US4243024A
Expired / Lapsed
US
⏱️ 0.0 years remaining
G-Protection system sensing a change in acceleration and tilt angle
Assignee: United States Department of the Navy
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Filing: 1979-04-02
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Granted: 1981-01-06
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Expires: 1999-04-02
Abstract
Abstract A gravity protective system for pilots including a pressurized suit and a control system therefor for regulating the pressure in the suit in response to variations in acceleration along the thoracic axis of the pilot. Signals indicative of acceleration along the vertical axis of the aircraft and cosine function of the tilt angle of the pilot's seat are combined with a derivative function of their product to produce a control signal for regulating the air pressure within the suit. A threshold control limits regulation to acceleration above a predetermined level, and a feedback circuit from the suit ensures rapid response without oscillation.
Inventors
- 👤 Richard J. Crosbie
- 👤 Paul R. Edwards
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 22:22
CPC Classifications
G; G09; G09B; G09B9/00; G09B9/02; G09B9/08; G09B9/10; B; B64; B64D; B64D10/00; Y; Y10; Y10T; Y10T137/00; Y10T137/0753
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
107 words
A G-protection system for the occupant of an aircraft, comprising in combination: a seat for supporting the occupant in the aircraft; sensor means, said means connected to said seat for producing a first signal indicative of the product of acceleration along the vertical axis of an aircraft and the cosine of the angle subtended by said axis with the thoracic axis of the occupant; a source of fluid pressure; control means connected to receive said first signal and said source for producing a regulated fluid pressure; and a G-suit connected to receive said regulated fluid pressure for constraining the occupant against body distension caused by the acceleration.
Claim 2
Dependent Claim
107 words
A G-protection system for the occupant of an aircraft, comprising in combination: a seat for supporting the occupant in the aircraft; sensor means, said means connected to said seat for producing a first signal indicative of the product of acceleration along the vertical axis of an aircraft and the cosine of the angle subtended by said axis with the thoracic axis of the occupant; a source of fluid pressure; control means connected to receive said first signal and said source for producing a regulated fluid pressure; and a G-suit connected to receive said regulated fluid pressure for constraining the occupant against body distension caused by the acceleration.
Claim 3
Dependent Claim
71 words
A G-protection system according to claim 1, wherein said control means further comprises: first differentiator means connected to receive said first signal for producing a second signal indicative of the derivative of said first signal; first summing means connected to receive said first and second signals for producing a third signal indicative of the sum thereof; and valve means connected to receive said third signal for producing said regulated fluid pressure.
Claim 4
Dependent Claim
36 words
A G-protection system according to claim 2 further comprising: feedback means connected to said G-suit and said first summing means for producing fourth signal modifying said first signal in response to the pressure in said G-suit.
Claim 5
Dependent Claim
32 words
A G-protection system according to claim 3 further comprising: threshold means for producing a fifth signal connected to said first summing means for inhibiting said first signal when below a predetermined level.
Claim 6
Dependent Claim
69 words
A G-protection system according to claim 3 wherein said feedback means further comprises: a pressure sensor for sensing the pressure in said G-suit for producing a sixth signal indicative thereof; second differentiator means connected to receive said sixth signal for producing a seventh signal indicative of the derivative of said sixth signal; and second summing means connected to receive said sixth and seventh signals for producing said fourth signal.
Claim 7
Dependent Claim
28 words
A G-protection system according to claim 5 further comprising: first factorial means connected to said first summing means for adjusting the ratio of said second and third signals.
Claim 8
Dependent Claim
28 words
A G-protection system according to claim 6 further comprising: second factorial means connected to said second summing means for adjusting the ratio of said sixth and seventh signals.
Claim 9
Dependent Claim
22 words
A G-protection system according to claim 7 wherein said seat is tiltable about an axis transverse to the fuselage of the aircraft.
Claim 10
Dependent Claim
78 words
A G-protection system according to claim 8 wherein said sensor means further comprises: a tilt angle sensor for generating an eighth signal indicative of the cosine of the angle subtended by the vertical axis of the aircraft and the tilt of said seat; an acceleration sensor for generating a ninth signal indicative of the acceleration along the vertical axis of the aircraft; and multiplier means connected to combine said eighth and ninth signals to produce said first signal.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1984-01-06 | 1984-07-07 | 1985-01-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-01-06 | 1988-07-07 | 1989-01-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-01-06 | 1992-07-07 | 1993-01-06 | $7700.00 | Window Closed / Lapsed |