U.S. patent application number 15/394588 was filed with the patent office on 2017-06-22 for door mechanism for satellite deployer system.
The applicant listed for this patent is Victor Dube. Invention is credited to Victor Dube.
Application Number | 20170174368 15/394588 |
Document ID | / |
Family ID | 55179240 |
Filed Date | 2017-06-22 |
United States Patent
Application |
20170174368 |
Kind Code |
A1 |
Dube; Victor |
June 22, 2017 |
DOOR MECHANISM FOR SATELLITE DEPLOYER SYSTEM
Abstract
Disclosed herein is an improved door system for a satellite
deployer for storing, transporting, and deploying space payloads,
as well as the method of its use. The satellite deployer's door
system as described herein allows for increased efficiency due to
the configuration of the mechanical structures used in the
satellite deployment process.
Inventors: |
Dube; Victor; (Austin,
TX) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Dube; Victor |
Austin |
TX |
US |
|
|
Family ID: |
55179240 |
Appl. No.: |
15/394588 |
Filed: |
December 29, 2016 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
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14445271 |
Jul 29, 2014 |
9567115 |
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15394588 |
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B64G 2001/643 20130101;
B64G 1/641 20130101; B64G 1/002 20130101; B64G 1/645 20130101 |
International
Class: |
B64G 1/64 20060101
B64G001/64 |
Claims
1. A method of deploying a space payload comprising: placing a
space payload inside of a satellite deployer, wherein said
satellite deployer comprises: a housing having an open end and an
interior volume; a door movably connected to said housing by a
hinge; a locking mechanism; and an ejection mechanism, transporting
said satellite deployer from a first location to a second location;
disengaging said locking mechanism; rotating said door
approximately 90 degrees about said hinge to uncover said open end;
and ejecting said space payload from said interior volume through
said open end.
2. The method of claim 1, further comprising placing at least one
additional space payload inside of said interior volume and
ejecting said at least one additional space payload out of said
open end.
3. The method of claim 1, wherein said space payload is ejected
into a predetermined trajectory.
4. A system for storing, transporting, and deploying a space
payload comprising: a housing having an open end and an interior
volume; a door movably attached to said housing by a hinge located
on said open end, wherein said hinge is configured to permit
movement of said door between an open position and a closed
position; a frame extension, wherein said frame extension
mechanically engages said door and said housing for preventing
movement of said door 90 degrees from said closed position; a
locking mechanism attached to said door at its confluence when
configured in a closed position; ejection mechanism for moving
items from within said interior volume; and a mounting system for
attaching the exterior of said housing to an external
structure.
5. The door mechanism of claim 4, wherein said open position is
approximately 90 degrees rotated about said hinge from said closed
position.
6. The system of claim 4, wherein said locking mechanism comprises
a ball lock.
7. The system of claim 4, wherein said door further comprises a
load point spaced apart from said hinge.
8. The system of claim 4, further comprising at least one circuit
adapted to trigger said locking mechanism.
9. The system of claim 4, wherein said door comprises two or more
door sections, wherein each of said door sections extends partially
across said open end when in said closed position.
10. The system of claim 9, wherein each of said door sections
extends approximately halfway across said open end when said door
is in said closed position.
11. The system of claim 4, wherein said open end comprises a
rectangular shape.
Description
FIELD OF THE INVENTION
[0001] The present disclosure relates to a door system for more
efficient deployment of payloads into space and the method of its
use. More specifically, the present disclosure delineates a door
system for use on a satellite deployer designed to store,
transport, and deploy space payloads, such as picosatellites,
including CubeSats, into space and method of its use. The door
system provided herein allows for more efficient packing of
satellite a ployers while maintaining their functionality.
BACKGROUND OF THE INVENTION
[0002] For the purposes of interpreting the disclosure made herein,
the terms "CubeSat deployer", "satellite deployer", "satellite
deployer system", or derivations thereof are used interchangeably
and should be considered synonymous.
[0003] Unless otherwise defined, all terms (including technical and
scientific terms) used herein have the same meaning as commonly
understood by one of ordinary skill in the art to which this
disclosure belongs. It will be further understood that terms, such
as those defined in commonly used dictionaries, should be
interpreted as having a meaning that is consistent with their
meaning in the context of the relevant art and the present
disclosure, and will not be interpreted in an idealized or overly
formal sense unless expressly so defined herein.
[0004] Aerospace development requires (by its nature) access to
space. Due to the difficulties, hazards, and costs inherent in
aerospace activities, satellites, have been, and will continue to
be the primary means for the vast majority of extra-planetary
operations. Satellites have been used in aerospace applications to
explore space, gather and relay data, perform experiments, and do
any other number of tasks for which their creators have designed
them.
[0005] Picosatellites, including CubeSats, provide a means for
minimizing the financial barrier to space entry. A CubeSat is a
miniature satellite having a width of 10 cm, a height of 10 cm and
a length that may be variable. Common CubeSat dimensions are "1U"
(10.0.times.10.0.times.13.5 cm), or multipliers thereof, ie. "2U"
(10.0.times.10.0.times.27.0 cm), and "3U"
(10.0.times.1.0.times.40.5 cm) 2U.times.3U
(10.0.times.20.0.times.40.5 cm), etc. The components used to build
CubeSats are usually relatively inexpensive, off-the-shelf,
electronics. The small size of these CubeSats and other
picosatellites coupled with their uniform dimensions and
inexpensive components make these satellites an attractive means of
accessing space at a relatively small cost.
[0006] Miniaturized satellites can simplify problems commonly
associated with mass production, although few satellites of any
size, other than "communications constellations" (where dozens of
satellites are used to cover the globe), have been mass-produced in
practice.
[0007] One reason for miniaturizing satellites, is to reduce the
cost associated with transporting them into space. Heavier
satellites require more energy to transport them into orbit or open
space, thereby requiring larger rockets with greater fuel
requirements, which results in higher costs. In contrast, smaller
and lighter satellites require less energy and less volume
(requiring smaller and cheaper launch vehicles) and may be launched
in multiples, or in other words, deployed in groups and at the same
time. These small satellites, such as CubeSats and other
picosatellites, can also be launched in a "piggyback" manner, using
excess capacity available on already loaded launch vehicles.
[0008] The high cost of transporting mass from the surface of a
stellar body into an orbit around a celestial body, or open space,
has limited the development of aerospace activity. This high cost
per unit mass has made minimizing the mass of the objects being
sent into space particularly important.
[0009] In order to achieve their purpose, CubeSats must be
transported out of the atmosphere and released into space (whether
that is into an orbit around a celestial body or into open space).
Satellite deployers are used to store and protect satellites during
their transportation into space. These satellite deployers protect
the payloads stored inside of them. from damage caused by the
inherent stresses resulting from launching such payloads into
space. The satellite deployer must also safely and efficiently
deploy their satellite payloads into the correct trajectory once
the system has reached space.
[0010] The standardized specification of CubeSats also allows for
the deployment means of these satellites to be standardized as
well. The standardization among both payloads and deployers enables
quick exchanges of payloads without the need of customized
payload-deployer interfaces. It also allows for easy
interchangeability of similarly dimensioned satellites.
[0011] Associated with the minimization of mass is the minimization
of volume. This is important in the field of space transportation
since there is a finite amount of usable storage volume inside of
space vehicles.
[0012] This minimization of mass and volume is important not only
for satellites, but for the systems used to store, transport and
deploy the satellites.
[0013] Satellite deployers may be designed as metal storage
containers into which satellites are placed. These container-type
satellite deployers usually provide a door at one end, through
which payloads may be loaded and unloaded. After loading, the
deployer system's door is sealed, and the deployer system is then
mounted onto a launch vehicle which is responsible for transporting
the deployer system, including any satellites or other space
payloads stored therein, into space. Once the system is in space,
the deployer may then be taken through an airlock so that the
deployer is in contact with space. Once the deployer is in contact
with space, the deployer's door is pointed in the desired direction
of deployment (away from any potential obstructions, such as other
deployer's doors). The door(s) to the deployer system are then
opened, and a propulsion means is used to eject the payload(s) into
space in a manner conforming to predetermined parameters depending
on the payload's intended use.
[0014] CubeSat deployers may have a housing that may be tubular in
shape with a door which opens to reveal an open end through which
the satellites may be ejected. Such satellite deployers have an
onboard ejection mechanism with which can be used to supply the
energy for ejecting the payloads from the interior volume of the
deployer into space. This deployment means may be one or more
springs, cold gas, hot gas, compressed gas, or other such energy
sources (or a combination thereof) capable of imparting a force
onto the space payload such that the payload is forced out of the
interior volume of the deployer. The door system is used to contain
the payloads during the storage phase until they are ready to be
deployed. Generally this type of satellite deployment system may
utilize a single door which opens wide, having a door travel path
of significantly more than 90 degrees. This type of door mechanism
requires a large door travel path to provide sufficient clearance
so as to allow for the egress of their space payload(s).
[0015] Current deployers can carry a maximum of three 1U CubeSats.
Their release mechanism generally consists of a motor with a lead
screw mechanism that is used to open the door and allow for release
of the payload. The combination of the maximum load and large door
mechanism limits the number of CubeSats the can be deployed for a
given mission.
[0016] On the international Space Station (ISS) the CubeSats and
their deployers must at some point pass through the limited. volume
of the craft's airlock. With this restriction, and based on the
dimensions of the ISS' airlock, which is known in the art, at most
only six 1U CubeSats may be deployed with current deployer systems
in any single airlock cycle on either the ISS itself, or on other
space vehicles having similarly configured. airlocks. The teachings
included in the present disclosure allow for a total of eight
satellite deployers loaded with six CubeSats each to pass through
an airlock with similar dimensions that of the ISS in a single
cycle. This results in the potential for 48 CubeSats deployments in
a single airlock cycle.
[0017] A limitation of current satellite deployer technology arises
as a result of the design of a deployer's openings and the
associated large door travel path, or envelope. The satellite
deployer's door system may rotate 180 degrees or more about a hinge
when transitioning from a closed to an open configuration. A door
travel path having a rotation greater than 90 degrees may impede an
adjacent door system's ability to open fully and/or may compromise
the open end of adjacent satellite deployers by blocking a portion
of said open end. This may result in the inability to effectively
use multiple satellite deployers when arranged in close proximity
to one another, preventing optimal packing of the satellite
deployers within the limited interior volume of space vehicles and
their airlocks,
[0018] Another limitation of current satellite deployers is the
lack of redundant lock-disengagement circuits. Due to the risks
inherent in space activities, redundant systems are recommended in
case of a malfunction, that would otherwise compromise
operations.
BRIEF SUMMARY OF THE INVENTION
[0019] The purpose of this summary is to present integral concepts
in a simplified form as a prelude to the more detailed disclosure
that is presented herein.
[0020] The present disclosure provides a system and method for
addressing the limitations of the existing technology and practices
associated with deployment of CubeSat satellites.
[0021] One embodiment of the present disclosure provides a door
mechanism associated with a housing compartment. This exemplary
door mechanism allows for free rotation of a door from a closed
position to an open and perpendicular (90.degree. degree) position
for enabling unencumbered ejection and disbursement of any housed
satellites.
[0022] A further embodiment of the present disclosure provides for
a door locking mechanism for restraining the door in a closed
position.
[0023] A further embodiment of the present disclosure comprises a
locking mechanism for releasibly retaining said door in said closed
position.
[0024] A further embodiment of the present disclosure provides for
a door locking mechanism comprising a ball lock.
[0025] A further embodiment of the present disclosure can be
mechanically operated.
[0026] A further embodiment of the present disclosure can be
electronically operated.
[0027] A further embodiment of the present disclosure comprises a
load point spaced apart from said hinge.
[0028] A further embodiment of the present disclosure comprises
circuitry for triggering a locking mechanism.
[0029] A further embodiment of the present disclosure comprises
multiple door sections.
[0030] Descriptions of certain illustrative aspects are described
herein in connection with the annexed. FIGURES. These aspects are
indicative of various non-limiting ways in which the disclosed
subject matter may be utilized, all of which are intended to be
within the scope of the disclosed subject matter. Other advantages,
emerging properties, and features will become apparent from the
following detailed disclosure when considered in conjunction with
the associated FIGURES that are also within the scope of the
disclosure.
BRIEF DESCRIPTION OF THE DRAWINGS
[0031] The novel features believed characteristic of the disclosed
subject matter will be set forth in any claims that are filed
later. The disclosed subject matter itself, however, as well as a
preferred mode of use, further objectives, and advantages thereof,
will best be understood by reference to the following detailed
description of an illustrative embodiment when read in conjunction
with the accompanying drawings, wherein:
[0032] FIG. 1 illustrates an exemplary CubeSat.
[0033] FIG. 2 depicts a deployer system having its door system in
an open configuration.
[0034] FIG. 3 depicts a deployer system having its door system in a
closed configuration.
[0035] FIG. 4 shows a closer view of a deployer system having its
door system in an open configuration.
[0036] FIG. 5 depicts a ball lock mechanism in a closed
configuration.
[0037] FIG. 6 depicts a ball lock mechanism in an open
configuration.
[0038] FIG. 7 shows eight satellite deployer systems in a matrix
configuration.
[0039] FIG. 8 shows eight satellite deployer systems with their
door systems in the open position while configured in a matrix
array, wherein each deployer is positioned such that it has two
sides of its housing in mechanical contact with another satellite
deployer system.
DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS
[0040] Reference now should be made to the drawings, in which the
same reference numbers are used throughout the different figures to
designate the same components.
Entire Deployer:
[0041] The disclosed system may incorporate both a door system and
a door locking mechanism, which allow the device disclosed herein
to operate more efficiently and dependably than other systems known
in the art.
[0042] FIG. 1 illustrates a simplified representation of a CubeSat
100, comprising six external surfaces, including two sides, a top,
a bottom, and a back.
[0043] FIG. 2 depicts an exemplary satellite deployer system with
the door system 206 in the open position, wherein the locking
mechanism 214 has been disengaged, and wherein the door system 206
has rotated about the hinges 212 approximately 90 degrees from a
closed position. The door system 206 has been stopped at, this 90
degree open position by having the door edge 210 mechanically
engage the frame extension 208.
[0044] FIG. 3 provides a representation of an exemplary satellite
deployer system with the door system 206 in a closed position,
wherein the locking mechanism 214 is engaged and is preventing the
door system 206 from rotating about the hinges 212.
[0045] FIG. 4 provides a closer view of an exemplary door mechanism
enabling a 90.degree. opening to be provided. The exemplary door
system 206 depicted in FIG. 4 comprises two doors, each spanning
approximately 50% of the open end 202 of the deployer's housing
200.
[0046] FIG. 5 illustrates a schematic representation of an
exemplary door mechanism enabling a 90.degree. opening to be
provided. The exemplary door system 206 of FIG. 5 comprises two
doors, each spanning approximately 50% of the open end 202 of the
deployer's housing 200. The schematic of FIG. 5 depicts such a
satellite deployer system having its door system 206 in a closed
position. In the embodiment of the satellite deployer system
depicted in FIG. 5 the frame extensions 208 are extending
perpendicular (at a 90 degree angle) to both the door system 206
when the door system 206 is in the closed position, and to the door
frame 204. In the embodiment depicted in FIG. 5 the frame
extensions 208
[0047] FIG. 6 depicts a schematic representation of an exemplary
door mechanism, having a locking mechanism 214 (in this depiction
the locking mechanism 214 is a ball lock), wherein the locking
mechanism 214 has been disengaged, allowing the door system 206 to
rotate about the hinge 208 until the door system 206 has been
stopped at the 90.degree. point due to mechanical engagement
between the frame extension 208 and the door edge 212.
[0048] FIG. 7 depicts a schematic representation of 8 satellite
deployers configured in a matrix fashion, wherein the exterior
surfaces of the satellite deployers' housings 200 are in physical
contact with one another. In this depiction the satellite deployers
have their door systems 206 configured in a closed position.
[0049] FIG. 8 depicts a schematic representation of 8 satellite
deployers configured in a matrix fashion, wherein the exterior
surfaces of the satellite deployers' housings 200 are in physical
contact with one another. In this depiction the satellite deployers
have their door systems 206 configured in an open position, showing
the ability for the doors system 206 detailed in this disclosure to
not impede in the envelop of adjacent deployer's door systems
206.
[0050] In one embodiment, the door mechanism for the satellite
deployer may comprise a housing 200 having at least one open end
202 and an interior volume 202, a door frame 204 disposed about the
perimeter of the housing's 200 open end 202, at least one frame
extension 208, and a door system 206 connected to the door frame
204 by at least one hinge 212.
[0051] In one embodiment, the open end 202 of the deployer's
housing 200 may be rectangular in shape.
[0052] An embodiment of the door frame 204 may comprise at least
one horizontal component coupled to a horizontal portion of the
housing's 200 open end 202, and at least one vertical component
coupled to a vertical portion of the housing's 200 open end
202.
[0053] Embodiments of the door system 206 may be configured to
allow the door system 206 to reversibly transition from a closed
position, wherein the door system 206 completely occludes the open
end 202 of the deployer's housing 200 to an open position, wherein
the door system 206 does not occlude any portion of the open end
202 of the deployer's housing 200. In one embodiment, the open
position may be achieved once the door system 206 has traveled
approximately 90 degrees about the hinge 212.
[0054] In one embodiment, the door system 206 may consist of a
single door. In an alternate embodiment, the door system 206 may
comprise two doors, each of which may extend across a portion of
the open end 202 of the housing 200 when in a closed configuration.
In a further embodiment, the door system 206 may comprise a
plurality of doors each of which may extend across a portion of the
open end 202 of the housing 200 when in a closed configuration.
[0055] An embodiment of the frame extension 208 may be coupled to
the door frame 204, and may extend perpendicularly from a component
of the door frame 204, The frame extension 208 may be positioned so
as to mechanically engage the door system 206 at the door edge 210
once the door system 206 has traveled approximately 90 degrees
about the hinge 212. In an embodiment, once the door system 206 has
traveled approximately 90 degrees about its hinge 212 from a closed
configuration the door edge 210 may mechanically engage the frame
extension 208 in such a manner that the frame extension 208 impedes
the door system 206, Preventing the door system 206 from any
further rotation about the hinge 212.
[0056] In one embodiment, one or more hinges 212 may engage both
the door frame 204 and the door system 206 at one or more hinge
points, enabling the door system 206 to rotate about the hinge 212
in a manner that allows the doors system 206 to reversibly travel
from a closed configuration to an open configuration.
[0057] Embodiments of the deployer housing 200, door frame 204,
door system 206, and/or other components of the door mechanism may
be made from any variety of, or combination of, materials suitable
for exposure to and use in space. Such materials are well known in
the art.
[0058] Embodiments of the satellite deployer door mechanism may
comprise a locking mechanism 214. The locking mechanism 214 may be
used to releasibly secure the door system 206 in place when the
door system 206 is configured in a closed position. The locking
mechanism 214 may be positioned at the confluence of the plurality
of doors in the event that the door system 206 comprises a
plurality of doors. Alternatively, the locking mechanism 214 may be
positioned between the door system 206 and the door frame 204. In
one embodiment the locking mechanism 214 may be a ball lock
mechanism. Some embodiments may provide for the locking system 214
to be activated by one or more of a plurality of independent
electronic or mechanical circuits, or a combination thereof.
[0059] Embodiments of the door mechanism may comprise one or more
Load Points 216. Embodiments of the Load Points 216 may be
positioned close to the hinges 212 so as to maximize the mechanical
load exerted on the hinge 212 and minimize the mechanical load
exerted on the locking mechanism 214.
[0060] Embodiments of the satellite deployer may have a mounting
system integrated with, or attached to, the exterior surface of the
housing 200, which may be used to secure the satellite delpoyer
housing 200 to an external structure. Such external structures may
include, but are not limited to, space transport vehicles, interior
walls of a cargo bay, or the housing of another satellite deployer,
etc.
CubeSat Storage:
[0061] In an embodiment of the disclosure, the satellite deployer's
door system 206 may be configured such that two doors may extend
halfway across the satellite deployer housing's 200 open end 202.
The door system 206, when in the fully open position, will have
rotated 90 degrees about its hinge 212 relative to the door
system's 206 closed position. When in the open position, the door
system 206 may be in plane (forming a 180 degree angle) with the
internal face of the walls of the satellite deployer housing 200 to
which the door system 206 is attached. By making the door system
206 open to the 90 degree position, the satellite deployer system
can ensure that the door system 206 will not impede the egress of
the space payload (i.e. a CubeSat 100) when they are
ejected/deployed.
[0062] Additionally, by making the door system 206 of the satellite
deployer extend no further than the aforementioned 90 degree
position, it may be ensured that the travel path of the door system
206 will not encroach on the travel path of another CubeSat
deployer' door system 206 placed adjacent to the first CubeSat
Deployer, even if the systems are positioned such that the face of
the exterior walls of two deployers' housings 200 are in lateral
physical contact. The ability of the CubeSat Deployer system to be
both stored, and used for deploying space payloads, while in very
close physical proximity with one another without hindering their
ability to operate effectively is a significant advantage over
deployers currently known in the art. This feature is of particular
importance given that the nature of space transport often calls for
minimizing the consumption of a limited volume while maintaining as
much utility as possible.
Door Mechanism:
[0063] In one embodiment of the present disclosure, the door system
206 may comprise two separate doors, with each extending halfway
across the satellite deployer housing's 200 open end 202 when in a
closed position.
[0064] In an embodiment, the doors may be connected to the open end
202 of the housing 200 at one or more hinge points.
[0065] In an embodiment, the door-to-housing hinge-joint may be
configured such that the door system 206 opens outward to a 90
degree angle. By having the door system 206 open to a 90 degree
angle it is possible for there to be no impedance of the ejection
of the payload. Additionally, the 90 degree door opening allows for
the travel path of the door system 206 to not interfere with that
of the travel path of any other similar satellite deployer's door
system 206 when the satellite deployers are positioned next to one
another in a matrix fashion, thus allowing for a maximum number of
satellite deployer systems, and thus maximum payload deployment
capability, in a minimum of space.
[0066] In one embodiment of the present disclosure, the contact
points between the payload and the door system 206 ("Load Points"
216) are positioned close to the hinges 212. Placing said Load
Points 206 close to the hinges 212 allows the mechanical load on
the hinges 212 to be maximized while the load on the locking
mechanism 214 is minimized.
[0067] In an embodiment of the disclosure, during the
transportation process, the door system 206 of the satellite
deployer system may be held in a closed position in which the door
system 206 fully occlude the open end 202 of the satellite deployer
system's housing 200 by a locking mechanism 214.
[0068] In another embodiment, the locking mechanism 214 may be
resetably engageable.
[0069] In another embodiment, the locking mechanism 214 may be
resetably disengageable.
[0070] In an embodiment, the locking mechanism 214 may be both
resetably engageable and resetably disengageable.
[0071] In another embodiment, the locking mechanism 214 may be
resetably disengageable through the operation of any of a plurality
of independent circuits.
[0072] In a further embodiment, the locking mechanism 214 may be
resetably disengageable through the operation of one or more of a
plurality independent circuits.
Locking Mechanism:
[0073] In one embodiment the locking mechanism 214 used to maintain
the door mechanism 206 in a closed position during storage and
transport is a ball-lock mechanism. Such a ball-lock mechanism uses
ball bearings recessed into the interior wall of the ball-lock
mechanism coupled with one or more adjusting screws to maintain
mechanical connection between the elements of the locking
system.
[0074] In an embodiment, the ball-lock mechanism is engageable
through the insertion of a pin from a disengaged position through
the activation of a pin-puller mechanism.
[0075] In an embodiment, the ball-lock mechanism is disengageable
through the retraction of a pin from an engaged position through
the activation of a pin-puller mechanism.
[0076] In one embodiment, the pin retraction used to disengage the
ball-lock mechanism may be achieved by coupling the characteristics
of shape memory alloy with a Dent Mechanism.
[0077] In an embodiment, the pin-puller mechanism may be resetably
engageable.
[0078] In another embodiment, the pin-puller mechanism may be
resetably disengageable.
[0079] In a further embodiment, the pin-puller mechanism may be
both resetably engageable and resetably disengageable.
[0080] The resetably engageable and disengageable pin-puller
mechanism allows for the ball-lock mechanism to be repeatedly
engaged and/or disengaged. This in turn allows the doors of the
system to be repeatedly opened and/or closed.
[0081] In an embodiment, the pin-puller mechanism may be triggered
by any of a plurality of independent circuits, such that there is
redundancy in the locking mechanism's operation system.
Payload Deployment:
[0082] Space payload deployment may be achieved when the one or
more circuits controlling the locking mechanism 214 are activated,
resulting in the disengagement of the locking mechanism 214,
allowing for the door system 206 to rotate to the 90 degree open
position, at which time an ejection mechanism is used to impart a
force on the payloads stored inside of the system's interior volume
202, resulting in the ejection of said payload from said system's
interior volume 202 into the surrounding space through the system's
(now) open end 202.
[0083] In an embodiment, the space payload deploying system is
configured such that each space payload deploying system can
retain, transport, and deploy up to eight CubeSats at any given
time.
[0084] In an embodiment, the space payload deploying system is
configured such that six deployers, arranged in a matrix
configuration, may pass through a standard space station airlock at
the same time.
[0085] Combining the two embodiments described immediately above
may allow for the deployment of 48 CubeSats in one cycle of an
airlock.
[0086] In an embodiment, the space payload may comprise
satellites.
[0087] In an embodiment, the space payload may comprise
picosatellites.
[0088] In a further embodiment, the space payload may comprise
CubeSats.
[0089] All methods described herein can be performed in a suitable
order unless otherwise indicated herein or otherwise clearly
contradicted by context. The use of any and all examples, or
exemplary language (e.g., "such as"), is intended merely to better
illustrate the disclosure and does not pose a limitation on the
scope of the disclosure unless otherwise claimed. No language in
the specification should be construed as indicating any non-claimed
element as essential to the practice of the disclosure as used
herein.
* * * * *