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SHOULDER HARNESS AND LAP

BELT RESTRAINT SYSTEM

NASA Case No. ARC-10519

Australia, Canada, France,
Great Britain, Italy, Japan
Sweden, West Germany

Address inquiries to:
Ames Research Center,
Attn: Patent Counsel
Mail Code: 200-11A
Moffett Field, CA 94035
U.S.A.

(Corresponding to U.S. Patent No. 3,887,233)

The present invention provides a shoulder harness which is held by inertia reels so that the user is not unduly restrained and can freely move about, yet the reels will instantly lock when the user is subjected to deceleration forces. The shoulder straps preferably pass through openings in the seat itself so that they are substantially at shoulder height and there is little chance of the straps slipping off of the shoulders. The combined restraint of the present invention provides for slippage between the lap belt and the shoulder straps so that it readily adapts itself to users of different sizes.

GRAVITY GRADIENT ATTITUDE

CONTROL SYSTEM
NASA Case No. GSC-10555 Address inquiries to:

Goddard Space Flight Center Canada, Japan

Attn: Patent Counsel
Mail Code: 204
Greenbelt, MD 20771

U.S.A.
(Corresponding to U.S. Patent No. 3,567,155)

A system for controlling and stabilizing the attitude of an artificial earth satellite includes a gravity gradient member mounted in a gimbal arrangement to have two degrees of freedom. The angular deviation of the gravity gradient member and the satellite relative to the local vertical and the spacecraft angle command input signal selectively drive a plurality of inertial momentum wheels, one for each of the three spacecraft axes, provided to dampen the gravity gradient member librations. The gravity gradient member is controlled so that the equalibrium position of the longitudinal axis thereof is maintained in alignment with the local vertical in response to signals indicative of the rate of change of movement thereof with respect to the remainder of the satellite and a signal indicative of the angular deviation of the satellite position from the angle command.

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TORQUER
ASSEMBLY

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AIRFOIL SHAPE FOR FLIGHT AT

SUBSONIC SPEEDS

NASA Case No. LAR-10585-1

Canada, France, Germany, Japan,
Italy, Israel, Sweden, Australia,
Great Britain, Netherlands

Address inquiries to:
Langley Research Center
Attn: Patent Counsel
Mail Code: 313
Langley Station
Hampton, VA 23665
U.S.A.

(Corresponding U.S. Patent-Application Pending)

This invention relates to an airfoil for an aircraft and more particularly to an airfoil with a design Mach number in the range . 7 to 1.0 and having an upper surface designed to delay shock wave induced boundary layer separation until high subsonic Mach numbers well above the critical Mach number are reached. The airfoil has an upper surface shaped to control flow accelerations and pressure distribution over the upper surface and prevents separation of the boundary layer due to shock wave formulation at high subsonic speeds well above the critical Mach number. A highly cambered trailing edge section improves overall airfoil lifting efficiency.

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WATER PURIFICATION MEMBRANES
AND METHOD OF PREPARATION

NASA Case No. ARC-10643

Australia, Canada, France,
Germany, Great Britain,
Italy, Japan, Israel,
Netherlands

Address inquiries to:
Ames Research Center
Attn: Patent Counsel
Mail Code: 200-11A
Moffett Field, CA 94035
U.S.A.

(Corresponding to U.S. Patent No. 3,847,652)

Reverse osmosis membrane technology has grown dramatically in recent years for the production of fresh water and is particularly important in the purification and reuse of water in space missions. The present invention contemplates the fabrication of membranes of allyl amine as thin films in the presence of a plasma discharge. The membranes are superior in that they do not have to be stored in pure H2O, demonstrate salt rejection rates of 95% or more, do not compress under use, are formed without pinholes, and in any desired configuration, and, possess high adhesion on a variety of substrates.

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SUPPRESSION OF FLUTTER

NASA Case No. LAR-10682-1

Great Britain, Japan, France,
Canada, West Germany, Italy,
Sweden

Address inquiries to:
Langley Research Center
Attn: Patent Counsel
Mail Code: 313
Langley Station
Hampton, VA 23665
U.S.A.

(Corresponding to U. S. Patent No. 3,734,432)

An active aerodynamic control system is described for controlling flutter over a large range of oscillatory frequencies unaffected by mass, stiffness, elastic axis, or center of gravity location of the system, mode of vibration, or subsonic Mach number. It consists of one or more pairs of leading edge and trailing edge, hinged or deformable control surfaces, each pair operated in concert by a stability augmentation system. Torsion and bending motions or deflections of the fluttering member are sensed and converted by the stability augmentation system into leading and trailing edge control surface deflections which produce lift forces and pitching moments to suppress flutter.

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