CN104613825A - Grid rudder structure for grid rudder guided missile - Google Patents
Grid rudder structure for grid rudder guided missile Download PDFInfo
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- CN104613825A CN104613825A CN201510037305.4A CN201510037305A CN104613825A CN 104613825 A CN104613825 A CN 104613825A CN 201510037305 A CN201510037305 A CN 201510037305A CN 104613825 A CN104613825 A CN 104613825A
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- rudder
- grid rudder
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Abstract
The invention discloses a grid rudder structure for a grid rudder guided missile. A grid rudder comprises a grid rudder face and a grid rudder connecting base fixed to a guided missile body; the grid rudder face and the grid rudder connecting base are connected through a grid rudder unfolding shaft, the axis of the grid rudder unfolding shaft is located on the front side of the middle line plane of the grid rudder face, and the middle line plane of the grid rudder face is a parallel plane one half of the length of a chord away from the front edge plane of the grid rudder face. The grid rudder structure solves the problem that in the unfolding process of the grid rudder, due to large resisting moment produced through aerodynamic force, the rapid unfolding capability of the grid rudder is insufficient.
Description
Technical field
The present invention relates to one and be used in the missile-borne grid rudder structure of band raster rudder.
Background technology
Grid rudder rudder face is embedded in by numerous thin cell walls 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, carried out large quantity research in grid rudder application aspect therefore 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 deployed condition.In prior art, the axis of grid rudder axis of dilatation 10 ' is positioned in described grid rudder rudder face 20 ' midline plane 30 '.
At present, for the bullet design of burying in launched by airplane in bullet or shrapnel, when interior bullet or the bullet of burying is separated initial, needs to overcome aerodynamic drag square suffered by grid rudder rudder face expansion process, the rapid deployment of grid rudder rudder face could be realized; As everyone knows, the large advantage of grid rudder opposite planar rudder one is exactly convenient folding and can by air force rapid deployment, but under different free stream Mach number, attitude angle and the angle of spread, the power-assisted square that air force is launched to produce to grid rudder rudder face is different, when the angle of spread is less, air force is launched also may to produce obstruction to grid rudder rudder face.Therefore, how to reduce grid rudder expansion process aerodynamic drag square, improving rapid deployment ability needs research and solution emphatically in engineering design.
Free stream Mach number when existing solution generally has three kinds: one to be by reducing grid rudder rudder face and launching and flying height are to reduce incoming flow dynamic pressure; Two is limit body attitude angle when grid rudder rudder face launches, and makes attitude angle unlikely excessive; Three is by optimizing grid rudder physical 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; The third method can propose requirements at the higher level to grid rudder profile and structural design, is not easy to practical application.
Summary of the invention
The technical problem to be solved in the present invention is to provide one and is used in the missile-borne grid rudder structure of band raster rudder.This is used in the missile-borne grid rudder structure of band raster rudder and solves grid rudder rudder face in expansion process, due to the larger moment of resistance that air 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:
One is used in the missile-borne grid rudder structure of band raster rudder, and described grid rudder comprises grid rudder rudder face and is fixed on the grid rudder Connection Block on missile airframe;
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 plane at distance grid rudder rudder face leading edge plane 1/2 chord length place.
Further, grid rudder rudder face chord length is b, and the scope of the distance d of the axis distance grid rudder rudder face leading edge plane of grid rudder axis of dilatation is: 0≤d < b/2.
Further, described grid rudder Connection Block is convexly equipped in missile airframe surface.
The present invention proposes one and be used in the missile-borne grid rudder structure of band raster rudder, namely when grid rudder axis of dilatation Position Design, not according to conventional thought, grid rudder axis of dilatation position is selected in grid rudder rudder face midline plane, but before being arranged on grid rudder rudder face midline plane, as far as possible near grid rudder rudder face leading edge plane.
The present invention takes full advantage of particularity stressed in grid rudder rudder face expansion process, namely the axial moment M1 produced along grid rudder rudderpost to direction axial force and grid rudder axis of dilatation position closely related, grid rudder axis of dilatation position is the closer to grid rudder rudder face leading edge plane, 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, greatly can 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 method, the not only successful of aerodynamic drag square suffered by grid rudder rudder face expansion process relatively in the present invention, and simpler, can not increase ballistic design, configuration design and structural 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 deployed condition.
Fig. 3 is the position view of grid rudder axis of dilatation in the present invention.
Fig. 4 is the stressed schematic diagram of grid rudder rudder face expansion process in the present invention.
Fig. 5 is the simulation result schematic diagram of the leeward rudder face of grid rudder suffered aerodynamic moment in expansion process in the present invention.
Fig. 6 is the simulation result schematic diagram of grid rudder rudder face suffered aerodynamic moment in expansion process windward in the present invention.
Detailed description of the invention
Below in conjunction with accompanying drawing 3 to 6, the specific embodiment of the present invention is described.
As shown in Figure 3,4, one is used in the missile-borne grid rudder structure of band raster rudder, the grid rudder Connection Block 3 that described grid rudder comprises grid rudder rudder face 1 and is fixed on missile airframe 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 missile airframe 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 plane at distance grid rudder rudder face leading edge plane 1/2 chord length place.
When grid rudder rudder face 1 chord length is b, the scope of the distance d of the axis distance grid rudder rudder face leading edge plane 5 of grid rudder axis of dilatation 4 is: 0≤d < b/2.Get d=0 in the present embodiment, be located in grid rudder rudder face leading edge plane 5 by grid rudder axis of dilatation position.
Fig. 4 is the stressed schematic diagram of grid rudder rudder face expansion process in the present invention; What aerodynamic force produced mainly comprises two parts to the moment of grid rudder axis of dilatation 4: one is by along the axial axial force F 1 of grid rudder rudder face 1 rudder, 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 M1 or M2 launches grid rudder rudder face 1, 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, and obviously, 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 larger the closer to grid rudder rudder face leading edge plane 5, L1, and M1 helps exhibition ability stronger.
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, greatly can 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 point, the aerodynamic moment under the different angle of spread obtained by numerical computations, the corresponding rudder face of Fig. 5 is leeward rudder, the corresponding rudder face of Fig. 6 is rudder windward, and abscissa θ is the angle of spread, and ordinate is the aerodynamic moment coefficient around grid rudder axis of dilatation; Cml
q, Cml
zbe respectively grid rudder axis of dilatation to be positioned in grid rudder rudder face leading edge plane and in grid rudder rudder face midline plane time the aerodynamic moment coefficient that calculates, it is hinder rudder face to launch that negative value represents aerodynamic moment, and helps exhibition on the occasion of representing aerodynamic moment.
Result of calculation 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 grid rudder rudder face leading edge plane, and aerodynamic moment Cml
qbe all on the occasion of, help exhibition.When grid rudder axis of dilatation position being located in grid rudder rudder face midline plane, when the angle of spread is less, aerodynamic moment Cml
zbeing negative value, is hinder to launch, along with the angle of spread increases, and Cml
zbecome on the occasion of, slowly have and help exhibition ability, but under the identical angle of spread, Cml
zall be less than Cml
q; It is visible when grid rudder axis of dilatation position is located on front side of grid rudder rudder face midline plane, when being particularly arranged in grid rudder rudder face leading edge plane, greatly can reduce the aerodynamic drag square of grid rudder rudder face 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 description orientation adopted herein " on ", D score, "left", "right" etc. are all convenience in order to illustrate based on the orientation in accompanying drawing shown in drawing, in actual device, these orientation may be different due to the disposing way of device.
In sum, embodiment of the present invention only provides a kind of embodiment of the best, technology contents of the present invention and technical characterstic 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 all equivalence changes done according to shape of the present invention, structure and principle, be all encompassed in protection scope of the present invention.
Claims (3)
1. be used in the missile-borne grid rudder structure of band raster rudder, it is characterized in that, described grid rudder comprises grid rudder rudder face and is fixed on the grid rudder Connection Block on missile airframe;
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 plane at distance grid rudder rudder face leading edge plane 1/2 chord length place.
2. one according to claim 1 is used in the missile-borne grid rudder structure of band raster rudder, it is characterized in that, grid rudder rudder face chord length is b, and the scope of the distance d of the axis distance grid rudder rudder face leading edge plane of grid rudder axis of dilatation is: 0≤d < b/2.
3. one according to claim 1 is used in the missile-borne grid rudder structure of band raster rudder, it is characterized in that, described grid rudder Connection Block is convexly equipped in missile airframe surface.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| CN104613825A true CN104613825A (en) | 2015-05-13 |
| CN104613825B CN104613825B (en) | 2016-06-01 |
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| CN201510037305.4A Active 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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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260726A (en) * | 2019-05-28 | 2019-09-20 | 上海宇航系统工程研究所 | A kind of grid rudder arrangement |
| CN112693623A (en) * | 2020-12-21 | 2021-04-23 | 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 |
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| 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 |
Non-Patent Citations (1)
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| 余旭东 等: "《飞行器结构设计》", 1 April 2010, 西安：西北工业大学出版社 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110260726A (en) * | 2019-05-28 | 2019-09-20 | 上海宇航系统工程研究所 | A kind of grid rudder arrangement |
| CN110260726B (en) * | 2019-05-28 | 2021-09-03 | 上海宇航系统工程研究所 | Grid rudder device |
| CN112693623A (en) * | 2020-12-21 | 2021-04-23 | 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 |
| 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 |
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| CN104613825B (en) | 2016-06-01 |
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