Patent US3671965A successfully refreshed from Google Patents.
US3671965A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Rapid deployment corner reflector
Assignee: United States Department of the Navy
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Filing: 1970-04-03
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Granted: 1972-06-20
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Expires: 1990-04-03
Abstract
Abstract A readily deployable, lightweight radar reflector having a large radar signature, the invention is compactly stowable aboard a carrier vehicle, immediately assuming an erect configuration on ejection from an airborne or surface vehicle. The present reflector is particularly intended to be ejected from aircraft traveling at high speeds, the erection of the reflecting surface being provided by the internal bias of pre-stressed hoops surrounding and supporting the reflecting surface.
Inventors
- 👤 David W Rabenhorst
- 👤 Kenneth E Darnell
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-28 11:59
CPC Classifications
H; H01; H01Q; H01Q15/00; H01Q15/14; H01Q15/18; H01Q15/20
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
337 words
In a system for ejecting a rapidly deployable, self-erecting reflective device from an aircraft, a supporting framework of solid, resilient hoops intersecting at right angles at each of two locations on the hoops to form joints, the hoops being pre-stressed to resist deformation thereof; wave reflective means mounted within the spatial boundaries defined by the framework, said means comprising a regular octahedral corner reflector having six corners, four of said corners being attached to the framework at points on one of said hoops, which points are removed from the joints by oneeighth of a circumference of the hoops, the remaining two corners being attached to the framework at points on the second hoops; connecting means joining the corners of the wave reflective means to the points on the supporting framework; restraining means formed in the aircraft for retaining the framework and attached wave reflective means in a reduced volume and under stress, the framework being deformed along an axis through the joints and the reflective means being collapsed under the influence of said restraining means, the restraining means comprising a cylindrical tube composed of two semi-cylindrical portions, a resilient band connecting corresponding aft ends of said portions and urging said portions apart, and a sleeve-like cap connecting corresponding forward ends of said portions; and means for ejecting the framework and attached wave reflective means from the vehicle, whereby said framework and attached wave reflective means will be released from the restraining means, the framework instantaneously reassuming its original configuration, thereby erecting said wave reflective means to an operative configuration, the ejection means comprising a cylindrical recess in the aircraft for receiving the cylindrical tube, which recess has a shoulder near its aft end, and pressure-producing means in the forward end of said recess for ejecting the tube from the recess, the shoulder displacing the cap from the tube as said tube moves from the recess to allow the tube portions to be biased apart by said resilient band, thereby releasing the framework and attached wave reflective means.
Claim 2
Dependent Claim
337 words
In a system for ejecting a rapidly deployable, self-erecting reflective device from an aircraft, a supporting framework of solid, resilient hoops intersecting at right angles at each of two locations on the hoops to form joints, the hoops being pre-stressed to resist deformation thereof; wave reflective means mounted within the spatial boundaries defined by the framework, said means comprising a regular octahedral corner reflector having six corners, four of said corners being attached to the framework at points on one of said hoops, which points are removed from the joints by oneeighth of a circumference of the hoops, the remaining two corners being attached to the framework at points on the second hoops; connecting means joining the corners of the wave reflective means to the points on the supporting framework; restraining means formed in the aircraft for retaining the framework and attached wave reflective means in a reduced volume and under stress, the framework being deformed along an axis through the joints and the reflective means being collapsed under the influence of said restraining means, the restraining means comprising a cylindrical tube composed of two semi-cylindrical portions, a resilient band connecting corresponding aft ends of said portions and urging said portions apart, and a sleeve-like cap connecting corresponding forward ends of said portions; and means for ejecting the framework and attached wave reflective means from the vehicle, whereby said framework and attached wave reflective means will be released from the restraining means, the framework instantaneously reassuming its original configuration, thereby erecting said wave reflective means to an operative configuration, the ejection means comprising a cylindrical recess in the aircraft for receiving the cylindrical tube, which recess has a shoulder near its aft end, and pressure-producing means in the forward end of said recess for ejecting the tube from the recess, the shoulder displacing the cap from the tube as said tube moves from the recess to allow the tube portions to be biased apart by said resilient band, thereby releasing the framework and attached wave reflective means.
References Cited (Backward Citations)
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US2463517A
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GB812376A
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US3568191A
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US3217325A
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1975-06-20 | 1975-12-20 | 1976-06-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-06-20 | 1979-12-20 | 1980-06-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-06-20 | 1983-12-20 | 1984-06-20 | $7700.00 | Window Closed / Lapsed |