Aeronautics and astronautics – Spacecraft – Reusable or returnable
Reexamination Certificate
1999-01-25
2001-05-15
Swiatek, Robert P. (Department: 3643)
Aeronautics and astronautics
Spacecraft
Reusable or returnable
Reexamination Certificate
active
06231010
ABSTRACT:
BACKGROUND OF THE INVENTION
1. Field of Invention
This invention relates generally to a habitation or laboratory module capable of being used in space flight. In particular, this invention relates to such a module that is lightweight, collapsible and compact prior to space flight, and is capable of being subsequently enlarged to provide an adequately large volume for human habitation, laboratory work, and space flight.
In general, modules for use in space can either be assembled on earth and transported into orbit or can be assembled in orbit with their individual parts being transported from earth. Each method of assembly has advantages and drawbacks.
If a module is to be assembled on earth and thereafter transported into orbit, then the overall weight and size of the module become limiting factors. The module may be launched and transported from earth into orbit in an existing launch vehicle, in which case the item must come within the weight and size parameters of the existing launch vehicle, or the module may be launched and transported from earth into orbit in a specially designed launch vehicle, in which case a substantial amount of time, money, and manpower is required to design, build, and test the new launch vehicle.
Pre-assembled modules, however, do provide certain advantages. For instance, all of the components and system interfaces of a pre-assembled module may be tested, calibrated, and repaired on the earth surface where replacement parts and technical expertise are readily available. In addition, a pre-assembled module can be utilized almost immediately once in orbit without having to wait for assembly or testing time.
If the space module is to be assembled in orbit, then the number of parts and the method of assembly of the module must be carefully considered. Because assembly in orbit typically requires extravehicular activity (space walks), the assembly of parts in orbit is difficult and highly dangerous for astronauts. Minimizing the number of parts to be assembled as well as the number and extent of astronaut space walks necessary for complete assembly is thus highly desirable.
Like pre-assembled modules, orbit-assembled modules also provide advantages. For example, the size and weight of an orbit-assembled module is theoretically unlimited, thereby providing designers with a greater range of design parameters and possibilities. In addition, the greater volumetric capacity that is possible in an orbit-assembled module provides a more comfortable living area to the astronauts and allows for a broader range of experiments to be conducted within the module.
It would thus be advantageous over the prior art to provide a space module that combines the advantages offered by, and limits some of the drawbacks inherent in, both pre-assembled and orbit-assembled modules.
2. Related Art
Space modules are generally known to the prior art. Illustrative of such modules are U.S. Pat. No. 3,169,725 issued to Berglund on Feb. 16, 1965; U.S. Pat. No. 3,144,219 issued to Schnitzer on Aug. 11, 1964; U.S. Pat. No. 4,730,797 issued to Minovitch on Mar. 15, 1988; U.S. Pat. No. 4,792,108 issued to Bull on Dec. 20, 1988; U.S. Pat. No. 4,825,599 issued to Swann, Jr. on May 2, 1989; U.S. Pat. No. 5,350,138 issued to Culbertson et al. on Sep. 27, 1994; U.S. Pat. No. 5,429,851 issued to Sallee on Jul. 4, 1995; and U.S. Pat. No. 5,580,013 issued to Velke on Dec. 3, 1996.
Although most of the listed patents include ingenious structures to be utilized in the outer space environment and some even include expandable components, none of the inventions disclosed in such patents include a structure that is compact during the launch stage and can thereafter be inflated to provide a fully habitable space in the deployed stage.
SUMMARY OF THE INVENTION
Accordingly, the objectives of this invention are to provide, inter alia, a module to be used in the outer space environment that:
combines the advantages offered by, and limits the drawbacks inherent in, pre-assembled and orbit-assembled modules;
is lightweight, collapsible and compact prior to and during its launch into orbit;
is capable of being subsequently enlarged while in orbit to provide an adequately large volume for human habitation, laboratory work, and space flight;
minimizes the number of parts to be assembled in orbit as well as the number and extent of astronaut space walks necessary to complete the assembly;
may be launched in existing launch vehicles;
allows for the majority of its components and system interfaces to be tested and calibrated on earth prior to launch;
can be efficiently and easily converted from its structurally efficient launch configuration to its deployed configuration;
is inflatable from its launch configuration to its deployed configuration, thereby providing an adequately large volume for human habitation and laboratory work, and
utilizes a number of key components for multiple functions thereby providing mass and volume efficiency to the module.
Other objectives of the invention will become apparent from time to time throughout the specification and claims as hereinafter related.
To achieve such objectives, the invention is a module that generally comprises a structural core and an inflatable shell. The inflatable shell is sealingly attached to the structural core. In its launch configuration, the interior and thickness of the inflatable shell are collapsed by vacuum. Also in this configuration, the inflatable shell is efficiently folded around the structural core, and the module is loaded into the payload bay of an existing launch vehicle, such as the Space Shuttle. On location, in orbit for example, the module is deployed, the inflatable shell is inflated, and the module achieves its deployed configuration. In its deployed configuration, the thickness of the inflatable shell automatically expands from its collapsed launch state to its full thickness, and the inflatable shell is inflated around the structural core, defining therein a large volume of habitable space for astronauts. A plurality of removable shelves are arranged interior to the structural core in the launch configuration. The structural core also includes at least one longeron that, in conjunction with the shelves, primarily constitute the rigid, strong, and lightweight load-bearing structure of the module during launch. The removable shelves are detachable from their arrangement in the launch configuration so that, when the module is in its deployed configuration and launch loads no longer exist, the shelves can be rearranged to provide a module interior arrangement suitable for human habitation and work. In the preferred embodiment, to provide efficiency in structural load paths and attachments, the shape of the inflatable shell is a cylinder with semi-toroidal ends in its deployed configuration.
REFERENCES:
patent: 3144219 (1964-08-01), Schnitzer
patent: 3169725 (1965-02-01), Berglund
patent: 3210026 (1965-10-01), Frisch
patent: 3364631 (1968-01-01), Pleasants
patent: 4730797 (1988-03-01), Minovitch
patent: 4792108 (1988-12-01), Bull
patent: 4825599 (1989-05-01), Swann, Jr.
patent: 4964597 (1990-10-01), Hijazi
patent: 5094409 (1992-03-01), King et al.
patent: 5350138 (1994-09-01), Culbertson et al.
patent: 5429851 (1995-07-01), Sallee
patent: 5580013 (1996-12-01), Velke
De La Fuente Horacio M.
Edeen Gregg A.
Gupta Shalini
Hess Linda F.
Kennedy Kriss J.
Barr Hardie R.
Swiatek Robert P.
The United States of America as represented by the Administrator
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