GB2162139A - Aircraft flutter control - Google Patents
Aircraft flutter control Download PDFInfo
- Publication number
- GB2162139A GB2162139A GB08418816A GB8418816A GB2162139A GB 2162139 A GB2162139 A GB 2162139A GB 08418816 A GB08418816 A GB 08418816A GB 8418816 A GB8418816 A GB 8418816A GB 2162139 A GB2162139 A GB 2162139A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- cantilever
- flutter
- aircraft
- tip
- 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.)
- Withdrawn
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/10—Vibration-dampers; Shock-absorbers using inertia effect
- F16F7/104—Vibration-dampers; Shock-absorbers using inertia effect the inertia member being resiliently mounted
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
A flutter damper at an aircraft wing tip, for suppressing one degree of freedom wing flutter associated with buffet or separated flows. The damper comprises a cantilever and tip weight combination tuned for oscillation at the wing first bending frequency and arranged for immersion in a viscous fluid, such as aircraft fuel. <IMAGE>
Description
SPECIFICATION
Improvements in or relating to aircraft flutter control
The present invention relates to aircraft flutter control, and is particularly concerned with means for attenuating one degree of freedom wing flutter. In the present specification however 'wing' refers not only to the mainplane but to any aircraft fixed plane, such as the tailplane and fin.
According to the present invention an aircraft wing carries a flutter damper mounted in the tip thereof and comprising a thin cantilever with a weight approximate its free end and arranged for immersion in a viscous damping liquid.
The cantilever may be mounted in a fuel tank on or extending to the wing tip, in which case it may be preferred to ensure that aircraft fuel remains around the cantilever in modes of flight when the wing flutter is a possibility. This can come about if the cantilever is mounted relatively low in the tank, since
provided the cantilever is immersed, the amount of
liquid present will not greatly affect damper operation, which remains effective to attenuate a wing flutter at quite a wide range of frequencies about the fundamental. In an alternative embodiment however the damper may include its own vessel of viscous liquid.
The cantilever is preferably anchored either in the trailing end or the nose of the wing tip or wing tip tank. The cantilever may have constant thickness and breadth, although the breadth may taper outwards to conform to the contours of its container.
For use in a particular aircraft wing context the dimensions of the damper, and the weight of its components are likely to be tuned for excitation at the first wing bending frequency. The damper can then be effective both to suppress flutter and to
reduce the response of the wing to atmospheric turbulance or buffet excitation wrought by separated flows.
An aircraft wing tip flutter damper in accordance with the invention will now be described by way of
example with reference to the accompanying draw
ing, which depicts a flutter damper in an aircraft
mainplane tip fuel tank.
As depicted in the drawing an aircraft main plane
10 has a wing tip fuel tank 11 containing a flutter
damper comprising a thin cantilever 12 and a weight
13. The anchorage of the cantilever is in the trailing
edge of the tip tank 11, and the cantilever, which is
tapered outwards toward the weight 13 is consider
ably thinner than even its anchorage breadth. The
arrangement is such that the plane of the cantilever
and that of the wing are parallel one to the other.
Rubber stops mounted in the tip tank 11 above and
below the weight 13to prevent the weight from
reaching, and perhaps damaging, walls of the tank.
In a wind tunnel test of a model having a span of
60 inches and a wing weight of 209 Ib, a damper at
the wing tip having a total weight (cantilever plus
pad plus viscous liquid) of 12.5 Ib was effective as a
flutter damper, when tuned to an oscillation frequen
cy equal to the first wing bending frequency. The cantilever length was 2 inches. In the preferred embodiment, when the cantilever is arranged to lie in fuel, the weight penalty is considerably lower, anc can be kept low by maximising the extent of the cantilever rather than the size of the weight 13.
1. An aircraft wing carrying a flutter damper mounted in the tip thereof and comprising a thin cantilever with a weight approximate its free end and arranged for immersion in a viscous damping liquid.
2. A wing as claimed in claim 1 and wherein the cantilever is mounted in a fuel tank at the wing tip.
3. A wing as claimed in claim 2 and wherein the cantilever is anchored in the trailing end of the tank.
4. Awing as claimed in claim 2 and wherein the cantilever is anchored in the nose end of the tank.
5. An aircraft wing substantially as hereinbefore described with reference to the accompanying draw ings.
**WARNING** end of DESC field may overlap start of CLMS **.
Claims (5)
1. An aircraft wing carrying a flutter damper mounted in the tip thereof and comprising a thin cantilever with a weight approximate its free end and arranged for immersion in a viscous damping liquid.
2. A wing as claimed in claim 1 and wherein the cantilever is mounted in a fuel tank at the wing tip.
3. A wing as claimed in claim 2 and wherein the cantilever is anchored in the trailing end of the tank.
4. Awing as claimed in claim 2 and wherein the cantilever is anchored in the nose end of the tank.
5. An aircraft wing substantially as hereinbefore described with reference to the accompanying draw ings.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB08418816A GB2162139A (en) | 1984-07-24 | 1984-07-24 | Aircraft flutter control |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB08418816A GB2162139A (en) | 1984-07-24 | 1984-07-24 | Aircraft flutter control |
Publications (2)
Publication Number | Publication Date |
---|---|
GB8418816D0 GB8418816D0 (en) | 1984-08-30 |
GB2162139A true GB2162139A (en) | 1986-01-29 |
Family
ID=10564346
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB08418816A Withdrawn GB2162139A (en) | 1984-07-24 | 1984-07-24 | Aircraft flutter control |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB2162139A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2208419A (en) * | 1987-04-28 | 1989-03-30 | Shimizu Construction Co Ltd | Restraining vibration of a structure |
FR2747364A1 (en) * | 1996-04-15 | 1997-10-17 | Aerospatiale | Vibration absorption in aircraft airframes in transonic flight |
CN111252235A (en) * | 2020-01-20 | 2020-06-09 | 西北工业大学 | Passive aileron buzz stabilizer based on fluid-solid coupling effect |
US20220242552A1 (en) * | 2021-02-02 | 2022-08-04 | Toyota Motor Engineering & Manufacturing North America, Inc. | Shear hardening material to suppress flutter in inflatable wings |
Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB433531A (en) * | 1934-02-09 | 1935-08-09 | John Alexander Gilmore | Improvements in or relating to vibration dampers for vehicles |
GB1196170A (en) * | 1966-09-13 | 1970-06-24 | Reactor Centrum Nederland | Improvements in and relating to Vibration Dampers |
-
1984
- 1984-07-24 GB GB08418816A patent/GB2162139A/en not_active Withdrawn
Patent Citations (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB433531A (en) * | 1934-02-09 | 1935-08-09 | John Alexander Gilmore | Improvements in or relating to vibration dampers for vehicles |
GB1196170A (en) * | 1966-09-13 | 1970-06-24 | Reactor Centrum Nederland | Improvements in and relating to Vibration Dampers |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2208419A (en) * | 1987-04-28 | 1989-03-30 | Shimizu Construction Co Ltd | Restraining vibration of a structure |
GB2208419B (en) * | 1987-04-28 | 1991-04-03 | Shimizu Construction Co Ltd | Method of restraining vibration of a structure and apparatus therefor |
US5016409A (en) * | 1987-04-28 | 1991-05-21 | Shimizu Construction Co., Ltd. | Method for restraining response of a structure to outside disturbances and apparatus therefor |
FR2747364A1 (en) * | 1996-04-15 | 1997-10-17 | Aerospatiale | Vibration absorption in aircraft airframes in transonic flight |
US5890675A (en) * | 1996-04-15 | 1999-04-06 | Aerospatiale Societe Nationale Industrielle | Process and device for damping vibrations or preventing their appearance in aircraft airframes in transonic flight |
CN111252235A (en) * | 2020-01-20 | 2020-06-09 | 西北工业大学 | Passive aileron buzz stabilizer based on fluid-solid coupling effect |
US20220242552A1 (en) * | 2021-02-02 | 2022-08-04 | Toyota Motor Engineering & Manufacturing North America, Inc. | Shear hardening material to suppress flutter in inflatable wings |
US11618548B2 (en) * | 2021-02-02 | 2023-04-04 | Toyota Motor Engineering & Manufacturing North America, Inc. | Shear hardening material to suppress flutter in inflatable wings |
Also Published As
Publication number | Publication date |
---|---|
GB8418816D0 (en) | 1984-08-30 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |