Patent US4807129A successfully refreshed from Google Patents.
US4807129A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Helicopter rotor and engine control
Assignee: Rolls Royce PLC
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Filing: 1987-01-28
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Granted: 1989-02-21
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Expires: 2007-01-28
Abstract
Abstract A Helicopter rotor and engine control apparatus in which the computers used to control the engines and the rotors are linked to exchange performance data and act together to improve the aircraft performance.
Inventors
- 👤 Malcolm Perks
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 20:25
CPC Classifications
B; B64; B64C; B64C13/00; B64C13/24; B64C13/38; B64C13/50; B64C13/503; B64C27/00; B64C27/54; B64C27/58; B64C27/68
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
154 words
A control system for a helicopter having a main rotor, a torque reaction device such as a tail rotor, an engine and a rotor gearbox, the control system comprising a set of pilot controls, an Active Control Computer and Engine Control Computer, a main rotor actuator and a tail rotor actuator, in which: the Active Control Computer is linked to receive data from the pilot's controls: the main rotor actuator and tail rotor actuator are linked to exchange data with the Active Control Computer; the main rotor actuator and tail rotor actuator act on their respective rotors to control the pitch of the rotor blades; the engine is linked to exchange data with the Engine Control Computer and linked to drive the rotor gearbox the rotor gearbox is linked to drive both the main rotor and the tail rotor; and the Active Control Computer is linked to exchange data with the Engine Control Computer.
Claim 2
Dependent Claim
154 words
A control system for a helicopter having a main rotor, a torque reaction device such as a tail rotor, an engine and a rotor gearbox, the control system comprising a set of pilot controls, an Active Control Computer and Engine Control Computer, a main rotor actuator and a tail rotor actuator, in which: the Active Control Computer is linked to receive data from the pilot's controls: the main rotor actuator and tail rotor actuator are linked to exchange data with the Active Control Computer; the main rotor actuator and tail rotor actuator act on their respective rotors to control the pitch of the rotor blades; the engine is linked to exchange data with the Engine Control Computer and linked to drive the rotor gearbox the rotor gearbox is linked to drive both the main rotor and the tail rotor; and the Active Control Computer is linked to exchange data with the Engine Control Computer.
Claim 3
Dependent Claim
58 words
A control system for a helicopter according to claim 1 in which the Active Control Computer informs the Engine Control Computer what torque is required from said engine, and said Engine Control Computer informs said Active Control Computer of the torque being produced by said engine, the rate of change of said torque and the maximum torque available.
Claim 4
Dependent Claim
37 words
A control system for a helicopter according to claim 2 in which the Active Control Computer initiates control of the main rotor and the tail rotor to move said rotors only in proportion to the available torque.
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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) | 1992-02-21 | 1992-08-22 | 1993-02-21 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-02-21 | 1996-08-22 | 1997-02-21 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-02-21 | 2000-08-22 | 2001-02-21 | $7700.00 | Window Closed / Lapsed |