Satellite stowage and deployment system

Abstract

Methods, systems, and devices for spacecraft stowage and deployment system are described. For example, a spacecraft stowage system may include a plurality of satellites (202), each including a body (220), a fixed antenna reflector (228), and an extendable arm (236). The system may further include a dispenser (252) to which the body (220) of each satellite is mounted. In some examples, each satellite (202) may be arranged around an axis of the dispenser (252) and the extendable arm (236) of each satellite (202) may have a stowed state such that the fixed antenna reflectors (228) are staggered at a first end of the dispenser and along the axis of the dispenser (252). Further, a method of deployment may include deploying a first reflector of a first satellite, releasing the first satellite, deploying a second reflector of a second satellite, and releasing the second satellite. Such operations may be extended to any quantity of satellites.

Description

SATELLITE STOWAGE AND DEPLOYMENT SYSTEMCROSS REFERENCE

[0001] The present Application for Patent claims priority to U.S. Provisional Patent Application No. 63 / 762,548 by MENDELSOHN et al., entitled “SATELLITE STOWAGE AND DEPLOYMENT SYSTEM,” filed February 24, 2025, which is assigned to the assignee hereof, and expressly incorporated by reference in its entirety herein.BACKGROUND

[0002] The following relates generally to communications, including satellite stowage and deployment systems.

[0003] Communications devices may communicate with one another using wired connections, wireless (e.g., radio frequency (RF)) connections, or both. Wireless communications between devices may be performed using a wireless spectrum that has been designated for a service provider, wireless technology, or both. In some examples, the amount of information that can be communicated via a wireless communications network is based on an amount of wireless spectrum designated to the service provider, and an amount of frequency reuse within the region in which service is provided. Satellite communications may use beamforming via antenna arrays to establish beams. However, processing and power constraints may limit throughput using beamforming.SUMMARY

[0004] The described techniques relate to improved methods, systems, devices, and apparatuses that support satellite stowage and deployment system.

[0005] A method for deploying a plurality of satellites from a spacecraft comprising a dispenser to which respective bodies of the plurality of satellites are removably mounted by an apparatus is described. The method may include deploying a first fixed antenna reflector of a first satellite of the plurality of satellites from a first stacked position to a first raised position away from the first stacked position, wherein the first stacked position is disposed at an end of a stack of the respective fixed antenna reflectors that is furthest from the dispenser, releasing, via a first detachable coupling that mounts a first body of the first satellite to the dispenser of the spacecraft, the first satellite from the dispenser, deploying a second fixed antenna reflector of a second satellite of the plurality of satellites from a second stackedAttorney Docket No. VS2641-WO-1 (78120.0749)position to a second raised position away from the second stacked position, wherein the second stacked position is proximate to the first stacked position and closer to the dispenser than the first stacked position, and releasing, via a second detachable coupling that mounts a second body of the second satellite to the dispenser of the spacecraft, the second satellite from the dispenser.

[0006] An apparatus for deploying a plurality of satellites from a spacecraft comprising a dispenser to which respective bodies of the plurality of satellites are removably mounted is described. The apparatus may include one or more memories storing processor executable code, and one or more processors coupled with the one or more memories. The one or more processors may individually or collectively be operable to execute the code to cause the apparatus to deploy a first fixed antenna reflector of a first satellite of the plurality of satellites from a first stacked position to a first raised position away from the first stacked position, wherein the first stacked position is disposed at an end of a stack of the respective fixed antenna reflectors that is furthest from the dispenser, release, via a first detachable coupling that mounts a first body of the first satellite to the dispenser of the spacecraft, the first satellite from the dispenser, deploy a second fixed antenna reflector of a second satellite of the plurality of satellites from a second stacked position to a second raised position away from the second stacked position, wherein the second stacked position is proximate to the first stacked position and closer to the dispenser than the first stacked position, and release, via a second detachable coupling that mounts a second body of the second satellite to the dispenser of the spacecraft, the second satellite from the dispenser.

[0007] Another apparatus for deploying a plurality of satellites from a spacecraft comprising a dispenser to which respective bodies of the plurality of satellites are removably mounted is described. The apparatus may include means for deploying a first fixed antenna reflector of a first satellite of the plurality of satellites from a first stacked position to a first raised position away from the first stacked position, wherein the first stacked position is disposed at an end of a stack of the respective fixed antenna reflectors that is furthest from the dispenser, means for releasing, via a first detachable coupling that mounts a first body of the first satellite to the dispenser of the spacecraft, the first satellite from the dispenser, means for deploying a second fixed antenna reflector of a second satellite of the plurality of satellites from a second stacked position to a second raised position away from the second stacked position, wherein the second stacked position is proximate to the first stacked position and closer to the dispenser than the first stacked position, and means for releasing, via a secondAttorney Docket No. VS2641-WO-1 (78120.0749)detachable coupling that mounts a second body of the second satellite to the dispenser of the spacecraft, the second satellite from the dispenser.

[0008] A non-transitory computer-readable medium storing code for deploying a plurality of satellites from a spacecraft comprising a dispenser to which respective bodies of the plurality of satellites are removably mounted is described. The code may include instructions executable by one or more processors to deploy a first fixed antenna reflector of a first satellite of the plurality of satellites from a first stacked position to a first raised position away from the first stacked position, wherein the first stacked position is disposed at an end of a stack of the respective fixed antenna reflectors that is furthest from the dispenser, release, via a first detachable coupling that mounts a first body of the first satellite to the dispenser of the spacecraft, the first satellite from the dispenser, deploy a second fixed antenna reflector of a second satellite of the plurality of satellites from a second stacked position to a second raised position away from the second stacked position, wherein the second stacked position is proximate to the first stacked position and closer to the dispenser than the first stacked position, and release, via a second detachable coupling that mounts a second body of the second satellite to the dispenser of the spacecraft, the second satellite from the dispenser.

[0009] An apparatus stowage system is described. The apparatus may include a plurality of satellites, each satellite of the plurality of satellites comprising a respective body, a respective fixed antenna reflector, and a respective articulating boom arm that couples the respective fixed antenna reflector to the respective body, a dispenser to which the respective body of each of the plurality of satellites are removably mounted, wherein, each of the plurality of satellites are arranged around an axis of the dispenser, and the respective articulating boom arm of each of the plurality of satellites having a corresponding stowed state such that the respective fixed antenna reflectors are staggered at a first end of the dispenser and along the axis of the dispenser.BRIEF DESCRIPTION OF THE DRAWINGS

[0010] FIG. 1 shows an example of a satellite communication system that supports satellite stowage and deployment systems in accordance with aspects described herein.

[0011] FIG. 2 shows an example of a satellite stowage and deployment scheme in accordance with examples as disclosed herein.Attorney Docket No. VS2641-WO-1 (78120.0749)

[0012] FIG. 3 shows an example of a satellite stowage and deployment scheme in accordance with examples as disclosed herein.

[0013] FIG. 4 shows an example of a satellite stowage and deployment scheme in accordance with examples as disclosed herein.

[0014] FIG. 5 shows an example of a satellite stowage and deployment scheme in accordance with examples as disclosed herein.

[0015] FIG. 6 shows an example of a satellite stowage and deployment scheme in accordance with examples as disclosed herein.

[0016] FIG. 7 shows an example of a satellite stowage and deployment scheme in accordance with examples as disclosed herein.

[0017] FIG. 8 shows an example of a process flow that supports satellite stowage and deployment systems in accordance with examples as disclosed herein.

[0018] FIG. 9 shows a flowchart illustrating methods that support satellite stowage and deployment system in accordance with examples as disclosed herein.DETAILED DESCRIPTION

[0019] Satellite communications or other satellite operations involve the transportation and deployment of satellites into orbit around the Earth. However, existing approaches to place satellites in orbit may be inefficient. For example, other arrangements of a satellite within a launch vehicle may only allow for a single satellite to be carried and deployed by the spacecraft, expending many resources to launch only a single satellite. Stowage and deployment of multiple satellites within a launch vehicle is regularly performed, but the satellites are generally packaged in a stack within a launch vehicle fairing to enable deployment, which limits the form factor for the satellite antenna and body to stackable forms. For example, foldable antennas (e.g., foldable antenna reflectors) may be used such that the satellite and antenna can be packed in a flat package for stowage, but foldable antennas increase the probability of failures in deployment. Such deficiencies may be present due to the design of the satellites, an arrangement of satellites within the spacecraft, or other limitations.

[0020] The techniques described herein involve stowage and deployment of multiple satellites having a fixed antenna from a single spacecraft. Such techniques may involve the use of a single dispenser to which multiple satellites may be mounted in such a way as toAttorney Docket No. VS2641-WO-1 (78120.0749)provide increased utilization of physical space within the spacecraft, increasing the quantity of satellites that may be deployed by a single spacecraft. For example, each satellite may include a body, a fixed antenna reflector, and an articulating boom arm coupling the fixed antenna reflector to the body. The multiple satellites may be arranged around the dispenser (e.g., at multiple distances along the dispenser) such that the fixed antenna reflectors of each satellite may be arranged in a stack at an end of the dispenser. To deploy the various satellites, a first fixed antenna reflector (e.g., on top of the stack) may be rotated or raised away from the stack, and the first satellite may be released from the dispenser. Similarly, a second reflector (e.g., that was positioned under the first reflector) may then be rotated or raised away from the stack, and the second satellite may be released from the dispenser. Such operations may be carried on for any quantity of satellites, thereby allowing for increased quantities of satellites to be carried and deployed by a spacecraft.

[0021] Aspects of the disclosure are initially described in the context of satellite communication systems. Aspects of the disclosure are then described with reference to a wireless communications system and radio architectures. Aspects of the disclosure are then described with reference to various depictions of a satellite stowage and deployment scheme and a process flow. Aspects of the disclosure are further illustrated by and described with reference to apparatus diagrams, system diagrams, block diagrams, and flowcharts that relate to satellite stowage and deployment system.

[0022] FIG. 1 shows an example of a satellite communication system 100 that supports satellite stowage and deployment systems in accordance with aspects described herein.Satellite communication system 100 may include a ground system 135, terminals 120, and satellite system 101. The ground system 135 may include a network of access nodes 140 that are configured to communicate with the satellite system 101 via feeder links 132. The access nodes 140 may be coupled with access node transceivers 145 that are configured to process signals received from and to be transmitted through corresponding access node(s) 140. The access node transceivers 145 may also be configured to interface with a network 125 (e.g., the Internet) — e.g., via a network device 130 (e.g., a network operations center, satellite and gateway terminal command centers, or other central processing centers or devices) that may provide an interface for communicating with the network 125.

[0023] Terminals 120 may include various devices configured to communicate signals with the satellite system 101 via terminal links 122. Terminals 120 may include fixed terminals (e.g., ground-based stationary terminals), mobile terminals mounted on orAttorney Docket No. VS2641-WO-1 (78120.0749)integrated with mobile platforms (e.g., boats, aircraft, ground-based vehicles, and the like) or portable platforms (e.g., laptops, tablets, handsets, and the like). A terminal 120 may communicate data and information with an access node 140 via the satellite system 101. The data and information may be communicated with a destination device such as a network device 130, or some other device or distributed server associated with a network 125.

[0024] Terminals 120 may include an antenna assembly 124 which may also include various hardware for mounting an antenna. An antenna assembly 124 may also include circuits and / or processors for converting (e.g., performing frequency conversion, modulating / demodulating, multiplexing / demultiplexing, filtering, forwarding, etc.) between radio frequency (RF) satellite communication signals, and satellite terminal communications signals transmitted between the antenna and a satellite terminal receiver. For mobile terminals, the antenna assembly may be mounted on the outside of the mobile or portable platform (e.g., outside of the fuselage of an aircraft), and may protrude from the mobile or portable platform, or may be integrated into a housing of the mobile or portable platform. The terminal 120 may include a transceiver, which may be mounted on the inside or outside of a mobile or portable platform and may include circuits and / or processors for performing various RF signal operations (e.g., receiving, performing frequency conversion, modulating / demodulating, multiplexing / demultiplexing, etc.).

[0025] The satellite system 101 may include a single satellite 105, or a network of satellites 105 that are deployed in space orbits (e.g., low earth orbit (LEO), medium earth orbit (MEO), geosynchronous orbit, geostationary orbit (GEO), etc.). Satellites 105 may include an antenna assembly 104 that may be equipped with one or multiple antennas (e.g., one or more antenna arrays). In some examples, the one or more satellites 105 equipped with multiple antennas may each include one or more antenna panels that include an array of evenly distributed antennas (which may also be referred to as antenna elements). The ground system 135 may also contain access nodes 140 with multiple antenna array elements.

[0026] The satellite system 101 may use the one or more satellites 105 to support beamforming techniques within the coverage area 155 of the satellite system to increase a utilization of resources used for communications. Beamforming, including using multipleinput multiple-output (MIMO) techniques, may be used to exploit multipath signal propagation and increase spectral efficiency by transmitting or receiving multiple signals via different spatial layers over the same frequency resources. The multiple signals may, for example, be transmitted by a transmitting device (e.g., satellite 105, terminal 120) via a set ofAttorney Docket No. VS2641-WO-1 (78120.0749)antennas in accordance with a set of weighting coefficients. Likewise, the multiple signals may be received by a receiving device (e.g., satellite 105, terminal 120) via a set of antennas in accordance with a set of weighting coefficients. Each of the multiple signals may be associated with a separate spatial stream and may carry bits associated with the same data stream (e.g., the same codeword) or different data streams (e.g., different codewords).

[0027] In some examples, some or all of the antenna elements on the satellite and / or the ground system may be arranged as an array of constituent receive and / or transmit feed elements that cooperate to enable various examples of on-board beamforming (OBBF), ground-based beamforming (GBBF), end-to-end beamforming, or other types of beamforming. In the GBBF implementation, there may be multiple transmit or receive antennas on the ground system access node(s).

[0028] To determine weighting coefficients to apply to the set of antennas such that N spatial layers are formed, an (M x N) MEMO matrix may be formed, where M may represent the quantity of antennas of the set of antennas. In some examples, M may be equal to N. The MIMO matrix may be determined based on a channel matrix and used to isolate the different spatial layers of the channel. In some examples, the weighting coefficients are selected to emphasize signals transmitted using the different spatial layers while reducing interference of signals transmitted in the other spatial layers. Accordingly, processing signals received at each antenna of the set of antennas (e.g., a signal received at the set of antennas) using the MIMO matrix may result in multiple signals being output, where each of the multiple signals may correspond to one of the spatial layers. In some examples, the weighting coefficients used for MIMO communications may be referred to as beam coefficients or beamforming coefficients, and the multiple spatial layers may be referred to as beams or spot beams.

[0029] The elements of the MIMO matrix used to form the spatial layers of the channel may be determined based on channel sounding probes communicated between a satellite system 101 and one or more devices. Channel sounding probes include reference signals transmitted periodically between a satellite system and a device (e.g., a terminal 120) coupled with the satellite system 101. For example, a channel sounding probe may be periodically transmitted from a terminal 120 to the satellite system 101, or from the satellite system 101 to a terminal 120, or both, and may include a sequence that is known to the transmitter and receiver (e.g., based on a terminal identifier or other parameters known to the transmitter and receiver). The receiving device (e.g., the terminal or the satellite system) may use the received channel sounding probe to evaluate the connection by correlating a received channel soundingAttorney Docket No. VS2641-WO-1 (78120.0749)probe to the expected signal for the channel sounding probe (e.g., to determine a signal strength, an interference, etc.) and make decisions based thereon. Due to the periodicity of the signal, the receiving device may know when the signal should be received.

[0030] Beamforming techniques may be used to shape or steer a communication beam 150 along a spatial path between a satellite system 101 and a location within the coverage area 155. A communication beam 150 may be formed by determining weighting coefficients for antenna elements of an antenna array that result in the signals transmitted from or received at the antenna elements being combined such that signals propagating in a particular orientation with respect to an antenna array experience constructive interference while others experience destructive interference. Thus, beamforming may be used to transmit signals having energy that is focused in a direction of a communication beam 150 and to receive signals that arrive in a direction of the communication beam 150 with increased signal power (relative to the absence of beamforming). The weighting coefficients may be used to apply amplitude offsets, phase offsets, true time delay (TTD), or combinations thereof to signals carried via the antennas. The beamforming may account for various signal propagation effects of atmospheric conditions 156 such as clouds, rain, or snow, and objects 158 such as trees, buildings, or vehicles.

[0031] In some examples, the weighting coefficients applied to the antennas may be used to form multiple communication beams 150, each associated with a different direction, where the multiple communication beams 150 may be used to communicate multiple signals having the same frequency at the same time to different user terminals. This may be referred to as multi-beam processing, and may support multiuser MIMO. The weighting coefficients used for beamforming may be referred to as beam coefficients, and the multiple signals may be referred to as beam signals. The resulting communication beams 150 may be referred to herein as beamformed spot beams, spot beams, or beams.

[0032] The amplitude and phase of each weighting coefficient may be calculated given the antenna array and reflector geometry, antenna location, and the desired beam locations. However, due to inaccuracies (e.g., in the satellite location, array orientation, geometry, atmospheric conditions 156, object 158, etc.), such an approach may not be practical. Instead, the weighting coefficients may be calculated by continuously measuring the MIMO propagation channel characteristics (e.g., pairwise channels from each system antenna element to each terminal antenna element) and adjusting the weighting coefficients based on the changing channel characteristics. The measured MIMO channel characteristics mayAttorney Docket No. VS2641-WO-1 (78120.0749)include pairwise gain and phase response and noise level and may be referred to as MEMO channel state information (CSI). Once the MIMO CSI is available, the weighting coefficients may be derived by solving a set of equations or applying a set of adaptation formulas. Various beamformer calculation and adaptation techniques may be used, including minimum mean square (MMSE) beamformer, zero forcing beamformer, singular value decomposition (SVD), MIMO sphere decoder, and others.

[0033] The beamformed communication beams 150 may be associated with a set of resources of the satellite system 101. The set of resources may include frequency resources, time resources, and polarization resources. Beamformed communication beams 150 may overlap spatially without interfering if they are associated with different resources. For example, a given frequency range for the satellite system 101 may be divided into frequency resources or channels, and a given amount of time may be divided into different recurring time slots, where a frequency resource may be used to carry a beam signal (e.g., a modulated signal carried in a beamformed spot beam) on one of the recurring time slots. Each frequency channel may carry a single modulated signal, while in other cases each frequency channel may be further divided to carry multiple modulated signals which may be multiplexed in time (e.g., time division multiple access (TDMA)) or frequency (frequency division multiple access (FDMA)). Information (e.g., data, control information) may be modulated onto the modulated signals using a variety of single-carrier or multi-carrier modulation techniques (e.g., Orthogonal Frequency Division Multiplexing (OFDM), Direct Sequence Spread Spectrum (DSSS), linearly pre-coded OFDM (LP-OFDM)).

[0034] In addition to being multiplexed in time or frequency, different polarizations may be used to define the resources for assignment to beams. For example, a set of resources may include a first sub-set of resources associated with a first polarization and a second sub-set of resources associated with a second, orthogonal, polarization. The first and second polarizations may be any orthogonal polarizations, and may be linearly polarized or circularly polarized (e.g., a right-hand circular polarization (RHCP), a left-hand circular polarization (LHCP)).

[0035] A spacecraft stowage system is described herein. The system may include a plurality of satellites, each including a body, a fixed antenna reflector, and an articulating boom arm. The system may further include a dispenser to which the body of each satellite is mounted. In some examples, each satellite may be arranged around an axis of the dispenser and the articulating boom arm of each satellite may have a stowed state such that the fixedAttorney Docket No. VS2641-WO-1 (78120.0749)antenna reflectors are staggered at a first end of the dispenser and the bodies are staggered along the axis of the dispenser. The fixed antenna reflectors may be stored in a stack with couplings between neighboring fixed antenna reflectors.

[0036] Further, a method of deployment may include deploying a first reflector of a first satellite from the stack of fixed antenna reflectors and releasing the first satellite via a mount or coupling between the dispenser and the first satellite. The method may further include deploying a second reflector of a second satellite from the remaining fixed antenna reflectors of the stack of fixed antenna reflectors and releasing the second satellite via a mount or coupling between the dispenser and the first satellite. Such operations may be extended to any quantity of satellites (e.g., third and fourth satellites)

[0037] FIG. 2 shows an example of a satellite stowage and deployment scheme 200 in accordance with examples as disclosed herein. The depiction of the satellite stowage and deployment scheme 200 includes multiple views of the satellites within the spacecraft to demonstrate, among other features, the stowage arrangement of the satellites.

[0038] The techniques described herein may employ one or more arrangements of satellites within a launch vehicle fairing as well as methods for one or more release sequences of the satellites from the launch vehicle. The techniques described herein allow for multiple satellites to be flown inside a single large fairing (e.g., the fairing 218) of a launch vehicle (e.g., a 5 meter-class launch vehicle). Though the examples described herein relate to one example of stowing and deploying four satellites (e.g., a first satellite 202, a second satellite 204, a third satellite 206, and a fourth satellite 208) in and from a spacecraft, the techniques described herein are also applicable to any other quantity of satellites.

[0039] Each satellite may include a body, a reflector, and arm, and an antenna. For example, the first satellite 202 may include the first body 220, the first reflector 228, the first arm 236, and the first feed assembly 244. The second satellite 204 may include the second body 222, the second reflector 230, the second arm 238, and the second feed assembly 246. The third satellite 206 may include the third body 224, the third reflector 232, the third arm 240, and the third feed assembly 248. The fourth satellite 208 may include the fourth body 226, the fourth reflector 234, the fourth arm 242, and the fourth feed assembly 250.

[0040] In some examples, the body of each satellite may support the antenna of the satellite. The antenna may include one or more antenna elements used for communications corresponding to the satellite. For example, an antenna may include a reflector and a feedAttorney Docket No. VS2641-WO-1 (78120.0749)assembly. Therefore, the first antenna 256 may include the first reflector 228 and the first feed assembly 244, the second antenna 258 may include the second reflector 230 and the second feed assembly 246, the third antenna 260 may include the third reflector 232 and the third feed assembly 248, and the fourth antenna 262 may include the fourth reflector 234 and the fourth feed assembly 250.

[0041] In some examples, the antenna of a satellite may operate as an array-fed reflector antenna (e.g., phased array-fed reflector (PAFR)), and may communicate signals via the reflector, which may reflect signals to and from one or more feeds (e.g., a feed array) of the antenna for communications with the satellite. In some examples, the reflector may be described as “fixed,” which may indicate that the reflector may not change size between stowage and deployment, may be non-furling, may be in its final shape, or that the size and shape of the reflector may not change after the reflector is deployed or after the entire satellite is deployed. In some examples, the arm may connect the reflector to the body of the satellite, and the arm may be extendable (e.g., telescoping, foldable, deployable, retractable, articulatable, or extendable in another manner) to allow positioning of the reflector towards or away from the body of the satellite (e.g., for stowage and deployment of the satellite from a spacecraft or for operation of the satellite, either of which may be in accordance with techniques described herein). The arms may be, for example, articulating boom arms that that are extendable such that they can extend from a stowage position in which the arm is shorter and an extended position in which the arm is longer. In some examples, an arm that is described as extendable may be considered to be retractable (e.g., may be able to return to a more compact position), articulatable, movable, or telescoping. The arms may be able to articulate (e.g., have one or more rotational joints) such that at least one section of the arm may be capable of being rotated relative to the body of the satellite, and at least one section of the arm may be capable of rotating relative to another section (e.g., to position an angle of the reflector). In some cases, the arm (including a connection to the reflector) may be capable of two-axis articulation (may be able to position the reflector along at least two axes).

[0042] In some examples, the multiple satellites may be arranged within the spacecraft to allow for deployment of the reflectors and release of the bodies of the satellites from the dispenser of the spacecraft. For example, the first body 220, the second body 222, the third body 224, and the fourth body 226 may be arranged around the dispenser 252 (e.g., around the axis 264 of the dispenser 252), and the first body 220, the second body 222, the third body 224, and the fourth body 226 may be staggered along the dispenser 252 (e.g., along the axisAttorney Docket No. VS2641-WO-1 (78120.0749)264 of the dispenser 252) to allow for deployment of reflectors and release of the satellite bodies without interference from other elements (e.g., of a same satellite or of a different satellite).

[0043] In some examples, such staggering may result in the relative positions of the reflectors of the satellites to also be staggered (e.g., given a uniform design of the satellites). As such, the first reflector 228, the second reflector 230, the third reflector 232, and the fourth reflector 234 may be arranged in a stack at an end of the dispenser 252.

[0044] In some examples, the arrangement of the satellites around the dispenser 252 (e.g., including the positions of the bodies around the dispenser 252 as well as the staggering of the bodies along the dispenser 252) may correspond to an order of deployment of the reflectors (or arrangement of the various reflectors in the stack), an order of release of the bodies of the satellites, or both. For example, the first reflector 228 of the first satellite 202 may be deployed first and the first body 220 of the first satellite 202 may then be released from the dispenser 252, after which the second reflector 230 may be deployed and the second body 222 may be released, and so on for each of the satellites in order.

[0045] In some examples, each of the reflectors may be a fixed antenna reflector and may have a diameter corresponding to a dimension of the launch vehicle fairing (e.g., a 3 to 9 meter class or of another size or class). By employing the stowage and deployment techniques described herein, such fixed antenna reflectors may be larger than would be possible using other approaches, improving communications characteristics (e.g., quality, reliability, and versatility) due to the larger reflector size.

[0046] The first reflector 228, the second reflector 230, the third reflector 232, and the fourth reflector 234 may be coupled with one another for support while the spacecraft is travelling. For example, neighboring reflectors may be coupled with one another via mating coupling structures embedded in or on each of the neighboring reflectors. One or more coupling structures may be included on one or more sides of the fixed antenna reflectors. In some examples, a reflector positioned closest to the dispenser 252 may be coupled directly to the dispenser using such coupling structures.

[0047] The first arm 236, the second arm 238, the third arm 240, and the fourth arm 242 may be arranged in a stowed position during transport of the satellites in the launch vehicle. For example, the first arm 236, the second arm 238, the third arm 240, and the fourth arm 242 may be in a folded, un-extended, or collapsed state to allow for efficient stowage of theAttorney Docket No. VS2641-WO-1 (78120.0749)satellites within the spacecraft. After a given reflector of a satellite is deployed and the corresponding body of the satellite is released from the dispenser 252, the corresponding arm of the satellite may be changed from the stowed state to a deployed state (e.g., an unfolded state, an extended state, or another state) to deploy the corresponding reflector to allow for reflection of signals to and from the corresponding antenna of the satellite.

[0048] In some examples, the first reflector 228, the second reflector 230, the third reflector 232, and the fourth reflector 234 may each include one or more cutouts 254 to allow for positioning of one or more arms (e.g., of other satellites) in the stowed state. For example, the first arm 236 may pass through the cutouts 254 of the second reflector 230, the third reflector 232, and the fourth reflector 234.

[0049] In some examples, the one or more cutouts 254 may be located at positions around one or more of the reflectors. In some examples, a quantity of cutouts 254 may correspond to a quantity of satellites that are to be stowed together (or such a quantity minus one, as a given satellite may not, in some examples, utilize a cutout for its own arm). In some examples, the cutouts 254 may be arranged regularly around one or more of the reflectors. In some examples, the pattern or regularity of the cutouts 254 may further be based on a position at which the arm is mounted to the reflector. For example, if there are four satellites, three cutouts 254 and the position at which the arm is mounted to the reflector may be regularly spaced around the reflector.

[0050] FIG. 3 shows an example of a satellite stowage and deployment scheme 300 in accordance with examples as disclosed herein. FIG. 3 depicts a portion of a process for deploying multiple satellites from a spacecraft.

[0051] As described herein, the process for deploying multiple satellites may involve a sub-process of deploying a reflector of a satellite and releasing a body of the satellite from the dispenser of the spacecraft. In some examples, such a sub-process may be repeated for each of the satellites of the plurality of satellites that are to be deployed from the spacecraft.

[0052] For example, FIG. 3 depicts an initial deployment of the first reflector 228. In some examples, one or more reflector couplings 320 may couple the first reflector 228 to the second reflector 230 and such reflector couplings 320 may be or may include a release mechanism. For example, such reflector couplings 320 may be or may include passive couplings or release mechanisms (e.g., released via a passive mechanism, such as a spring), active couplings (e.g., released via an active mechanism, such as a motor). Additionally, orAttorney Docket No. VS2641-WO-1 (78120.0749)alternatively, the one or more reflector couplings 320 may be or may include launch locks, explosive bolts, cuttable blots, or other release mechanisms (e.g., a hold down and release mechanism (HDRM) or a separation nut release mechanism (SNRM)) for coupling and decoupling neighboring reflectors. In some cases, a reflector may include a hole that a lock of another structure of the coupling may pass through, with the mechanism behind the surface of the reflector (e.g., away from the other structure, such as on a side that faces away from the other structure).

[0053] After the one or more reflector couplings 320 between the first reflector 228 and the second reflector 230 are released, the first reflector 228 may be rotated or otherwise moved away from the stack of the reflectors (e.g., to a position such as the position shown in FIG. 3). In some examples, to facilitate such a rotation or movement, a hinge or other movable coupling may be used between the first arm 236 and the first reflector 228.

[0054] FIG. 4 shows an example of a satellite stowage and deployment scheme 400 in accordance with examples as disclosed herein. The satellite stowage and deployment scheme 400 depicts a portion of a process for deploying multiple satellites from a spacecraft.

[0055] After the first reflector 228 is moved to a deployed position away from the stack of other reflectors, the first body 220 may be released from the dispenser 252 and the first satellite 202 may be deployed away from the dispenser 252. In some examples, one or more release mechanisms may be employed to release the first body 220 from the dispenser 252. In some examples, the one or more release mechanisms may be launch locks, passive devices such as spring-driven devices, active devices actuated by a motor, or any other type of release mechanism. Further, in some examples, separate mechanisms may be employed to secure the first body 220 to the dispenser 252 and to propel the first satellite 202 away from the dispenser 252. For example, one or more launch locks may be employed to secure the first body 220 to the dispenser 252 and one or more passive or active mechanisms may be used to propel the first satellite away from the dispenser 252.

[0056] FIG. 5 shows an example of a satellite stowage and deployment scheme 500 in accordance with examples as disclosed herein. The satellite stowage and deployment scheme 500 depicts a portion of a process for deploying multiple satellites from a spacecraft.

[0057] After the first satellite 202 is moved away from the dispenser 252, the second satellite 204 may be deployed. For example, one or more reflector couplings 320 that couple the second reflector 230 to the third reflector 232 may be released, disengaged, or actuated toAttorney Docket No. VS2641-WO-1 (78120.0749)free the second reflector 230 from the stack of remaining reflectors, after which the second reflector 230 may be deployed away from the stack of remaining reflectors (e.g., to the position depicted in FIG. 5). In some examples, the deployment of the second reflector 230 may be similar to the deployment of the first reflector 228 as described herein.

[0058] FIG. 6 shows an example of a satellite stowage and deployment scheme 600 in accordance with examples as disclosed herein. The satellite stowage and deployment scheme 500 depicts a portion of a process for deploying multiple satellites from a spacecraft.

[0059] After the second reflector 230 is moved to a deployed position away from the stack of other reflectors, the second body 222 may be released from the dispenser 252 and the second satellite 204 may be deployed away from the dispenser 252. In some examples, one or more release mechanisms may be employed to release the second body 222 from the dispenser 252. In some examples, the one or more release mechanisms may be launch locks, passive devices such as spring-driven devices, active devices actuated by a motor, or any other type of release mechanism. Further, in some examples, separate mechanisms may be employed to secure the second body 222 to the dispenser 252 and to propel the second satellite 204 away from the dispenser 252. For example, one or more launch locks may be employed to secure the second body 222 to the dispenser 252 and one or more passive or active mechanisms may be used to propel the second satellite away from the dispenser 252.

[0060] The patterns described herein may be continued for any quantity of satellites. For example, as depicted in FIG. 6, after the second satellite 204 is moved away from the dispenser 252, the third satellite 206 may be deployed. For example, one or more reflector couplings 320 that couple the third reflector 232 to the fourth reflector 234 may be released and the third reflector 232 may be deployed away from the stack of remaining reflectors, after which the third body 224 may be released and moved away from the dispenser 252 to deploy the third satellite 206.

[0061] At some point in the sequence of deploying the multiple satellites, a final satellite (e.g., the fourth satellite 208) may be deployed. For example, one or more one or more reflector couplings 320 that couple the fourth reflector 234 to the dispenser 252 may be released, allowing the fourth reflector 234 to be deployed away from the dispenser 252, after which the fourth body 226 may be released from the dispenser 252 and propelled away from the dispenser 252 to deploy the fourth satellite 208.Attorney Docket No. VS2641-WO-1 (78120.0749)

[0062] FIG. 7 shows an example of a satellite stowage and deployment scheme 700 in accordance with examples as disclosed herein.

[0063] The satellite stowage and deployment scheme 700 depicts a deployed state of the first arm 236 of the first satellite (e.g., in contrast to the stowed state of the first arm 236 depicted in FIGs. 2 through 6). For example, to transition from the stowed state to the deployed state, the first arm 236 may be unfolded, extended, or otherwise deployed, thereby moving the first reflector 228 away from the first body 220 into position for reflecting signaling to and from the first feed assembly 244.

[0064] In some examples, for each satellite, the arm may be extended after the body of the satellite is released from the dispenser 252 and propelled away from the dispenser 252. In some examples, the arm may be extended before a following reflector is deployed away from the stack of remaining reflectors. Such a sequence may be continued for multiple satellites (e.g., the arm of each satellite may be extended before the reflector of the next satellite is deployed). Additionally, or alternatively, the arm of a satellite may be Additionally, or alternatively, some or all of the satellites may be deployed away from the dispenser 252, after which all of the arms may be extended away from the respective bodies of the satellites simultaneously or in an overlapping manner.

[0065] FIG. 8 shows an example of a process flow 800 in accordance with examples as disclosed herein. The process flow 800 may implement various aspects of the present disclosure described herein. The elements described in the process flow 800 (e.g., the first satellite 804, the second satellite 806, the third satellite 808, and the fourth satellite 810) may be examples of similarly named elements described herein.

[0066] In the following description of the process flow 800, the operations between the various entities or elements may be performed in different orders or at different times. Some operations may also be left out of the process flow 800, or other operations may be added. Although the various entities or elements are shown performing the operations of the process flow 800, some aspects of some operations may also be performed by other entities or elements of the process flow 800 or by entities or elements that are not depicted in the process flow, or any combination thereof.

[0067] The process flow 800 may relate to a satellite stowage and deployment scheme. For example, a plurality of satellites may be deployed from a spacecraft including a dispenser to which respective bodies of the plurality of satellites are removably mounted. In someAttorney Docket No. VS2641-WO-1 (78120.0749)examples, each of the plurality of satellites includes a respective body, a respective fixed antenna reflector, and a respective extendable arm that couples the respective fixed antenna reflector to the respective body. In some examples, before deploying the first fixed antenna reflector of the first satellite 804, each respective fixed antenna reflector of the plurality of satellites are disposed substantially parallel to one another.

[0068] In some examples, at 820, the satellite stowage and deployment scheme may include releasing, from the spacecraft, one or more fairings that cover the plurality of satellites.

[0069] In some examples, at 822, the satellite stowage and deployment scheme may include deploying a first fixed antenna reflector of a first satellite 804 of the plurality of satellites from a first stacked position to a first raised position away from the first stacked position and the first stacked position is disposed at an end of a stack of the respective fixed antenna reflectors that is furthest from the dispenser. In some examples, deploying the first fixed antenna reflector of the first satellite 804 includes releasing a coupling between the first fixed antenna reflector of the first satellite 804 and the second fixed antenna reflector of the second satellite 806. In some examples, the first detachable coupling is a spring-driven device capable of propelling the first satellite 804 or the second satellite 806 away from the dispenser.

[0070] In some examples, at 824, the satellite stowage and deployment scheme may include releasing, via a first detachable coupling that mounts a first body of the first satellite 804 to the dispenser of the spacecraft, the first satellite 804 from the dispenser.

[0071] In some examples, at 826, the satellite stowage and deployment scheme may include extending a first extendable arm of the first satellite 804 away from the first body of the first satellite 804.

[0072] In some examples, at 828, the satellite stowage and deployment scheme may include deploying a second fixed antenna reflector of a second satellite 806 of the plurality of satellites from a second stacked position to a second raised position away from the second stacked position and the second stacked position is proximate to the first stacked position and closer to the dispenser than the first stacked position. In some examples, deploying the second fixed antenna reflector of the second satellite 806 includes releasing a coupling between the second fixed antenna reflector of the second satellite 806 and the dispenser or a third fixed antenna reflector of a third satellite 808. In some examples, the second detachable coupling isAttorney Docket No. VS2641-WO-1 (78120.0749)a spring-driven device capable of propelling the first satellite 804 or the second satellite 806 away from the dispenser.

[0073] In some examples, at 830, the satellite stowage and deployment scheme may include releasing, via a second detachable coupling that mounts a second body of the second satellite 806 to the dispenser of the spacecraft, the second satellite 806 from the dispenser.

[0074] In some examples, at 832, the satellite stowage and deployment scheme may include extending a second extendable arm of the second satellite 806 away from the second body of the second satellite 806.

[0075] In some examples, at 834, the satellite stowage and deployment scheme may include deploying a third fixed antenna reflector of a third satellite 808 of the plurality of satellites from a third stacked position to a third raised position away from the third stacked position and the third stacked position is proximate to the second stacked position and closer to the dispenser than the second stacked position.

[0076] In some examples, at 836, the satellite stowage and deployment scheme may include releasing, via a third detachable coupling that mounts a third body of the third satellite 808 to the dispenser of the spacecraft, the third satellite 808 from the dispenser. In some examples, an order of the deployment of the first fixed antenna reflector of the first satellite 804, the release of the first satellite 804, the deployment of the second fixed antenna reflector of the second satellite 806, the release of the second satellite 806, the deployment of the third fixed antenna reflector of the third satellite 808, and the release of the third satellite 808 is based on respective positions of the first satellite 804, the second satellite 806, and the third satellite 808 around the dispenser.

[0077] In some examples, at 838, the satellite stowage and deployment scheme may include extending a third extendable arm of the third satellite 808 away from the third body of the third satellite 808.

[0078] In some examples, at 840, the satellite stowage and deployment scheme may include deploying a fourth fixed antenna reflector of a fourth satellite 810 of the plurality of satellites from a fourth stacked position to a fourth raised position away from the fourth stacked position and the fourth stacked position is proximate to the third stacked position and closer to the dispenser than the third stacked position.Attorney Docket No. VS2641-WO-1 (78120.0749)

[0079] In some examples, at 842, the satellite stowage and deployment scheme may include releasing, via a fourth detachable coupling that mounts a fourth body of the fourth satellite 810 to the dispenser of the spacecraft, the fourth satellite 810 from the dispenser.

[0080] In some examples, at 844, the satellite stowage and deployment scheme may include extending a fourth extendable arm of the fourth satellite 810 away from the fourth body of the fourth satellite 810.

[0081] FIG. 9 shows a flowchart illustrating a method 900 that supports satellite stowage and deployment systems in accordance with examples as disclosed herein. The operations of the method 900 may be implemented by a satellite deployment system or its components as described herein. For example, the operations of the method 900 may be performed by a satellite deployment system as described with reference to FIGs. 1 through 8. In some examples, a satellite deployment system may execute a set of instructions to control the functional elements of the satellite deployment system to perform the described functions. Additionally, or alternatively, the satellite deployment system may perform aspects of the described functions using special-purpose hardware.

[0082] At 905, the method may include deploying a first fixed antenna reflector of a first satellite of the plurality of satellites from a first stacked position to a first raised position away from the first stacked position, wherein the first stacked position is disposed at an end of a stack of the respective fixed antenna reflectors that is furthest from the dispenser. The operations of 905 may be performed in accordance with examples as disclosed herein.

[0083] At 910, the method may include releasing, via a first detachable coupling that mounts a first body of the first satellite to the dispenser of the spacecraft, the first satellite from the dispenser. The operations of 910 may be performed in accordance with examples as disclosed herein.

[0084] At 915, the method may include deploying a second fixed antenna reflector of a second satellite of the plurality of satellites from a second stacked position to a second raised position away from the second stacked position, wherein the second stacked position is proximate to the first stacked position and closer to the dispenser than the first stacked position. The operations of 915 may be performed in accordance with examples as disclosed herein.Attorney Docket No. VS2641-WO-1 (78120.0749)

[0085] At 920, the method may include releasing, via a second detachable coupling that mounts a second body of the second satellite to the dispenser of the spacecraft, the second satellite from the dispenser. The operations of 920 may be performed in accordance with examples as disclosed herein.

[0086] In some examples, an apparatus as described herein may perform a method or methods, such as the method 900. The apparatus may include features, circuitry, logic, means, or instructions (e.g., a non-transitory computer-readable medium storing instructions executable by a processor), or any combination thereof for performing the following aspects of the present disclosure:

[0087] It should be noted that these methods describe examples of implementations, and that the operations and the steps may be rearranged or otherwise modified such that other implementations are possible. In some examples, aspects from two or more of the methods may be combined. For example, aspects of each of the methods may include steps or aspects of the other methods, or other steps or techniques described herein.

[0088] Information and signals described herein may be represented using any of a variety of different technologies and techniques. For example, data, instructions, commands, information, signals, bits, symbols, and chips that may be referenced throughout the description may be represented by voltages, currents, electromagnetic waves, magnetic fields or particles, optical fields or particles, or any combination thereof.

[0089] The various illustrative blocks and modules described in connection with the disclosure herein may be implemented or performed with a general purpose processor, a DSP, an ASIC, an FPGA, or other programmable logic device, discrete gate or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. A general purpose processor may be a microprocessor, but in the alternative, the processor may be any conventional processor, controller, microcontroller, or state machine. A processor may also be implemented as a combination of computing devices (e.g., a combination of a DSP and a microprocessor, multiple microprocessors, one or more microprocessors in conjunction with a DSP core, or any other such configuration).

[0090] The functions described herein may be implemented in hardware, software executed by a processor, firmware, or any combination thereof. If implemented in software executed by a processor, the functions may be stored on or transmitted over as one or more instructions or code on a computer readable medium. Other examples and implementationsAttorney Docket No. VS2641-WO-1 (78120.0749)are within the scope of the disclosure and appended claims. For example, due to the nature of software, functions described herein can be implemented using software executed by a processor, hardware, firmware, hardwiring, or combinations of any of these. Features implementing functions may also be physically located at various positions, including being distributed such that portions of functions are implemented at different physical locations.

[0091] Computer readable media includes both non transitory computer storage media and communication media including any medium that facilitates transfer of a computer program from one place to another. A non-transitory storage medium may be any available medium that can be accessed by a general purpose or special purpose computer. By way of example, and not limitation, non-transitory computer readable media may include RAM, ROM, electrically erasable programmable read-only memory (EEPROM), flash memory, compact disk read-only memory (CDROM) or other optical disk storage, magnetic disk storage or other magnetic storage devices, or any other non-transitory medium that can be used to carry or store desired program code means in the form of instructions or data structures and that can be accessed by a general purpose or special purpose computer, or a general purpose or special purpose processor. Also, any connection is properly termed a computer readable medium. For example, if the software is transmitted from a website, server, or other remote source using a coaxial cable, fiber optic cable, twisted pair, digital subscriber line (DSL), or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of medium. Disk and disc, as used herein, include CD, laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu ray disc where disks usually reproduce data magnetically, while discs reproduce data optically with lasers. Combinations of the above are also included within the scope of computer readable media.

[0092] As used herein, including in the claims, “or” as used in a list of items (e.g., a list of items prefaced by a phrase such as “at least one of’ or “one or more of’) indicates an inclusive list such that, for example, a list of at least one of A, B, or C means A or B or C or AB or AC or BC or ABC (i.e., A and B and C). Also, as used herein, the phrase “based on” shall not be construed as a reference to a closed set of conditions. For example, an exemplary step that is described as “based on condition A” may be based on both a condition A and a condition B without departing from the scope of the present disclosure. In other words, asAttorney Docket No. VS2641-WO-1 (78120.0749)used herein, the phrase “based on” shall be construed in the same manner as the phrase “based at least in part on.”

[0093] In the appended figures, similar components or features may have the same reference label. Further, various components of the same type may be distinguished by following the reference label by a dash and a second label that distinguishes among the similar components. If just the first reference label is used in the specification, the description is applicable to any one of the similar components having the same first reference label irrespective of the second reference label, or other subsequent reference label.

[0094] The description set forth herein, in connection with the appended drawings, describes example configurations and does not represent all the examples that may be implemented or that are within the scope of the claims. The term “exemplary” used herein means “serving as an example, instance, or illustration,” and not “preferred” or “advantageous over other examples.” The detailed description includes specific details for the purpose of providing an understanding of the described techniques. These techniques, however, may be practiced without these specific details. In some instances, well known structures and devices are shown in block diagram form in order to avoid obscuring the concepts of the described examples.

[0095] The description herein is provided to enable a person skilled in the art to make or use the disclosure. Various modifications to the disclosure will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other variations without departing from the scope of the disclosure. Thus, the disclosure is not limited to the examples and designs described herein but is to be accorded the broadest scope consistent with the principles and novel features disclosed herein.Attorney Docket No. VS2641-WO-1 (78120.0749)

Claims

CLAIMSWhat is claimed is:

1. A spacecraft stowage system, comprising:a plurality of satellites (202, 204, 206, 208), each satellite of the plurality of satellites (202, 204, 206, 208) comprising a respective body (220, 222, 224, 226), a respective fixed antenna reflector (228, 230, 232, 234), and a respective extendable arm (236, 238, 240, 242) that couples the respective fixed antenna reflector to the respective body (220, 222, 224, 226); anda dispenser (252) to which the respective body (220, 222, 224, 226) of each of the plurality of satellites (202, 204, 206, 208) are removably mounted, wherein:each of the plurality of satellites (202, 204, 206, 208) are arranged around an axis (264) of the dispenser (252), andthe respective extendable arm (236, 238, 240, 242) of each of the plurality of satellites having a corresponding stowed state such that the respective fixed antenna reflectors (228, 230, 232, 234) are staggered at a first end of the dispenser (252) and along the axis (264) of the dispenser (252).

2. The spacecraft stowage system of claim 1, wherein:the plurality of satellites (202, 204, 206, 208) are removably mounted to the dispenser (252) at a plurality of different distances from the first end of the dispenser (252).

3. The spacecraft stowage system of any one of claims 1 through 2, wherein:a first fixed antenna reflector (228) of a first satellite (202) of the plurality of satellites is removably coupled with a second fixed antenna reflector (230) of a second satellite of the plurality of satellites via a first coupling; andthe second fixed antenna reflector (230) of the second satellite (204) of the plurality of satellites (202, 204, 206, 208) is removably coupled with the dispenser (252) via a second coupling at the first end of the dispenser (252).

4. The spacecraft stowage system of claim 3, wherein:the first coupling and the second coupling each comprise a release mechanism.Attorney Docket No. VS2641-WO-1 (78120.0749)5. The spacecraft stowage system of any of claims 1 through 4, wherein the respective extendable arms are disposed outside of the respective fixed antenna reflectors while the respective extendable arms are in the corresponding stowed state.

6. The spacecraft stowage system of claim 5, wherein: each respective fixed antenna reflector comprises a plurality of cutouts into which the respective extendable arms of other satellites of the plurality of satellites (202, 204, 206, 208) are positioned while the respective extendable arms of other satellites of the plurality of satellites (202, 204, 206, 208) are in the corresponding stowed state; andthe plurality of cutouts are arranged radially around a perimeter of the each respective fixed antenna reflector.

7. The spacecraft stowage system of any one of claims 1 through 6, wherein:for each satellite of the plurality of satellites (202, 204, 206, 208), the respective extendable arm (236, 238, 240, 242) is coupled with the respective fixed antenna reflector with a movable coupling.

8. The spacecraft stowage system of any one of claims 1 through 7, wherein:for each satellite of the plurality of satellites (202, 204, 206, 208), the respective extendable arm (236, 238, 240, 242) comprises one or more articulating joints.

9. The spacecraft stowage system of any one of claims 1 through 8, wherein:the fixed antenna reflectors (228, 230, 232, 234) are non-furling reflectors.

10. The spacecraft stowage system of any one of claims 1 through 9, wherein:in the corresponding stowed state, each respective extendable arm (236, 238, 240, 242) is oriented substantially parallel to the dispenser (252).Attorney Docket No. VS2641-WO-1 (78120.0749)11. The spacecraft stowage system of any one of claims 1 through 10, wherein:the plurality of satellites (202, 204, 206, 208) are spaced substantially equally around the dispenser (252).

12. The spacecraft stowage system of any one of claims 1 through 11, wherein:the respective bodies of the plurality of satellites (202, 204, 206, 208) are disposed substantially parallel to the dispenser (252); andthe respective fixed antenna reflectors of the plurality of satellites (202, 204, 206, 208) are disposed substantially perpendicular to the dispenser (252).

13. The spacecraft stowage system of any one of claims 1 through 12, wherein:each satellite of the plurality of satellites (202, 204, 206, 208) comprises an antenna (256, 258, 260, 262) that comprises the respective fixed antenna reflector (228, 230, 232, 234), and a feed assembly (244, 246, 248, 250) located on the respective body (220, 222, 224, 226).

14. A method for deploying a plurality of satellites (202, 204, 206, 208) from a spacecraft comprising a dispenser (252) to which respective bodies (220, 222, 224, 226) of the plurality of satellites (202, 204, 206, 208) are removably mounted, each of the plurality of satellites (202, 204, 206, 208) comprising a respective body (220, 222, 224, 226), a respective fixed antenna reflector (228, 230, 232, 234), and a respective extendable arm (236, 238, 240, 242) that couples the respective fixed antenna reflector (228, 230, 232, 234) to the respective body (220, 222, 224, 226), the method comprising:deploying a first fixed antenna reflector (228) of a first satellite (202) of the plurality of satellites (202, 204, 206, 208) from a first stacked position to a first raised position away from the first stacked position, wherein the first stacked position is disposed at an end of a stack of the respective fixed antenna reflectors (228, 230, 232, 234) that is furthest from the dispenser (252);releasing, via a first detachable coupling that mounts a first body (220) of the first satellite to the dispenser (252) of the spacecraft, the first satellite (202) from the dispenser (252);Attorney Docket No. VS2641-WO-1 (78120.0749)deploying a second fixed antenna reflector (230) of a second satellite (204) of the plurality of satellites (202, 204, 206, 208) from a second stacked position to a second raised position away from the second stacked position, wherein the second stacked position is proximate to the first stacked position and closer to the dispenser (252) than the first stacked position; andreleasing, via a second detachable coupling that mounts a second body (222) of the second satellite (204) to the dispenser (252) of the spacecraft, the second satellite (204) from the dispenser (252).

15. The method of claim 14, further comprising:deploying a third fixed antenna reflector (232) of a third satellite (206) of the plurality of satellites (202, 204, 206, 208) from a third stacked position to a third raised position away from the third stacked position, wherein the third stacked position is proximate to the second stacked position and closer to the dispenser (252) than the second stacked position; andreleasing, via a third detachable coupling that mounts a third body (224) of the third satellite (206) to the dispenser (252) of the spacecraft, the third satellite (206) from the dispenser (252).

16. The method of claim 15, further comprising:deploying a fourth fixed antenna reflector (234) of a fourth satellite (208) of the plurality of satellites (202, 204, 206, 208) from a fourth stacked position to a fourth raised position away from the fourth stacked position, wherein the fourth stacked position is proximate to the third stacked position and closer to the dispenser (252) than the third stacked position; andreleasing, via a fourth detachable coupling that mounts a fourth body (226) of the fourth satellite (208) to the dispenser (252) of the spacecraft, the fourth satellite (208) from the dispenser (252).

17. The method of claim 15, wherein an order of the deployment of the first fixed antenna reflector (228) of the first satellite, the release of the first satellite, the deployment of the second fixed antenna reflector (230) of the second satellite, the release of the second satellite, the deployment of the third fixed antenna reflector (232) of the third satellite, and the release of the third satellite is based at least in part onAttorney Docket No. VS2641-WO-1 (78120.0749)respective positions of the first satellite, the second satellite, and the third satellite around the dispenser (252).

18. The method of any one of claims 14 through 17, wherein deploying the first fixed antenna reflector of the first satellite comprises:releasing a coupling (320) between the first fixed antenna reflector (228) of the first satellite and the second fixed antenna reflector (230) of the second satellite.

19. The method of any one of claims 14 through 18, wherein deploying the second fixed antenna reflector (230) of the second satellite comprises:releasing a coupling (320) between the second fixed antenna reflector (230) of the second satellite and the dispenser (252) or a third fixed antenna reflector (232) of a third satellite.

20. The method of any one of claims 14 through 19, wherein the first detachable coupling and the second detachable coupling are spring-driven devices capable of propelling the first satellite or the second satellite away from the dispenser (252).

21. The method of any one of claims 14 through 20, wherein before deploying the first fixed antenna reflector (228) of the first satellite, each respective fixed antenna reflector (228, 230, 232, 234) of the plurality of satellites (202, 204, 206, 208) are disposed substantially parallel to one another.

22. The method of any one of claims 14 through 21, further comprising:extending a first extendable arm of the first satellite away from the first body (220) of the first satellite; andextending a second extendable arm of the second satellite away from the second body (222) of the second satellite.

23. The method of any one of claims 14 through 22, further comprising:releasing, from the spacecraft, one or more fairings (218) that cover the plurality of satellites.

24. The method of any one of claims 14 through 23, wherein:Attorney Docket No. VS2641-WO-1 (78120.0749)each respective fixed antenna reflector comprises a plurality of cutouts into which the respective extendable arms of other satellites of the plurality of satellites (202, 204, 206, 208) are positioned while the respective extendable arms of other satellites of the plurality of satellites (202, 204, 206, 208) are in corresponding stowed states prior to deploying the respective fixed antenna reflectors; andthe plurality of cutouts are arranged radially around a perimeter of the each respective fixed antenna reflector.

25. The method of any one of claims 14 through 24, wherein: for each satellite of the plurality of satellites (202, 204, 206, 208), the respective extendable arm (236, 238, 240, 242) is coupled with the respective fixed antenna reflector with a movable coupling.

26. The method of any one of claims 14 through 25, wherein: for each satellite of the plurality of satellites (202, 204, 206, 208), the respective extendable arm (236, 238, 240, 242) comprises one or more articulating joints.

27. The method of any one of claims 14 through 26, wherein: the fixed antenna reflectors (228, 230, 232, 234) are non-furling reflectors.

28. The method of any one of claims 14 through 27, wherein: when the plurality of satellites (202, 204, 206, 208) are mounted to the dispenser (252), each respective extendable arm (236, 238, 240, 242) is oriented substantially parallel to the dispenser (252).

29. The method of any one of claims 14 through 28, wherein: the plurality of satellites (202, 204, 206, 208) are spaced substantially equally around the dispenser (252).

30. The method of any one of claims 14 through 29, wherein, when the plurality of satellites (202, 204, 206, 208), when mounted to the dispenser (252):the respective bodies (220, 222, 224, 226) of the plurality of satellites (202, 204, 206, 208) are disposed substantially parallel to the dispenser (252); andAttorney Docket No. VS2641-WO-1 (78120.0749)the respective fixed antenna reflectors of the plurality of satellites (202, 204, 206, 208) are disposed substantially perpendicular to the dispenser (252).

31. The method of any one of claims 14 through 30, wherein: each satellite of the plurality of satellites (202, 204, 206, 208) comprises an antenna (256, 258, 260, 262) that comprises the respective fixed antenna reflector (228, 230, 232, 234), and a feed assembly (244, 246, 248, 250) located on the respective body (220, 222, 224, 226).Attorney Docket No. VS2641-WO-1 (78120.0749)

Images