US3833191A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Powered aircraft ejection seat
Assignee: Individual
•
Filing: 1971-11-22
•
Granted: 1974-09-03
•
Expires: 1991-11-22
Abstract
Abstract A device for enhancing the survival prospects of a pilot evacuating an aircraft over enemy-held territory by providing him with up to fifty miles of powered flight. A turbinepowered rotor blade assembly is attached to a conventional ejection seat, and is under the control of the pilot. By directing a portion of the seat''s jet blast against a movable rudder member, the pilot is able to guide the unit in any desired direction. A feature of the concept resides in the provision of contrarotating helicopter rotor blades which may be telescoped to facilitate stowage and reduce the overall size of the unit. In the vent of malfunction the pilot may descend by conventional parachute.
Inventors
- 👤 R Morton
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 21:39
CPC Classifications
B; B64; B64D; B64D25/00; B64D25/08; B64D25/10
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
211 words
An aircraft occupant survival vehicle, including an ejection seat assembly whereby an aircraft occupant located in said seat is forcibly separated from the aircraft and transported through space in a controlled fashion to a safe landing area, comprising: a. a catapultable aircraft occupant seat including a bottom portion, said seat being adapted for mounting on an aircraft fuselage structure for separation therefrom upon command; b. means for separating said seat from the aircraft fuselage; c. a plurality of internally hollow, airfoil contoured, rotor blades movable from a stored position to an operational position; said rotor blades including a blade propelling gas exit nozzle located adjacent the tip portions thereof and in communication with said hollow interior; d. a rotor hub movable from a stored position to an operational position mounted on the back portion of the seat and supporting said rotor blades; said rotor hub being ported to conduct a pressurized gas to the hollow interior of each blade; e. a gas pressure source located in the seat for driving said rotor blades and hub; and f. a gas duct located in the seat for conducting pressurized gas from the gas source to the gas exit nozzles adjacent the blade tips through the ported hub and hollow interior of the blades.
Claim 2
Dependent Claim
211 words
An aircraft occupant survival vehicle, including an ejection seat assembly whereby an aircraft occupant located in said seat is forcibly separated from the aircraft and transported through space in a controlled fashion to a safe landing area, comprising: a. a catapultable aircraft occupant seat including a bottom portion, said seat being adapted for mounting on an aircraft fuselage structure for separation therefrom upon command; b. means for separating said seat from the aircraft fuselage; c. a plurality of internally hollow, airfoil contoured, rotor blades movable from a stored position to an operational position; said rotor blades including a blade propelling gas exit nozzle located adjacent the tip portions thereof and in communication with said hollow interior; d. a rotor hub movable from a stored position to an operational position mounted on the back portion of the seat and supporting said rotor blades; said rotor hub being ported to conduct a pressurized gas to the hollow interior of each blade; e. a gas pressure source located in the seat for driving said rotor blades and hub; and f. a gas duct located in the seat for conducting pressurized gas from the gas source to the gas exit nozzles adjacent the blade tips through the ported hub and hollow interior of the blades.
Claim 3
Dependent Claim
22 words
The device of claim 1 including an occupant controlled pressure release valve mechanism for venting off excess gas from said pressure source.
Claim 4
Dependent Claim
40 words
The device of claim 1 including gas pressure control means provided on the rotor assembly to permit control of gas flow to one of said contrarotating hub blade assemblies relative to the gas flow to the other of said assemblies.
Claim 5
Dependent Claim
32 words
The device of claim 1 including a control arm connected for movement into a position adjacent one side of the operator with movement of the rotor hub assembly to the operational position.
Claim 6
Dependent Claim
19 words
The device of claim 1 wherein the blade and hub assembly comprises two sets of rotors arranged for contrarotation.
Claim 7
Dependent Claim
49 words
The device of claim 2 wherein the gas pressure source also provides gas discharge through a rearwardly directed discharge nozzle to impart forward motion to said vehicle: and the directional movement of the vehicle can be varied by an occupant adjustable control connected to such vehicle propelling discharge nozzle.
Claim 8
Dependent Claim
35 words
The device of claim 1 wherein each rotor blade has an inboard and an outboard portion telescopically arranged so as to allow blade elongation along its axis to thereby increase the effective blade surface area.
Claim 9
Dependent Claim
29 words
The device of claim 1 wherein the rotor assembly includes resilient means normally urging the blades from the stored position to the operating position with blade ends oppositely extending.
Claim 10
Dependent Claim
19 words
The device of claim 8 wherein latch means are provided to retain the blades in their oppositely extending position.
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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) | 1977-09-02 | 1978-03-04 | 1978-09-03 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1981-09-02 | 1982-03-04 | 1982-09-03 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1985-09-02 | 1986-03-04 | 1986-09-03 | $7700.00 | Window Closed / Lapsed |