Aircraft

Abstract

An aircraft is provided that is convertible in flight between a rotary wing configuration and a fixed wing configuration. In its fixed wing configuration the aircraft resembles a Blended Wing Body (BWB) having a swept wing angle . Conversions from the fixed wing configuration to the rotary wing configuration, and vice versa, are accomplished by flipping an outboard portion of one wing through 180 to reorient the leading edge of the outboard portion by an angle of 2 to establish a reverse sweep. In its rotary configuration, the entire aircraft is rotated.

Claims

1. An aircraft, wherein the aircraft is convertible in-flight between a rotary wing configuration R and a fixed wing configuration F, the aircraft comprising: a base member, wherein the base member defines a symmetrical plane; a pair of outboard wing portions extending from the base member on opposite sides of the symmetrical plane, wherein each outboard wing portion has a leading edge and the leading edge is oriented at an angle relative to the symmetrical plane in the fixed wing configuration F; an actuator mounted on the base member at a distance d from the symmetrical plane for flipping an outboard wing portion of the aircraft about a reconfiguration axis perpendicular to the symmetrical plane to convert the aircraft from F to R and vice versa, wherein the outboard wing portion is at a distance greater than d from the symmetrical plane; a pair of thrusters mounted on the aircraft, wherein the thrusters are each mounted on the aircraft on opposite sides of the symmetrical plane at a distance s from the symmetrical plane, wherein s>d and wherein the thrusters propel the entire aircraft in fixed wing flight when the aircraft is in F, and rotates the entire aircraft for rotary wing flight when the aircraft is in R wherein the pair of thrusters include a first thruster mounted on the aircraft at a distance s.sub.1 from the symmetrical plane, and a second thruster mounted on the aircraft at a distance s.sub.2 from the symmetrical plane and wherein s.sub.1 is not equal to s.sub.2; and a controller mounted on the base member and connected to the actuator for converting the aircraft between F and R, and connected to each thruster for controlling forces exerted on the base member of the aircraft.

2. An aircraft as recited in claim 1 wherein a wing span for F of the aircraft is in a range of 5 ft. to 150 ft.

3. An aircraft as recited in claim 1 wherein the aircraft has a sweep angle in F, and is in a range between 0 and 60.

4. An aircraft as recited in claim 1 wherein the outboard wing portion is flipped 180 to change an orientation of its leading edge by an angle of 2.

5. An aircraft as recited in claim 1 wherein the thrusters are embedded in the aircraft.

6. An aircraft as recited in claim 1 further comprising ailerons on each outboard wing portion for remotely controlling the aircraft in rotary wing flight maneuvers with combined aileron movements for collective and cyclic controls when the aircraft is in R, and in fixed wing flight maneuvers with combined aileron movements for roll, yaw and pitch when the aircraft is in F.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) The novel features of this invention, as well as the invention itself, both as to its structure and its operation, will be best understood from the accompanying drawings, taken in conjunction with the accompanying description, in which similar reference characters refer to similar parts, and in which:

(2) FIG. 1 is a schematic presentation of a typical flight envelope for an aircraft of the present invention;

(3) FIG. 2 is a perspective view of an aircraft in accordance with the present invention in a fixed wing configuration F;

(4) FIG. 3A is a top plan view of an aircraft of the present invention with the aircraft in its fixed wing configuration F; and

(5) FIG. 3B is a top plan view of the aircraft shown in FIG. 3A, with the aircraft in its rotary wing configuration R.

DESCRIPTION OF THE PREFERRED EMBODIMENTS

(6) Referring initially to FIG. 1 an aircraft in accordance with the present invention is shown, and depending on its configuration is generally designated 10 or 10. More particularly, the aircraft 10 is shown flying on a typical flight path 12 that requires both rotary wing and fixed wing flight capabilities. As shown in FIG. 1, and for disclosure purposes only, the aircraft when designated 10 will be generally considered as being in a fixed wing configuration (this configuration is hereinafter sometimes referred to as F). On the other hand, when designated 10 it will be generally considered that the aircraft 10 is in the rotary wing configuration (this configuration is hereinafter sometimes referred to as R). As also indicated in FIG. 1, rotary wing flight for the aircraft 10 will require the entire aircraft 10 to be rotated, in R, at an angular velocity, . For F, however, =0. In either configuration, aircraft 10 (R), as well as aircraft 10 (F), will both have a flight velocity vector V that is indicative of forward flight along the flight path 12. With this in mind, unless rotary wing flight is being specifically considered, reference may sometimes be made to only aircraft 10.

(7) In FIG. 2, the aircraft 10 is presented in F (i.e. fixed wing configuration) and it is shown to essentially resemble a Blended Wing Body (BWB). As such, the aircraft 10 has a base member 14, with an outboard wing portion 16 attached thereto. It is to be appreciated that in F, the aircraft 10 effectively defines a symmetrical plane 18. In general, the symmetrical plane 18 is defined by the forward flight path 12 of an in-flight aircraft 10, and a rotation axis 20 about which the aircraft 10 will rotate at the angular velocity when the aircraft 10 is in R (i.e. rotary wing configuration). Thus, the symmetrical plane 18 is used for the purpose of structurally defining the aircraft 10 and its variants, F and R.

(8) Still referring to FIG. 2 it will be seen that the aircraft 10 includes a left thruster 22 and a right thruster 24. Both of which will be generally positioned at a distance s from the symmetrical plane 18, but on opposite sides of the symmetrical plane 18. Although both the left thruster 22 and the right thruster 24 are shown externally above the BWB of aircraft 10, it will be appreciated that the thrusters 22 and 24 may be embedded within the BWB of the aircraft 10.

(9) FIG. 2 also shows that an actuator 26 is mounted on the aircraft 10 at a distance d from the symmetrical plane 18. Preferably, the actuator 26 is mounted internally within the BWB of the aircraft 10. In any event, the functional purpose of the actuator 26 is to flip the outboard wing portion 16, together with the right thruster 24, around a reconfiguration axis 28 through an angle of approximately 180. As the outboard wing portion 16 is being flipped, there may also be an actuator on the opposite wing to change its angle of attack. As shown, the reconfiguration axis 28 is perpendicular to the symmetrical plane 18. The consequence of this is to reconfigure the aircraft 10 from F to R. This reconfiguration will be best appreciated with reference to FIGS. 3A and 3B.

(10) In FIG. 3A, with aircraft 10 in F, it will be seen that the outboard wing portion 16 for the BWB of the aircraft 10 has a leading edge 30 that is inclined at an angle relative to the reconfiguration axis 28. On the other hand, in FIG. 3B, after the outboard wing portion 16 has been flipped and the aircraft 10 is in R, the leading edge 30 in F becomes a trailing edge 30 in R. This relationship would indicate that the outboard wing portion 16 may be optimally designed as a symmetrical or semi-symmetrical airfoil. There is, however, another important consideration that results from the F to R conversion. The consideration here is that for F of aircraft 10, the thrust T.sub.L of left thruster 22, and the thrust T.sub.R of right thruster 24 are in the same direction. This orientation is provided to propel the aircraft 10 in F at a flight velocity V along the flight path 12. In R for aircraft 10, however, the thrust T.sub.L of left thruster 22, and the thrust T.sub.R of right thruster 24 are in opposite directions. The consequence here is that for aircraft 10 in R, T.sub.L and T.sub.R generate a force couple on the aircraft 10 that will cause it to rotate with an angular velocity about the rotation axis 20.

(11) For control of the aircraft 10/10 in F and R, it is envisioned that the flight controls will include, in combination, a left aileron 32 and a right aileron 34. Additionally, the combination may also include a left flap 36 and a right flap 38. With consideration for the aircraft 10 in F, the aileron combination 32/34 can be conventionally controlled with opposed aileron movements for roll and yaw control, while also being used together in concert for pitch control. On the other hand, with the aircraft 10 in R, the ailerons of the combination 32/34 can be separately moved cyclically during each rotation of the aircraft 10 to aerodynamically tilt the L/T vector of the aircraft 10 for directional flight. If used, the flap combination 36/38 can be employed to emphasize and influence the actions of the aileron combination 32/34 described above. As another control feature, the flap combination 36/38 can also be used to help reduce during and R to F conversion.

(12) As envisioned for the present invention, a typical flight envelope for the aircraft 10/10 will entail take offs and landings with the aircraft 10 in R. This, however, does not preclude take offs and landings with the aircraft 10 in F. In either case, long distance legs of a flight will most likely be performed in F. Further, it is envisioned that during a mission the aircraft 10 may periodically loiter at a selected location(s) in R. Consequently, conversions of the aircraft 10/10 from R to F, and F to R, will be necessary for any mission.

(13) In general, R to F and F to R conversions will necessarily be accomplished at altitude, with the expectation of some control loss and some altitude loss during a conversion. Depending on the size of the aircraft 10/10, altitude loss can be minimized. Moreover, during a conversion, the momentum MV of the aircraft will have a stabilizing influence and will provide a reference for control transition between rotary wing and fixed wing flight. In each case, entry into a conversion should be made with minimum power on each of the thrusters 22, 24, and as well as V should be reduced to just above a stall condition. Once an F/R or R/F conversion has been completed, power on the thrusters 22, 24 can be applied as needed to restore flight control.

(14) While the particular Aircraft as herein shown and disclosed in detail is fully capable of obtaining the objects and providing the advantages herein before stated, it is to be understood that it is merely illustrative of the presently preferred embodiments of the invention and that no limitations are intended to the details of construction or design herein shown other than as described in the appended claims.