US3870253A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft vectored flight control means
Assignee: McDonnell Douglas Corp
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Filing: 1973-07-02
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Granted: 1975-03-11
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Expires: 1993-07-02
Abstract
Abstract An aircraft of either stable or unstable configuration having all movable wing tip surfaces for rapid increases in lift and subsequent aircraft longitudinal pitch control results from positioning of the wing tip surfaces for positive pitching moments which are then trimmed by trailing edge elevators to produce beneficial positive trim lift forces and having vertical control surfaces to obtain direct side forces for superior control of the aircraft. The aircraft herein has the unique capability of fuselage pointing in the horizontal and vertical axes without change in the flight path as would be the case with conventional aircraft.
Inventors
- 👤 William S Leidy
- 👤 Donald M Scheller
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 21:33
CPC Classifications
B; B64; B64C; B64C3/00; B64C3/38; Y; Y02; Y02T; Y02T50/00; Y02T50/10
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
6 words
In an aircraft, the combination of:
Claim 2
Dependent Claim
6 words
In an aircraft, the combination of:
Claim 3
Dependent Claim
27 words
an elongated fuselage providing a primary lifting surface having the aerodynamic center and center of gravity offset from each other on the longitudinal axis of the fuselage;
Claim 4
Dependent Claim
27 words
an elongated fuselage providing a primary lifting surface having the aerodynamic center and center of gravity offset from each other on the longitudinal axis of the fuselage;
Claim 5
Dependent Claim
256 words
In an aircraft, the combination of: 1. an elongated fuselage providing a primary lifting surface having the aerodynamic center and center of gravity offset from each other on the longitudinal axis of the fuselage; 2. all movable wing surfaces pivotally mounted on the outboard sides of said fuselage and having the aerodynamic center offset from said aerodynamic center and center of gravity in the direction of the longitudinal axis of the aircraft, a. said primary surface and wing surfaces having the respective aerodynamic centers thereof acting to impose pitching moments in opposition to each other about the center of gravity; 3. longitudinal elevator control surface means operable on said fuselage aft of the center of gravity, a. said elevator control surface means providing longitudinal flight control forces to trim and control pitching moments on the aircraft imposed by said primary surface and wing surfaces; 4. and control means connected to said wing surfaces and elevator control surface means for selective operation for a. controlling the pointing of the longitudinal axis of the aircraft about the center of gravity independently of a predetermined longitudinal flight path and load factor by deflection of said elevator control surface and counter deflection of said wing surfaces, b. and controlling a change in the altitude of the aircraft while flying a predetermined flight path by vertical translation of the aircraft to a different elevation generally parallel to said predetermined flight path by concurrent deflection of said wing and elevator surfaces to positive and negative angles of incidence in a selective mode.
Claim 6
Dependent Claim
256 words
In an aircraft, the combination of: 1. an elongated fuselage providing a primary lifting surface having the aerodynamic center and center of gravity offset from each other on the longitudinal axis of the fuselage; 2. all movable wing surfaces pivotally mounted on the outboard sides of said fuselage and having the aerodynamic center offset from said aerodynamic center and center of gravity in the direction of the longitudinal axis of the aircraft, a. said primary surface and wing surfaces having the respective aerodynamic centers thereof acting to impose pitching moments in opposition to each other about the center of gravity; 3. longitudinal elevator control surface means operable on said fuselage aft of the center of gravity, a. said elevator control surface means providing longitudinal flight control forces to trim and control pitching moments on the aircraft imposed by said primary surface and wing surfaces; 4. and control means connected to said wing surfaces and elevator control surface means for selective operation for a. controlling the pointing of the longitudinal axis of the aircraft about the center of gravity independently of a predetermined longitudinal flight path and load factor by deflection of said elevator control surface and counter deflection of said wing surfaces, b. and controlling a change in the altitude of the aircraft while flying a predetermined flight path by vertical translation of the aircraft to a different elevation generally parallel to said predetermined flight path by concurrent deflection of said wing and elevator surfaces to positive and negative angles of incidence in a selective mode.
Claim 7
Dependent Claim
46 words
The improvement in the aircraft of claim 1 wherein said fuselage center of gravity is forward of said aerodynamic center for said primary surface to render said aircraft essentially stable, and said aerodynamic center for said wing surfaces is forward of said fuselage center of gravity.
Claim 8
Dependent Claim
65 words
all movable wing surfaces pivotally mounted on the outboard sides of said fuselage and having the aerodynamic center offset from said aerodynamic center and center of gravity in the direction of the longitudinal axis of the aircraft, a. said primary surface and wing surfaces having the respective aerodynamic centers thereof acting to impose pitching moments in opposition to each other about the center of gravity;
Claim 9
Dependent Claim
65 words
all movable wing surfaces pivotally mounted on the outboard sides of said fuselage and having the aerodynamic center offset from said aerodynamic center and center of gravity in the direction of the longitudinal axis of the aircraft, a. said primary surface and wing surfaces having the respective aerodynamic centers thereof acting to impose pitching moments in opposition to each other about the center of gravity;
Claim 10
Dependent Claim
43 words
longitudinal elevator control surface means operable on said fuselage aft of the center of gravity, a. said elevator control surface means providing longitudinal flight control forces to trim and control pitching moments on the aircraft imposed by said primary surface and wing surfaces;
Claim 11
Dependent Claim
43 words
longitudinal elevator control surface means operable on said fuselage aft of the center of gravity, a. said elevator control surface means providing longitudinal flight control forces to trim and control pitching moments on the aircraft imposed by said primary surface and wing surfaces;
Claim 12
Dependent Claim
46 words
The improvement in the aircraft of claim 1 wherein said fuselage center of gravity is rearwardly of said aerodynamic center for said primary surface to render said aircraft essentially unstable, and said aerodynamic center for said wing surfaces is rearwardly Of said fuselage center of gravity.
Claim 13
Dependent Claim
50 words
The aircraft of claim 1 wherein said pitching moments imposed by said primary and wing surfaces are unequal to impose a resultant nose-down pitching moment on the aircraft, and said longitudinal elevator control surface means and wing surfaces are operated by said control means to counteract said nose-down pitching moment.
Claim 14
Dependent Claim
111 words
and control means connected to said wing surfaces and elevator control surface means for selective operation for a. controlling the pointing of the longitudinal axis of the aircraft about the center of gravity independently of a predetermined longitudinal flight path and load factor by deflection of said elevator control surface and counter deflection of said wing surfaces, b. and controlling a change in the altitude of the aircraft while flying a predetermined flight path by vertical translation of the aircraft to a different elevation generally parallel to said predetermined flight path by concurrent deflection of said wing and elevator surfaces to positive and negative angles of incidence in a selective mode.
Claim 15
Dependent Claim
111 words
and control means connected to said wing surfaces and elevator control surface means for selective operation for a. controlling the pointing of the longitudinal axis of the aircraft about the center of gravity independently of a predetermined longitudinal flight path and load factor by deflection of said elevator control surface and counter deflection of said wing surfaces, b. and controlling a change in the altitude of the aircraft while flying a predetermined flight path by vertical translation of the aircraft to a different elevation generally parallel to said predetermined flight path by concurrent deflection of said wing and elevator surfaces to positive and negative angles of incidence in a selective mode.
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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) | 1978-03-10 | 1978-09-09 | 1979-03-11 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1982-03-10 | 1982-09-09 | 1983-03-11 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1986-03-10 | 1986-09-09 | 1987-03-11 | $7700.00 | Window Closed / Lapsed |