The present invention relates generally to testing apparatuses and reaction enclosures. More specifically, the present invention relates to reactor microplates adapted for microgravity environments.
Reactor microplates allow researchers to have greater control over when to begin a microgravity project at the appropriate time when the pre-determined orbit and conditions have been reached. In general, a microplate reactor provides a structure where the reactants or research materials for zero-gravity research are kept separate. The microplate reactor further provides a mechanism which allows the reactants or research materials to be mixed within the microplate reactor, so the experiment or project can be carried out. The biggest obstacle most of the currently available devices face is providing a structure which allows various projects/experiments to be carried out while meeting the requirements of the National Aeronautics and Space Administration (NASA). Now, various devices and structures have been used to perform microgravity projects and/or experiments. Most provide a structure which meet the various mission requirements, such as weight limitations, space limitations, etc. However, few provide a structure which allows various microgravity projects and/or experiments to be carried out without risking the various reactants/research materials to accidentally mix while meeting NASA requirements. Thus, an objective of the present invention is to provide a reactor microplate which meets NASA requirements and provides a structure which allows for various experiments/projects to be carried out whenever the astronaut is ready to perform the experiments/projects.
The present invention is a reactor microplate. The reactor microplate provides researchers control over when to begin the microgravity project/experiment once the reactor microplate reaches orbit. The fundamental concept behind the microplate reactor is a separation of materials intended for zero-gravity research, generally fluids or gels, between two chambers. The materials are allowed to mix when a crewmember rotates, by use of a standard tool, the valve cylinder. This opens the passage between the reaction chambers. The valve cylinder can take multiple forms and may be duplicated on either side of a common reaction chamber to provide activation/deactivation functionality. In order to meet NASA safety requirements, all valve cylinders are designed with double O-ring seals between the chambers and the external environment to provide double-redundant containment from release of potentially hazardous substances. Activation and deactivation chambers are functionally identical; though deactivation chambers are included, for example, in experiments where customers may want to keep biological samples that have been inoculated into the main chamber from the activation/deactivation chamber. In such a case, the deactivation chamber would contain preservatives which keep samples in stasis until their retrieval. The dimensions of the reactor microplate unit preferably are 127 by 85 by 20 millimeters in order to conform to the ANSI Standard for Microplate Footprint Dimensions (ANSI SLAS 1-2004/formerly ANSI/SBS 1-2004). The number of chambers in the reactor plate is variable depending on customer requirements. The dimensions of all wells are configurable to customer requirements. Reactions can be observed or measured through the film/containment windows. These windows are preferably made of Lexan, but can be configurable depending on the user's demands. In some cases, where ultraviolet (UV) wavelengths are needed to activate a given experiment, or to read the reaction in a plate reader using UV wavelengths, quartz windows may be used. Samples may either be viewed by microscope on orbit, read in a microplate reader on orbit, or returned to Earth for direct observation on removal from containment chambers. The body of the unit is preferably made of Delrin Plastic.
All illustrations of the drawings are for the purpose of describing selected versions of the present invention and are not intended to limit the scope of the present invention.
The present invention generally relates to a research apparatus intended for micro-gravity use. More specifically, the present invention is a reactor microplate that allows for safe mixing of solutions in orbit. Generally, the present invention is used to mix fluids without running a risk of potential exposure for an astronaut/researcher; for this, the present invention meets the safety requirements set forth by the National Aeronautics and Space Administration (NASA) through multiple redundant containing systems.
Referring to
To allow astronauts/researchers to view or take measurements of the reaction occurring within the chamber-mixing assembly 6, the present invention includes observation windows. Specifically, the first retaining mechanism 7 and the second retaining mechanism 8 each further comprises a first disk-receiving hole 10, a first transparent disk 11, a first annular seal 12, and a first cover hole 13. The first disk-receiving hole 10 is positioned concentric with the reaction chamber 9. Additionally, the first disk-receiving hole 10 normally traverses into the planar housing 1 from the top surface 2 to allow the first transparent disk 11 to be mounted to the planar housing 1 flush with the top surface 2. The first annular seal 12 is a flexible ring that prevents solution leaking at the interface between the first transparent disk 11 and the planar housing 1. For this, the first annular seal 12 is concentrically positioned within the first disk-receiving hole 10. The first transparent disk 11 is transparent disk that allows the astronaut/researcher to view inside the reaction chamber 9. The first transparent disk 11 is concentrically mounted within the first disk-receiving hole 10 with the first annular seal 12 being pressed into an O-ring housing in between the planar housing 1 and the first transparent disk 11. Specifically, the first annular seal 12 and the first transparent disk 11 are mounted to the planar housing 1 by the first cover. The first cover plate 4 is positioned adjacent to the first transparent disk 11, opposite the planar housing 1; thus, the first annular seal 12 and the first transparent disk 11 are pressed in between the planar housing 1 and the first cover. The first cover plate 4 is attached to the planar housing 1 through a plurality of first fasteners; wherein each of the plurality of first fasteners may be a screw, a bolt, a screw and threaded bushing combination, and any other standard fastener. The plurality of first fasteners is distributed about the first cover plate 4 with each of the plurality of first fasteners traversing through the first cover plate 4 and into the planar housing 1. The first cover hole 13 exposes a portion of the first transparent disk 11 to allow the astronaut/researcher to see inside the reaction chamber 9. The first cover hole 13 is concentrically positioned with the first transparent disk 11 and normally traverses through the first cover. Additionally, the first cover hole 13 is sized partially smaller than the first transparent disk 11 to ensure that the outer perimeter of the first transparent disk 11 is pressed against the first cover plate 4.
In one embodiment, the present invention provides the astronaut/researcher an additional window for the first retaining mechanism 7 and the second retaining mechanism 8, integrated into a bottom surface 3 of the planar housing 1. In this embodiment, the reaction chamber 9 of the first retaining mechanism 7 and the reaction chamber 9 of the second retaining mechanism 8 each further traverse through the planar housing 1 from the top surface 2 to the bottom surface 3. Additionally, the present invention further comprises a second cover plate 5; and, the first retaining mechanism 7 and the second retaining mechanism 8 each further comprise a second disk-receiving hole 14, a second transparent disk 15, a second annular seal 16, and a second cover hole 17. In general, the top surface 2 and the bottom surface 3 are symmetrical about a top plane of the present invention. The description below applies to both the first retaining mechanism 7 and the second retaining mechanism 8. The second disk-receiving hole 14 is positioned concentric with the reaction chamber 9. Additionally, the second disk-receiving hole 14 normally traverses into the planar housing 1 from the bottom surface 3 to allow the second transparent disk 15 to be mounted to the planar housing 1 flush with the bottom surface 3. The second annular seal 16 is a flexible ring that prevents solution leaking at the interface between the second transparent disk 15 and the planar housing 1. For this, the second annular seal 16 is concentrically positioned within the second disk-receiving hole 14. The second transparent disk 15 is a transparent disk that allows the astronaut/researcher to view inside the reaction chamber 9. The second transparent disk 15 is concentrically mounted within the second disk-receiving hole 14 with the second annular seal 16 being pressed in between the planar housing 1 and the second transparent disk 15. Specifically, the second annular seal 16 and the second transparent disk 15 are mounted to the planar housing 1 by the second cover. The second cover plate 5 is mounted parallel and adjacent to the bottom surface 3 of the planar housing 1. Thus, the second annular seal 16 and the second transparent disk 15 are pressed in between the planar housing 1 and second first cover. The second cover plate 5 is attached to the planar housing 1 through a plurality of second fasteners; wherein each of the plurality of second fasteners may be a screw, a bolt, a screw and threaded bushing combination, and any other standard fastener. The plurality of second fasteners is distributed about the second cover plate 5 with each of the plurality of second fasteners traversing through the second cover plate 5 and into the planar housing 1. The second cover hole 17 exposes a portion of the second transparent disk 15 to allow the astronaut/researcher to see inside the reaction chamber 9. The second cover hole 17 is concentrically positioned with the second transparent disk 15 and normally traverses through the first cover. Additionally, the second cover hole 17 is sized partially smaller than the second transparent disk 15 to ensure the that the outer perimeter of the second transparent disk 15 is pressed against the second cover plate 5.
Referring to
To load solutions, gases, or gels into the present invention, the chamber-mixing assembly 6 further comprises a first loading port 22, a first plug 23, a second loading post, and a second plug 25. The first loading port 22 allows for materials to be loaded into the first retaining mechanism 7. Referring to
The second loading port 24 allows for materials to be loaded into the second retaining mechanism 8. Referring to
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The retaining plate secures the cylindrical shaft 28 within the cylinder-receiving hole 27. Thus, the retaining plate is positioned perpendicular to the cylindrical shaft 28 and is laterally connected to the planar housing 1. The access hole exposes one end of the cylindrical shaft 28 such that a tool may be used to physically engage and rotate the cylindrical shaft 28. The access hole is concentrically positioned with the cylindrical shaft 28 and normally traverses through the retaining plate. The engagement feature allows an external tool to engage and rotate the cylindrical shaft 28. The engagement feature is positioned within the access hole and mechanically integrated into the cylindrical shaft 28. It is preferred that the engagement feature is a slot to allow a flat-head screw driver to engage and rotate the cylindrical shaft 28.
In one embodiment, the valve control assembly 26 further comprises a semi-annular track and a track slider that limit the radial range of the cylindrical shaft 28. The semi-annular track is positioned concentric with the access hole. Additionally, the semi-annular track is integrated in between the cylindrical shaft 28 and the retaining plate. The track slider is terminally integrated into the cylindrical shaft 28 and is mechanically engaged with the semi-annular track. This provides a radial rotating range to the cylindrical shaft 28, thus providing an easy means of determining the location of the connecting groove.
Referring to
In one embodiment, the at least one valve control assembly 26 comprises a first control assembly 30 and a second control assembly 31. The first control assembly 30 and the second control assembly 31 divide the plurality of mixing assemblies in two and allow the astronaut/researcher to initiate different experiments at different times. For this, the first control assembly 30 and the second control assembly 31 are positioned opposite to each other along the planar housing 1. Specifically, the cylinder-receiving hole 27 of the first control assembly 30 extends along a first set of mixing assemblies 20 from the plurality of mixing assemblies. Accordingly, the connecting groove from each of the first set of mixing assemblies 20 laterally traverse into the cylindrical shaft 28 of the first control assembly 30. The cylinder-receiving hole 27 of the second control assembly 31 extends along a second set of mixing assemblies 21 from the plurality of mixing assemblies. Accordingly, the connecting groove from each of the second set of mixing assemblies 21 laterally traverse into the cylindrical shaft 28 of the second control assembly 31.
Although the invention has been explained in relation to its preferred embodiment, it is to be understood that many other possible modifications and variations can be made without departing from the spirit and scope of the invention as hereinafter claimed.
The current application claims a priority to the U.S. Provisional Patent application Ser. No. 62/636,543 filed on Feb. 28, 2018.
Number | Date | Country | |
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62636543 | Feb 2018 | US |