CN113310659A - Passive flutter protection device, high-speed flutter model comprising same and working method thereof - Google Patents
Passive flutter protection device, high-speed flutter model comprising same and working method thereof Download PDFInfo
- Publication number
- CN113310659A CN113310659A CN202110586418.5A CN202110586418A CN113310659A CN 113310659 A CN113310659 A CN 113310659A CN 202110586418 A CN202110586418 A CN 202110586418A CN 113310659 A CN113310659 A CN 113310659A
- Authority
- CN
- China
- Prior art keywords
- flutter
- model
- passive
- speed
- guard
- 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
- 238000000034 method Methods 0.000 title claims abstract description 19
- 230000005540 biological transmission Effects 0.000 claims abstract description 12
- 230000008859 change Effects 0.000 claims abstract description 6
- 238000009826 distribution Methods 0.000 claims abstract description 4
- 239000006260 foam Substances 0.000 claims description 45
- 238000004458 analytical method Methods 0.000 claims description 13
- 238000010276 construction Methods 0.000 claims description 10
- 239000002131 composite material Substances 0.000 claims description 6
- 238000004026 adhesive bonding Methods 0.000 claims description 5
- 239000000463 material Substances 0.000 claims description 4
- 239000007769 metal material Substances 0.000 claims description 3
- 230000003014 reinforcing effect Effects 0.000 claims description 2
- 238000012546 transfer Methods 0.000 claims description 2
- 238000012360 testing method Methods 0.000 abstract description 29
- 230000000694 effects Effects 0.000 abstract description 7
- 238000004064 recycling Methods 0.000 abstract description 4
- 230000001629 suppression Effects 0.000 description 13
- 238000013461 design Methods 0.000 description 10
- 238000005516 engineering process Methods 0.000 description 10
- 238000013459 approach Methods 0.000 description 7
- 230000008901 benefit Effects 0.000 description 4
- 238000013016 damping Methods 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000011161 development Methods 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000010146 3D printing Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000002238 attenuated effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000005094 computer simulation Methods 0.000 description 1
- 230000001808 coupling effect Effects 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000003631 expected effect Effects 0.000 description 1
- 238000013213 extrapolation Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
-
- 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
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention provides a passive flutter protection device, a high-speed flutter model comprising the same and a working method thereof. The passive flutter protection device is connected with the bearing force transmission structure of the high-speed flutter model, is assembled at a specific structure area of the high-speed flutter model in accordance with the external outline of the main structure of the high-speed flutter model, and is damaged under a specific load condition so as to change the mass distribution and the pneumatic appearance of the high-speed flutter model, further change the self-excitation condition of the high-speed flutter model and protect the main structure and the bearing force transmission structure of the high-speed flutter model from being damaged. Therefore, the method can realize the technical effects of protecting and recycling the main structure of the model, reducing the damage cost, quickly repairing the model, improving the reliability of the critical flutter test, reducing the damage degree of the damage of the model to the wind tunnel and the like.
Description
Technical Field
The invention relates to the technical field of wind tunnel tests of aircraft flutter models, in particular to a passive flutter protection device, a high-speed flutter model comprising the passive flutter protection device and a working method of the high-speed flutter model.
Background
Elastic structures such as aircraft undergo self-excited vibration in a uniform airflow with non-attenuated amplitude due to coupling effects of aerodynamic forces, elastic forces and inertial forces. The phenomenon of vibration that does not converge (diverge) is referred to in the field of aeroelasticity as flutter.
The flutter problem is more prominent especially when the airplane flies at supersonic speed. Therefore, modern aircraft designs take into account the effects of flutter from the outset, rather than checking against the flutter criteria after the design is complete. Generally, one can perform flutter analysis on an aircraft through calculation and wind tunnel tests.
The aircraft flutter model wind tunnel test is a technical means for obtaining the flutter characteristic of an aircraft through a dynamic similarity model, can be used for determining or checking the flutter characteristic of the whole or a part of the aircraft so as to ensure the flutter safety characteristic within a flight envelope range, and comprises a low-speed flutter model wind tunnel test and a high-speed flutter model wind tunnel test. The wind tunnel test of the low-speed flutter model is used for mastering the subsonic flutter characteristic of the whole aircraft or parts of the aircraft and the influence rule of sensitive parameters on the flutter characteristic. The wind tunnel test of the high-speed flutter model of the aircraft is an important working link in the process of aircraft development and evidence collection, and the model realizes the purpose of researching the flutter characteristic of the aircraft in a wind tunnel in a transonic region by simulating the dynamic characteristic of the aircraft.
At present, when the flutter analysis is carried out on an airplane, the flutter analysis is limited in that only a numerical solution exists in a transonic unsteady aerodynamic equation, and the flutter analysis cannot be reasonably linearized or subjected to frequency domain. Therefore, the influence of the transonic flutter characteristic of the aircraft, particularly the transonic airflow compressibility characteristic, on the flutter characteristic of the aircraft can only be verified through a transonic flutter model wind tunnel test before the aircraft is subjected to flutter test flight. Such models are commonly referred to in the art as "high-speed flutter wind tunnel test models" or "high-speed flutter models".
In the technical field, the traditional wind tunnel test protection technology of the high-speed flutter model can be generally summarized as follows: an active protection technology approach and a passive protection technology approach. The active protection technology comprises the following steps: program-controlled active turning off, manual active turning off, program-controlled rudder deflection flutter suppression, program-controlled limit flutter suppression and the like; the passive protection technology approach includes: passive limit flutter suppression, damper vibration absorption and vibration reduction and the like.
For example, the prior document CN106005368A (published as 2016, 10, 12) discloses a flutter model of a flexible wing with a variable trailing edge, which is designed by segmenting the trailing edge frame section of the wing, wherein the segments are hinged to each other, and a series of link mechanisms are used to drive and control the deflection angles of different frame sections, so that the trailing edge of the wing can be deformed by the movement of the mechanism, thereby achieving the purpose of flutter suppression. This document discloses a programmed rudder flutter suppression method in the above-mentioned active protection technique.
For another example, the conventional document CN205209736U (publication date 2016, 5, month, and 4) discloses a flutter suppression device and a rudder surface flutter model having the same. The brake pin of the document has a braking position and an unlocking position in the sliding groove, and when the brake pin is in the unlocking position, the control surface flutter model is controlled to be in a free rotation state; if the control surface vibrates in the test process, the vibration suppression device is started, the brake pin assembly is pushed to the unlocking position by the control element, and the brake pin inserts the control surface of the model to be dead, so that the vibration is suppressed. This document discloses a program-controlled limit flutter suppression or the like in the above-described active protection technique.
For example, the prior document CN109115450A (publication date 1/2019) discloses a wind tunnel model damper and a wind tunnel model assembly. The wind tunnel model damper of the document changes the fundamental frequency of the whole damper by changing the position of the adjusting component. The wind tunnel model damper is placed in a head cavity of a wind tunnel model, and is driven to vibrate together when the wind tunnel model vibrates in the wind tunnel test process, and the vibration of the wind tunnel model can be inhibited by the damping force generated by the damper. This document discloses a vibration absorbing and damping method of the damper in the passive protection technology.
However, the above-mentioned prior art protection techniques have the following significant disadvantages:
firstly, when different types of flutter occur, the high-probability model flutter suppression protection cannot be ensured, so that the conventional high-speed flutter test is still planned and developed in a subcritical flutter test mode, and the dependence of a test result on data extrapolation accuracy is strong;
secondly, when the model vibrates, the local model is damaged, so that the model cannot continue to be subjected to subsequent state tests due to the fact that the model cannot be repaired, and the integrity of the tests is influenced;
thirdly, because a control system, such as a steering engine, a hinge and other components are introduced into the model structure, extra damping and rigidity nonlinear links are often introduced, so that the simulation difficulty of a physical model simulation theoretical model is obviously increased;
fourthly, the structural space layout design of the model for dynamic simulation becomes more difficult due to the addition of an active suppression or damping vibration absorption and reduction mechanism in the structural space of the model.
In view of the above, there is no passive flutter protection device for a high-speed flutter model in the present technical field, which is different from the active protection technical approach and the passive protection technical approach of the traditional high-speed flutter model wind tunnel test, and adopts a passive flutter suppression (i.e. failure damage control design) structure introduced into a model specific structural area to realize the specific stage of the model in the flutter wind tunnel test and the specific form damage in the model specific structural area, thereby realizing the technical effects of protecting and recycling the main structure of the model, reducing the damage cost, quickly repairing the model, improving the reliability of the critical flutter test, reducing the damage degree of the model damage to the wind tunnel, and the like. Therefore, how to design a passive flutter protection device for high-speed flutter model that can meet the above requirements is a critical technical problem to be solved.
Disclosure of Invention
It is therefore an object of the present invention to provide a passive flutter guard which addresses all of the above-mentioned deficiencies of the prior art.
The invention also aims to provide a high-speed flutter model and a working method thereof, wherein the high-speed flutter model realizes the research on the flutter characteristics of the transonic region of the aircraft in a wind tunnel by simulating the dynamic characteristics of the aircraft.
In order to solve the above object of the invention, according to a first aspect of the present invention, there is provided a passive flutter guard for a high speed flutter model, wherein:
the passive flutter protection device is connected with a bearing force transmission structure of the high-speed flutter model, is assembled at a specific structural area of the high-speed flutter model in accordance with the external contour of a main structure of the high-speed flutter model, and
the passive flutter protection device is damaged under a specific load condition so as to change the mass distribution and the pneumatic appearance of the high-speed flutter model, further change the self-excitation condition of the high-speed flutter model and protect a main structure and a bearing force transmission structure of the high-speed flutter model from being damaged.
Preferably, in the passive flutter preventing device of the present invention, the passive flutter preventing device has an upper and lower two-piece structure including: an upper member; and a lower assembly including at least one rib, a foam, and a skin.
Preferably, in the passive flutter preventing device of the present invention, the passive flutter preventing device has a quadrangular shape.
Preferably, in the passive flutter preventing device, a groove is arranged on the upper surface of the foam piece along the longitudinal direction of the foam piece, so that the load-bearing force transmission structure of the high-speed flutter model can pass through the groove; at least one slot is provided on an upper surface of the foam member in a lateral direction thereof, the at least one rib being disposed in the at least one slot.
Preferably, in the passive flutter preventing device, a notch is arranged in the upper part of the at least one rib plate, and the depth of the notch is consistent with the depth of the groove of the foam piece, so that the load-bearing force transmission structure of the high-speed flutter model can penetrate through the notch.
Preferably, in the passive flutter preventing device of the present invention, the lower assembly includes three ribs, one of which is located in the slot of the foam member, and the other two ribs are located at both ends of the foam member in the longitudinal direction thereof, respectively.
Preferably, in the passive flutter preventing device of the present invention, the rib plate is made of a rigid material, such as a metal material or a composite material, for reinforcing the overall strength of the foam member.
Preferably, in the passive flutter preventing device of the present invention, the skin is wrapped over the foam member to which the rib has been fitted, and a cut groove having a contour conforming to a contour of the cut groove of the foam member is provided on an upper surface of the skin.
Preferably, in the passive flutter preventing device, the foam piece is machined and molded by finished foam, and the foam piece is connected with the rib plate and the skin by gluing or clamping.
Preferably, in the passive flutter preventing device, the skin is made of a composite material, and the skin is connected with the rib plate and the foam piece through a gluing mode or a clamping mode.
Preferably, in the passive flutter preventing device of the present invention, the passive flutter preventing device has a one-piece structure for being directly sleeved on the load-bearing force transmission structure of the high-speed flutter model.
Preferably, in the passive flutter preventing device of the present invention, the passive flutter preventing device has an upper and lower two-piece structure including an upper part and a lower component, wherein the upper part or the lower component is constituted by a closed sandwich structure composed of a foam piece and a skin, or the upper part or the lower component is realized by a lightweight structure including a shell structure composed of a honeycomb-skin combination or 3D printing.
According to a second aspect of the invention there is provided a high speed flutter model comprising the passive flutter guard of the invention, wherein the load bearing force transfer structure of the high speed flutter model extends along the longitudinal axis of the main structure and is mounted in the main structure.
Preferably, in the high-speed flutter model of the invention, the high-speed flutter model has a proximal end and a distal end, and the specific structural region is close to the distal end of the high-speed flutter model.
Preferably, in the high-speed flutter model of the invention, the load-bearing force transmission structure is a main beam or a load-bearing frame-stringer structure.
According to a third aspect of the invention, there is provided a method of operation of the high speed flutter model of the invention, comprising the steps of:
establishing a theoretical analysis model corresponding to a physical model, and finding a specific structural area sensitive to model flutter characteristics by carrying out flutter analysis, wherein the passive flutter protection device is arranged in the specific structural area;
secondly, obtaining a specific loading condition of the specific structure region through analysis;
thirdly, controlling the failure and damage of the specific structural area according to the specific load condition
In view of the above, the core technology of the invention is as follows, different from the active protection technology approach and the passive protection technology approach of the traditional wind tunnel test of the high-speed flutter model: by introducing a passive flutter suppression (namely failure damage control design) structure into a model specific structure area, the specific flutter generation stage of the model in a high-speed flutter wind tunnel test is realized, and the specific form damage is generated in the model specific structure area. Therefore, the method can realize the technical effects of protecting and recycling the main structure of the model, reducing the damage cost, quickly repairing the model, improving the reliability of the critical flutter test, reducing the damage degree of the damage of the model to the wind tunnel and the like.
Drawings
In order to more clearly illustrate the technical solution provided by the present invention, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 schematically illustrates a preferred embodiment of the overall structure of a high speed flutter model incorporating the passive flutter guard of the present invention;
FIG. 2 schematically illustrates a preferred embodiment of the passive flutter guard of the present invention assembled to a high speed flutter model, wherein the passive flutter guard has a two-piece construction;
figure 3 schematically shows a preferred embodiment of the specific composition of the lower assembly of the passive flutter guard of the present invention;
figure 4 schematically shows a section of the structure of the passive flutter guard according to the invention, taken along the line a-a in the figure, in connection with a main girder; and
FIG. 5 shows a diagram of the expected effect of the test implementation of the high-speed flutter model under specific load conditions.
List of reference numerals in the figures in the technical solutions and embodiments:
1 high speed flutter model
1A proximal end
1B distal end
2 passive flutter protection device
21 upper part
22 lower assembly
221 rib plate
221a notch
222 foam piece
222a are slotted
222b slot
223 covering
223a cutting groove
3 main beam
4 main structure
5 fastener
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention.
In this regard, it is first noted that in the detailed description of these embodiments, it is not possible for the specification to describe in detail all of the features of an actual embodiment in order to provide a concise description. It should be appreciated that in the development of any such actual implementation, as in any engineering or design project, numerous implementation-specific decisions are made to achieve the developers' specific goals, such as compliance with system-related and business-related constraints, which may vary from one implementation to another. Moreover, it should be further appreciated that such a development effort might be complex and tedious, but would nevertheless be a routine undertaking of design, fabrication, and manufacture for those of ordinary skill having the benefit of this disclosure, and thus should not be construed as a complete understanding of this disclosure.
In addition, it is to be noted that technical terms or scientific terms used in the claims and the specification should have a general meaning as understood by those having ordinary skill in the art to which the present invention belongs, unless otherwise defined. The terms "a" or "an," and the like, do not denote a limitation of quantity, but rather denote the presence of at least one. The word "comprise" or "comprises", and the like, means that the element or item listed before "comprises" or "comprising" covers the element or item listed after "comprising" or "comprises" and its equivalent, and does not exclude other elements or items. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, nor are they restricted to direct or indirect connections.
The present invention will be described in detail below with reference to fig. 1 to 5 so that the advantages and features of the present invention can be easily understood by those skilled in the art, thereby clearly defining the scope of the present invention.
First, the overall structure of the high-speed flutter model of the present invention will be described with reference to fig. 1. FIG. 1 schematically illustrates a preferred embodiment of the overall structure of a high speed flutter model incorporating the passive flutter guard of the present invention.
As shown in the figure, the high-speed flutter model 1 of the invention comprises a passive flutter protection device 2, a main beam 3 and a main structure 4. Wherein the high-speed flutter model 1 has a near end 1A and a far end 1B. The main beam 3 extends along the longitudinal axis of the main structure 4 and is mounted in the main structure 4, and the passive flutter preventing device 2 is connected with the main beam 3, thereby being assembled at a specific structural area of the high-speed flutter model 1. As shown in fig. 1, the specific structural region is near the distal end of the high-speed flutter model 1, but is not limited thereto. In addition, the main beams 3 can be replaced by other load-bearing force-transmission structures, such as a load-bearing frame-stringer structure and the like.
Next, the structure of the passive flutter preventing device 2 of the present invention and its assembly will be described in detail with reference to fig. 2 to 4.
Referring to fig. 2, a preferred embodiment of the passive flutter guard 2 of the present invention is schematically illustrated in assembled form to a high speed flutter model 1. As shown, the passive flutter guard 2 has an upper and lower two-piece construction, including an upper piece 21 and a lower assembly 22.
Referring to fig. 3, a preferred embodiment of the specific construction of the lower assembly 22 of the passive flutter guard 2 of the present invention is schematically illustrated. As shown, in the preferred embodiment, the lower assembly 22 includes at least one rib 221, a foam piece 222, and a skin 223.
As shown in fig. 4, a structural section view of the passive flutter preventing device 2 and the main beam 3 taken along the line a-a in the figure is schematically shown. As shown in the drawings, the passive flutter guard 2 of the present invention has a quadrangular shape, but is not limited thereto, as long as it can be embedded at a specific structural region of the high-speed flutter model 1 in conformity with the outer contour of the main structure 4 of the high-speed flutter model.
The lower assembly 22 is the main body portion of the passive flutter guard 2 of the present invention. As shown in fig. 3, a slot 222a is provided on the upper surface of the foam piece 222 in the longitudinal direction thereof, and the main beam 3 of the high-speed flutter model 1 passes through the slot 222 a. In addition, at least one slot 222b in which the rib 221 is placed is provided on the upper surface of the foam piece 222 in the lateral direction thereof.
Preferably, the ribs 221 are made of a rigid material, such as a metal material or a composite material, to reinforce the overall strength of the foam piece 222. In addition, a notch 221a is provided in the upper portion of the rib plate 221, and the depth of the notch 221a is identical to the depth of the groove 222a on the upper surface of the foam piece 222, so that the main beam 3 of the high-speed flutter model 1 passes therethrough.
According to a preferred embodiment of the present invention, as shown in fig. 3, the lower assembly 22 comprises three ribs 221, wherein one rib 221 is located in the slot 22b, and the other two ribs 221 are located at both ends of the foam member along the longitudinal direction thereof.
As also shown in fig. 3, skin 223 is wrapped over foam 222, which has been fitted with ribs 221. A cut 223a is provided on the upper surface of the skin 223, the contour of the cut 223a conforming to the contour of the cut 222a on the upper surface of the foam piece 222.
Preferably, the foam piece 222 is machined from a finished foam, which is joined to the ribs 221 and the skin 223 by gluing, but not limited thereto, for example, by snap-fitting or the like.
In addition, skin 223 is preferably made of composite material and is connected with ribs 221 and foam piece 222 by gluing, but is not limited thereto, and for example, a snap-fit manner or the like may be used. As shown in fig. 4, the passive flutter protection device 2 of the invention is connected with the main beam 3 of the high-speed flutter model 1 by a fastener 5 in an up-and-down combined structure, but the passive flutter protection device 2 of the invention can also be connected with the main beam 3 of the high-speed flutter model 1 in an integrated structure, for example, under certain specific areas and connection conditions, the passive flutter protection device 2 of the invention can also be directly sleeved on the main beam 3 of the high-speed flutter model 1.
It is also worth mentioning that the above described configurations of the upper member 21 and the lower assembly 22 of the passive flutter guard 2 are merely examples, and that other embodiments are possible without departing from the spirit or scope of the general inventive concept.
As a first variant: the ribs are removed and the upper part or lower assembly is replaced by a closed sandwich structure consisting of only foam pieces and skin.
Again as in the second variant: the upper part or lower assembly can be realized with other lightweight structures, as long as the profile of the structure and its assemblability with the main structure are guaranteed, for example: shell structures with honeycomb-skin combinations and 3D printing, etc.
Next, the working method of the high-speed flutter model of the present invention is introduced, which includes the following steps:
establishing a theoretical analysis model corresponding to a physical model, and finding a specific structural area sensitive to model flutter characteristics by carrying out flutter analysis;
secondly, obtaining a specific load condition of a specific structure area through analysis;
and step three, performing failure and damage control design on a specific structural area (namely the passive flutter protection device) according to specific load conditions.
In summary, compared with the prior art, the core technology of the present invention is: by introducing a passive flutter suppression (namely failure damage control design) structure into a model specific structure area, the specific flutter generation stage of the model in a high-speed flutter wind tunnel test is realized, and the specific structural area of the model is damaged in a specific form, so that the technical effects of protecting and recycling the main structure of the model, reducing damage cost, quickly repairing the model, improving the reliability of critical flutter test, reducing the damage degree of the damage of the model to the wind tunnel and the like are realized.
Due to the technical scheme, the invention has the following outstanding progress and remarkable technical effect:
firstly, in a specific stage of flutter in a high-speed flutter wind tunnel test, a model generates self-excitation vibration under the action of wind tunnel incoming flow, and in the process that the self-excitation vibration amplitude of the model is gradually and rapidly increased, a passive flutter protection device 2 on the high-speed flutter model 1 is damaged under a specific load condition (the expected implementation effect is shown in figure 5), so that the mass distribution and the pneumatic appearance of the model are changed, the self-excitation condition of the model is further changed, and a main structure 4 and a main beam 3 of the model are protected from being damaged.
Secondly, the rapid repair of the damaged part caused by the self-excited vibration can be realized by the spare parts of the passive flutter preventing device 2 which is easy to install and low in cost.
Thirdly, the damage part of the vibration is controllable, so that the influence degree of the damaged model on the damage of the wind tunnel facility can be effectively reduced.
Fourthly, because the passive flutter protection device 2 is installed in a mode of being connected with a main beam or other load-bearing force transmission structures in an approximate rigid connection mode, the function of the passive flutter protection device is realized without introducing nonlinear factors, and the dynamic characteristic of the model is simulated in a lower technical difficulty range.
Preferred embodiments of the present invention have been described in detail above, but it is understood that other advantages and modifications will readily occur to those skilled in the art upon reading the foregoing teachings of the invention. Therefore, the invention in its broader aspects is not limited to the specific details and representative embodiments shown and described herein. Accordingly, reasonable combinations and modifications of the elements of the above-described embodiments can be made by those skilled in the art to make various modifications without departing from the spirit or scope of the general inventive concept as defined by the appended claims and their equivalents.
Claims (25)
1. A passive flutter protection device for a high-speed flutter model is characterized in that:
the passive flutter protection device is connected with a bearing force transmission structure of the high-speed flutter model, is assembled at a specific structural area of the high-speed flutter model in accordance with the external contour of a main structure of the high-speed flutter model, and
the passive flutter protection device is damaged under a specific load condition so as to change the mass distribution and the pneumatic appearance of the high-speed flutter model, further change the self-excitation condition of the high-speed flutter model and protect a main structure and a bearing force transmission structure of the high-speed flutter model from being damaged.
2. The passive flutter guard of claim 1 wherein the passive flutter guard has an upper and lower two piece construction comprising:
an upper member; and
a lower assembly including at least one rib, a foam, and a skin.
3. The passive flutter guard of claim 1 or 2 wherein the passive flutter guard is quadrilateral in shape.
4. The passive flutter guard of claim 2 wherein:
the upper surface of the foam piece is provided with a groove along the longitudinal direction of the foam piece, so that the load-bearing force transmission structure of the high-speed flutter model can penetrate through the groove;
at least one slot is provided on an upper surface of the foam member in a lateral direction thereof, the at least one rib being disposed in the at least one slot.
5. The passive flutter guard of claim 4 wherein an upper portion of the at least one rib has a notch therein, the notch having a depth corresponding to a depth of the slot of the foam member for passage therethrough of the load-bearing force-transmitting structure of the high speed flutter model.
6. The passive flutter guard of claim 4 wherein the lower assembly comprises three ribs, one of the ribs being located in the slot of the foam member and two of the ribs being located at respective ends of the foam member in a longitudinal direction thereof.
7. The passive flutter guard of claim 2 wherein the ribs are made of a rigid material for reinforcing the overall strength of the foam member.
8. The passive flutter guard of claim 7 wherein the rigid material is a metallic material or a composite material.
9. The passive flutter guard of claim 4 wherein the skin is wrapped over the foam member to which the ribs have been assembled, a slot being provided in an upper surface of the skin, the slot having a profile that conforms to a profile of the slot of the foam member.
10. The passive flutter guard of claim 2 wherein the foam member is machined from finished foam.
11. The passive flutter guard of claim 10 wherein the foam member is connected to the rib and the skin by gluing.
12. The passive flutter guard of claim 10 wherein the foam member is snap-fit to the rib and the skin.
13. The passive flutter protection device of claim 2 wherein the skin is made of a composite material.
14. The passive flutter protection device of claim 13 wherein the skin is adhesively bonded to the ribs and the foam member.
15. The passive flutter guard of claim 13 wherein the skin is snap-fit to the rib and the foam member.
16. The device of claim 1, wherein the device has a one-piece construction for nesting directly into the load-bearing force-transmitting structure of the high-speed flutter model.
17. The device according to claim 1, wherein the device has an upper and lower two-piece construction comprising an upper piece and a lower assembly, wherein the upper piece or the lower assembly is formed by a closed sandwich construction consisting of a foam piece and a skin.
18. The device of claim 1, wherein the device has a two-piece construction comprising an upper piece and a lower piece, wherein the upper piece or the lower piece is realized by a lightweight construction.
19. The passive flutter guard of claim 18 wherein the lightweight construction comprises a honeycomb-skin combination.
20. The passive flutter guard of claim 18 wherein the lightweight structure comprises a 3D printed shell structure.
21. A high speed flutter model comprising the passive flutter guard of claims 1-20, wherein a load bearing force transmitting structure of the high speed flutter model extends along a longitudinal axis of and is mounted in the main structure.
22. The high-speed flutter model of claim 21, wherein the high-speed flutter model has a proximal end and a distal end, the particular structural region being proximate the distal end of the high-speed flutter model.
23. A high speed flutter model according to claim 21 or 22 wherein the load bearing force transfer structure is a main beam.
24. A high speed flutter model according to claim 21 or 22 wherein the load bearing force transmitting structure is a load bearing frame-stringer structure.
25. A method of operating a high speed flutter model according to claims 21-24, comprising the steps of:
step one, establishing a theoretical analysis model corresponding to a physical model, and finding a specific structural area sensitive to model flutter characteristics by performing flutter analysis, wherein the passive flutter protection device according to claims 1-20 is installed in the specific structural area;
secondly, obtaining a specific loading condition of the specific structure region through analysis;
and thirdly, performing failure and damage control on the specific structure area according to the specific load condition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110586418.5A CN113310659B (en) | 2021-05-27 | 2021-05-27 | Passive flutter protection device, high-speed flutter model comprising same and working method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110586418.5A CN113310659B (en) | 2021-05-27 | 2021-05-27 | Passive flutter protection device, high-speed flutter model comprising same and working method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113310659A true CN113310659A (en) | 2021-08-27 |
| CN113310659B CN113310659B (en) | 2022-09-02 |
Family
ID=77375688
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110586418.5A Active CN113310659B (en) | 2021-05-27 | 2021-05-27 | Passive flutter protection device, high-speed flutter model comprising same and working method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113310659B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114264445A (en) * | 2021-11-26 | 2022-04-01 | 中电科芜湖通用航空产业技术研究院有限公司 | Flutter test flight excitation device and method |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09269274A (en) * | 1996-04-01 | 1997-10-14 | Natl Aerospace Lab | Flutter stop device for wing in wind tunnel test |
| CN102235937A (en) * | 2010-05-06 | 2011-11-09 | 中国商用飞机有限责任公司 | Airplane model flutter suppression device |
| CN104002966A (en) * | 2014-06-03 | 2014-08-27 | 北京航空航天大学 | Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor |
| CN105571815A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Emergency protecting device for rudder face |
| CN205633011U (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Wing model that shimmys |
| CN108602551A (en) * | 2016-01-05 | 2018-09-28 | 空中客车英国运营有限责任公司 | Aircraft wing with the removable Wing tip device for Load alleviation |
| CN112238932A (en) * | 2020-11-20 | 2021-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft flutter suppression device and aircraft thereof |
-
2021
- 2021-05-27 CN CN202110586418.5A patent/CN113310659B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH09269274A (en) * | 1996-04-01 | 1997-10-14 | Natl Aerospace Lab | Flutter stop device for wing in wind tunnel test |
| CN102235937A (en) * | 2010-05-06 | 2011-11-09 | 中国商用飞机有限责任公司 | Airplane model flutter suppression device |
| CN104002966A (en) * | 2014-06-03 | 2014-08-27 | 北京航空航天大学 | Rotor blade structure design capable of inhibiting rotation chattering of tilt rotor |
| CN105571815A (en) * | 2014-10-11 | 2016-05-11 | 中国航空工业集团公司西安飞机设计研究所 | Emergency protecting device for rudder face |
| CN108602551A (en) * | 2016-01-05 | 2018-09-28 | 空中客车英国运营有限责任公司 | Aircraft wing with the removable Wing tip device for Load alleviation |
| CN205633011U (en) * | 2016-05-16 | 2016-10-12 | 中国航空工业集团公司西安飞机设计研究所 | Wing model that shimmys |
| CN112238932A (en) * | 2020-11-20 | 2021-01-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Aircraft flutter suppression device and aircraft thereof |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114264445A (en) * | 2021-11-26 | 2022-04-01 | 中电科芜湖通用航空产业技术研究院有限公司 | Flutter test flight excitation device and method |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113310659B (en) | 2022-09-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US6375127B1 (en) | Active control surface modal system for aircraft buffet and gust load alleviation and flutter suppression | |
| Milgram et al. | Rotors with trailing edge flaps: Analysis and comparison with experimental data | |
| Rajabi et al. | A comparative study of the effects of constructional elements on the mechanical behaviour of dragonfly wings | |
| CN113310659B (en) | Passive flutter protection device, high-speed flutter model comprising same and working method thereof | |
| Friedmann et al. | Rotary wing aeroelasticity-a historical perspective | |
| EP2700574A1 (en) | Passive load alleviation for a fiber reinforced wing box of an aircraft with a stiffened shell structure | |
| CN111523178B (en) | Method for reducing vibration load of composite rotor hub | |
| Friedmann | Rotary-wing aeroelasticity with application to VTOL vehicles | |
| CN207570758U (en) | flutter model combined connecting device and flutter model system | |
| Cheng | Structural dynamics modeling of helicopter blades for computational aeroelasticity | |
| Austin et al. | Aeroelastic tailoring of advanced composite lifting surfaces in preliminary design | |
| Nguyen | Active control of helicopter blade stall | |
| Sanghi et al. | Influence of Aileron Placement on Roll Response of High-Aspect-Ratio-Wing Aircraft | |
| Han et al. | Lagwise loads analysis of a rotor blade with an embedded chordwise absorber | |
| Perera et al. | Structural and dynamic analysis of a seamless aeroelastic wing | |
| Saito et al. | Application of an active device for helicopter noise reduction in JAXA | |
| Anobile et al. | Investigation on a high-frequency controller for rotor BVI noise alleviation | |
| Amoozgar et al. | Cross-sectional design of a composite rotor blade for twist morphing | |
| Amoozgar et al. | Twist morphing of a hingeless rotor blade using a moving mass | |
| Jegley et al. | Structural response and failure of a full-scale stitched graphite-epoxy wing | |
| Pitt | Static and dynamic aeroelastic analysis of structural wing fold hinges that are employed as an aeroelastic tailoring tool | |
| Bain et al. | Computational modeling of variable-droop leading edge in forward flight | |
| Heyland et al. | The Adaptive Wing Project(DLR)- Survey on targets and recent results from active/adaptive structures viewpoint | |
| Liu et al. | Simultaneous vibration and noise reduction in rotorcraft-practical implementation issues | |
| Shin et al. | Control of integral twist-actuated helicopter blades for vibration reduction |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |