CN208897309U - A kind of leading edge part sweepback type grid airvane and play flight device - Google Patents
A kind of leading edge part sweepback type grid airvane and play flight device Download PDFInfo
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- CN208897309U CN208897309U CN201821476709.9U CN201821476709U CN208897309U CN 208897309 U CN208897309 U CN 208897309U CN 201821476709 U CN201821476709 U CN 201821476709U CN 208897309 U CN208897309 U CN 208897309U
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- leading edge
- airvane
- edge part
- sweepback
- grid
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Abstract
The utility model relates to a kind of leading edge part sweepback type grid airvane and play flight device, what is solved is that transonic speed drag characteristic is big, the grid rudder transonic speed low technical problem of aeroperformance, being used by leading edge part sweepback type grid airvane includes frame, and cell walls are equipped in frame and form grid rudder face；The leading edge part sweepback of the cell walls and frame at curved-surface structure technical solution, preferably resolve the problem, can be used for playing flight device etc. application in.
Description
Technical field
The utility model relates to play flight device field, and in particular to a kind of leading edge part sweepback type grid airvane and bullet
Flight device.
Background technique
Grid rudder is a kind of by the thin wall embedded lattice-shaped air-operated control rudder face formed on frame of muti-piece, is had outside itself
Wide size is small, can be close to aircraft surface folding, Strength Mass than high feature, and in terms of low speed and high speed have compared with
Good lift efficiency.Simultaneously because pneumatic chord length is shorter, the pressure heart is longitudinally varying smaller along rocket body, the hinge moment of generation is small, drop
The low requirement to servo-steering system, is conducive to the miniaturization of servosystem.Due to above-mentioned advantage, grid rudder obtains the country
The outer concern that studies for a long period of time for playing flight device field, and relatively broad application is obtained, the R77 including Russia is absolutely empty to be led
Bullet, AA-12 air-to-air missile, white poplar M guided missile, U.S.'s MOAB bomb etc., and the fast boat Launch Vehicle Series of China etc..
What the leading edge of existing grid rudder was generally flush with, there is the theoretical deficiency with application aspect in the grid rudder of this type: by
In there are flow choking effect and complicated inside Shock wave interaction, the transonic speed section aerodynamic lift characteristic of grid rudder is declined；
The front face area of grid rudder is big, causes aerodynamic drag larger, thereby results in range or carrying capacity loss；Most of rudder designs
Lack waling, thus the use for the flight operating condition that makes a very bad impression.Simultaneously because grid rudder has certain exhibition to size, grid
Lattice wall is relatively thin, and there are certain inconveniences in the transport and use process under non-folded state.
Therefore, in order to solve the above technical problems, the utility model proposes a kind of leading edge part sweepback type grid airvanes
And play flight device.
Summary of the invention
Technical problem to be solved in the utility model is that transonic speed drag characteristic existing in the prior art is big, grid rudder
The transonic speed low technical problem of aeroperformance, provides a kind of new leading edge part sweepback type grid airvane, which has
The feature that transonic speed drag characteristic is big can effectively be inhibited；In addition, the utility model also provides a kind of use grid airvane
Bullet flight device.
In order to solve the above technical problems, the technical solution adopted is as follows: a kind of leading edge part sweepback type grid airvane, institute
Stating leading edge part sweepback type grid airvane includes frame, and cell walls are equipped in frame and form grid rudder face；The cell walls
The sweepback of leading edge part at curved-surface structure.
Further, the leading edge part sweepback of the frame is at curved-surface structure.
Further, past at the tie point of tie point or cell walls and frame of the curved-surface structure between cell walls
Air-flow direction of flow is prominent, recessed along air-flow direction of flow in the middle position of cell walls and the middle position of frame.
Further, the rudder root zone domain of the leading edge part sweepback type grid airvane is structure thicker；The leading edge office
Sweepback type grid airvane in portion's is connected with rudderpost, is provided at least one reinforcing rib among the grid of rudderpost.
Further, it is connected between the leading edge part sweepback type grid airvane and rudderpost by flange arrangement.
Further, the grid rear of the leading edge part sweepback type grid airvane is also curved-surface structure.
The technical solution provided by the utility model for playing flight device is as follows: being provided with leading edge part sweepback type grid air
Rudder；The leading edge part sweepback type grid airvane is vertically mounted on the control plane for playing flight device；The grid airvane
Leading edge is windward side and installs towards flight device head is played, and the rear of grid airvane is leeward and towards playing flight device
Tail portion installation.
Further, the quantity of the leading edge part sweepback type grid airvane is 4.
The utility model has the beneficial effects that the utility model proposes leading edge part sweepback type grid airvane and play arrow fly
Row device, solving the problems, such as existing grid rudder, transonic speed aeroperformance is low, can effectively inhibit transonic speed drag characteristic is big to lack
Point, while modularized design facilitates the dismounting of rudder to use, also to adapt to fold design and use.
Detailed description of the invention
The present invention will be further described with reference to the accompanying drawings and examples.
A kind of leading edge part sweepback type grid air rudder system of Fig. 1, the utility model embodiment form figure.
A kind of leading edge part sweepback type grid airvane of Fig. 2, the utility model embodiment are playing the peace on flight device
Dress figure.
Fig. 3, schematic diagram when a kind of leading edge part sweepback type grid airvane of the utility model embodiment deflects.
A kind of leading edge part sweepback type grid airvane of Fig. 4, the utility model embodiment form explosive view.
Fig. 5, a kind of leading edge part sweepback type grid airvane expanded application form of the utility model embodiment.
In figure: cell walls -1, frame -2, connecting rod -3, connecting flange -4, abutted flange -5, bearing p- 6, reinforcing rib -
7, rudderpost -8, fastening nut -9, landing nipple -10, the tie point -11 between cell walls, the middle position -12 of cell walls, grid
The tie point -13 of lattice wall and frame, the middle position -14 of frame, grid rudder leading edge -15, grid rudder rear -16, leading edge part
Sweepback type grid airvane -20 play flight device -30.
Specific embodiment
In order to make the purpose of the utility model, technical solutions and advantages more clearly understood, with reference to embodiments, to this
Utility model is further elaborated.It should be appreciated that specific embodiment described herein is only to explain that this is practical new
Type is not used to limit the utility model.
As shown in Figure 1, a kind of leading edge part sweepback type grid airvane 20 is present embodiments provided, behind the leading edge part
Plunderring type grid airvane 20 includes frame 2, and cell walls 1 are equipped in frame 2 and form grid rudder face；Cell walls 1 by welding or
The mode inlayed, which is mounted in frame 2, forms grid rudder face, or whole rudder face uses increasing material manufacturing, monoblock cast or integrated machine
Processing method is realized.The leading edge part sweepback of the cell walls 1 is at curved-surface structure.Preferably, the leading edge of frame 2 also local sweepback
At curved-surface structure.
Specifically, sweepback at tie point 11 or cell walls and frame of the curved-surface structure between cell walls tie point
It is prominent toward air-flow direction of flow at 13, along air-flow incoming flow side at the middle position of cell walls 12 and the middle position of frame 14
To recessed.
By related wind tunnel test verification and Fluid Mechanics Computation analysis it can be seen that this design method changes grid
Hole pipe type flowing form can greatly reduce the probability that flowing is jammed in high subsonic speed section, so as to avoid critical horse
The problem of lift efficiency sharply declines near conspicuous number；Simultaneously after shock wave occurs in low supersonic section lattice pars intramuralis, before lattice wall
The bending irregularities of edge, so that interfering with each other between dramatically reducing shock wave, also improves the lift in this stage
Characteristic；Simultaneously because the change of above-mentioned liquid form, the aerodynamic drag of the transonic speed section of grid rudder also decreases.Therefore, this
Kind structure design form improves the transonic speed aeroperformance of grid rudder well.
Preferably, the rudder root zone domain of the leading edge part sweepback type grid airvane 20 is structure thicker；The leading edge office
Portion's sweepback type grid airvane 20 is connected with rudderpost 8, is provided at least one reinforcing rib 7 among the grid of rudderpost 8.It is this
The whole intensity and whole rigidity with root of rudder can be improved in design.
Increase connection cell walls between 2 tie point of grid tie point and grid and frame using the grid rudder of this form
1.It is calculated by aerodynamic loading and the intrinsic frequency of grid rudder structure can be improved in structural finite element analysis, this structure design form
Rate and overall stiffness, to reduce the overall deformation of grid rudder；So that Path of Force Transfer more optimizes, the strong of grid rudder is improved
Degree, and make load act under frame 2, the stress distribution of cell walls 1 it is more uniform.
Preferably, as Figure 1 and Figure 4, pass through method between the leading edge part sweepback type grid airvane 20 and rudderpost 8
Blue structure connection.Airvane 20 is combined by connecting rod 3 with connecting flange 4；Abutted flange 5 is logical on connecting flange 4 and rudderpost 8
It crosses screw to fix, while being realized and being positioned by internal connection；Rudderpost 8 connect 6 supports and realization with rocket body by bearing, uses
Fastening nut 9 fixes lengthwise position, realizes steering engine transmission by landing nipple 10.It can be convenient using the grid rudder of this form
Module design is realized on ground, while facilitating installation and removal, to improve the convenience of rudder application.
Optionally, the connection of grid rudder and rudderpost 8 can use other modes, and the connection of rudderpost 8 and servo motor can also
Change in the form of according to servo mechanism.
Preferably, as shown in figure 5, the rudder face of grid rudder can be the mode of whole sweepforward, the leading edge and rear of rudder are song
Face type, to adapt to fold design and use.
As shown in Fig. 2, the utility model additionally provides a kind of bullet for applying leading edge part sweepback type grid airvane 20
Flight device 30.When leading edge part sweepback type grid airvane 20, which is applied to, to be played on flight device 30, general multiple groups make in pairs
It with (typically 4), is vertically mounted on plays 30 control plane corresponding position of flight device when in use, grid rudder leading edge 15 is
Simultaneously towards the installation of flight device head is played, grid rudder rear 16 is leeward and pacifies towards flight device caudal directions are played for windward side
Dress.
As shown in figure 3, a kind of leading edge part sweepback type grid airvane 20 of the utility model embodiment, when in use around
The generation of rudderpost 8 deflects clockwise or counterclockwise, and rudder face can be laid out for "+" shape or " x " shape, realizes different channels by combination
Control.
Although the illustrative specific embodiment of the utility model is described above, in order to the art
Technical staff is it will be appreciated that the utility model, but the utility model is not limited only to the range of specific embodiment, to this technology
For the those of ordinary skill in field, as long as long as the utility model that various change is limited and determined in the attached claims
In spirit and scope, all are created using the utility model of the utility model design in the column of protection.
Claims (8)
1. a kind of leading edge part sweepback type grid airvane, it is characterised in that: the leading edge part sweepback type grid airvane packet
It includes frame (2), cell walls (1) is installed in frame (2) and forms grid rudder face；The leading edge part sweepback of the cell walls (1) at
Curved-surface structure.
2. leading edge part sweepback type grid airvane according to claim 1, it is characterised in that: before the frame (2)
The sweepback of edge part is at curved-surface structure.
3. leading edge part sweepback type grid airvane according to claim 1 or 2, it is characterised in that: the curved-surface structure
It is prominent toward air-flow direction of flow at the tie point (13) of tie point (11) or cell walls and frame between cell walls, in grid
It is recessed along air-flow direction of flow at the middle position (12) of lattice wall and the middle position (14) of frame.
4. leading edge part sweepback type grid airvane according to claim 1, it is characterised in that: leading edge part sweepback
The rudder root zone domain of type grid airvane is structure thicker；The leading edge part sweepback type grid airvane is connected with rudderpost (8), leans on
At least one reinforcing rib (7) is provided among the grid of nearly rudderpost (8).
5. leading edge part sweepback type grid airvane according to claim 4, it is characterised in that: leading edge part sweepback
It is connect between type grid airvane and rudderpost (8) by flange arrangement.
6. leading edge part sweepback type grid airvane according to claim 1, it is characterised in that: leading edge part sweepback
The grid rear of type grid airvane is also curved-surface structure.
7. a kind of bullet flight device, it is characterised in that: the bullet flight device is provided with as claimed in any one of claims 1 to 6
Leading edge part sweepback type grid airvane；The leading edge part sweepback type grid airvane is vertically mounted on the control for playing flight device
Face processed；The leading edge of the grid airvane is windward side and installs towards flight device head is played that the rear of grid airvane is
Leeward is simultaneously installed towards flight device tail portion is played.
8. bullet flight device according to claim 7, it is characterised in that: the leading edge part sweepback type grid airvane
Quantity is 4.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821476709.9U CN208897309U (en) | 2018-09-12 | 2018-09-12 | A kind of leading edge part sweepback type grid airvane and play flight device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821476709.9U CN208897309U (en) | 2018-09-12 | 2018-09-12 | A kind of leading edge part sweepback type grid airvane and play flight device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208897309U true CN208897309U (en) | 2019-05-24 |
Family
ID=66571930
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821476709.9U Withdrawn - After Issue CN208897309U (en) | 2018-09-12 | 2018-09-12 | A kind of leading edge part sweepback type grid airvane and play flight device |
Country Status (1)
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| CN (1) | CN208897309U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731467A (en) * | 2020-06-30 | 2020-10-02 | 北京星际荣耀空间科技有限公司 | Grid rudder and aircraft |
-
2018
- 2018-09-12 CN CN201821476709.9U patent/CN208897309U/en not_active Withdrawn - After Issue
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111731467A (en) * | 2020-06-30 | 2020-10-02 | 北京星际荣耀空间科技有限公司 | Grid rudder and aircraft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191231 Address after: 100176 Beijing Daxing District Beijing economic and Technological Development Zone, 9 South of Shing Sheng 1 1 3 story 329 Co-patentee after: Beijing Star glory Technology Co., Ltd Patentee after: Beijing interstellar glory InterSpace Technology Ltd Address before: 100176 Beijing Daxing District Beijing economic and Technological Development Zone, 9 South of Shing Sheng 1 1 3 story 329 Patentee before: Beijing interstellar glory InterSpace Technology Ltd |
|
| TR01 | Transfer of patent right | ||
| CP03 | Change of name, title or address |
Address after: 100032 1-14-214, 2nd floor, 136 Xiwai street, Xicheng District, Beijing Patentee after: Beijing Star glory Space Technology Co.,Ltd. Patentee after: Beijing Star glory Technology Co.,Ltd. Address before: 100176 329, 3rd floor, building 1, No.9, Disheng South Street, Beijing Economic and Technological Development Zone, Daxing District, Beijing Patentee before: BEIJING XINGJIRONGYAO SPACE TECHNOLOGY Co.,Ltd. Patentee before: Beijing Star glory Technology Co.,Ltd. |
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| CP03 | Change of name, title or address | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20190524 Effective date of abandoning: 20210408 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20190524 Effective date of abandoning: 20210408 |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |