Claims
- 1. An aircraft, comprising:a flying wing extending laterally to two ends from a center point, substantially without a fuselage or an empennage, wherein the wing is swept, having a substantially constant chord; a power module configured to provide power for the aircraft; and a support structure including a plurality of supports, wherein the supports form a tetrahedron having comers in supportive contact with the wing at points laterally intermediate between the center point and each end, and wherein the tetrahedron also has a corner in supportive contact with the wing's center point; wherein the wing is configured with an airfoil having a negative pitching moment, and with reflex at a trailing edge of the wing; and wherein the wing is configured with a slat.
- 2. The aircraft power system of claim 1, and further comprising a second power module configured to provide power for the aircraft, wherein the first and second power modules are located laterally along the wing at approximately the location where the tetrahedron corners are in supportive contact with the wing at points laterally intermediate between the center point and each end.
- 3. An aircraft, comprising:a flying wing extending laterally to two ends from a center point, substantially without a fuselage or an empennage, wherein the wing is swept, having a substantially constant chord; a power module configured to provide power for the aircraft; and a support structure including a plurality of supports, wherein the supports form a tetrahedron having corners in supportive contact with the wing at points laterally intermediate between the center point and each end, and wherein the tetrahedron also has a corner in supportive contact with the wing's center point.
- 4. The aircraft of claim 3, and further comprising a second power module configured to provide power for the aircraft, wherein the first and second power modules are located laterally along the wing at approximately the location where the tetrahedron corners are in supportive contact with the wing at points laterally intermediate between the center point and each end.
- 5. The aircraft of claim 3, wherein the body is characterized by an aspect ratio of at least 20; and wherein when body is not configured with additional pitch-angle stabilization devices.
Parent Case Info
The present application claims priority from two U.S. provisional patent applications, Serial No. 60/194,137, filed Apr. 3, 2000, and Ser. No. 60/241,713, filed Oct. 18, 2000, which are both incorporated herein by reference for all purposes.
US Referenced Citations (22)
Foreign Referenced Citations (5)
Number |
Date |
Country |
582542 |
Jan 1933 |
DE |
648122 |
Jul 1937 |
DE |
28 03 041 |
Aug 1979 |
DE |
375515 |
Jun 1932 |
GB |
WO 9934467 |
Jul 1999 |
WO |
Non-Patent Literature Citations (2)
Entry |
Williams, Arthur L., “A New and Less Complex Alternative to the Handley Page Slat”, Journal of Aircraft vol. 23, No. 3, pp. 200-206 (Mar. 1986). |
Brown, “Eternal Airplane—A Solar Electric Wing Takes Off”, Popular Science, Apr., 1994, pp. 70-75 & 100. |
Provisional Applications (2)
|
Number |
Date |
Country |
|
60/194137 |
Apr 2000 |
US |
|
60/241713 |
Oct 2000 |
US |