SATELLITE DEPLOYER METHOD, SYSTEM, AND APPARATUS

Abstract

The disclosure relates to an improved satellite deployer system and method utilizing a novel geometric configuration employing a draft geometry between a satellite and a deployer that prevents jamming of a satellite during deployment while simultaneously reducing satellite deployment tipoff rates. The satellite deployer system includes a receptacle having the general shape of an extruded cylinder or polygon with draft. The satellite deployer system includes a satellite shaped to conform with the inside of the receptacle. The satellite deployer system includes a releasable mechanism to hold the satellite in the receptacle. The satellite deployer system includes an ejector mechanism that pushes or pulls the satellite out of the receptacle. The satellite is deployed from the launch vehicle by the ejector mechanism after the releasable mechanism is released.

Claims

1. A satellite deployer system, comprising: a receptacle with draft, wherein the smaller diameter of said receptacle locates on the side facing a launch vehicle; a satellite shaped to conform with the inside of said receptacle; a releasable mechanism to hold said satellite in said receptacle; and an ejector mechanism that pushes or pulls said satellite out of said receptacle, wherein said satellite is deployed from said launch vehicle by said ejector mechanism after said releasable mechanism is released.

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

3. The satellite deployer system of claim 1, wherein said receptacle has an interface flange for receiving said satellite.

4. The satellite deployer system of claim 3, wherein said satellite has an outward facing interface flange connecting said interface flange of said receptacle.

5. The satellite deployer system of claim 4, wherein said releasable mechanism joins said interface flange and said outward facing interface.

6. The satellite deployer system of claim 3, wherein said outward facing interface flange comprises a tab.

7. The satellite deployer system of claim 1, wherein said satellite has a flyaway ring, wherein flyaway ring conforms to the inner shape of said receptacle.

8. The satellite deployer system of claim 1, wherein said ejector mechanism comprises one of a spring, a hydraulic or pneumatic ejector, a reaction motor, and a magnet.

9. The satellite deployer system of claim 1, wherein said receptacle comprises a door for enclosing said satellite within said receptacle, wherein said releasable mechanism secures said door in place until deployment of said door.

10. The satellite deployer system of claim 9, wherein said door operates by a hinge.

11. The satellite deployer system of claim 1, wherein said receptacle comprises adapters with rails.

12. The satellite deployer system of claim 11, wherein said satellite comprises rail-like structures, wherein said rails in said receptacle receives said satellite at said rail-like structures.

13. The satellite deployer system of claim 1, wherein said satellite comprises a trash bag.

14. The satellite deployer system of claim 1, wherein said satellite provides a material made of soft structure.

15. A method of proving a satellite deployer system, said method comprising the steps of: providing a receptacle with draft, the smaller diameter of said receptacle locating on the side facing a launch vehicle; providing a satellite shaped to conform with the inside of said receptacle; housing said satellite in said receptacle; providing a releasable mechanism to hold said satellite in said receptacle; providing an ejector mechanism; and ejecting said satellite from said receptacle via said ejection mechanism.

16. The method of claim 15, further comprising providing an interface flange at said receptacle.

17. The method of claim 16, further comprising providing an outward facing interface flange at said satellite for connecting said interface flange of said receptacle.

18. The method of claim 17, further comprising joining said interface flange and said outward facing interface by said releasable mechanism.

19. The method of claim 18, further comprising providing a door at said receptacle for enclosing said satellite within said receptacle, said door secured by said releasable mechanism.

20. The method of claim 18, further comprising: providing adapters with rails in said receptacle; providing rail-like structures at said satellite; and receiving said rail-like structures at said rails for connecting said satellite to said receptacle.

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 illustrates the novel principles of the inventive device;

[0037] FIG. 2 illustrates a first embodiment of the inventive device;

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

[0039] FIG. 4 illustrates the second embodiment of the inventive device utilizing a door for a restraint mechanism;

[0040] FIG. 5 illustrates the second embodiment of the inventive device utilizing adapters for CubeSat satellites;

[0041] FIG. 6 illustrates the second embodiment of the inventive device configured for transportation and deployment of soft articles;

[0042] FIG. 7 illustrates the second embodiment of the inventive device configured for transportation and deployment of trash.

DETAILED DESCRIPTION OF ILLUSTRATIVE EMBODIMENTS

[0043] 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.

[0044] 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.

[0045] 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 the concept of draft 100 (e.g. as used in molds to mass produce objects) is well known in the art and is utilized to ensure rapid and jam-free ejection of molded parts 101 from molds 102 automatically. For example, disposable plastic cups are formed in the general shape of a truncated cone or, in other words, an extruded cylinder 101 with a specific draft angle 100.

[0046] The draft angle 100 is not particularly specific as the principle of a separating pair of nested cones 101/102 only requires a tiny amount of movement 103 along the cylinder's axial axis 104 to ensure complete separation of all surfaces. Draft separation relies on the geometric principle of nested triangles. If any two triangles (contained in parts 101/102) contact each other on their hypotenuse sides and are moved apart from each other with a motion 103 parallel to either opposing side, the entire hypotenuse sides are separated. This is in contradistinction to nested cylinders 105/106 where the contacting sides remain in contact until they are completely separated from each other.

[0047] In FIG. 2 the first embodiment of the invention utilizes receptacle 200 located on the launch vehicle side of the apparatus having the general shape of a shallow extruded cylinder with draft (i.e. a cone) where the smaller diameter of extruded cylinder 200 has an interface flange 201 (outward or inward facing) that is fastened (i.e. bolted, riveted, welded, bonded, etc.) to the launch vehicle side and, on the opposing larger diameter side of the cone, another outward facing interface flange 201 is provided that can join to a flyaway ring 202 on satellite 203 side. On the satellite side, a flyaway ring 202 is provided whose shape generally conforms to the inside of receptacle 200 whose larger diameter side has an outward facing flange 201 that is fastened (i.e. bolted, riveted, welded, bonded, etc.) to satellite 203 side. This same outward facing flange 201 mates to receptacle 200 outward facing flange 201 and both are joined by releasable mechanisms 204 that permit separation of receptacle 200 and flyaway ring 202 when desired. It is important to note that the conic shape of receptacle 200 and flyaway ring 202 with the added flanges 201 produces an extremely high strength to weight ratio structure which is highly desirable for spacecraft launch purposes. Finally, after release of the releasable mechanisms 204, ejector mechanism 205 is provided that pushes satellite 203 out of receptacle 200 by applying the ejection force vector 206 to satellite 203 through the center of gravity 207 of satellite 203 thereby minimizing or eliminating tip-off moments. Any convenient ejector mechanism 205 may be utilized to induce separation, for example, a spring or multiple springs, hydraulic or pneumatic ejectors, reaction motors (e.g. cold gas rockets, solid/liquid rocket motors, etc.). It is not intended to limit the invention to any particular ejector mechanism 205.

[0048] A second embodiment of the invention illustrated in FIG. 3 utilizes receptacle 200 located on the launch vehicle side of the apparatus having the general shape of a deep extruded cylinder or (in this example, an eight-sided) polygon with draft where the smaller diameter of the extruded cylinder/polygon has an interface flange 201 (outward or inward facing) that is fastened (i.e. bolted, riveted, welded, bonded, etc.) to the launch vehicle side and, on the opposing larger diameter side of the extruded cylinder/polygon, another outward facing interface flange 201 is provided that can join to a flange 201 on satellite 203. Satellite 203 is shaped to generally conform to the inside of the deep receptacle 200 and is generally completely encased by receptacle 200. The larger diameter side of satellite 203 has an outward facing flange 201 or tabs 201 that are fastened (i.e. bolted, riveted, welded, bonded, etc.) to or are inherently built into satellite 203 side body. This same outward facing flange on satellite 203 side mates to receptacle 200 outward facing flange 201 and both are joined by releasable mechanisms 204 that permit separation of receptacle 200 and satellite 203 when desired. It is important to note that the conic shape of receptacle 200 with the added flanges 201 produces an extremely high strength to weight ratio structure which is highly desirable for spacecraft launch purposes. Finally, after release of the releasable mechanisms 204, ejector mechanism 205 is provided that pushes satellite 203 out of receptacle 200 by applying the ejection force vector 206 to satellite 203 (in this example) ahead of the center of gravity 207 of satellite 203 thereby minimizing or eliminating tip-off moments. Any convenient ejector mechanism 205 may be utilized to induce separation, for example, a spring or multiple springs, hydraulic or pneumatic ejectors, reaction motors (e.g. cold gas rockets, solid/liquid rocket motors, etc.). It is not intended to limit the invention to any particular ejector mechanism 205.

[0049] In FIG. 4 an alternate method of containment and release may be to utilize a door 400 at the larger diameter end of receptacle 200 where a hinge 401 and opposing releasable mechanism 204 hold the door 400 in place for launch and, with the release of the releasable mechanism 204, permits the door 400 to open and release satellite 203 contained inside receptacle 200. Finally, after release of the releasable mechanisms 204 (or door 400), an ejector mechanism 205 is provided that pushes satellite 203 out of receptacle 200 by applying the ejection force vector to satellite 203 through the center of gravity of satellite 203 thereby minimizing or eliminating tip-off moments. In this embodiment the ejector mechanism 205 may apply the ejection force behind satellite 203 center of gravity or (which is more desirable) in front of satellite 203 center of gravity thus providing an inherently stable application of ejection force (similar to a tractor-like application of force) and adds to the ability of the system to provide a low tip-off rate ejection of satellite 203. Any convenient ejector mechanism 205 may be utilized to induce separation, for example, a spring or multiple springs, hydraulic or pneumatic ejectors, reaction motors (e.g. cold gas rockets, solid/liquid rocket motors, etc.), permanent magnets, electromagnetic, etc. Any parallel or straight-line motion mechanisms may be used (e.g. scissor jack mechanisms or pneumatic bag as illustrated, etc.) in conjunction with a motive force to provide straight line motion of the motive force. It is not intended to limit the invention to any particular ejector mechanism 205.

[0050] A peculiar and extremely useful property of this embodiment is that since receptacle 200 completely encases satellite 203, receptacle 200 is capable of handling the majority of the launch loads of satellite 203 and receptacle 200 thus, when satellite 203 is deployed from receptacle 200, the additional structural weight generally required to handle launch loads is left behind on the launch vehicle. This is particularly useful for orbital upper stage applications where it is desirable to minimize the amount of unused structure mass in the structure that is propelled onward from the launch vehicle after achieving initial orbital velocity (and microgravity) above a planetary body. For example, an electrically propelled upper stage must survive launch loads but does not require a strong structure after achieving low earth orbit since the force applied by the electric thruster is extremely low. The second embodiment of the inventive device permits this mode of transportation where essentially all the launch loads are taken up by receptacle 200 and the ejected upper stage 203 may utilize an extremely lightweight, gossamer-like structure.

[0051] In FIG. 5 the addition of adapters 500 to the second embodiment adapts a standard, rectangular format satellite 203 (e.g. a rail type CubeSat) to be deployed from receptacle 200 formed as deep extruded four-sided polygon with draft. As an example, four adapter structures 500 are formed that, on the inner surface, each interface with one rail 501 of a CubeSat 203 and, on the outer surface, each conform to the draft surface of receptacle 200. Upon installation of CubeSat 203 into receptacle 200, the four adapters 500 follow the draft of receptacle 200 and present a uniform clamping force to the four rails 501 of CubeSat 203 thereby restraining the motion of CubeSat 203 to the center of receptacle 200. CubeSat 203 and the four adapters 500 are then constrained in place by a forward door 400 hinged 401 to receptacle 200. A releasable mechanism 204 secures the door 400 in place until the desired deployment. When deployment of satellite 203 occurs, the releasable mechanism 204 opens receptacle 200 door 400 and an ejector mechanism 205 of any convenient choice (e.g. spring, pneumatic, etc.) pushes CubeSat 203 out of receptacle 200 while simultaneously urging adapters 500 outward. Urging adapters 500 outward removes the clamping force imposed upon four rails 501 and releases CubeSat 203. The adapters should be restrained to receptacle 200 by any convenient means known in the art (e.g. t-pin on adapter 500 and slot in receptacle 200) to prevent any unnecessary debris from being released from receptacle 200 during satellite 203 deployment.

[0052] In FIG. 6 the second embodiment is also particularly suited for transporting and deploying inflatable spacecraft or soft goods to an orbital location. In the past, most inflatable structures or soft good items have been simply bundled and strapped to a flat plate. This method presents a variety of problems, most notably the lack of securing the load's center of gravity in a specific location. Such variability of center of gravity causes significant problems with launch vehicle and spacecraft guidance systems that can end in the loss of control resulting in the loss of a launch vehicle or result in a collision. The inventive device overcomes these problems by completely encasing the soft structure (a.k.a. satellite) 203 inside receptacle 200 during launch and, when deployment is desired, ejected from receptacle 200. It should be noted that satellite 203 inside receptacle 200 can be completely incapable of handling any launch loads whatsoever as all launch loads can be accommodated by receptacle 200 structure. This enables an entirely new and novel method of satellite 203 construction. The draft angle 100 provided on the side of receptacle 200 also accommodates any changes in the geometry of the soft goods 203 during deployment which could potentially cause jamming or hang up of soft goods 203 in receptacle 200 during deployment.

[0053] FIG. 7 illustrates a further benefit of the second embodiment of the inventive device for the disposal of trash 700 in a manned space station situation. Trash 700 may be loosely defined as the undesirable remains of activities that need to be removed from the area of activities. As such, it is highly desirable to spend as little time planning and performing trash 700 removal as well as minimizing orbital debris (i.e. keeping trash 700 together as a large, trackable space object) which poses a significant problem in the spacecraft environment. The second embodiment of the inventive device may be configured to utilize a trash bag 701 that generally conforms to receptacle 200 installed in an airlock 702 (e.g. Johnson, et. al. U.S. Pat. No. 10,569,911 as used in FIG. 7). Receptacle 200 is in the shape of a deep extruded cylinder or polygon with draft where the smaller diameter of the extruded cylinder/polygon is positioned on the inner side of an airlock 702 and, the opposing larger diameter side of the extruded cylinder/polygon receptacle 200 is pointed in the deployment direction from the airlock 702. Receptacle 200 can be mounted in the airlock 702 via any convenient manner such as flanges or attaching the sides of receptacle 200 to the inner walls of the airlock 702. The trash bag 701 can be filled with trash from either the small diameter end of receptacle 200 or the large diameter end of receptacle 200. Once the bag 701 is sealed, it is ready for deployment from receptacle 200. An ejection mechanism 205 (e.g. a pneumatic bag, spring system, etc.) is placed between the filled trash bag 701 and receptacle 200 on the small diameter end of receptacle 200. It should be noted that the airlock 702 wall could form a wall (or end cap) of receptacle 200 and the ejection mechanism 205 could be mounted on the airlock 702 wall. The large diameter end of the trash bag 701 can utilize some form of releasable restraint (e.g. straps held down with releasable mechanism 204) between the larger diameter, forward end of receptacle 200 and the trash bag 701. It should be noted that the releasable restraint 204 could also be connected between the trash bag 701 and the airlock 702 wall.

[0054] Upon completion of filling the trash bag 701, placing the ejection mechanism 205 and restraining the trash bag 701, the airlock 702 may be depressurized, the airlock 702 opened to space and the large diameter end of receptacle 200 be pointed in the desired ejection direction to space. The releasable restraint 204 is released, the ejection mechanism 205 is operated, and the trash bag 701 is deployed into space.

[0055] A significant advantage to this trash disposal system is that any shaped object may be placed into the trash bag 701 during the loading process without regard or concern of jamming of the ejection of the trash bag 701 during the eventual ejection process due to receptacle 200's wall draft. Any object, rigid or flexible (e.g. bags of liquids) may be accommodated so long as it can fit within the confines of receptacle 200. The trash bag 701 can be filled to any capacity so long as the entire trash bag 701 fits within the confines of receptacle 200. The trash bag 701 need not be rigid in any way. This eliminates any planning concerns on the part of the crew for trash disposal and trash may be added to the bag until it is full at which point it may be sealed and ejected from the spacecraft.

[0056] It should be noted that a convenient, low shock releasable mechanism 204 that could be utilized with the inventive device is detailed in the Applicant's co-pending Provisional Patent Application 63/087,250 dated Oct. 4, 2020.

[0057] In summary, here has been shown a satellite deployer system that utilizes 1. A receptacle 200 located on the launch vehicle side of the apparatus having the general shape of an extruded cylinder or polygon with angled sides (i.e. draft) where the smaller diameter of the extruded cylinder or polygon is located on the launch vehicle side, 2. A satellite 203 whose shape generally conforms to the inside of the receptacle, 3. A releasable restraint system that holds satellite 203 in place until the desired deployment time and 4. An ejector mechanism 205 that pushes satellite 203 out of receptacle 200 in a general straight line motion.

[0058] 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.

[0059] 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.

[0060] 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.

[0061] 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.