US5082207A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Active flexible wing aircraft control system
Assignee: Boeing North American Inc
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Filing: 1990-07-16
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Granted: 1992-01-21
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Expires: 2010-07-16
Abstract
Abstract A system for controlling an aircraft by aeroelastic deflections of the wings which is effective beyond control surface reversal is disclosed. The system includes flexible wings, leading and trailing edge control surfaces attached to the wings, sensors to measure selected aircraft flight parameters, an information processing system to receive and process pilot command signals and signals from the sensors, and control mechanisms in the wing that respond to processed signals from the information processing system. The control mechanisms selectively position the control surfaces to produce loads such that the wings are deflected in a desired manner for aircraft control. The system can be used for aircraft control (including maintaining stability), optimum cruise, and maneuver performance. Augmentation can be added for maneuver load control, gust load alleviation, and flutter suppression.
Inventors
- 👤 Jan Tulinius
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-29 17:52
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; B; B64; B64C; B64C13/00; B64C13/02; B64C13/16; B64C3/00; B64C3/38; B64C3/44; Y; Y02; Y02T; Y02T50/00; Y02T50/10; Y02T50/40
Claims Analysis
Total Claims: 42
Claim 1
Independent Claim
125 words
A system for control of an aircraft in one or more of its axes comprising: flexible wings; flight control surfaces mounted on said flexible wings; aircraft sensors for providing signals indicative of the overall motion of the aircraft; processing means responsive to said signals from said aircraft sensors for determining control surface movements which will aeroelastically induce desired deflections in said wings to effect the desired control of the aircraft and selectively generating control signals to bring about said control surface movements; and control means receiving said control signals from said processing means for moving said control surfaces in accordance with said control signals in a manner to aeroelastically induce said desired deflections of said flexible wings to produce said desired control of the aircraft.
Claim 2
Independent Claim
125 words
A system for control of an aircraft in one or more of its axes comprising: flexible wings; flight control surfaces mounted on said flexible wings; aircraft sensors for providing signals indicative of the overall motion of the aircraft; processing means responsive to said signals from said aircraft sensors for determining control surface movements which will aeroelastically induce desired deflections in said wings to effect the desired control of the aircraft and selectively generating control signals to bring about said control surface movements; and control means receiving said control signals from said processing means for moving said control surfaces in accordance with said control signals in a manner to aeroelastically induce said desired deflections of said flexible wings to produce said desired control of the aircraft.
Claim 3
Dependent Claim
15 words
The system of claim 1, wherein the system provides for roll control of the aircraft.
Claim 4
Dependent Claim
15 words
The system of claim 1, wherein the system provides for pitch control of the aircraft.
Claim 5
Dependent Claim
16 words
The system of claim 2, wherein the system also provides for pitch control of the aircraft.
Claim 6
Dependent Claim
16 words
The system of claim 4, wherein the system also provides for yaw control of the aircraft.
Claim 7
Dependent Claim
23 words
The system of claim 2, wherein the roll control is provided in the manner set forth under conditions of and beyond aileron reversal.
Claim 8
Dependent Claim
23 words
The system of claim 4, wherein the roll control is provided in the manner set forth under conditions of and beyond aileron reversal.
Claim 9
Dependent Claim
23 words
The system of claim 5, wherein the roll control is provided in the manner set forth under conditions of and beyond aileron reversal.
Claim 10
Dependent Claim
34 words
The system of claim 1, wherein said processing means generates said control signals for movement of said control surfaces which will bring about the desired control by said aeroelastically induced deflections in said wings.
Claim 11
Dependent Claim
15 words
The system of claim 1, wherein the aircraft is without a horizontal tail or canard.
Claim 12
Dependent Claim
15 words
The system of claim 2, wherein the aircraft is without a horizontal tail or canard.
Claim 13
Dependent Claim
15 words
The system of claim 3, wherein the aircraft is without a horizontal tail or canard.
Claim 14
Dependent Claim
15 words
The system of claim 4, wherein the aircraft is without a horizontal tail or canard.
Claim 15
Dependent Claim
15 words
The system of claim 5, wherein the aircraft is without a horizontal tail or canard.
Claim 16
Dependent Claim
47 words
The system of claim 1, wherein the leading and trailing edges of said wings have at least one of said flight control surfaces mounted thereon, and said flight control surfaces are mounted to allow for their deflection above and below the wing to which they are mounted.
Claim 17
Dependent Claim
40 words
The system of claim 1, wherein said control signals are such that said control means moves said control surfaces to cause said wings to aeroelastically deflect such that said desired control of the aircraft is effected with substantially minimum drag.
Claim 18
Dependent Claim
40 words
The system of claim 2, wherein said control signals are such that said control means moves said control surfaces to cause said wings to aeroelastically deflect such that said desired control of the aircraft is effected with substantially minimum drag.
Claim 19
Dependent Claim
40 words
The system of claim 3, wherein said control signals are such that said control means moves said control surfaces to cause said wings to aeroelastically deflect such that said desired control of the aircraft is effected with substantially minimum drag.
Claim 20
Dependent Claim
40 words
The system of claim 4, wherein said control signals are such that said control means moves said control surfaces to cause said wings to aeroelastically deflect such that said desired control of the aircraft is effected with substantially minimum drag.
Claim 21
Dependent Claim
40 words
The system of claim 5, wherein said control signals are such that said control means moves said control surfaces to cause said wings to aeroelastically deflect such that said desired control of the aircraft is effected with substantially minimum drag.
Claim 22
Dependent Claim
40 words
The system of claim 6, wherein said control signals are such that said control means moves said control surfaces to cause said wings to aeroelastically deflect such that said desired control of the aircraft is effected with substantially minimum drag.
Claim 23
Dependent Claim
40 words
The system of claim 9, wherein said control signals are such that said control means moves said control surfaces to cause said wings to aeroelastically deflect such that said desired control of the aircraft is effected with substantially minimum drag.
Claim 24
Dependent Claim
75 words
The system of claim 1, wherein said processing means also selectively generates performance signals relative to control surface movements to aeroelastically induce desired wing defections to effect a configuration for said wings substantially optimized for the flight conditions; and wherein said control means is also for moving said control surfaces in a manner responsive to said performance signals to cause said wings to be aeroelastically deflected into a configuration substantially optimized for the flight conditions.
Claim 25
Dependent Claim
29 words
The system of claim 1, also including command means generating signals for said aircraft control, and wherein said processing means is responsive to said signals from said command means.
Claim 26
Dependent Claim
16 words
The system of claim 16, wherein said aircraft sensors sense mach number, aircraft attitude, and altitude.
Claim 27
Dependent Claim
33 words
The system of claim 16, also including wing sensors for providing signals indicative of motion of said wings, and wherein said processing means is also responsive to said signals from said wing sensors.
Claim 28
Dependent Claim
63 words
The system of claim 1, also including wing sensors for providing signals indicative of motion of said wings, and wherein said processing means is also responsive to said signals from said wings sensors, and wherein said processing means compensates for damaged or inoperative control surfaces which fail to aeroelastically induce deflection in said wings to bring about the desired control of the aircraft.
Claim 29
Dependent Claim
13 words
The system of claim 10, wherein the aircraft is without a vertical tail.
Claim 30
Dependent Claim
17 words
The system of claim 5, wherein the aircraft is without a vertical tail, horizontal tail, or canard.
Claim 31
Dependent Claim
63 words
The system of claim 1, wherein said processing means also selectively generates control signals relative to control surface movements to aeroelastically induce desired wing deflections to maintain stability of the aircraft, and wherein said control means also moves said control surfaces in accordance with said control signals in a manner to aeroelastically induce said desired wing deflections to maintain stability of the aircraft.
Claim 32
Dependent Claim
63 words
The system of claim 10, wherein said processing means also selectively generates control signals relative to control surface movements to aeroelastically induce desired wing deflections to maintain stability of the aircraft, and wherein said control means also moves said control surfaces in accordance with said control signals in a manner to aeroelastically induce said desired wing deflections to maintain stability of the aircraft.
Claim 33
Dependent Claim
115 words
The system of claim 16, wherein said aircraft has a fuselage, said fuselage is mounted to said wings, and also including fuselage flight control surfaces and a second control means, said fuselage flight control surfaces mounted to the aircraft fuselage, said processing means also generates second control signals, said second control means being responsive to said second control signals for moving said fuselage flight control surfaces, said fuselage flight control surfaces working in combination with said flight control surfaces on said wing to effect said desired control of the aircraft, said second control signals being such that in combination with said first control signals, said control of the aircraft is effected with substantially minimum drag.
Claim 34
Independent Claim
118 words
A method for control of an aircraft having flexible wings and flight control surfaces mounted on the wings, in one or more of the axes of the aircraft, comprising: sensing overall motion of the aircraft; determining desired control of the aircraft; determining control surface movements in response to said desired control of the aircraft and said sensed overall motion of the aircraft which will aeroelastically induce desired wing deflections to produce said desired control; generating control signals to bring about said control surface movements; and moving the control surfaces on said wings in response to said control signals in a manner to aeroelastically induce said desired deflections in said wings to produce said desired control of the aircraft.
Claim 35
Independent Claim
118 words
A method for control of an aircraft having flexible wings and flight control surfaces mounted on the wings, in one or more of the axes of the aircraft, comprising: sensing overall motion of the aircraft; determining desired control of the aircraft; determining control surface movements in response to said desired control of the aircraft and said sensed overall motion of the aircraft which will aeroelastically induce desired wing deflections to produce said desired control; generating control signals to bring about said control surface movements; and moving the control surfaces on said wings in response to said control signals in a manner to aeroelastically induce said desired deflections in said wings to produce said desired control of the aircraft.
Claim 36
Dependent Claim
17 words
The method of claim 33, wherein said system is for roll and pitch control of the aircraft.
Claim 37
Dependent Claim
31 words
The method of claim 33, also including generating command signals for said control of the aircraft, and wherein said moving the control surfaces is also in response to said command signals.
Claim 38
Dependent Claim
30 words
The method of claim 33, also including generating command signals for control of the aircraft, and wherein said moving the control surfaces is also in response to said command signals.
Claim 39
Dependent Claim
32 words
The method of claim 33, wherein said moving the control surfaces is in a manner to aeroelastically deflect said wings to effect the desired control of the aircraft with substantially minimum drag.
Claim 40
Dependent Claim
32 words
The method of claim 34, wherein said moving the control surfaces is in a manner to aeroelastically deflect said wings to effect the desired control of the aircraft with substantially minimum drag.
Claim 41
Dependent Claim
32 words
The method of claim 35, wherein said moving the control surfaces is in a manner to aeroelastically deflect said wings to effect the desired control of the aircraft with substantially minimum drag.
Claim 42
Dependent Claim
23 words
The method of claim 34, wherein said roll control is provided in the manner set forth under conditions of and beyond aileron reversal.
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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) | 1995-01-20 | 1995-07-22 | 1996-01-21 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1999-01-20 | 1999-07-22 | 2000-01-21 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2003-01-20 | 2003-07-22 | 2004-01-21 | $7700.00 | Window Closed / Lapsed |