CN207717314U - A kind of aerofoil flutter model frame segment structure - Google Patents
A kind of aerofoil flutter model frame segment structure Download PDFInfo
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- CN207717314U CN207717314U CN201721628593.1U CN201721628593U CN207717314U CN 207717314 U CN207717314 U CN 207717314U CN 201721628593 U CN201721628593 U CN 201721628593U CN 207717314 U CN207717314 U CN 207717314U
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Abstract
The utility model discloses a kind of aerofoil flutter model frame segment structures, belong to flutter test device design field.Including：Beams of metal, leading edge, rear, covering cover board, common rib, ribs, self-locking device, self-locking push rod and bayonet lock；Leading edge, rear and the common rib of the left and right sides are connected with each other composition main frame, and ribs is arranged in main frame, for connecting leading edge and rear；Beams of metal passes through common rib, ribs and is connect with ribs, and entire main frame is mounted on beams of metal；Covering cover board is provided with the covering rib with bayonet lock, by bayonet lock limit on the common rib of both sides；One end of ribs is provided with self-locking device, and covering cover board is provided with self-locking push rod；Covering cover board is removably mounted at by self-locking push rod and self-locking device cooperation on main frame.The utility model during the test, can effectively save test period, reduce experimentation cost, and ensure that the smooth clean and tidy of frame section shape, improve the accuracy of test result.
Description
Technical field
The utility model belongs to flutter test device design field, and in particular to a kind of aerofoil flutter model frame section knot
Structure.
Background technology
When designing plane airfoil flutter model, the rigidity of aerofoil is simulated with roof beam structure, aerofoil is simulated with Wooden frame section
Shape, in the past design tie up shape wooden frame when, masking sheet was papered to simulate the covering of aerofoil, Huo Zheyong on wooden frame using dope
Screw is directly anchored to shape mask is tieed up on wooden frame, although these methods can meet experiment needs, replaces state more
It is time-consuming, and model aesthetics is insufficient.
Utility model content
The purpose of this utility model：To solve the above-mentioned problems, the utility model proposes a kind of aerofoil flutter model frames
Segment structure realizes the Fast Installation of dimension shape mask by self-locking bayonet unit, can greatly save test period and labour is strong
Degree；Self-locking buckle uses built-in design, ties up on shape covering without any protrusion, both avoids in experiment to the slight dry of air-flow
It disturbs, but also model is more aesthetically pleasing generous.
The technical solution of the utility model：A kind of aerofoil flutter model frame segment structure, including：Beams of metal, leading edge, rear,
Covering cover board, common rib, ribs, self-locking device, self-locking push rod and bayonet lock；
The leading edge, rear and the common rib of the left and right sides are connected with each other composition main frame, and the ribs is arranged in master
In frame, for connecting leading edge and rear；
The beams of metal passes through the common rib, the ribs and is connect with the ribs, and entire main frame is pacified
On beams of metal；
The covering cover board is provided with the covering rib with bayonet lock, by bayonet lock limit on the common rib of both sides；
One end of the ribs is provided with self-locking device, and the covering cover board is provided with and self-locking device cooperation installation
Self-locking push rod；
The covering cover board is removably mounted at by self-locking push rod and self-locking device cooperation on main frame.
Preferably, the covering cover board is vertically arranged with covering rib along its left and right sides；
The covering rib has been uniformly arranged cylindrical bayonet lock along its horizontal direction.
Preferably, the self-locking device includes：Shell, spring clip plate, compression spring and positive stop hook；
The shell is made of bottom plate, both sides edge and outer panel；
Compression spring is provided in the shell, compression spring both ends are connect with spring clip plate and Housing Base respectively；
It moves up and down along shell edge under the spring clip plate stress, one end is provided with screens portion, for locking certainly
Lock push rod；
The spring clip plate is provided with positive stop hook, and described positive stop hook one end is mounted on the spring clip plate, other end card
In hull outside plate, it can slide and be locked on outer panel along outer panel.
Preferably, the spring clip plate is U-shaped, is internally provided with pedestal；
The positive stop hook is Z-shaped, and one end of which is fixed on pedestal, the other end is stuck on hull outside plate.
Preferably, the outer panel is provided with Y type screens slots, and the positive stop hook coordinates with screens slot；
The positive stop hook is located at the straightway of screens slot in its natural state, is in screens slot always；
The positive stop hook is locked at the limit section of screens slot under the action of compression spring.
Preferably, the spring clip plate is made of limiting section and body part；
The limiting section is used for Clamping and self-locking push rod, and limiting section being capable of the contraction of opposing body portion and expansion；
Preferably, the common rib upper and lower ends are symmetrically arranged with limiting slot, and the limiting slot is set with bayonet lock cooperation
It sets；
The limit channel opening positioned at homonymy is towards unanimously；
The limiting slot is obliquely installed along common rib.
The advantageous effect of technical solutions of the utility model：A kind of aerofoil flutter model frame segment structure of the utility model, is being tried
During testing, test period can have effectively been saved, has reduced experimentation cost, and ensure that the smooth whole of frame section shape
It is clean, improve the accuracy of test result.
Description of the drawings
Fig. 1 is the overall structure diagram of a preferred embodiment of the utility model aerofoil flutter model frame segment structure；
Fig. 2 is the main frame structure schematic diagram of embodiment illustrated in fig. 1；
Fig. 3 is the covering covering plate structure schematic diagram of embodiment illustrated in fig. 1；
Fig. 4 is the locking device overall structure diagram of embodiment illustrated in fig. 1；
Fig. 5 is the locking device internal structure schematic diagram of embodiment illustrated in fig. 1；
Fig. 6 is the Y type screens slot schematic diagrames of embodiment illustrated in fig. 5；
Fig. 7 is the locking device nature schematic diagram of embodiment illustrated in fig. 1；
Wherein, 1- beams of metals, 2- leading edges, 3- rears, 4- covering cover boards, the common ribs of 5-, 6- ribs, 7- self-locking devices,
8- covering ribs, 9- self-locking push rods, 10- bayonet locks, 11- shells, 12- spring clip plates, 13- pedestals, 14- compression springs, 15- limits
Position hook, 16- screens slots, 17- limiting slots.
Specific implementation mode
To keep the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Attached drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the utility model.In the accompanying drawings, from beginning
Same or similar element or element with the same or similar functions are indicated to same or similar label eventually.Described reality
It is the utility model a part of the embodiment to apply example, instead of all the embodiments.Below with reference to the embodiment of attached drawing description
It is exemplary, it is intended to for explaining the utility model, and should not be understood as limiting the present invention.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained without creative efforts
Example, shall fall within the protection scope of the present invention.The embodiments of the present invention are described in detail below in conjunction with the accompanying drawings.
In the description of the present invention, it should be understood that term "center", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom" "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown, is merely for convenience of describing the present invention and simplifying the description, rather than indicates or imply and is signified
Device or element must have a particular orientation, with specific azimuth configuration and operation, therefore should not be understood as to this practicality
The limitation of novel protected range.
As shown in Figures 1 to 7；A kind of aerofoil flutter model frame segment structure, including：Beams of metal 1, rear 3, covers at leading edge 2
Skin cover board 4, common rib 5, ribs 6, self-locking device 7, self-locking push rod 9 and bayonet lock 10；
Leading edge 2, rear 3 and the common rib 5 of the left and right sides are connected with each other composition main frame, and ribs 6 is arranged in main frame
It is interior, for connecting leading edge 2 and rear 3；
In the present embodiment, leading edge 2 and rear 3 are sticked to by AB glue on ribs 6, and two common ribs 5 are sticked to by AB glue
Between leading edge 2 and rear 3.
Common rib 5 is provided with through-hole, is passed through for beams of metal 1, and mounting hole, mounting hole and 1 gap of beams of metal is arranged in ribs 6
Cooperation；
Beams of metal 1 passes through common rib 5, ribs 6 and be bonded by AB glue with ribs 6, and entire main frame is mounted on
On beams of metal 1.
In the present embodiment, 5 upper and lower ends of common rib are symmetrically arranged with limiting slot 17, and limiting slot 17 is set along the inclination of common rib 5
It sets, limiting slot 17 is equipped with bayonet lock 10 and positioned at the limiting slot 17 of homonymy opening towards unanimously.When common rib 5 is installed, appoint
The anticipate installation side of common rib 5 can be adopted to spacing bayonet lock 10.
Covering cover board 4 is vertically arranged with covering rib 8 along its left and right sides, and covering rib 8 sticks at covering lid by AB glue
The marginal position of plate, covering rib 8 have been uniformly arranged cylindrical bayonet lock 10 along its horizontal direction；
One end of ribs 6 is provided with self-locking device 7, and covering cover board 4 is provided with the self-locking with the cooperation installation of self-locking device 7
Push rod 9；
Covering cover board 4 is limited by bayonet lock 10 matches on the common rib 5 of both sides, then by self-locking push rod 9 and self-locking device 7
Conjunction is removably mounted on main frame.
In the present embodiment, self-locking device 7 includes：Shell 11, spring clip plate 12, compression spring 14 and positive stop hook 15；
Wherein, shell is made of bottom plate, both sides edge and outer panel；
Compression spring 14 is provided in shell, 14 both ends of compression spring are connect with spring clip plate 12 and Housing Base respectively,
It moves up and down along shell edge under 12 stress of spring clip plate, one end is provided with screens portion, for locking self-locking push rod；Spring
Clamping plate 12 is provided with positive stop hook 15, and 15 one end of positive stop hook is mounted on spring clip plate 12, and the other end is stuck in hull outside plate, energy
It is enough to slide and be locked on outer panel along outer panel.
It can be understood that：Spring clip plate 12 is U-shaped, is internally provided with pedestal 13, and positive stop hook 15 is in Z types, and one end is solid
It is scheduled on pedestal 13, the other end is stuck on hull outside plate.
In the present embodiment, outer panel is provided with Y type screens slot 16, and positive stop hook 15 coordinates with screens slot 16；Positive stop hook 15 exists
It is located at the straightway of screens slot 16 under natural conditions, is in screens slot always；Effect of the positive stop hook 15 in compression spring 14
Under, it is locked at the limit section of screens slot 16.
In the present embodiment, spring clip plate 12 is made of limiting section and body part；Limiting section is used for Clamping and self-locking push rod, limit
It position portion being capable of the contraction of opposing body portion and expansion；When limiting section enters shell, limiting section is located along the same line with body part,
And clamping self-locking push rod；When limiting section is detached from shell, limiting section is expanded rapidly, discharges self-locking push rod.
When covering cover board 4 is mounted on main frame, bayonet lock 10 is stuck in the limiting slot 17 on common rib 5, and self-locking push rod 9 pushes away
Dynamic pedestal 13 is moved toward the 11 bottom plate direction of shell of self-locking device, and pedestal 13 drives positive stop hook 15 along the Y type screens of shell 11
Slot 16 limits section movement toward it, and positive stop hook 15 is eventually stuck in Y type screens slot 16, and spring clip plate 12 clamps self-locking push rod 9,
And it is covering cover board and main frame is mutually locked.
When unloading covering cover board 4 from main frame, self-locking push rod 9 is pushed so that hook 15 is toward 11 bottom of self-locking device shell
Portion direction moves and crosses the limit section of Y type screens slot 16, unlocks；
Compression spring 14 pushes pedestal 13 and spring clip plate 12 to be moved together toward 11 top-direction of self-locking device shell, spring
Clamping plate 12 unclamps self-locking push rod 11.
It is last it is to be noted that：Above example is only to illustrate the technical solution of the utility model, rather than limits it
System.Although the utility model is described in detail with reference to the foregoing embodiments, those skilled in the art should manage
Solution：Its still can with technical scheme described in the above embodiments is modified, or to which part technical characteristic into
Row equivalent replacement；And these modifications or replacements, various embodiments of the utility model that it does not separate the essence of the corresponding technical solution
The spirit and scope of technical solution.
Claims (7)
1. a kind of aerofoil flutter model frame segment structure, which is characterized in that including：Beams of metal (1), leading edge (2), rear (3), covering
Cover board (4), common rib (5), ribs (6), self-locking device (7), self-locking push rod (9) and bayonet lock (10)；
The common rib (5) of the leading edge (2), rear (3) and the left and right sides is connected with each other composition main frame, the ribs (6)
It is arranged in main frame, for connecting leading edge (2) and rear (3)；
The beams of metal (1) passes through the common rib (5), the ribs (6) and is connect with the ribs (6), will be entire
Main frame is mounted on beams of metal (1)；
The covering cover board (4) is provided with the covering rib (8) with bayonet lock (10), is limited in the general of both sides by bayonet lock (10)
On logical rib (5)；
One end of the ribs (6) is provided with self-locking device (7), and the covering cover board (4) is provided with matches with self-locking device (7)
Close the self-locking push rod (9) of installation；
The covering cover board (4) is removably mounted at by self-locking push rod (9) and the self-locking device (7) cooperation on main frame.
2. aerofoil flutter model frame segment structure as described in claim 1, it is characterised in that：The covering cover board (4) is along its left side
Right both sides are vertically arranged with covering rib (8)；
The covering rib (8) has been uniformly arranged cylindrical bayonet lock (10) along its horizontal direction.
3. aerofoil flutter model frame segment structure as described in claim 1, it is characterised in that：The self-locking device (7) includes：Shell
Body (11), spring clip plate (12), compression spring (14) and positive stop hook (15)；
The shell is made of bottom plate, both sides edge and outer panel；
Be provided with compression spring (14) in the shell, compression spring (14) both ends respectively with spring clip plate (12) and Housing Base
Connection；
It moves up and down along shell edge under spring clip plate (12) stress, one end is provided with screens portion, for locking certainly
Lock push rod；
The spring clip plate (12) is provided with positive stop hook (15), and described positive stop hook (15) one end is mounted on the spring clip plate (12)
On, the other end is stuck in hull outside plate, can be slided and is locked on outer panel along outer panel.
4. aerofoil flutter model frame segment structure according to claim 3, it is characterised in that：The spring clip plate (12) is in U
Type is internally provided with pedestal (13)；
The positive stop hook (15) is Z-shaped, and one end of which is fixed on pedestal (13), the other end is stuck on hull outside plate.
5. aerofoil flutter model frame segment structure according to claim 3, it is characterised in that：The outer panel is provided with Y types
Screens slot (16), the positive stop hook (15) coordinate with screens slot (16)；
The positive stop hook (15) is located at the straightway of screens slot (16) in its natural state, is in screens slot always；
The positive stop hook (15) is locked at the limit section of screens slot (16) under the action of compression spring (14).
6. aerofoil flutter model frame segment structure according to claim 3, it is characterised in that：The spring clip plate is by limiting section
And body part composition；
The limiting section is used for Clamping and self-locking push rod, and limiting section being capable of the contraction of opposing body portion and expansion.
7. aerofoil flutter model frame segment structure according to claim 1, it is characterised in that：The common rib (5) up and down two
End is symmetrically arranged with limiting slot (17), and the limiting slot is equipped with the bayonet lock (10)；
The limiting slot (17) opening positioned at homonymy is towards unanimously；
The limiting slot (17) is obliquely installed along common rib (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721628593.1U CN207717314U (en) | 2017-11-29 | 2017-11-29 | A kind of aerofoil flutter model frame segment structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721628593.1U CN207717314U (en) | 2017-11-29 | 2017-11-29 | A kind of aerofoil flutter model frame segment structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207717314U true CN207717314U (en) | 2018-08-10 |
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ID=63057664
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721628593.1U Active CN207717314U (en) | 2017-11-29 | 2017-11-29 | A kind of aerofoil flutter model frame segment structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595728A (en) * | 2019-09-02 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Pre-stress technology-based flutter model and design method thereof |
| CN113432821A (en) * | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Emergency method for flutter suppression in low-speed flutter wind tunnel test |
-
2017
- 2017-11-29 CN CN201721628593.1U patent/CN207717314U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110595728A (en) * | 2019-09-02 | 2019-12-20 | 中国航空工业集团公司沈阳飞机设计研究所 | Pre-stress technology-based flutter model and design method thereof |
| CN110595728B (en) * | 2019-09-02 | 2021-07-09 | 中国航空工业集团公司沈阳飞机设计研究所 | Pre-stress technology-based flutter model and design method thereof |
| CN113432821A (en) * | 2021-06-01 | 2021-09-24 | 中国航空工业集团公司沈阳飞机设计研究所 | Emergency method for flutter suppression in low-speed flutter wind tunnel test |
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