The United States of America as Represented by the Administrator of the

Other

Ian O MacConochie

Martin M Mikulas, Jr

Ashby G Lawson

Charles F Bryan, Jr

Richard R Adams

Jack E Pennington

Rebecca L Kinkead

Charles A Briener

Bordie D Poole, Jr

H Neale Kelly

A non-clogging gutter system comprised of two components: A half cylinder with flanges whose principal axis is orientated parallel to the edge of an inclined roof and is fastened to the vertical plane of the eaves and a gutter located just below the half cylinder, also mounted on the vertical plane of the eaves, but whose outer edge is recessed compared to the half cylinder. In operation, rainwater hydraulically flows down the inclined roof and onto the half cylinder where large debris, relatively unimpeded, is discharged to the ground, while the rainwater and macroscopic particles, by virtue of their higher molecular attraction compared to mass, adhere to the half cylinder finally discharging into the gutter because of the more normal orientation of the gravity vector compared to the half cylinder's surface. The gutter is shaped so that its cross sectional area increases exponentially from bottom-to-top so that, even in light rains, the flow velocity will be relatively high, reducing dwell-time of rainwater in the gutter and thence reducing the amount of settling of macroscopic particles such as shingle grits, seeds, and pollen.

Discriminator rain gutter system

An improved shuttle with variable internal volume is provided by the present invention. Space shuttle orbiter 10 includes a telescoping main propulsion unit 20. This main propulsion unit 20 contains the main rocket engines 22 and fuel tanks 21 and telescopes into the shuttle. A variable cavity 30 is located between this unit 20 and the crew compartment 25. Accordingly, the positioning of the telescoping main propulsion unit 20 determines the volume of the variable cavity 30. Thus, the volume of the variable length of the entire shuttle 10 may be increased or decreased to achieve desired configurations for optimal storage. In one embodiment of the present invention, paylod 35 also telescopes within variable cavity 30.

Shuttle orbiter with telescoping main propulsion unit and payload

A two-stage earth-to-orbit transport includes an orbiter vehicle and a pair of boosters, each having a depolyable oblique wing located along a longitudinal axis of the booster. The wing is deployed in an oblique disposition in supersonic and hypersonic speeds, and disposed at 90.degree. for subsonic speeds encountered during entry. The oblique wing is driven axially and rotated by means of a turret mounted on rails.

Two-stage earth-to-orbit transport with translating oblique wings for

A space spider crane 15 is provided for the movement, placement, and/or assembly of various components on or in the vicinity of a space structure 120. Space spider crane 15 is comprised of a small central body 16 to which manipulators 24 and legs 25 are attached. The legs 25 are equipped with constant pressure gripping end effectors 29 to safely grip space structure 120. Walking by legs 25 or repairing and placing by the manipulators 24 may be controlled either by computer software 140 or a remotely situated human operator 135, who maintains visual contact with the space spider crane via television cameras 22 located at strategic positions on space spider crane 15. One possible walking program consists of a parallel motion walking program that results in small central body 16 alternatively leaning forward and backward relative to end effectors 29.

Space spider crane

A reusable, externally applied thermal protection system is disclosed and functions by utilizing shell tile structure 10 which effectively separates its primary functions as an insulator and load absorber. Tile 10 consists of structurally strong upper and lower metallic shells 12,16 manufactured from materials meeting the thermal and structural requirements incident to tile 10 placement on the spacecraft. A lightweight, high temperature package of insulation 26 is utilized in upper shell 12, while a lightweight, low temperature insulation 28 is utilized in lower shell 16. Assembly of tile 10, which is facilitated by self-locking mechanism 20, may occur subsequent to installation of lower shell 16 on the spacecraft structural skin 30.

Shell tile thermal protection system

The present invention discloses a miniature spectrally selective dosimeter capable of measuring selected bandwidths of radiation exposure on small mobile areas. This is achieved by the combination of photovoltaic detectors, electrochemical integrators (E-cells) and filters in a small compact case which can be easily attached in close proximity to and substantially parallel to the surface being measured. In one embodiment two photovoltaic detectors 13 and 8, two E-cells 15 and 9 and three filters 14 and 16 are packaged in a small case 17 with attaching means consisting of a safety pin 19. In another embodiment, two detectors 31 and 32, one E-cell 33 and three filters 34 and 35 are packaged in a small case 36 with attaching means consisting of a clip 37 to clip over a side piece 38 of an eye glass frame 39. In a further embodiment, the electro-optic elements are packaged in a wristwatch case 51 with attaching means being a watchband 52. The filters in all embodiments allow only selected wavelengths of radiation to be detected by the photovoltaic detectors and then integrated by the E-cells.

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Yorktown, VA, United States of America

Ian O MacConochie