished and restocked on Earth and / or at an orbital dock between missions.

Description

[Technical field]

[0001] TECHNICAL FIELD The present technology relates generally to space vehicles, such as satellites, having paraglider re-entry capabilities, and related systems and methods.

[0002] (CROSS-REFERENCE TO RELATED APPLICATIONS) This application claims priority to pending U.S. Provisional Application No. 63 / 280,567, filed November 17, 2021, and incorporated herein by reference. [Background technology]

[0003] Satellites have been used for decades to perform useful missions in space, including Earth orbit. One drawback of existing satellite technology is that satellites are limited in the amount of fuel and / or other consumables they carry during their missions. A further drawback is that satellites and other space missions generate debris in space. Thus, there remains a need for satellites that can return to Earth to aid in refueling, refueling, and / or retrieving space debris back to Earth. [Brief description of the drawings]

[0004] [Figure 1A] 1A-1C are partial schematic isometric views of a space vehicle (e.g., a satellite) going through several stages of a mission, in accordance with an exemplary embodiment of the present technique;

[0005] [Figure 1B] 1 is a partial schematic diagram of an entire reusable cycle of a space vehicle, including launch, return, and refurbishment, in accordance with an embodiment of the present technology.

[0006] [Figure 2A] 1 illustrates a solar panel in a deployed configuration for performing a mission, as configured in accordance with an embodiment of the present technique. [Figure 2B]1 illustrates an exemplary space vehicle having a heat shield in a deployed configuration for return to Earth, as constructed in accordance with an embodiment of the present technique.

[0007] [Figure 3A] 1 illustrates a portion of an exemplary space vehicle constructed in accordance with an embodiment of the present technology; [Figure 3B] 1 illustrates a portion of an exemplary space vehicle constructed in accordance with an embodiment of the present technology;

[0008] [Figure 4A] 1 illustrates an exemplary technique for deploying solar panels on a space vehicle in accordance with an embodiment of the present technique. [Figure 4B] 1 illustrates an exemplary technique for deploying solar panels on a space vehicle in accordance with an embodiment of the present technique.

[0009] [Figure 5A] 1 is a partial cross-sectional schematic diagram of a portion of an exemplary space vehicle, showing a pressurized tank and paraglider system, configured in accordance with an embodiment of the present technology; [Figure 5B] 1 is a partial cross-sectional schematic diagram of a portion of an exemplary space vehicle, showing a pressurized tank and paraglider system, configured in accordance with an embodiment of the present technology;

[0010] [Figure 6A] 1 shows a representative diagram of a space vehicle having an expandable heat shield in accordance with an embodiment of the present technique; [Figure 6B] 1 shows a representative diagram of a space vehicle having an expandable heat shield in accordance with an embodiment of the present technique; [Figure 6C] 1 shows a representative diagram of a space vehicle having an expandable heat shield in accordance with an embodiment of the present technique;

[0011] [Figure 7A] 1 illustrates, in a partially schematic manner, a re-entry system configured to return a space vehicle to Earth in accordance with an embodiment of the present technique; [Figure 7B] 1 illustrates, in a partially schematic manner, a re-entry system configured to return a space vehicle to Earth in accordance with an embodiment of the present technique;

[0012] [Figure 7C] 1 illustrates an exemplary space vehicle carried by inflatable wings during descent in accordance with an embodiment of the present technique.

[0013] [Figure 8] FIG. 1 is a partial schematic block diagram of an assembly / refurbishment facility configured in accordance with an embodiment of the present technology.

[0014] [Figure 9A] 4 illustrates an exemplary satellite configured in accordance with a further embodiment of the present technique; [Figure 9B] 4 illustrates an exemplary satellite configured in accordance with a further embodiment of the present technique; [Figure 9C] 4 illustrates an exemplary satellite configured in accordance with a further embodiment of the present technique; [Figure 9D] 4 illustrates an exemplary satellite configured in accordance with a further embodiment of the present technique;

[0015] [Figure 10] 1 illustrates a dispersion map showing the dispersion footprint of a vehicle configured to land by inflatable paraglider wings in accordance with an embodiment of the present technology; DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0016] The present technology generally relates to space vehicles (such as satellites) having deployable flexible inflatable wings (e.g., paraglider wings) for returning to Earth, and related systems and methods. A space vehicle configured according to an embodiment of the present technology can be launched into space to perform one or more missions and return to Earth under the support, control, and / or guidance of the inflatable wings. After arriving at Earth, the space vehicle can be refurbished, refueled, and / or otherwise re-equipped for further missions. This cycle can be repeated multiple times, and the space vehicle may have a much longer service life than a conventional satellite. Furthermore, such space vehicles can be used to bring materials back to Earth. For example, in an exemplary embodiment, such space vehicles can be used to return space debris to Earth.

[0017] Specific details of some embodiments of the present technology are described below with reference to selected configurations to provide a thorough understanding of these embodiments, with the understanding that the present technology may be implemented in the context of other embodiments. Some details describing structures and / or processes are well known and often associated with other types of space vehicles and / or related systems and / or components, but for clarity are not described herein as they may unnecessarily obscure some important aspects of the present disclosure. Furthermore, although the following disclosure describes some embodiments of different aspects of the present technology, some other embodiments of the present technology may have different configurations and / or components than those described in this section. Thus, the present technology may have other embodiments having additional elements and / or not having some of the elements described below with reference to Figures 1-9D.

[0018] Many embodiments of the technology described below may take the form of computer or machine or controller executable instructions, including routines executed by a programmable computer or controller. Those skilled in the art will appreciate that the technology may be implemented on computer / controller systems other than those shown and described below. The technology may be embodied in a special purpose computer, controller, or data processor that is specifically programmed, configured, or constructed to execute one or more of the computer executable instructions described below. Thus, the terms "computer" and "controller" as used generally herein refer to any data processor, and may include Internet appliances and handheld devices (palmtop computers, wearable computers, cellular or mobile phones, multiprocessor systems, processor-based or programmable consumer electronics, network computers, minicomputers, etc.). Information processed by these computers may be presented on any suitable display medium, including liquid crystal displays (LCDs).

[0019] The technology may also be practiced in a distributed environment where tasks or modules are performed by remote processing devices linked through a communications network. In a distributed computing environment, program modules or subroutines may be located in local and remote memory storage devices. Aspects of the technology described below may be stored or distributed on a computer-readable medium, including a magnetic or optically readable or removable computer disk, and distributed electronically over a network. Data structures and data transmissions specific to aspects of the technology are also included within the scope of embodiments of the technology.

[0020] 1A and 1B generally illustrate an exemplary mission of a satellite performed in accordance with the present technology. Referring first to FIG. 1A, an exemplary space vehicle 110, e.g., a satellite, is shown in a first stage after deployment from a launch vehicle. In stage 2 of FIG. 1A, the space vehicle 110 performs a mission. For example, the mission may include a sensing mission, an observation mission, a space debris collection mission, and / or any other suitable mission. In stage 3, the space vehicle 110 inflates a deployable re-entry heat shield in preparation for re-entering the Earth's atmosphere. In stage 4, the space vehicle 110 deploys a paraglider or other inflatable wings to glide back to Earth.

[0021] As used herein, the term paraglider generally refers to a type of inflatable / foldable wing. Paragliders differ from parachutes in that parachutes slow descent but provide little or no lateral maneuverability. Paragliders differ from parafoils in that they typically have a higher glide ratio than parafoils, supporting a greater range of lateral movement and a greater level of lateral maneuverability. For example, paragliders typically have glide ratios greater than 4:1. The inflatable cells of a paraglider typically have different geometries (e.g., different sizes and / or shapes) across the span of the paraglider wing. The speed capabilities / range of a paraglider differ from a parafoil due to these factors, and as a result, a paraglider can be deployed at higher altitudes and fly longer distances than a parafoil.

[0022] FIG. 1B shows, in a schematic manner, additional elements of the overall cycle performed by the space vehicle 110, similar to the stages described above with reference to FIG. 1A. For example, the overall system 100 may include a launch site 102, where a launch vehicle 101 is directed into space. The launch vehicle 101 carries the space vehicle 110 and deploys it, for example, at or near a suitable orbital insertion point. After the space vehicle 110 completes its mission, it deploys an inflatable heat shield 181. Upon re-entering the Earth's atmosphere, the space vehicle 110 may deploy a re-entry system 190, which may include a drogue chute 191 that is deployed first, followed by a paraglider 193 or other inflatable wing. In some embodiments, the drogue chute 191 separates from the overall landing system 190 and descends to Earth on its own, while the space vehicle 110 returns to Earth under the control of the paraglider 193. In at least some embodiments, the space vehicle returns to Earth at or near launch site 102. The space vehicle may land at any of a variety of suitable terrestrial sites, including terrestrial sites, water-based sites, and / or airborne sites. Exemplary terrestrial sites include the ground, a platform, a building, a net, a terrestrial vehicle, and / or other suitable terrestrial surfaces. Exemplary water-based sites include a fresh or saltwater surface, a floating platform, an aircraft carrier, a barge, another water-based vehicle, and / or other suitable water-based surfaces. Exemplary airborne sites include an airborne location where a helicopter or other airborne vehicle captures the space vehicle, for example, by hooking it. In any of these embodiments, the overall system 100 may further include a ground system 170 (terrestrial or water-based), which in some embodiments includes an assembly / refurbishment facility 171. At the assembly / refurbishment facility 171, the space vehicle 110 is refurbished and returned to the same or a different launch vehicle 101 for a new mission.

[0023] 2A-7C illustrate an exemplary space vehicle 110 configured in accordance with some embodiments of the present technology. For purposes of description in the following figures, some elements may be removed to provide visibility of other elements. Thus, while some of the figures described below appear to show an incomplete space vehicle, it will be understood that selected elements are not present solely to enhance the reader's ability to understand other particular features of the overall system.

[0024] 2A is a partial schematic isometric view of an exemplary space vehicle 110 configured in accordance with an embodiment of the present technology. The space vehicle 110 may include a first end portion 111, a second end portion 112, and a central portion 113 located between the first end portion 111 and the second end portion 112. The space vehicle 110 may include, for example, a payload bay 114 disposed in the central portion 113. The payload bay 114 may include one or more payload openings, for example, a first payload opening 115 and a second payload opening 116. The first payload opening 115 is disposed in the central portion 113, and the second payload opening 116 is disposed in the first end portion 111.

[0025] The space vehicle 110 may include one or more structural panels 119 that provide the overall vehicle structure, and may further include one or more solar panels 120 that collect energy to operate the space vehicle systems, including the propulsion system 160 (shown in FIG. 2B). During a mission in space, the solar panels 120 may be deployed outwardly from the space vehicle 110, as shown in FIG. 2A. The solar panels 120 may be stored along a central portion 113 of the space vehicle upon re-entry. One or more actuators 135 (one shown diagrammatically in FIG. 2A) may move the solar panels between a stored position and a deployed position under the direction of a vehicle controller, described below with reference to FIG. 3A. The space vehicle 110 may further include a radiator system 118 that directs heat generated by components aboard the space vehicle 110 outwardly into space. In some embodiments, the radiator system 118 may be mounted on the structural panels 119, the solar panels 120, and / or other suitable elements and / or structures of the space vehicle 110.

[0026] To aid in re-entry, space vehicle 110 may include a heat shield 181 disposed at or towards second end portion 112. Heat shield 181 may form part of an overall re-entry system 180 and may be deployed to shield space vehicle 110 from heat encountered during re-entry. Second end portion 112 may also house a landing system 190, such as a deployable paraglider system 193, that guides space vehicle 110 to the ground after re-entry.

[0027] 2B is a partial schematic view of the space vehicle 110 with the solar panels 120 retracted for re-entry. Additionally, a heat shield 181 is deployed in preparation for re-entry. The heat shield 181 may include a flexible thermal protection layer 182 that helps shield the space vehicle 110. Two first attachment elements 194a (one shown diagrammatically) attach the space vehicle 110 to a corresponding paraglider line during final descent. The space vehicle 110 may further include one or more propulsion modules 161 that may be used to maintain the orientation of the space vehicle 110 en route to the mission, during the mission, and / or to re-orient the space vehicle for re-entry towards the end of the mission. Further details of the propulsion system 160 are provided below.

[0028] 3A is a partial schematic diagram of the space vehicle 110 with some components removed to show elements within the space vehicle 110. The space vehicle 110 may include a first bulkhead 123a at the first end portion 111, a second bulkhead 123b at the second end portion 112, and an intermediate avionics bulkhead 121, with avionics housed between the avionics bulkhead 121 and the second bulkhead 123b. The avionics on board the space vehicle 110 may include a vehicle controller 122 for controlling the operation of the space vehicle itself (e.g., propulsion and navigation operations, as well as operations to deploy and / or retract the solar panels 120, the heat shield 181, the paraglider system 193, and / or other systems). A payload controller 124 may control the operation of other systems or sensors, including systems carried within the payload bay 114, such as a telescope, a retractable arm, and / or a system for retrieving space debris. Further exemplary systems include docking and other rendezvous systems, magnets, telescoping booms, servos (eg, to hold or latch other elements open or closed), and / or recovery nets.

[0029] A paraglider system 193, shown in a stowed state, is positioned adjacent to the second bulkhead 123b. The payload bay 114 is housed between the first bulkhead 123a and the second bulkhead 123b. A structural panel 119, extending longitudinally along the longitudinal axis L of the space vehicle 110, may be attached between the two bulkheads 123a, 123b to support the overall structure of the space vehicle. Figure 3A further shows an exemplary stowed or fixed solar panel 120a, also aligned along the longitudinal axis L.

[0030] Figure 3B illustrates an embodiment of a space vehicle 110 having one or more fixed solar panels 120a disposed radially outward from corresponding structural panels 119, parallel to the longitudinal axis L. As also shown in Figure 3B, one or more deployable solar panels 120b can operate both to provide power during a mission of the space vehicle 110 and to provide access to the payload bay 114. Thus, the deployable solar panels 120b can operate both as solar panels and as doors to the payload bay 114.

[0031] In the embodiment shown in FIG. 3B, the individual deployable solar panels 120b are hinged along an axis transverse to the longitudinal axis L of the space vehicle 110. In other embodiments, the deployable solar panels 120b may have other configurations for deployment and storage. For example, referring now to FIG. 4A, the space vehicle 110 may include a deployable solar panel 120b including a plurality of segments 125, e.g., six segments identified as segments 125a-125f. The deployable solar panel 120b is shown in a deployed position in FIG. 4A. To store the deployable panel 120b, the first three segments 125a-c are pivoted together about a first axis 127a (e.g., parallel to the longitudinal axis L) to overlie the second three segments 125d-125f, as indicated by arrow A. The folded assembly is then rotated about the second axis 127b to fold the corresponding overlapping segments against the three corresponding edges 128a, 128b, 128c of the bulkheads 123a, 123b, as shown by arrow B. Thus, the first and sixth segments 125a, 125b are folded against the first edge 128a, the second and fifth segments 125b, 125e are folded against the second edge 128b, and the third and fourth segments 125c, 125d are folded against the third edge 128c. In certain embodiments, the deployable solar panel 120b may be deployed and stored using any number of suitable mechanisms. For example, the joints between adjacent segments may be spring loaded and biased toward the deployed position. A cable or cables may be wound to refold the segments into the stored position.

[0032] 4A also illustrates in greater detail a representative propulsion module 161. Propulsion module 161 may include one or more vernier thrusters 162 and one or more ACS thrusters 163. Vernier thrusters 162 may be used to impart small, precise position and orientation adjustments to space vehicle 110, while ACS thrusters 163 may be used to impart larger scale movements, such as, for example, positioning space vehicle 110 for re-entry and / or other maneuvers.

[0033] Figure 4B is a partial schematic diagram of one embodiment of the space vehicle 110 shown in Figure 4A, showing a solar concentrating element 129 (e.g., a solar cell and / or a battery) mounted on a deployable solar panel 120b, and a plurality of fixed solar panels 120a. In other embodiments, the fixed solar panel 120a may be replaced with a second deployable solar panel 128b that operates in a manner similar to the deployable configuration described above with reference to Figure 4A. Thus, each deployable solar panel 120b may extend in a generally opposite direction from one another.

[0034] FIG. 5A is a partial schematic diagram of a representative space vehicle 110 having a plurality of longitudinal structural elements 130 extending along a longitudinal axis L of the space vehicle 110 and providing structural support in conjunction with bulkheads 123a, 123b. As also shown in FIG. 5A, the space vehicle 110 may include an inflator 184 operably coupled to the heat shield 181 for deploying it. For example, the inflator may include an airtight pressurized tank 183 that supplies pressurized gas to the heat shield 181, an on-board gas generator 185, and / or another suitable gas source for deploying the heat shield. Representative gases for such a cryogenic gas system include nitrogen, hydrogen, and / or argon, with nitrogen and hydrogen being particularly suitable as gas generator products. The pressurized tank may also supply gas to the propulsion system 160, which may also operate via cryogenic (non-combustible) gas. The heat shield includes a nose cone 198, and a flexible material forming a majority of the heat shield is folded forward and packaged around the nose cone 198. FIG. 5B is a partial schematic end view of the space vehicle 110 shown in FIG. 5A, showing the avionics bulkhead 121, the pressurized tank 183, and the stowed paraglider system 193.

[0035] 6A-6C show an exemplary space vehicle 110 with a heat shield 181 in a deployed configuration. FIG. 6A is a partially schematic, partially cutaway view of the space vehicle 110 showing the longitudinal structural elements 130 and the expanded heat shield 181. As shown in FIG. 6A, the heat shield 181 may include a plurality of annular elements, each of which may include one or more expandable cells, that together form a generally conical shell toward the second end 112 of the space vehicle 110. This arrangement shields the space vehicle 110 with the second end portion 112 facing at least partially downward as the space vehicle 110 descends through the atmosphere.

[0036] FIG. 6B is a partial schematic end view of the space vehicle 110 taken generally along line 6B-6B of FIG. 6A, showing the second bulkhead 123b, the avionics bulkhead 121, the pressurized tank 183, and the deployed heat shield 181.

[0037] 6C illustrates the space vehicle 110 with the heat shield 181 deployed and the outwardly facing thermal protective layer 182 positioned to protect the remainder of the heat shield 181 and the space vehicle 110 from re-entry heat loads. Exemplary materials for the heat shield 181 include Sigratherm KFA-5, Hi-Nicalon SiC, Zylon Webbing, silicon carbide, aerogel, carbon felt, Nextel 440 BF-2 (e.g., 20 mil), Kapton (e.g., about 0.5 mil to about 1.0 mil), Pyrogel 3350, Nextel 312 AF-14 (e.g., 14 mil), Kevlar (e.g., 5 mil), silicone coated Kevlar (e.g., 7-13 mil), and / or silicone coated Zylon (e.g., 7-13 mil).

[0038] The space vehicle 110 may further include photogrammetry and / or other visualization equipment 138 (shown diagrammatically in FIG. 6C), e.g., one or more cameras, to assess the expansion of the heat shield 181 and further to inflate, deflate, and / or otherwise control the heat shield in real time. Thus, visual sensors may monitor the heat shield when it is in a deployed state, a stowed state, and / or any intermediate state. Information obtained via these equipment may also be used to guide the refurbishment process, which is further described below with reference to FIG. 8. The aforementioned instruments may also be used to assess the performance and condition of the landing system (e.g., paraglider) during descent, and again to guide refurbishment operations after the space vehicle has landed. 7A-7C are schematic diagrams of an exemplary landing system 190 for a space vehicle 110. Beginning with FIG. 7A, the landing system 190 includes a paraglider system 193 including a wing 195 formed from a plurality of wing cells 196, with the individual wing cells 196 separated by wing ribs 189. The wing 195 may include an aerodynamic surface 197 and may be formed from a fabric or other flexible, foldable material that is easily compressed and compacted when stored and deploys under aerodynamic pressure to form a structurally semi-rigid shape suitable for generating sufficient lift to support the space vehicle 110. Exemplary materials include Porcher Skytex 32, Porcher Skytex 27 Double Coat, Porcher 7000 (all available from Porcher Sport of La Tour-du-Pin, France), Dominico N20D, Dominico 30, Dominico 20 (all available from Dominico Tex Corporation of Daegu, South Korea).

[0039] In Fig. 7A, the individual wing ribs are indicated by reference numerals 189a-189g. The ribs are attached to line cascades 187 that include individual lines 186. Thus, as shown in Fig. 7A, the paraglider system 193 may include two line cascade assemblies 187, one for the right half of the wing 195 and one for the left half of the wing 195. Each line cascade 187 may be connected to a corresponding second attachment element 194b, which is connected to the first attachment element 194a described above with reference to Fig. 2B.

[0040] 7B is a partial schematic isometric view of wing ribs 189a-189g having a generally airfoil type shape. In at least some embodiments, ribs 189a-189g all have similar or identical shapes and sizes, although they appear to have different thicknesses depending on the curvature of wing 195. In other embodiments, the airfoil shape may vary along the span of wing 195.

[0041] Figure 7C shows space vehicle 110 with wings 195 inflated and deployed to guide space vehicle 110 to its landing site. As mentioned above, a drogue parachute may be used to extract, deploy and / or inflate wings 195, and then detach from wings 195 as space vehicle 110 descends. For purposes of illustration, details of line cascade 187 are not shown in Figure 7C.

[0042] In operation, the wings 195 may be deployed at altitudes greater than 18 kilometers, such as 20 kilometers or more. This altitude, combined with a high glide ratio (e.g., at least 5:1, up to 12:1 or greater) of the wings 195, may provide several advantages. For example, it may allow the space vehicle 110 to avoid weather systems while having sufficient range to land at an intended landing site. Alternatively, the additional range may allow the space vehicle 110 to land at a greater variety of alternative landing sites, if conditions require.

[0043] In certain embodiments, the shape of the wings 195 may be controlled using a feedback control algorithm that modifies the shape of the wings to control the rate of descent and / or trajectory of the space vehicle 110. Exemplary techniques for steering the wings may include servos connected in line cascade, and / or brake fans or other suitable devices. The control algorithm may dynamically reduce the control input based on the IMU limits from the combined acceleration and gyro sensors. In general, the space vehicle 110 deploys the wings 195 after decelerating to a subsonic Mach number, e.g., a Mach number less than 0.7, and while the space vehicle is within a target altitude window. A typical altitude window is 3 km to 30 km. Appropriate sensors (e.g., flight speed sensor and altimeter) may be used to identify target parameters that trigger deployment. The deployment of the paraglider may be accomplished using the drogue chute described above alone or in combination with a heat shield. The paraglider wing 195 may also include features to prevent the lines constituting the line cascade from tangling and / or devices configured to untangle lines that may become tangled.

[0044] The overall system may include one or more of several technologies to target a specific landing location. For example, a radio frequency (RF) beacon may be a homing beacon. In other embodiments, the space vehicle 110 may land according to a waypoint determined by GPS. In other embodiments, an optical beacon or digital map optical reference (e.g., on-board) may be used in conjunction with cameras and / or other sensors to avoid hazards and / or match detected features with corresponding features on a map. More generally, any of the following technologies may be used alone or in combination to navigate to the landing site once the paraglider is deployed: GPS, radar altimetry, optical navigation, radio ranging, quantum compass, ground beacon-based systems, and / or remote control via a human operator on the ground. In any of the foregoing embodiments, the space vehicle 110 may receive up-to-date weather and / or other relevant information to enable real-time or near real-time deviations from a pre-planned descent path, for example, in an automated manner under the control of the vehicle controller 122 (FIG. 3A). In some embodiments, the information is uploaded to the space vehicle from the ground or downloaded from an orbiting satellite. In other embodiments, this information may be replaced or supplemented with information obtained by the space vehicle 110 itself. In any of these embodiments, the information may include weather information as described above, or other information such as changed conditions at the target landing site. Thus, the space vehicle may fly according to primary, secondary, and tertiary safety zones and may trigger course corrections in real time via collected real-time weather (and / or other) information. Any suitable technique may be used for jet stream and geographic route planning, such as statistical evaluation of ERA5 reanalysis datasets.

[0045] In addition to the aforementioned techniques for controlling the descent path of the space vehicle, the space vehicle 110 may include structural components such as small fins, small winglets, grid fins, and / or other aerodynamic surfaces. Such surfaces may be controlled to alter the center of pressure of the space vehicle and / or to control its orientation during the paraglider's deployment and / or descent. Residual cryogenic gas from the propellant tanks may also be used during the descent and landing phases to properly position and / or orient the space vehicle.

[0046] In at least some embodiments, the deployed heat shield 181 is folded before the paraglider 193 is deployed to avoid interfering with the aerodynamic operation of the paraglider. For example, the heat shield 181 can be deflated and (optionally) re-stowed (or partially re-stowed), or the heat shield can be removed and returned separately to a refurbishment site, described below. In other embodiments, the heat shield can operate as a descending surface even after the paraglider 193 is deployed. Thus, the heat shield 181 can help to orient and / or decelerate the space vehicle 110. Thus, features of the paraglider system can be designed to account for aerodynamic forces resulting from the presence of the expanded heat shield 181 when descending through the atmosphere.

[0047] 8 is a schematic block diagram of an exemplary assembly and / or refurbishment facility 171 that can be used for both manufacturing space vehicles and refurbishment of such vehicles according to embodiments described herein. Facility 171 may thus include production line 172a and refurbishment line 172b. Production line 172a may include one or more component stations 150 that feed components to assembly line 151. Assembly line 151 produces completed space vehicles 110. Once space vehicle 110 is constructed, all systems are verified and validated, as shown in block 153. In block 154, space vehicle 110 is launched via launch vehicle, separated from the launch vehicle to perform a mission (block 155), and recovered (block 156), as described above.

[0048] Once the space vehicle 110 is recovered, it may be returned to facility 171, this time on refurbishment line 172b. Refurbishment line 172b may include an initial inspection station (block 157) and a refurbishment station (block 158). For example, at the initial inspection station, the space vehicle may be evaluated for damage, wear, and / or other issues that need to be addressed before the next mission. Suitable techniques for evaluating the space vehicle may include EMI techniques, x-ray techniques, thermal vacuum chamber testing, and / or other non-invasive testing techniques. Exemplary issues that may arise as a result of such testing include micrometeorite damage, vibration damage, and / or effects of radiation fields and / or electromagnetic interference.

[0049] As a result of the need for refurbishment, the space vehicle 110 may be specifically tailored for multiple access events. Specifically, elements of the space vehicle 110 may be positioned, configured, and / or arranged to allow easy entry into the interior of the space vehicle and easy access to elements of the space vehicle that may require refurbishment over the life of the space vehicle. For example, the space vehicle 110 may include interior compartments that are easily accessible via latches, quick release mechanisms, and / or conventional fasteners. Elements of the space vehicle 110 that may otherwise be located in small, inaccessible spaces are purposefully positioned for ease of access. This differs from conventional satellites, which are typically manufactured from the inside out and are not specifically designed to be accessed multiple times after performing a mission.

[0050] Once the vehicle has been modified, it may re-enter the production line 172a at block 153 (verification and validation) to continue the cycle and perform additional missions.

[0051] 9A-9D show a space vehicle 910 configured in accordance with further exemplary embodiments of the present technology. Starting with FIG. 9A, the space vehicle 910 may include a first end portion 911 carrying a propulsion deck 964 and a second end portion 912 carrying a re-entry system 980. The propellant deck 964 may carry one or more propulsion system elements and may be aligned along the longitudinal axis L (as well as at other locations) due to the absence of a payload bay door at the first end portion 911. The payload bay 914 is located in a central portion 913 between the propulsion deck 964 and the re-entry system 180 and is accessed via two opposing payload openings 915, one of which is shown in FIG. 9A. The space vehicle 910 may include a number of deployable solar panels 920b, which alone or in conjunction with one or more door panels 931, power the space vehicle 910 and control access to the payload bay 914.

[0052] Figure 9B shows the space vehicle 910 with the deployable solar panels 920b deployed and the door panel 931 open to allow access to the payload bay 114. Thus, sensors and / or other devices located within the payload bay 914 may have access to the outside environment. Figure 9C is a further illustration of the space vehicle 910 with the deployable solar panels 920b in the process of being stowed. Figure 9D shows the space vehicle 910 with the inflatable heat shield 981 deployed for re-entry.

[0053] In yet another embodiment, in addition to the general system elements described above with reference to FIG. 1B, the system may include a permanent or semi-permanent orbital platform that houses the space vehicle 110 during its mission. The orbital platform or orbital dock may include a common interface attachment mechanism for different space vehicles to connect. Once connected, the space vehicle may receive power and / or other supplies to perform its mission. The orbital dock may provide station keeping, power, data, communications, and / or thermal management for the space vehicle it hosts. The orbital dock may be launched with a deployable satellite on board. Once the dock is in orbit, the satellite may be detached and proceed to perform a mission before returning to Earth. One advantage of this arrangement is that the life of the space vehicle may be further extended and the number of times the space vehicle must return to Earth for refurbishment may be reduced. A further feature related to this advantage is that all the above operations are performed autonomously and therefore no crew is required on board the orbital dock.

[0054] One drawback of conventional space vehicle recovery systems is that the variance of approach errors for such space vehicles is on the order of about 10 km to over 1,000 km by the time the space vehicle lands. A representative variance zone is shown in FIG. 10. A conventional method to address this drawback is to carry additional on-board propellant that is used to fire thrusters that compensate for inaccuracies in the main engine combustion. A drawback of this approach is that it reduces the payload capacity of the space vehicle, which is neither efficient nor economical. In contrast, embodiments of the present technology include robotic or other automated paragliders that can be deployed in the upper atmosphere (e.g., at altitudes of 10 km or more, 15 km or more, or 20 km or more) where the error variance is smaller than on the ground. Paragliders have a high glide ratio and are controllable, so they can more easily fly within traditional dispersion zones (allowing for greater flexibility in landing sites) and / or can be controlled to operate within smaller dispersion zones (allowing for precise landings closer to the launch and / or refurbishment sites). As shown diagrammatically in FIG. 10 with an "x," the vehicle can be controlled to any of a number of landing zones, including, but not limited to, landing zones at the ends of the nominal trajectory.

[0055] From the foregoing, it will be understood that, although specific embodiments of the disclosed technology have been described herein for purposes of illustration, various modifications may be made without departing from the technology. For example, the space vehicle may perform missions other than those specifically identified above, including retrieving satellites in orbit and returning them to Earth for refurbishment and reuse. The space vehicle may have solar panels and / or other features different from those specifically shown herein.

[0056] Certain aspects of the technology described in connection with particular embodiments may be combined or eliminated in other embodiments. Moreover, although advantages associated with particular embodiments of the disclosed technology are described in connection with those embodiments, other embodiments may also exhibit such advantages, and not all embodiments necessarily exhibit such advantages to fall within the scope of the technology. Thus, the present disclosure and related technology may encompass other embodiments not expressly shown or described herein.

[0057] As used herein, the term "and / or," such as in "A and / or B," refers to A only, B only, or both A and B.

[0058] As used herein, the terms "about" and "approximately" refer to values ​​within 10% of the stated value.

[0059] In the event that the materials incorporated by reference herein conflict with the present disclosure, the present disclosure shall control.

[0060] The following examples provide further representative features of the present technology. Example 1 Reusable space vehicles; a foldable, deployable and retractable re-entry heat shield mounted on said space vehicle; a foldable, deployable, and retractable flexible paraglider wing mounted on said space vehicle; a payload bay mounted on the space vehicle; a solar panel mounted on said space vehicle and positioned to act as a door from said payload bay; a propulsion system on board the space vehicle, the propulsion system including a plurality of thrusters; a pressurized tank coupled to both the heat shield and the propulsion system for (a) providing propulsion to the space vehicle, and (b) inflating the heat shield; A space system comprising: Example 2 the space vehicle being elongated along a longitudinal axis; The space system of embodiment 1, wherein the solar panels are hinged on an axis aligned with the longitudinal axis. Example 3 the space vehicle being elongated along a longitudinal axis; The space system of any of Examples 1-2, wherein the solar panels are hinged on an axis transverse to the longitudinal axis. Example 4 at least one visual sensor mounted on the space vehicle and positioned to image at least one of the heat shield or the paraglider wing in at least one of a deployed state, a stowed state, or an intermediate state between the deployed state and the stowed state; The space system according to any one of Examples 1 to 3, further comprising: Example 5 a ground-based refurbishment facility configured to refurbish the space vehicle after it returns from space; The space system according to any one of Examples 1 to 4, further comprising: Example 6 Reusable space vehicles; a foldable, deployable and retractable re-entry heat shield mounted on said space vehicle; a foldable, deployable, and retractable flexible paraglider wing mounted on said space vehicle; A space system comprising: Example 7 an inflator coupled to the heat shield for deploying the heat shield The space system of Example 6 further comprises: Example 8 8. The space system of embodiment 7, wherein the inflator comprises an airtight pressurized tank, a gas generator, or both. Example 9 The space system of any of Examples 6-8, wherein the heat shield includes a plurality of expandable annular elements arranged to form a generally conical shape upon deployment. Example 10 The space system of any of Examples 6 to 9, wherein the paraglider wing includes a plurality of inflatable cells separated by ribs. Example 11 a deployable and retractable solar panel mounted on said space vehicle; an actuator operably coupled to the solar panel; a controller operably coupled to the actuator; Further equipped with The controller, when executed, deploying the solar panels while the space vehicle is in space; and Re-storing said solar panels in preparation for said space vehicle to return to Earth from space. 11. The space system of any one of Examples 6 to 10, having an instruction to perform the above. Example 12 a payload bay mounted on the space vehicle; a deployable and retractable solar panel mounted on said space vehicle; The space system of any of Examples 6 to 11, further comprising: the solar panel being movable between a first position covering at least a portion of the payload bay and a second position exposing at least a portion of the payload bay. Example 13 When executed, deploying the heat shield; deploying the paraglider wings mounted on the space vehicle; and Landing said space vehicle on the Earth's surface. The space system of any one of Examples 6 to 12, further comprising a controller having instructions to perform the above. Example 14 launching the space vehicle into space; Returning the space vehicle to Earth, deploying a foldable heat shield mounted on said space vehicle; deploying foldable paraglider wings mounted on the space vehicle; and Landing said space vehicle on the Earth's surface. and A method for operating a space system, comprising: Example 15 15. The method of claim 14, wherein deploying the paraglider wings includes deploying the paraglider wings at an altitude greater than 15 km. Example 16 determining that the space vehicle has decelerated to subsonic speed; deploying the foldable paraglider wings based at least in part on determining that the space vehicle has decelerated to subsonic speed; 16. The method of any of Examples 14-15, further comprising: (Example 17) navigating the space vehicle to a landing site after the paraglider wings are deployed (a) autonomously, (b) through human interaction, or (c) through both (a) and (b). The method of any of Examples 14-16, further comprising: (Example 18) deforming the wing to control at least one of a descent rate or a trajectory of the space vehicle. The method of any of Examples 14-17, further comprising: (Example 19) 19. The method of any of embodiments 14-18, wherein deploying the paraglider wings includes deploying the paraglider wings after the space vehicle has decelerated to less than Mach 0.7. (Example 20) deploying a drogue chute to deploy said paraglider wings. The method of example 19, further comprising: Example 21 receiving information updates and automatically altering the orbit of the space vehicle from a preplanned descent path based at least in part on the information updates. The method of any of Examples 14-20, further comprising: Example 22 folding said heat shield prior to deploying said paraglider wings. The method of any of Examples 14-21, further comprising: (Example 23) deploying the paraglider wings while the heat shield is deployed. The method of any of Examples 14-22, further comprising: Example 24 modifying the space vehicle after landing; relaunching said space vehicle after modification; The method of any of Examples 14-23, further comprising: (Example 25) 25. The method of example 24, wherein modifying includes accessing a compartment of the space vehicle, modifying a component within the compartment, and re-securing the compartment within the compartment. (Example 26) manufacturing said space vehicle and refurbishing said space vehicle at the same facility. The method of example 24, further comprising:

Claims

1. A reusable space vehicle configured to operate in space and re-enter the Earth's atmosphere; a foldable, deployable, and retractable re-entry heat shield mounted on the space vehicle, the re-entry heat shield deploying into a position that protects the space vehicle from thermal loads; a foldable, deployable, and retractable flexible paraglider wing mounted on the space vehicle, the paraglider wing deploying away from the heat shield and providing lift to the space vehicle within the atmosphere for landing; a payload bay mounted on the space vehicle; solar panels mounted on the space vehicle and positioned to operate without interfering with the payload bay during spaceflight; a propulsion system onboard the space vehicle, the propulsion system including a plurality of thrusters; one or more pressurized tanks coupled to one or both of the heat shield and the propulsion system for (a) providing propulsion for the space vehicle, or (b) inflating the heat shield; a vehicle controller coupled to the heat shield, the paraglider wings, and the propulsion system to enable coordinated guidance, navigation, and control of the space vehicle in space, during re-entry into the atmosphere, and within the atmosphere; A space system comprising:

2. the space vehicle is elongated along a longitudinal axis; The space system of claim 1 , wherein the solar panels are hinged on an axis aligned with the longitudinal axis.

3. the space vehicle is elongated along a longitudinal axis; The space system of claim 1 , wherein the solar panels are hinged on an axis transverse to the longitudinal axis.

4. at least one sensor mounted on the space vehicle and positioned to sense at least one of the heat shield or the paraglider wing in at least one of a deployed state, a stowed state, or an intermediate state between the deployed state and the stowed state; The space system of claim 1 further comprising:

5. a ground-based refurbishment facility configured to refurbish the space vehicle after it returns from space; The space system of claim 1 further comprising:

6. A reusable space vehicle configured to operate in space and within the Earth's atmosphere; a foldable, deployable, and retractable re-entry heat shield mounted on the space vehicle, the heat shield configured to be deployed to withstand thermal loads upon re-entry into the atmosphere; and a foldable, deployable, and retractable flexible paraglider wing mounted on the space vehicle, the paraglider wing configured to be deployed to provide lift and control for the space vehicle; one or more sensors mounted on the space vehicle that determine the state of the heat shield and the paraglider wings and provide vehicle velocity, acceleration, position, and gyroscopic data; a vehicle controller coupled to the sensor, the heat shield, and the paraglider wings, the vehicle controller selectively deploying the heat shield and deploying and manipulating the paraglider wings to facilitate coordinated re-entry of the space vehicle from space into and within the atmosphere; A space system comprising:

7. an inflator coupled to the heat shield for deploying the heat shield The space system of claim 6 further comprising:

8. The space system of claim 7 , wherein the inflator comprises an airtight pressurized tank, a gas generator, or both.

9. The space system of claim 6 , wherein the heat shield includes a plurality of inflatable annular elements arranged to form a generally conical shape when deployed.

10. 7. The space system of claim 6, wherein the paraglider wing comprises a plurality of inflatable cells separated by ribs, the wing having a glide ratio greater than 5:

1.

11. a deployable and retractable solar panel mounted on the space vehicle; an actuator operably coupled to the solar panel; a controller operably coupled to the actuator; Furthermore, The controller, when executed, deploying the solar panels while the space vehicle is in space; and Re-storing the solar panels in preparation for the space vehicle's return from space to Earth.

7. The space system of claim 6, further comprising instructions to:

12. a payload bay mounted on the space vehicle; a deployable and retractable solar panel mounted on said space vehicle; Furthermore, 7. The space system of claim 6, wherein the solar panel is movable between a first position covering at least a portion of the payload bay and a second position exposing at least a portion of the payload bay.

13. The controller, when executed, deploying the heat shield; deploying the paraglider wings mounted on the space vehicle; and Landing said space vehicle on the Earth's surface. The space system of claim 6 , further comprising instructions to:

14. A method of launching a space vehicle configured as a satellite into space; operating the space vehicle independently for at least a portion of a mission; returning the space vehicle to Earth, deploying a foldable heat shield carried by said space vehicle to protect against thermal loads; deploying foldable paraglider wings mounted on said space vehicle to enable deceleration and control of said space vehicle; providing one or more sensors on board the space vehicle to provide sensor data indicative of a state of the space vehicle, including deployment of the heat shield and the paraglider wings; and selectively coordinating operation of the heat shield and the paraglider wings using the sensor data to re-enter the space vehicle into the atmosphere and to guide, navigate, and control the space vehicle to land at a target location on the Earth's surface. and A method for operating a space system, comprising:

15. 15. The method of claim 14, wherein deploying the paraglider wings includes deploying the paraglider wings at an altitude greater than 15 km.

16. determining that the space vehicle has decelerated to subsonic speed; deploying the foldable paraglider wings based at least in part on determining that the space vehicle has decelerated to subsonic speed; 15. The method of claim 14, further comprising:

17. navigating the space vehicle to a landing site after the paraglider wings are deployed (a) autonomously, (b) with human interaction, or (c) with both (a) and (b).

15. The method of claim 14, comprising:

18. deforming the wings to control at least one of the descent rate or trajectory of the space vehicle.

15. The method of claim 14, further comprising:

19. 15. The method of claim 14, wherein deploying the paraglider wings comprises deploying the paraglider wings after the space vehicle has decelerated to less than Mach 0.

7.

20. deploying a drogue chute to deploy the paraglider wings.

20. The method of claim 17, further comprising:

21. receiving information updates and automatically altering the orbit of the space vehicle from a pre-planned descent path based at least in part on the information updates; 15. The method of claim 14, further comprising:

22. folding the heat shield before deploying the paraglider wings.

15. The method of claim 14, further comprising:

23. deploying the paraglider wings while the heat shield is deployed.

15. The method of claim 14, further comprising:

24. modifying the space vehicle after landing; relaunching said space vehicle after modification; 15. The method of claim 14, further comprising:

25. 25. The method of claim 24, wherein modifying comprises accessing a compartment of the space vehicle, modifying a component within the compartment, and re-securing the compartment within the compartment.

26. manufacturing said space vehicle and modifying said space vehicle at the same facility; 25. The method of claim 24, further comprising:

27. ​​The method of claim 14, wherein deploying foldable paraglider wings mounted on the space vehicle to enable deceleration and control of the space vehicle includes deploying paraglider wings having a glide ratio of at least 5:

1.

28. A refurbishable space vehicle in the form of a satellite configured to operate in space and re-enter the Earth's atmosphere; a deployable and foldable re-entry heat shield coupled to the space vehicle via an actuator, the heat shield configured to protect the space vehicle from thermal loads when deployed; a deployable, foldable, flexible wing coupled to the space vehicle via a plurality of cords, the wing having a surface, the space vehicle being steerable through deformation of the surface of the wing by applying tension to the cords upon deployment; a payload mounted on the space vehicle; one or more thrusters mounted on said space vehicle; one or more sensors onboard the space vehicle configured to assess the state of the space vehicle, including the state of the heat shield and the state of the wings, during re-entry and within the atmosphere; a vehicle controller coupled to the heat shield, the wings, the propulsion system, and the sensors to enable coordinated guidance, navigation, and control of the space vehicle as it descends into and within the atmosphere for landing at a target location on the Earth's surface; A space system comprising:

29. The space system of claim 28, further comprising an inflator coupled to the heat shield to deploy the heat shield.

30. The space system of claim 28, wherein the heat shield includes a plurality of expandable annular elements arranged to form a generally conical shape when deployed.

31. The space system of claim 28, wherein the heat shield includes a plurality of heat-resistant material elements that are mechanically deployed to form a generally conical shape when deployed.

32. The space system of claim 28, wherein the wing is a paraglider having a glide ratio greater than 5:

1.

33. The space system of claim 28, wherein the wing is a paraglider having a glide ratio greater than 12:

1.

34. A deployable and retractable solar panel mounted on said space vehicle; an actuator operably coupled to the solar panel; Furthermore, the vehicle controller is operably coupled to the actuator; The vehicle controller, when executed, deploying the solar panels while the space vehicle is in space; and and re-storing the solar panels in preparation for the space vehicle's return from space to Earth.

30. The space system of claim 28 having instructions to:

35. The space system of claim 28, further comprising a deployable and retractable solar panel mounted on the space vehicle, the solar panel being movable between a first position covering at least a portion of the payload and a second position exposing at least a portion of the payload.

36. The space system of claim 28, wherein the wing comprises a plurality of inflatable cells separated by ribs.

37. The space system of claim 28, wherein the wing comprises a flexible material.

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