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US3750985A
Expired / Lapsed
US
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Side force control devices
Assignee: Northrop Grumman Corp
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Filing: 1971-02-12
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Granted: 1973-08-07
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Expires: 1991-02-12
Abstract
Abstract An airplane embodying devices functioning to provide an essentially true side force acting to alter the horizontal flight path of an airplane without sideslip and to avoid roll movements normally associated with maneuvers of this type.
Inventors
- 👤 W Wheldon
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 16:48
CPC Classifications
G; G05; G05D; G05D1/00; G05D1/08; G05D1/0808; G05D1/0816; G05D1/085; G05D1/04; G05D1/042; G05D1/044
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
172 words
In an airplane having a pair of variable pitch propellers, a rudder, a pitch changing actuator for each of said propellers and a rudder actuator, the combination comprising: a. a pilot''s control member movable in either of two substantially opposite direction from a neutral position, b. on-off switch means accessible to the pilot, c. side force control means coupled to said pilot''s control member through said on-off switch means, and d. means connecting the output of said control means to said pitch changing actuators and to said rudder actuator, e. said side force control means responsive to movements of said pilot''s control member functioning to change the pitch of at least one of said propellers to produce yaw in one direction and to move said rudder in the other direction to cancel the yaw moment of said propellers, whereby aerodynamic forces are present providing a true side force acting at the center of gravity of said airplane insuring the latter will change its azimuthal flight path without any substantial rolling or sideslip.
Claim 2
Dependent Claim
172 words
In an airplane having a pair of variable pitch propellers, a rudder, a pitch changing actuator for each of said propellers and a rudder actuator, the combination comprising: a. a pilot''s control member movable in either of two substantially opposite direction from a neutral position, b. on-off switch means accessible to the pilot, c. side force control means coupled to said pilot''s control member through said on-off switch means, and d. means connecting the output of said control means to said pitch changing actuators and to said rudder actuator, e. said side force control means responsive to movements of said pilot''s control member functioning to change the pitch of at least one of said propellers to produce yaw in one direction and to move said rudder in the other direction to cancel the yaw moment of said propellers, whereby aerodynamic forces are present providing a true side force acting at the center of gravity of said airplane insuring the latter will change its azimuthal flight path without any substantial rolling or sideslip.
Claim 3
Dependent Claim
144 words
In an airplane which includes a rudder and opposite wing mounted variable-pitch propellers, apparatus operable to perform a flat turn comprising: a. means interconnecting the control means for saId rudder with the pitch control means for said propellers, b. a manually-controlled switch operable to actuate said interconnecting means from an inoperable to an operable condition, c. a pilot''s turn controller connected to said interconnecting means, and d. side force control means in said interconnecting means responsive to said turn controller when said interconnecting means is operable to differentially change the pitch of said propellers in one yaw-producing direction and to deflect said rudder in the opposite yaw-producing direction, e. whereby the lateral side force on said airplane from said rudder deflection combined with an initial yawing motion started by said propeller pitch differential operation can produce an essentially wings-level flat turn of said airplane.
Claim 4
Dependent Claim
144 words
In an airplane which includes a rudder and opposite wing mounted variable-pitch propellers, apparatus operable to perform a flat turn comprising: a. means interconnecting the control means for saId rudder with the pitch control means for said propellers, b. a manually-controlled switch operable to actuate said interconnecting means from an inoperable to an operable condition, c. a pilot''s turn controller connected to said interconnecting means, and d. side force control means in said interconnecting means responsive to said turn controller when said interconnecting means is operable to differentially change the pitch of said propellers in one yaw-producing direction and to deflect said rudder in the opposite yaw-producing direction, e. whereby the lateral side force on said airplane from said rudder deflection combined with an initial yawing motion started by said propeller pitch differential operation can produce an essentially wings-level flat turn of said airplane.
References Cited (Backward Citations)
US2597020A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-08-06 | 1977-02-05 | 1977-08-07 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-08-06 | 1981-02-05 | 1981-08-07 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-08-06 | 1985-02-05 | 1985-08-07 | $7700.00 | Window Closed / Lapsed |