US4476395A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Tandem-generator design for aircraft
Assignee: Lockheed Martin Corp
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Filing: 1981-10-19
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Granted: 1984-10-09
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Expires: 2001-10-19
Abstract
Abstract The invention is an aircraft power generation system which includes a tandem generator (10) which includes left and right generators (14, 15) arranged within a single housing (12). The left and right generators (14, 15) are driven at the anti-drive end of the tandem generator (10) by a gear arrangement including gears (22), (24) and (26). A phase indexer (36) including a phase adjust nut (38) is arranged in conjunction with driven gear (26) to provide for "vernier" phase-alignment of the generator rotors. In an alternative embodiment, phase-alignment of the generator rotors is accomplished by arranging them in-line to form an in-line tandem generator (10'). In a preferred arrangement, an in-line generator (70) is arranged to be isolated from an aircraft engine via an electromechanical disconnect (108). The disconnect (108) includes a pin (130) activated by a solenoid (110), which upon receipt of a disconnect command or signal, pulls the pin (130) from a hole (131) in ring gear (114) thereby disconnecting the tandem generator (70).
Inventors
- 👤 Michael J. Cronin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 15:50
CPC Classifications
H; H02; H02K; H02K7/00; H02K7/18; H02K7/1807; H02K16/00
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
217 words
An aircraft power generation system comprising in combination: an aircraft engine, said engine having at least one drive shaft; a tandem generator driven by said at least one drive shaft, said tandem generator comprising two permanent magnet AC synchronous generators arranged in a single housing; a mechanical drive mechanism interactively interposed between said at least one drive shaft and said tandem generator; and disconnect means associated with said mechanical drive mechanism for selectively isolating said engine from said tandem generator when said engine is running, said disconnect means comprising: means for speed adjustment between said engine and said tandem generator, said speed adjustment means comprising a planetary differential having interactive sun gear, planet gear, planet carrier and ring gear elements within a planetary differential housing for carrying out said speed adjustment; disconnect means including an electric solenoid mounted to said housing and adapted to actuate pin means for selectively locking or releasing said ring gear element by moving said pin into "lock" and "release" positions; electromechanical switch means for actuating said electric solenoid and further including logic means for activating said switch means responsive to abnormal torque of said mechanical drive system, mechanical overheating of said power generation system and electrothermal overheating of said power generation system; and means for monitoring the position of said ring gear.
Claim 2
Dependent Claim
217 words
An aircraft power generation system comprising in combination: an aircraft engine, said engine having at least one drive shaft; a tandem generator driven by said at least one drive shaft, said tandem generator comprising two permanent magnet AC synchronous generators arranged in a single housing; a mechanical drive mechanism interactively interposed between said at least one drive shaft and said tandem generator; and disconnect means associated with said mechanical drive mechanism for selectively isolating said engine from said tandem generator when said engine is running, said disconnect means comprising: means for speed adjustment between said engine and said tandem generator, said speed adjustment means comprising a planetary differential having interactive sun gear, planet gear, planet carrier and ring gear elements within a planetary differential housing for carrying out said speed adjustment; disconnect means including an electric solenoid mounted to said housing and adapted to actuate pin means for selectively locking or releasing said ring gear element by moving said pin into "lock" and "release" positions; electromechanical switch means for actuating said electric solenoid and further including logic means for activating said switch means responsive to abnormal torque of said mechanical drive system, mechanical overheating of said power generation system and electrothermal overheating of said power generation system; and means for monitoring the position of said ring gear.
Claim 3
Dependent Claim
89 words
An aircraft power generation system as in claim 1 wherein said monitoring means comprises an electro-optical system comprising light emitting means mounted to said housing, reflector means mounted on said ring gear, and photo transistor means mounted on said housing, said light emitting, reflector and photo transistor means being arranged relative to each other such that reflected light from said reflector activates said electric solenoid when said gear housing is in a predetermined position relative to said ring gear whereby said pin engages a hole in said ring gear.
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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) | 1987-10-09 | 1988-04-09 | 1988-10-09 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-10-09 | 1992-04-09 | 1992-10-09 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-10-09 | 1996-04-09 | 1996-10-09 | $7700.00 | Window Closed / Lapsed |