Patent US4010920A successfully refreshed from Google Patents.
US4010920A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apparatus and method to control forward control surface type aircraft in flight
Assignee: Individual
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Filing: 1974-11-19
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Granted: 1977-03-08
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Expires: 1994-11-19
Abstract
Abstract The control surface-type wing, forward of the center of gravity of the aircraft is placed to be shiftable longitudinally with respect to the center of gravity of the aircraft and also adjustable with respect to a transverse and longitudinal axis of the aircraft to thereby provide for sensitive control of the aircraft flight.
Inventors
- 👤 Hans U. Farner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-31 22:56
CPC Classifications
B; B64; B64C; B64C5/00; B64C5/04; B64C13/00; B64C5/10
Claims Analysis
Total Claims: 22
Claim 1
Independent Claim
195 words
Method to control a heavier-than-air, forward-control wing aircraft, having a first wing (4) to provide part of the lift, a forward lifting-and-control wing (5), and support means (6,8,9,11) supporting said forward lifting and control wing (5) on the aircraft, said method comprising the steps of generating a first lift force vector aft of the center of gravity of the aircraft to provide part of the lift by locating the first wing (4) behind the center of gravity (3) generating a second lift force vector forwardly of the center of gravity (3) of the aircraft to provide the remaining part of the lift by locating the forward lifting and control wing (5) forwardly of the center of gravity (3); and shifting the second lift force vector derived from the forward lifting-and-control wing (5) in the direction of the longitudinal axis of the aircraft and with respect to the center of gravity thereof, said second lift force vector being shifted by moving said entire forward lifting and control wing (5) and said support means (6,8,9,11) therefor with respect to the center of gravity of the aircraft in a direction parallel to the longitudinal axis of the aircraft.
Claim 2
Dependent Claim
195 words
Method to control a heavier-than-air, forward-control wing aircraft, having a first wing (4) to provide part of the lift, a forward lifting-and-control wing (5), and support means (6,8,9,11) supporting said forward lifting and control wing (5) on the aircraft, said method comprising the steps of generating a first lift force vector aft of the center of gravity of the aircraft to provide part of the lift by locating the first wing (4) behind the center of gravity (3) generating a second lift force vector forwardly of the center of gravity (3) of the aircraft to provide the remaining part of the lift by locating the forward lifting and control wing (5) forwardly of the center of gravity (3); and shifting the second lift force vector derived from the forward lifting-and-control wing (5) in the direction of the longitudinal axis of the aircraft and with respect to the center of gravity thereof, said second lift force vector being shifted by moving said entire forward lifting and control wing (5) and said support means (6,8,9,11) therefor with respect to the center of gravity of the aircraft in a direction parallel to the longitudinal axis of the aircraft.
Claim 3
Dependent Claim
27 words
Method according to claim 1 further comprising the step of rotating the second lift force vector about an axis transverse to the longitudinal axis of the aircraft.
Claim 4
Dependent Claim
27 words
Method according to claim 1 further comprising the step of rotating the second lift force vector about an axis parallel to the longitudinal axis of the aircraft.
Claim 5
Dependent Claim
40 words
Method according to claim 1, further comprising the step of moving the second lift force vector derived from the forward wing at a location remote from the longitudinal axis of the aircraft about an axis transverse to said longitudinal axis.
Claim 6
Dependent Claim
155 words
Aircraft control system to control a heavier-than-air, forward-control airfoil aircraft having a first lifting wing (4) to provide lift, a forward lifting-and-control wing (5) located forwardly of the center of gravity (3) to provide a controlled lift vector; said first lifting wing (4) being located behind the center of gravity (3) of the aircraft (1) and providing only part of the lift; a support means (6,8,9,11) supporting said forward lifting-and-control wing (5) on the aircraft (1); and means (7, 7'; 10, 10'; 12, 13) movably securing said support means (6,8,9,11) supporting said forward lifting and control wing (5) in the aircraft for movement of said entire forward lifting and control wing (5) and the support means (6,8,9,11) therefor in a direction parallel to the longitudinal axis of the aircraft to thereby move the entire forward lifting-and-control wing (5) and its support means (6,8,9,11) longitudinally with respect to the center of gravity (3) of the aircraft.
Claim 7
Dependent Claim
155 words
Aircraft control system to control a heavier-than-air, forward-control airfoil aircraft having a first lifting wing (4) to provide lift, a forward lifting-and-control wing (5) located forwardly of the center of gravity (3) to provide a controlled lift vector; said first lifting wing (4) being located behind the center of gravity (3) of the aircraft (1) and providing only part of the lift; a support means (6,8,9,11) supporting said forward lifting-and-control wing (5) on the aircraft (1); and means (7, 7'; 10, 10'; 12, 13) movably securing said support means (6,8,9,11) supporting said forward lifting and control wing (5) in the aircraft for movement of said entire forward lifting and control wing (5) and the support means (6,8,9,11) therefor in a direction parallel to the longitudinal axis of the aircraft to thereby move the entire forward lifting-and-control wing (5) and its support means (6,8,9,11) longitudinally with respect to the center of gravity (3) of the aircraft.
Claim 8
Dependent Claim
75 words
System according to claim 5 wherein said support means comprises an elongated, shaft-like member (11); and said movable securing means comprises shaft support means for said shaft-like member (11), said shaft support means including a leading guide element (12) and a rear guide element (13), the rear guide element including a tubular member (15), guide tracks (14) located in the tubular member (15), the elongated shaft-like member (11) being longitudinally movable in the guide tracks.
Claim 9
Dependent Claim
78 words
System according to claim 6, including a control element (22) and interconnecting means (20, 18, 19, 21, 24) connecting the control element to longitudinally move said shaft-like member (11); a tilt control means (25); and connecting means (26, 26') connecting said tilt control means (25) with the said tubular member (15), to transfer movement from said tilt control means to rotate said tubular member (15) and hence said forward lifting-and-control wing about the longitudinal axis of the aircraft.
Claim 10
Dependent Claim
60 words
System according to claim 6, wherein the guide tracks (14) are inclined with respect to the shaft-like member (11) supporting the forward lifting and control wing (5) to provide for relative rotation of the forward lifting-and-control wing (5) with respect to an axis transverse to the longitudinal axis of the aircraft conjointly with longitudinal movement of said forward lifting-and-control wing.
Claim 11
Dependent Claim
23 words
System according to claim 6, wherein the tubular member (15) is rotatable about an axis parallel to the longitudinal axis of the aircraft.
Claim 12
Dependent Claim
57 words
System according to claim 5, wherein the forward lifting-and-control wing comprises wing portions (5a, 5b), one located on either side of said support means, said wing portions being relatively movable with respect to the aircraft and with respect to each other; and control means (25) and interconnecting means (26) connecting said control means to said wing portions.
Claim 13
Dependent Claim
38 words
System according to claim 5, wherein the forward lifting-and-control wing (5c) is formed with movable flaps (50a, 50b); and control means (25) and interconnecting means (26) connecting the control means to the movable flaps to move the flaps.
Claim 14
Dependent Claim
50 words
System according to claim 5 further comprising control means (22, 25) which are pilot-controllable connected to the support means (6, 8, 9, 11) to move the forward lifting-and-control wing (5), selectively and as controlled, longitudinally with respect to the aircraft and rotatably with respect to the first lifting wing (4).
Claim 15
Dependent Claim
28 words
System according to claim 12, wherein at least a portion of the forward lifting-and-control wing is movable about an axis transverse to the longitudinal axis of the aircraft.
Claim 16
Dependent Claim
28 words
System according to claim 12, wherein at least a portion of the forward lifting-and-control wing is movable about an axis parallel to the longitudinal axis of the aircraft.
Claim 17
Dependent Claim
35 words
System according to claim 5 wherein the securing means for said support means secure said support means, and hence said forward lifting-and-control wing for rotational movement with respect to the longitudinal axis of the aircraft.
Claim 18
Dependent Claim
83 words
System according to claim 15, including a control element (22) and connecting means (20, 18, 19, 21, 24) connecting the control element to move said support means (11) and hence said forward lifting-and-control wing (5) longitudinally of the aircraft; and control means (25) and interconnecting means (26, 26'), connecting said control means (25) with said lifting-and-control wing (5) and transferring movement from said control means to rotate said lifting-and-control wing (5) also about an axis parallel to the longitudinal axis of the aircraft.
Claim 19
Dependent Claim
79 words
System according to claim 5, including a control element (22) and connecting means (20, 18, 19, 21, 24) connecting the control element to move said support means (11) and hence said forward lifting-and-control wing (5) longitudinally of the aircraft; and control means (25) and interconnecting means (26) connecting said control means (25) with said lifting-and-control wing (5) and transferring movement from said control means (25) to rotate said lifting-and-control wing (5) also about the longitudinal axis of the aircraft.
Claim 20
Dependent Claim
102 words
System according to claim 5, including a control element (22) and connecting means (20, 18, 19, 21, 24) connecting the control element to move said entire support means (11) and hence said forward lifting-and-control wing (5) longitudinally of the aircraft; and control means (25) and interconnecting means (26) connecting said control means (25) with said support means (11) and transferring movement from said control means to at least a portion (5, 5a, 5b; 50a, 50b) of the lifting-and-control wing to rotate at least said portion of the lifting-and-control wing about an axis transverse with respect to the longitudinal axis of the aircraft.
Claim 21
Dependent Claim
29 words
System according to claim 18, wherein said interconnecting means moves substantially the entire forward lifting-and-control wing about the axis transverse with respect to the longitudinal axis of the aircraft.
Claim 22
Dependent Claim
29 words
System according to claim 5, wherein said support means are movable to change the level of the forward lifting-and-control wing (5) with respect to the axis of the aircraft.
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) | 1980-03-07 | 1980-09-06 | 1981-03-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-03-07 | 1984-09-06 | 1985-03-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-03-07 | 1988-09-06 | 1989-03-08 | $7700.00 | Window Closed / Lapsed |