초록 ▼

An aircraft is disclosed. The aircraft has a canard control surface 25 and an aft control surface 10. The canard control surface comprises an integral aerofoil which in its entirety pivots about a first axis of rotation 28. The canard control surface has a center of lift p which is rearward of the f

An aircraft is disclosed. The aircraft has a canard control surface 25 and an aft control surface 10. The canard control surface comprises an integral aerofoil which in its entirety pivots about a first axis of rotation 28. The canard control surface has a center of lift p which is rearward of the first axis. The aft control surface is rearward of the canard control surface and comprises an integral aerofoil which in its entirety pivots about a second axis of rotation 13. The aft control surface having a center of lift P which is rearward of the first axis. The canard control surface and the aft control surface act in unison to produce a directional change in the aircraft.

대표청구항 ▼

1. An aircraft, comprising: a canard control surface and an aft control surface; the canard control surface comprising an integral aerofoil which in its entirety pivots about a first axis of rotation, the canard control surface having a centre of lift which is rearward of the first axis; the af

1. An aircraft, comprising: a canard control surface and an aft control surface; the canard control surface comprising an integral aerofoil which in its entirety pivots about a first axis of rotation, the canard control surface having a centre of lift which is rearward of the first axis; the aft control surface being rearward of the canard control surface and comprising an integral aerofoil which in its entirety pivots about a second axis of rotation, the aft control surface having a center of lift which is rearward of the first axis; the canard control surface and the aft control surface acting in unison to produce a directional change in the aircraft; the canard control surface and the aft control surface being both generally horizontally oriented and acting in unison by rotating in different directions; the aft control surface comprising the primary lifting wings of the aircraft, the wings each being independently rotatable about the second axis. 2. The aircraft of claim 1, wherein: the second axis comprises an unbroken dual-wing shaft forming a common pivot axis for each wing. 3. The aircraft of claim 1, wherein: the primary lifting wings are interchangeable with similar wings or wings of a different size or shape. 4. The aircraft of claim 1, wherein: one or each wing may serve as a fuel cell laden with fuel. 5. The aircraft of claim 1, wherein: at least one control surface further comprises a bias mechanism which permits a limited degree of rotational movement away from a central rest position but which imposes a restorative force toward the central rest position. 6. The aircraft of claim 2, wherein: at least one control surface further comprises a bias mechanism which permits a limited degree of rotational movement away from a central rest position but which imposes a restorative force toward the central rest position. 7. The aircraft of claim 3, wherein: at least one control surface further comprises a bias mechanism which permits a limited degree of rotational movement away from a central rest position but which imposes a restorative force toward the central rest position. 8. The aircraft of claim 4, wherein: at least one control surface further comprises a bias mechanism which permits a limited degree of rotational movement away from a central rest position but which imposes a restorative force toward the central rest position.