CN104613825B - A kind of grid rudder structure being used on band raster rudder guided missile - Google Patents
A kind of grid rudder structure being used on band raster rudder guided missile Download PDFInfo
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- CN104613825B CN104613825B CN201510037305.4A CN201510037305A CN104613825B CN 104613825 B CN104613825 B CN 104613825B CN 201510037305 A CN201510037305 A CN 201510037305A CN 104613825 B CN104613825 B CN 104613825B
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Abstract
The present invention discloses a kind of grid rudder structure being used on band raster rudder guided missile, the grid rudder Connection Block that described grid rudder comprises grid rudder rudder face and is fixed on guided missile body; Connected by grid rudder axis of dilatation between described grid rudder rudder face and grid rudder Connection Block; The axis of described grid rudder axis of dilatation is positioned at the front side of described grid rudder rudder face midline plane, and described grid rudder rudder face midline plane is the parallel planes at edge plane 1/2 chord length place in face of distance grid rudder rudder. The invention solves grid rudder in expansion process, due to the bigger moment of resistance that aerodynamic force produces, cause the problem of grid rudder rapid deployment scarce capacity.
Description
Technical field
The present invention relates to a kind of grid rudder structure being used on band raster rudder guided missile.
Background technology
Grid rudder rudder face is embedded in the many lift surface system formed in frame, it has better lift performance in given space, and convenient folding, also there is the little advantage of hinge moment simultaneously, therefore carried out big quantity research in grid rudder application aspect both at home and abroad. In the prior art, as shown in Figure 1, 2, Fig. 1 is that on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of folded state, and Fig. 2 is that on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of expansion state. In prior art, the axis of grid rudder axis of dilatation 10 ' is positioned in the midline plane 30 ' of described grid rudder rudder face 20 '.
At present, for the bullet design buried in launched by airplane in bullet or shrapnel, when interior bury bullet or bullet separation initial, it is desirable to overcome aerodynamic drag square suffered by grid rudder rudder face expansion process, could realize the rapid deployment in grid rudder rudder face; It is known that, the big advantage of grid rudder opposite planar rudder one is exactly convenient folding and can by aerodynamic force rapid deployment, but under different free stream Mach number, attitude angle and the angle of spread, the power-assisted square that grid rudder rudder face is launched to produce by aerodynamic force is different, when the angle of spread is less, grid rudder rudder face is launched may also can produce to hinder by aerodynamic force. Therefore, how to reduce grid rudder and launch Process Gas dynamic resistance square, it is to increase rapid deployment ability needs research and solution emphatically in engineering design.
Existing solution generally have three kinds: one be by reduce grid rudder rudder face launch time free stream Mach number and flight height to reduce the pressure that flows; Two is limit body attitude angle when grid rudder rudder face is launched, and makes attitude angle unlikely excessive; Three is by optimizing grid rudder geometrical dimension to reduce aerodynamic drag square. First two method not only all can limit the ballistic design of guided missile, buries bullet or bullet operational performance in impact, and can increase the difficulty of segregational stability design; Grid rudder profile and structure design can be proposed requirements at the higher level by the third method, are not easy to practical application.
Summary of the invention
The technical problem to be solved in the present invention is to provide a kind of grid rudder structure being used on band raster rudder guided missile. This grid rudder structure being used on band raster rudder guided missile solves grid rudder rudder face in expansion process, due to the bigger moment of resistance that aerodynamic force produces, causes the problem of grid rudder rudder face rapid deployment scarce capacity.
For solving the problems of the technologies described above, the present invention adopts following technical proposals:
The grid rudder structure being used on band raster rudder guided missile, the grid rudder Connection Block that described grid rudder comprises grid rudder rudder face and is fixed on guided missile body;
Connected by grid rudder axis of dilatation between described grid rudder rudder face and grid rudder Connection Block;
The axis of described grid rudder axis of dilatation is positioned at the front side of described grid rudder rudder face midline plane, and described grid rudder rudder face midline plane is the parallel planes at edge plane 1/2 chord length place in face of distance grid rudder rudder.
Further, grid rudder rudder face chord length is b, and the axis of grid rudder axis of dilatation apart from the scope of the distance d of edge plane in face of grid rudder rudder is: 0��d < b/2.
Further, described grid rudder Connection Block is convexly equipped in Missile Body surface.
The present invention proposes a kind of grid rudder structure being used on band raster rudder guided missile, namely when grid rudder axis of dilatation Position Design, not according to conventional thought, grid rudder axis of dilatation position is selected in the midline plane of grid rudder rudder face, but before being arranged on grid rudder rudder face midline plane, edge plane in face of grid rudder rudder as far as possible.
The present invention takes full advantage of the singularity being subject to power in grid rudder rudder face expansion process, namely along grid rudder rudder axial direction due axial force produce axial moment M1 and grid rudder axis of dilatation position closely related, grid rudder axis of dilatation position is the closer to edge plane in face of grid rudder rudder, and axial moment more easily helps exhibition. And before being positioned at grid rudder rudder face midline plane by selection and the position of grid rudder axis of dilatation forward as far as possible, it is possible to greatly reduce aerodynamic drag square suffered in grid rudder rudder face expansion process, thus reach the object of grid rudder rapid deployment.
Other reduces structure and the method for aerodynamic drag square suffered by grid rudder rudder face expansion process, not only successful relatively in the present invention, and simpler, can not increase ballistic design, configuration design and structure design difficulty, more easily implement in engineering practice.
Accompanying drawing explanation
Fig. 1 is that in prior art, on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of folded state.
Fig. 2 is that in prior art, on band raster rudder guided missile, grid rudder rudder face is the schematic diagram of expansion state.
Fig. 3 is the position view of grid rudder axis of dilatation in the present invention.
Fig. 4 is that in the present invention, process is launched by power schematic diagram in grid rudder rudder face.
Fig. 5 is the emulation result schematic diagram of grid rudder leeward rudder face suffered pneumatic moment in expansion process in the present invention.
Fig. 6 is the emulation result schematic diagram of grid rudder rudder face suffered pneumatic moment in expansion process windward in the present invention.
Embodiment
Below in conjunction with accompanying drawing 3 to 6, the specific embodiment of the present invention is described.
As shown in Figure 3,4, a kind of grid rudder structure being used on band raster rudder guided missile, the grid rudder Connection Block 3 that described grid rudder comprises grid rudder rudder face 1 and is fixed on guided missile body 2; Connected by grid rudder axis of dilatation 4 between described grid rudder rudder face 1 and grid rudder Connection Block 3; Described grid rudder Connection Block 3 is convexly equipped in guided missile body 2 surface.
The axis of described grid rudder axis of dilatation 4 is positioned at the front side of described grid rudder rudder face midline plane 11, and described grid rudder rudder face midline plane 11 is the parallel planes at edge plane 1/2 chord length place in face of distance grid rudder rudder.
When grid rudder rudder face 1 chord length is b, the axis of grid rudder axis of dilatation 4 apart from the scope of the distance d of edge plane 5 in face of grid rudder rudder is: 0��d < b/2. Get d=0 in the present embodiment, it is located in face of grid rudder rudder in edge plane 5 by grid rudder axis of dilatation position.
Fig. 4 is that in the present invention, process is launched by power schematic diagram in grid rudder rudder face; The moment to grid rudder axis of dilatation 4 that aerodynamic force produces mainly comprises two portions: one is by the axial force F 1 along grid rudder rudder face 1 rudder direction of principal axis, the moment M1=F1xL1 of generation, and wherein arm of force L1 is the distance between axial force F 1 vector and grid rudder axis of dilatation 4; Two is the normal force F2 along grid rudder rudder face 1 normal direction, the moment M2=F2xL2 of generation, and wherein arm of force L2 is the distance between normal force F2 vector and grid rudder axis of dilatation 4.
The synthesis of M1 and M2 determines grid rudder rudder face 1 pneumatic resultant couple M=M1+M2 suffered in expansion process, reduces the inhibition that grid rudder rudder face 1 is launched by M1 or M2, can improve the developing power of grid rudder rudder face 1 entirety; For M1, arm of force L1 size directly determines that M1's helps exhibition ability, however, be evident that the position of axial moment M1 and grid rudder axis of dilatation 4 is closely related, and the position of grid rudder axis of dilatation 4 is more big the closer to edge plane 5, L1 in face of grid rudder rudder, and M1 helps exhibition ability more strong.
Before the present invention is positioned at grid rudder rudder face midline plane 11 by selection and the position of grid rudder axis of dilatation 4 forward as far as possible, can greatly reduce aerodynamic drag square suffered in grid rudder rudder face 1 expansion process, thus reach the object of grid rudder rudder face 1 rapid deployment.
As shown in Figure 5,6, under design state, the pneumatic moment under the different angle of spread obtained by numerical evaluation, the corresponding rudder face of Fig. 5 is leeward rudder, the corresponding rudder face of Fig. 6 is rudder windward, and X-coordinate �� is the angle of spread, and ordinate zou is the pneumatic moment coefficient around grid rudder axis of dilatation; Cmlq��CmlzBeing respectively the pneumatic moment coefficient that grid rudder axis of dilatation is positioned in face of grid rudder rudder in edge plane and calculates in the midline plane of grid rudder rudder face time, it is hinder rudder face to launch that negative value represents pneumatic moment, and is just being worth and is representing aerodynamic moment and help exhibition.
Calculation result shows, no matter is the leeward rudder of grid rudder or the rudder windward of grid rudder, when grid rudder axis of dilatation position being located in face of grid rudder rudder in edge plane, and pneumatic moment CmlqIt is all just be worth, helps exhibition. When grid rudder axis of dilatation position being located in the midline plane of grid rudder rudder face, when the angle of spread is less, pneumatic moment CmlzIt is negative value, it is hinder to launch, along with the angle of spread increases, CmlzTurn into just being worth, slowly have and help exhibition ability, but under the identical angle of spread, CmlzAll it is less than Cmlq; It is visible when grid rudder axis of dilatation position is located on front side of the midline plane of grid rudder rudder face, when being particularly arranged in face of grid rudder rudder in edge plane, can greatly reduce grid rudder rudder face at the aerodynamic drag square suffered by expansion process, improve and help exhibition moment, thus improve grid rudder rapid deployment ability, reduce the design requirement to the expansion moment that development mechanism provides.
The word in the description orientation adopted herein " on ", D score, "left", "right" etc. be all the convenience in order to illustrate based on the orientation shown in attached picture in picture face, in actual device, these orientation may be different due to the disposing way of device.
In sum, enforcement mode of the present invention only provides the enforcement mode of a kind of the best, technology contents and the technology feature of the present invention disclose as above, but the personage being familiar with the technology still may do the various replacement and the modification that do not deviate from creation spirit of the present invention based on disclosed content; Therefore, protection scope of the present invention is not limited to the technology contents that embodiment discloses, therefore the equivalence change that all shapes according to the present invention, structure and principle are done, all it is encompassed in protection scope of the present invention.
Claims (3)
1. the grid rudder structure being used on band raster rudder guided missile, it is characterised in that, the grid rudder Connection Block that described grid rudder comprises grid rudder rudder face and is fixed on guided missile body;
Connected by grid rudder axis of dilatation between described grid rudder rudder face and grid rudder Connection Block;
The axis of described grid rudder axis of dilatation is positioned at the front side of described grid rudder rudder face midline plane, and described grid rudder rudder face midline plane is the parallel planes at edge plane 1/2 chord length place in face of distance grid rudder rudder.
2. a kind of grid rudder structure being used on band raster rudder guided missile according to claim 1, it is characterized in that, grid rudder rudder face chord length is b, and the axis of grid rudder axis of dilatation apart from the scope of the distance d of edge plane in face of grid rudder rudder is: 0��d < b/2.
3. a kind of grid rudder structure being used on band raster rudder guided missile according to claim 1, it is characterised in that, described grid rudder Connection Block is convexly equipped in Missile Body surface.
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| CN201510037305.4A CN104613825B (en) | 2015-01-23 | 2015-01-23 | A kind of grid rudder structure being used on band raster rudder guided missile |
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| CN201510037305.4A CN104613825B (en) | 2015-01-23 | 2015-01-23 | A kind of grid rudder structure being used on band raster rudder guided missile |
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| CN110260726B (en) * | 2019-05-28 | 2021-09-03 | 上海宇航系统工程研究所 | Grid rudder device |
| CN112693623B (en) * | 2020-12-21 | 2022-05-27 | 中国空气动力研究与发展中心高速空气动力研究所 | Missile grid rudder hinge moment model claw disc type self-locking positioning structure |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2637063A1 (en) * | 1973-11-27 | 1990-03-30 | Cem Comp Electro Mec | Method of producing armour plates made of ceramic and plates obtained by the said method |
| US5048773A (en) * | 1990-06-08 | 1991-09-17 | The United States Of America As Represented By The Secretary Of The Army | Curved grid fin |
| CA2670325A1 (en) * | 2006-11-30 | 2008-12-11 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
| CN103162580A (en) * | 2013-03-05 | 2013-06-19 | 西北工业大学 | Grid fin of supersonic velocity guided missile |
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2015
- 2015-01-23 CN CN201510037305.4A patent/CN104613825B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2637063A1 (en) * | 1973-11-27 | 1990-03-30 | Cem Comp Electro Mec | Method of producing armour plates made of ceramic and plates obtained by the said method |
| US5048773A (en) * | 1990-06-08 | 1991-09-17 | The United States Of America As Represented By The Secretary Of The Army | Curved grid fin |
| CA2670325A1 (en) * | 2006-11-30 | 2008-12-11 | Raytheon Company | Detachable aerodynamic missile stabilizing system |
| CN103162580A (en) * | 2013-03-05 | 2013-06-19 | 西北工业大学 | Grid fin of supersonic velocity guided missile |
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