CA2505013A1 - Flight device with a lift-generating fuselage - Google Patents
Flight device with a lift-generating fuselage Download PDFInfo
- Publication number
- CA2505013A1 CA2505013A1 CA002505013A CA2505013A CA2505013A1 CA 2505013 A1 CA2505013 A1 CA 2505013A1 CA 002505013 A CA002505013 A CA 002505013A CA 2505013 A CA2505013 A CA 2505013A CA 2505013 A1 CA2505013 A1 CA 2505013A1
- Authority
- CA
- Canada
- Prior art keywords
- flight device
- wings
- fuselage
- span
- flight
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 241000251468 Actinopterygii Species 0.000 claims abstract 2
- 239000012530 fluid Substances 0.000 claims 8
- 239000003381 stabilizer Substances 0.000 claims 5
- 230000008719 thickening Effects 0.000 claims 2
- 230000007704 transition Effects 0.000 claims 2
- 230000009194 climbing Effects 0.000 claims 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/0009—Aerodynamic aspects
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0045—Fuselages characterised by special shapes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/10—All-wing aircraft
- B64C2039/105—All-wing aircraft of blended wing body type
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
- Circuits Of Receivers In General (AREA)
- Preparation Of Compounds By Using Micro-Organisms (AREA)
- Optical Record Carriers And Manufacture Thereof (AREA)
Abstract
The invention relates to an aircraft comprising a lift-producing fuselage (1 ) whose largest span (11) lies in the middle third (14) of the total length an d whose horizontal projection progressively diminishes in the front third (13) and in the rear third (15). The aircraft also comprises two wings (2), where by the surface of the projection of both wings represents, in a horizontal plan e, less than thirty percent of the total lift surface, and the wings are locate d in the middle third (14) of the total length of the fuselage. The aircraft additionally comprises a horizontal tail unit (4) situated in the rear third of the fuselage. The aircraft has a shape similar to that of a fish.
Claims (38)
1. Flight device with:
a lift-generating fuselage (1), whose widest span (11) lies in the middle third (14) of the total length, and whose outline tapers progressively in the front third (13) and in the rear third (15), two wings (2), the projection area of both wings on a horizontal plane representing less than 30 percent of the total lifting surface and the wings being located in the middle third (14) of the total length of said fuselage, a horizontal stabilizer (4) at the rear third of the fuselage.
a lift-generating fuselage (1), whose widest span (11) lies in the middle third (14) of the total length, and whose outline tapers progressively in the front third (13) and in the rear third (15), two wings (2), the projection area of both wings on a horizontal plane representing less than 30 percent of the total lifting surface and the wings being located in the middle third (14) of the total length of said fuselage, a horizontal stabilizer (4) at the rear third of the fuselage.
2. Flight device according to claim 1, wherein the projection area of both wings (2) on a horizontal plane represents less than 20 percent of the total lifting surface.
3. Flight device according to claim 1, wherein the projection area of both wings (2) on a horizontal plane represents less than 15 percent of the total lifting surface.
4. Flight device according to one of the claims 1 to 3, wherein the projection area of both wings (2) on a vertical plane represents less than 60 percent of the projection area of both wings on a horizontal plane.
5. Flight device according to one of the claims 1 to 4, wherein said horizontal stabilizer (4) has approximately the same span as said middle third of the fuselage (1).
6. Flight device according to one of the claims 1 to 5, wherein the ratio between the lift surface of said second third of the flight device including the wings and the lift surface of the first third of the flight device is between 1.6 and 3.0, and wherein the ratio between the lift surface of said second third of the flight device including the wings and the lift surface of the last third of the fuselage is between 2.0 and 4.0, the lift surface of said last third being smaller than the lift surface of the first third.
7. Flight device according to one of the claims 1 to 6, with a cockpit (3) that is located in a thickening (16) of the fuselage's upper side, said thickening (16) being as long as said fuselage (1).
8. Flight device according to claim 1, wherein said cockpit (3) is partially integrated in said fuselage (1).
9. Flight device according to one of the claims 1 to 8, wherein the entire configuration has fluid transitions, so that it is not exactly discernible where said fuselage (1) stops and where said wings (2) start.
10. Flight device according to one of the claims 1 to 9, wherein the entire configuration has fluid transitions, so that the boundary between fuselage (1) and cockpit (3) is not exactly discernible.
11. Flight device according to one of the claims 1 to 10, wherein the outlet edge (20) of said wings (2) on the wing tip (22) has an angle between 60° and 120° to the flight device's longitudinal axis (12).
12. Flight device according to claim 11, wherein the outlet edge (20) of said wings (2) on the wing tip (22) has an angle between 70°
and 110° to the flight device's longitudinal axis (12).
and 110° to the flight device's longitudinal axis (12).
13. Flight device according to claim 12, wherein the outlet edge (20) of said wings (2) on the wing tip (22) has an angle between 80°
and 100° to the flight device's longitudinal axis (12).
and 100° to the flight device's longitudinal axis (12).
14. Flight device according to claim 13, wherein the outlet edges (20) of said wings (2) on the wing tip (22) have an angle of 90°
to the flight device's longitudinal axis (12).
to the flight device's longitudinal axis (12).
15. Flight device according to one of the claims 1 to 14, wherein the front edge (21) of said wings (2) has a shape that, from front to back, is first concave and then convex, and wherein the angle of the tangent of said curves, at the inflexion point 23 between the concave segment and the convex segment, has an angle between 35° and 55° relative to the flight device's longitudinal axis (12).
16. Flight device according to one of the claims 1 to 14, wherein the wings (2) have a smaller angle of incidence than the lift-generating fuselage.
17. Flight device according to one of the claims 1 to 16, wherein the steering around the longitudinal axis occurs only through swinging in opposite direction of said horizontal stabilizer (4).
18. Flight device according to one of the claims 1 to 17, wherein the ratio between the height and the length of the flight device is between 0,2 and 0,35.
19. Flight device according to one of the claims 1 to 18, having an aspect ratio of .lambda. < 3 (.lambda. = ~/S, with /representing the wings' span and S
the wings' surface).
the wings' surface).
20. Flight device according to one of the claims 1 to 19, wherein the ratio between the length (12) and the maximal span of the flight device including wings is between 0.5 and 1.5.
21. Flight device according to one of the claims 1 to 20, wherein the ratio between the length (12) and the maximal span of the flight device including wings is between 0.75 and 1.5.
22. Flight device according to one of the claims 1 to 21, wherein the ratio between the length (12) and the maximal span of the flight device including wings is between 0.7 and 1Ø
23. Flight device according to one of the claims 1 to 22, wherein the volume V available for freight has the following ratio to the length L (12) and to the maximal span I of the flight device including wings:
where the factor k lies between 30 and 90.
where the factor k lies between 30 and 90.
24. Flight device according to one of the claims 1 to 23, with at least one powering unit (6) that is at least partially integrated in the fuselage (1).
25. Flight device according to claim 23, with at least one powering unit engine intake (60) on the underside of the flight device.
26. Flight device according to one of the claims 24 or 25, with at least one additional powering unit engine intake (61) on the upper side of the flight device.
27. Flight device according to claim 26, wherein said additional powering unit engine intake (61) is used only during take-off and/or climbing flight.
28. Flight device according to one of the claims 26 or 27, wherein said additional powering unit engine intake (61) has a nearly even outer surface on the upper side of the fuselage.
29. Flight device according to one of the claims 1 to 28, with a circular gas exhaust (63) at the end of the fuselage (1).
30. Flight device according to one of the claims 1 to 29, having an analogy to the shape of a fish.
31. Flight device according to one of the claims 1 to 30, wherein the left and the right front edges (10) from the tip of the flight device up to said widest span build each a fluid, continuous line with two inflexion points.
32. Flight device according to one of the claims 1 to 31, wherein the transversal cross section surface from the tip of the flight device to said widest span are fluid and continuous.
33. Flight device according to one of the claims 1 to 32, wherein the transversal outline from the tip of the flight device to said widest span are fluid and continuous.
34. Flight device according to one of the claims 31 to 33, wherein said widest span is located in the rear 50 percent of the total length of the flight device.
35. Flight device according to claim 34, wherein said widest span is located in the rear 30 percent of the total length of the flight device.
36. Flight device with:
a lift-generating fuselage (1), a horizontal stabilizer (4), characterized in that the left and the right outer profile from the tip of the flight device to the widest span build each a fluid continuous line with two inflexion points.
a lift-generating fuselage (1), a horizontal stabilizer (4), characterized in that the left and the right outer profile from the tip of the flight device to the widest span build each a fluid continuous line with two inflexion points.
37. Flight device according to claim 36, characterized in that the transversal cross section surface and/or the transversal outline from the tip of the flight device to said widest span are fluid and continuous.
38. Flight device with:
a lift-generating fuselage (1), a horizontal stabilizer (4), characterized in that the transversal cross section surface and/or the transversal outline from the tip of the flight device to said widest span are fluid and continuous.
a lift-generating fuselage (1), a horizontal stabilizer (4), characterized in that the transversal cross section surface and/or the transversal outline from the tip of the flight device to said widest span are fluid and continuous.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CH2044/01 | 2001-11-06 | ||
| CH20442001 | 2001-11-06 | ||
| PCT/CH2002/000598 WO2003039951A1 (en) | 2001-11-06 | 2002-11-06 | Aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CA2505013A1 true CA2505013A1 (en) | 2003-05-15 |
| CA2505013C CA2505013C (en) | 2011-02-15 |
Family
ID=4567274
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA2505013A Expired - Fee Related CA2505013C (en) | 2001-11-06 | 2002-11-06 | Flight device with a lift-generating fuselage |
Country Status (5)
| Country | Link |
|---|---|
| EP (1) | EP1444130B1 (en) |
| AT (1) | ATE299111T1 (en) |
| CA (1) | CA2505013C (en) |
| DE (1) | DE50203592D1 (en) |
| WO (1) | WO2003039951A1 (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1620310B1 (en) * | 2003-05-05 | 2006-06-28 | Team Smartfish GmbH | Aircraft with a lift-generating fuselage |
| DE102014201040A1 (en) | 2014-01-21 | 2015-07-23 | Airbus Operations Gmbh | aircraft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2298040A (en) * | 1939-08-21 | 1942-10-06 | Manta Aircraft Corp | Fluid foil |
| GB1075403A (en) * | 1964-06-04 | 1967-07-12 | British Aircraft Corp Ltd | Improvements in space vehicles |
| US4033526A (en) * | 1974-05-31 | 1977-07-05 | William Benson | Aerodynamic flow body |
| RU2033945C1 (en) * | 1992-05-22 | 1995-04-30 | Научно-производственная кооперативная фирма "ЭКИП" | Flying vehicle, boundary layer suction control system, control system of injection to boundary layer, device for fixing position of shedding of flow from trailing edge of fuselage and its air cushion alighting gear |
| US5813628A (en) * | 1996-05-13 | 1998-09-29 | Redwood Aircraft Corporation | Lifting-fuselage/wing aircraft having low induced drag |
| US6264136B1 (en) * | 1998-07-27 | 2001-07-24 | Paul H. Weston | High efficiency combination wing aircraft |
-
2002
- 2002-11-06 EP EP02771971A patent/EP1444130B1/en not_active Expired - Lifetime
- 2002-11-06 DE DE50203592T patent/DE50203592D1/en not_active Expired - Lifetime
- 2002-11-06 CA CA2505013A patent/CA2505013C/en not_active Expired - Fee Related
- 2002-11-06 AT AT02771971T patent/ATE299111T1/en not_active IP Right Cessation
- 2002-11-06 WO PCT/CH2002/000598 patent/WO2003039951A1/en not_active Application Discontinuation
Also Published As
| Publication number | Publication date |
|---|---|
| CA2505013C (en) | 2011-02-15 |
| WO2003039951A1 (en) | 2003-05-15 |
| DE50203592D1 (en) | 2005-08-11 |
| EP1444130A1 (en) | 2004-08-11 |
| EP1444130B1 (en) | 2005-07-06 |
| ATE299111T1 (en) | 2005-07-15 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| EEER | Examination request | ||
| MKLA | Lapsed |
Effective date: 20131106 |