MODULAR SATELLITE DEPLOYER METHOD, SYSTEM, AND APPARATUS

Abstract

The invention discloses a modular satellite deployer system and method utilizing a novel geometric door configuration employing a novel geometry that permits any number or combination of satellites to deploy from a common sized satellite deployer. The satellite deployer system includes an enclosure. The satellite deployer system includes two or more satellites shaped to conform with the inside of the enclosure. The satellite deployer system includes multi segmented doors, door release mechanisms, and multi segmented ejector mechanisms. Each of multi segmented ejector mechanisms is capable of pushing a satellite of the two or more satellites out of the enclosure. Two or more satellites deploy from the enclosure in any desired sequence by selectively opening the multi segmented doors using the multi segmented door release mechanisms and the multi segmented ejector mechanisms.

Claims

1. A satellite deployer system, comprising: an enclosure; a satellite shaped to conform with the inside of said enclosure; a door connected at a side of said enclosure; a door release mechanism connected to said door; and an ejector mechanism that pushes said satellite out of said enclosure, wherein said satellite deploys from said enclosure by selectively opening said door using said door release mechanism and said ejector mechanism.

2. The satellite deployer system of claim 1, wherein said enclosure has a shape of an extruded cylinder or polygon.

3. The satellite deployer system of claim 1, wherein said door connects to said enclosure via a hinge.

4. The satellite deployer system of claim 1, wherein said enclosure comprises rails.

5. The satellite deployer system of claim 4, wherein said satellite comprises rail-receiving structures, wherein said rails receive said rail-receiving structures, and wherein when said ejector mechanism pushes said satellite forcing said rail-receiving structures to slide along said rails and pushing said door open for deploying said satellite.

6. The satellite deployer system of claim 1, wherein said ejector mechanism comprises a pusher plate.

7. The satellite deployer system of claim 1, wherein said door release mechanism is a low shock release device.

8. A satellite deployer system, comprising: an enclosure; two or more satellites shaped to conform with the inside of said enclosure; multi segmented doors connected at a side of said enclosure; door release mechanisms, each connecting a door of said multi segmented doors; and multi segmented ejector mechanisms, each capable of pushing a satellite of said two or more satellites out of said enclosure, wherein said two or more satellites deploy from said enclosure in any desired sequence by selectively opening said multi segmented doors using said door release mechanisms and said multi segmented ejector mechanisms.

9. The satellite deployer system of claim 8, wherein said enclosure has a shape of an extruded cylinder or polygon.

10. The satellite deployer system of claim 8, wherein said multi segmented doors converge at a common point.

11. The satellite deployer system of claim 8, wherein said multi segmented doors are restrained with a common circular element.

12. The satellite deployer system of claim 11, wherein each of said multi segmented doors comprises resistive cutting wire elements.

13. The satellite deployer system of claim 12, wherein said resistive cutting wire elements are restrained by electrically conductive posts, wherein said electrically conductive posts keep said resistive cutting wire elements in tension against said circular element.

14. The satellite deployer system of claim 13, wherein said resistive cutting wire elements fuse and cut through said circular element to release a door of said multi segmented doors.

15. The satellite deployer system of claim 13, wherein each of said resistive cutting wire elements individually heats up and cuts through said circular element near the edge of a door in order to release said door.

16. The satellite deployer system of claim 8, wherein said enclosure comprises rails.

17. The satellite deployer system of claim 16, wherein each of said two or more satellites comprises rail-receiving structures, wherein said rails receive said rail-receiving structures, and wherein when a multi segmented ejector mechanism of said multi segmented ejector mechanisms pushes a satellite of said two or more satellites forcing said rail-receiving structures to slide along said rails and pushing corresponding door open for deploying said satellite.

18. A method of providing a satellite deployer system, said method comprising the steps of: providing an enclosure; providing two or more satellites conforming to the shape of the inside of said enclosure; providing multi segmented doors connected at a side of said enclosure; providing door release mechanisms, each connecting a door of multi segmented doors; providing multi segmented ejector mechanisms, each capable of pushing a satellite of said two or more satellites out of said enclosure; releasing said two or more satellites in any combination by sequencing said multi segmented door release mechanisms to open said multi segmented doors; and ejecting said two or more satellites from said receptacle via corresponding ejection mechanism of multi segmented ejector mechanisms.

19. The method of claim 18, further comprising: providing a common circular element for restraining said multi segmented doors; providing resistive cutting wire elements at each door of said multi segmented doors; and providing electrically conductive posts for restraining said resistive cutting wire elements, said electrically conductive posts keeping said resistive cutting wire elements in tension against said circular element.

20. The method of claim 19, further comprising fusing said resistive cutting wire elements for cutting through said circular element to release a door of said multi segmented doors.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0035] The present subject matter will now be described in detail with reference to the drawings, which are provided as illustrative examples of the subject matter to enable those skilled in the art to practice the subject matter. Notably, the figures and examples are not meant to limit the scope of the present subject matter to a single embodiment, but other embodiments are possible by way of interchange of some or all of the described or illustrated elements and, further, wherein:

[0036] FIG. 1 is an isometric view of a closed state of the inventive device;

[0037] FIG. 2 is an isometric view of an open state of the inventive device;

[0038] FIG. 3 illustrates a second open state of the inventive device;

[0039] FIG. 4 illustrates a third open state of the inventive device;

[0040] FIG. 5 illustrates the door restraint system of the inventive device; and

[0041] FIG. 6 is a closer view of the door restraint system of the inventive device.

DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS

[0042] The detailed description set forth below in connection with the appended drawings is intended as a description of exemplary embodiments in which the presently disclosed process can be practiced. The term “exemplary” used throughout this description means “serving as an example, instance, or illustration,” and should not necessarily be construed as preferred or advantageous over other embodiments. The detailed description includes specific details for providing a thorough understanding of the presently disclosed method and system. However, it will be apparent to those skilled in the art that the presently disclosed process may be practiced without these specific details. In some instances, well-known structures and devices are shown in block diagram form to avoid obscuring the concepts of the presently disclosed method and system.

[0043] In the present specification, an embodiment showing a singular component should not be considered limiting. Rather, the subject matter preferably encompasses other embodiments including a plurality of the same component, and vice-versa, unless explicitly stated otherwise herein. Moreover, applicants do not intend for any term in the specification or claims to be ascribed an uncommon or special meaning unless explicitly set forth as such. Further, the present subject matter encompasses present and future known equivalents to the known components referred to herein by way of illustration.

[0044] The figures herein provided, in conjunction with the written description here, clearly provide enablement of all claimed aspects of the disclosed subject matter. Accordingly, in FIG. 1 a deployer enclosure 100 that can accommodate up to a 12 U format CubeSat is illustrated. The front of enclosure 100 is comprised of a set of eight door flaps 101 on hinges 102 that form the front side of enclosure 100. All door flaps 101 intersect at the common point 103. All other five sides of enclosure 100 are generally solid panels that may or may not have openings, either open holes in the panels or doors on the panels, to access the contents inside enclosure 100. Hinges 102 may be formed of any hinge system as is well known in the art but a fabric or flex hinge, as is well known in the art, is preferred as it is less likely to bind or seize under the vacuum and thermal conditions of space.

[0045] FIG. 2 illustrates the release and deployment of a 12 U format CubeSat satellite 200 from enclosure 100. Release of satellite 200 is accomplished by opening all eight door flaps 101 simultaneously. Release of door flaps 101 permits pusher plate 201 to force satellite 200 (i.e., rail-receiving structures at satellite) to slide along rails 202 thus pushing open door flaps 101 while satellite 200 is ejected from enclosure 100. Pusher plate 201 is restrained from leaving enclosure 100 by any well-known means. Additionally, hinges 102 can utilize a torsion spring or some other method to urge door flaps open in addition to the force of the deploying satellite 200.

[0046] This door geometry has multiple advantages, namely 1. each of the door flaps 101 can open independently of the other door flaps 101, 2. each door flap 101 is hinged on a single edge which, when combined with all the other door flaps 101, provides the maximum length of hinge available and thus, maximum strength available to all the door flaps 101 to restrain the satellite 200 inside enclosure 100, and 3. All door flaps 101 can be restrained at the common intersection 103.

[0047] As mentioned earlier, each of the door flaps 101 can open independently of the other door flaps 101. This advantage is illustrated in FIG. 3 where only four of the eight door flaps 101 open to permit a single 6 U CubeSat satellite 300 to be ejected while a second 6 U CubeSat satellite 300 (hidden behind closed door flaps 101) is still restrained. Later, the closed-door flaps 101 can be opened to release the additional hidden 6 U CubeSat 300. The two 6 U CubeSat satellites 300 are typically restrained with an additional set of four rails (hidden behind closed door flaps 101) added to enclosure 100 along the dividing plane between the two 6 U CubeSat satellites 300. In addition, a pusher plate 201 is required for each satellite 300 contained in enclosure 100.

[0048] FIG. 4 further illustrates the advantage of the door flap 101 geometry where only two pair of the eight door flaps 101 open to permit a single 3 U CubeSat satellite 400 to be ejected while three other 3 U CubeSat satellites 400 (hidden behind closed door flaps 101) are still restrained. Later, the closed-door flaps 101 can be opened in similar pairs to release the additional hidden 3 U CubeSat satellites 400. The four 3 U CubeSat satellites 300 are typically restrained with an additional set of twelve rails (hidden behind closed door flaps 101) added to enclosure 100 along the two dividing planes between the four 3 U CubeSat satellites 300, one in each quadrant of enclosure 100. In addition, a separate pusher plate 201 is required for each satellite 400 contained in enclosure 100.

[0049] An additional advantage of this door geometry is that a combination of two 3 U CubeSat format satellites 400 and one 6 U CubeSat format satellite 300 can be accommodated where, for example, the 6 U CubeSat format satellite 300 can be released as in FIG. 3 and the two other 3 U CubeSat format satellites 400 can be released as in FIG. 4 in any order desired. Of course, the satellites 300 and 400 are restrained using the proper combination of additional rails 202 and a proper amount of pusher plates 201 as needed.

[0050] One way to overcome changing out of pusher plates 201 is to simply use four pusher plates 201 with each pusher plate 201 utilizing its own spring, one in each quadrant of the enclosure 100, that may be tied together with mending plates. In the case of a 12 U CubeSat format satellite 200, four pusher plates 201 are tied together. In the case of a 6 U CubeSat format satellite 300, two pusher plates 201 are tied together. In the case of 3 U CubeSat format satellites 300, only one pusher plate 201 per satellite 400 is used.

[0051] FIG. 5 illustrates a method of door securing and release mechanism. All door flaps 101 (that are hinged on hinges 102) converge at a common point 103. Additionally, all door flaps are restrained with a common circular element 500. Force on doors from satellites inside of enclosure 100 will tend to put circular element 500 in tension. Circular element 500 can be made of a high strength polymer (e.g. aramid fiber or monofilament line) such that resistive heating cutting wire elements 501 and 502 (e.g. composed of nichrome wire or similar electrical resistive element) are able to fuse and thus cut through the circular element 500 to release door flaps 101.

[0052] FIG. 6 is a detail view of the release mechanism. Circular element 500 is restrained by fasteners (e.g. screws) on posts 600. This permits easy access for changing out circular element 500 after testing or reloading of the deployer with satellites. Resistive cutting wire element 501 is restrained by electrically conductive posts 601 and 603. Resistive heating cutting wire element 502 is restrained by electrically conductive posts 602 and 603. Posts 601, 602 and 603 can use some form of spring mechanism or be springs themselves to keep resistive heating cutting wire elements 501 and 502 in tension against circular element 500 to urge the resistive heating cutting wire elements 501 and 502 through circular element 500 as they are melting circular element 500. Each door flap 101 has two resistive heating cutting wire elements 501 and 502. Since each resistive heating cutting wire elements 501 and 502 can be individually heated and cut through circular element 500 near the edge of each door flap 101, each door flap 101 may be released in any order desired. An additional advantage of having dual resistive cutting wire elements 501 and 502 is that redundant release of each door panel is possible in the event of failure of either or both resistive cutting wire elements 501 and 502 on a single door flap 101 in that the two neighboring door flaps 101 are also capable of cutting circular element 500 near the adjacent edge of each door flap 101 thus releasing the door flap 101 with failed resistive cutting wire elements 501 and/or 502.

[0053] Door flaps 101 may be constructed of common printed circuit board material to enable convenient electrical connection of electrically conductive posts 601 and 603 to release control circuitry via, for example, a flexible cable that passes over hinge 102.

[0054] It should be noted that this door release mechanism is a low shock release device.

[0055] In summary, here has been shown a satellite deployer system that utilizes 1. A receptacle located on the launch vehicle side of the apparatus having a rectangular shape of an extruded box with at least two rails per accommodated satellite located on the inside walls of the box (generally in the inside corners of said box) where the rails can be reconfigured at any time to accommodate any number of satellites, 2. A satellite (or multiple satellites) whose shape generally conforms to the inside of the receptacle and is constrained by said rails, 3. A releasable set of doors that holds satellite(s) in place until the desired deployment time and is able to selectively deploy any number of satellites contained in said receptacle in any desired order and 4. An ejector mechanism that pushes satellite(s) out of the receptacle in a general straight line motion.

[0056] It will be apparent to those skilled in the art that various modifications and variations can be made in the present disclosure without departing from the scope or spirit of the disclosure. Other embodiments of the disclosure will be apparent to those skilled in the art from consideration of the specification and practice of the disclosure disclosed herein. It is intended that the specification and examples be considered as exemplary only, with a true scope and spirit of the disclosure being indicated by the following claims.

[0057] The detailed description set forth here, in connection with the appended drawings, is intended as a description of exemplary embodiments in which the presently disclosed subject matter may be practiced. The term “exemplary” used throughout this description means “serving as an example, instance, or illustration,” and should not necessarily be construed as preferred or advantageous over other embodiments.

[0058] This detailed description of illustrative embodiments includes specific details for providing a thorough understanding of the presently disclosed subject matter. However, it will be apparent to those skilled in the art that the presently disclosed subject matter 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 presently disclosed method and system.

[0059] The foregoing description of embodiments is provided to enable any person skilled in the art to make and use the subject matter. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the novel principles and subject matter disclosed herein may be applied to other embodiments without the use of the innovative faculty. The claimed subject matter set forth in the claims is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein. It is contemplated that additional embodiments are within the spirit and true scope of the disclosed subject matter.