GB1286104A - Improvements relating to aircraft having variable sweep wings - Google Patents
Improvements relating to aircraft having variable sweep wingsInfo
- Publication number
- GB1286104A GB1286104A GB4408369A GB4408369A GB1286104A GB 1286104 A GB1286104 A GB 1286104A GB 4408369 A GB4408369 A GB 4408369A GB 4408369 A GB4408369 A GB 4408369A GB 1286104 A GB1286104 A GB 1286104A
- Authority
- GB
- United Kingdom
- Prior art keywords
- root
- axis
- wing
- aircraft
- stringers
- 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.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/40—Varying angle of sweep
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Tires In General (AREA)
Abstract
1286104 Aircraft with variable sweep wings MESSERSCHMITT-BOLKOW-BLOHM GmbH 5 Sept 1969 [25 Sept 1968] 44083/69 Heading B7G An aircraft has variable sweep wings 4, each having a root area extending from swivel axis 45 and an outer area extending from the root area to the wing tip, the outer area being stiffened by chordal ribs 41 or stringers and the root area by webs 42, Fig. 4, or stringers 43, Fig. 5, varying in direction with respect to the spanwise axis of the wing. The webs 42 may radiate from the swivel axis 45; or the stringers 43 may vary in their inclination to the spanwise axis from 45 degrees near the swivel axis to 90 degrees where the root area meets the outer area. Thus the wing has high torsional rigidity about the spanwise axis and low flexural rigidity along that axis so that in the swept-back position the angle of attack decreases from root to tip (since the trailing edge of a cross-section 7 is at a greater distance from the root mounting than the leading edge) to a greater extent than in the unswept position, whereby the tendency of the centre of lift to shift backwards as the wing is swept backwards to be reduced or avoided.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE19681781305 DE1781305C3 (en) | 1968-09-25 | 1968-09-25 | Variable sweep wing |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1286104A true GB1286104A (en) | 1972-08-23 |
Family
ID=5704734
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB4408369A Expired GB1286104A (en) | 1968-09-25 | 1969-09-05 | Improvements relating to aircraft having variable sweep wings |
Country Status (3)
| Country | Link |
|---|---|
| DE (1) | DE1781305C3 (en) |
| FR (1) | FR2018847A7 (en) |
| GB (1) | GB1286104A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115556959A (en) * | 2022-09-14 | 2023-01-03 | 北京机电工程研究所 | Wing surface shear backswept form design method, deformation wing, wing and aircraft |
-
1968
- 1968-09-25 DE DE19681781305 patent/DE1781305C3/en not_active Expired
-
1969
- 1969-09-05 GB GB4408369A patent/GB1286104A/en not_active Expired
- 1969-09-24 FR FR6932617A patent/FR2018847A7/fr not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115556959A (en) * | 2022-09-14 | 2023-01-03 | 北京机电工程研究所 | Wing surface shear backswept form design method, deformation wing, wing and aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| DE1781305A1 (en) | 1970-12-03 |
| FR2018847A7 (en) | 1970-06-26 |
| DE1781305B2 (en) | 1974-07-11 |
| DE1781305C3 (en) | 1975-02-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PLNP | Patent lapsed through nonpayment of renewal fees |