CN104833276A - Synchronous unfolding mechanism for grid fins - Google Patents
Synchronous unfolding mechanism for grid fins Download PDFInfo
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- CN104833276A CN104833276A CN201510252313.0A CN201510252313A CN104833276A CN 104833276 A CN104833276 A CN 104833276A CN 201510252313 A CN201510252313 A CN 201510252313A CN 104833276 A CN104833276 A CN 104833276A
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Abstract
The invention relates to a synchronous unfolding mechanism for grid fins. The synchronous unfolding mechanism for the grid fins comprises a base body which is fixedly connected with one end of a model, a limiting ring is matched with the periphery of the base body, one ends of multiple connecting rods are hinged to the limiting ring through connecting shafts, the other ends of the connecting rods are movably connected with multiple grid fins through grid fin shafts, the periphery of each grid fin shaft is connected with a torsion spring in a sleeved mode, and the grid fins are evenly distributed on the periphery of the base body in the peripheral direction. The synchronous unfolding mechanism for the grid fins is simple in structure, convenient to use and capable of being connected with the test model, switching of the grid fins from the folding state to the unfolding state is achieved by using the connecting rods and the tension springs, the unfolding states of all the grid fins are synchronous, and the stable control of a trajectory is effectively achieved; by means of the synchronous unfolding mechanism for the grid fins, when all the grid fins are folded on the periphery of the model, the outer diameter between a pair of adjacent grid fins is not more than the maximum diameter of the model.
Description
Technical field
The present invention relates to trajectory emission test and field tests, particularly relate to a kind of lattice fin synchronous expansion mechanism that can be connected with test model.
Background technology
Lattice fin is a kind of novel missile wing, and it has, and tangential size is little, aspect ratio is large, hinge moment is little, lift efficiency is good and control efficiency advantages of higher, and is easy to be folded on bomb body, so there is good application prospect on tactical missile.Before Tactical Missiles is launched, being fixed in launching tube, is matched in clearance between body external diameter and launching tube, must be able to be folded on bomb body when therefore lattice fin is in cylinder, and ensures that its folding rear maximum outside diameter is no more than the diameter of model.And after body goes out cylinder, four lattice fins need by folded state synchronous expansion, thus realize the stability contorting to trajectory, therefore in the urgent need to relating to a kind of lattice fin synchronous expansion mechanism.
Summary of the invention
The applicant, for above-mentioned existing issue, is studied improvement, provides a kind of lattice fin synchronous expansion mechanism, utilizes the present invention can realize lattice fin by folding into expansion, and can ensure that expansion process is synchronous, thus realizes the stability contorting to trajectory.
The technical solution adopted in the present invention is as follows:
A kind of lattice fin synchronous expansion mechanism, comprise matrix, one end of described matrix and model is affixed, also spacing ring is coordinated in the periphery of described matrix, one end of many connecting rods by pitman shaft and described spacing ring hinged, the other end of described connecting rod is flexibly connected with multiple lattice fin by lattice fin axle, and be all socketed torque spring in the periphery of each lattice fin axle, each lattice fin is along the circumferential direction distributed in the periphery of matrix.
Further improvement as technique scheme:
Described matrix is circular, and the circumferencial direction along described matrix stretches out and forms multiple first boss, and each first boss is connected with one end of described model, along circumferencial direction also uniform multiple groove of described matrix by securing member and installing hole;
Described spacing ring is also circular, and formed multiple for coordinating the second boss of matrix at the inner circumferential extension of described spacing ring, each second boss is along the circumferential direction uniform;
Periphery at described model, the uniform lattice fin mounting groove of the circumferencial direction along model, the groove depth of described lattice fin mounting groove is identical with the thickness of described lattice fin.
Beneficial effect of the present invention is as follows:
Structure of the present invention is simple, easy to use, it can be connected with test model, utilize connecting rod, torque spring achieves the conversion of each lattice fin from folded state to deployed condition, each lattice fin deployed condition is synchronous, effectively achieve the stability contorting to trajectory, and utilize the present invention can also realize each lattice fin when being folded to model periphery, the external diameter between adjacent a pair lattice fin is no more than the maximum gauge of model.
Accompanying drawing explanation
Fig. 1 is perspective view of the present invention.
Fig. 2 is sectional structure schematic diagram of the present invention.
Fig. 3 is the structure for amplifying schematic diagram of Fig. 2 at A place.
Wherein: 1, matrix; 101, groove; 102, the first boss; 2, lattice fin; 3, spacing ring; 301, the second boss; 4, pitman shaft; 5, connecting rod; 6, torque spring; 7, lattice fin axle; 8, model; 801, lattice fin mounting groove.
Detailed description of the invention
Below in conjunction with accompanying drawing, the specific embodiment of the present invention is described.
As shown in Figure 1, Figure 2 and Figure 3, lattice fin synchronous expansion mechanism, comprise matrix 1, matrix 1 is affixed with the tail end of model 8, also coordinate spacing ring 3 in the periphery of matrix 1, one end of many connecting rods 5 is hinged by pitman shaft 4 and spacing ring 3, and the other end of connecting rod 5 is flexibly connected with multiple lattice fin 2 by lattice fin axle 7, all be socketed torque spring 6 in the periphery of each lattice fin axle 7, each lattice fin 2 is along the circumferential direction distributed in the periphery of matrix 1.As shown in Figure 1 and Figure 2, matrix 1 is circular, circumferencial direction along matrix 1 stretches out and is formed in multiple first boss 102(the present invention, first boss 102 is 8), each first boss 102 is connected with one end of model 8 by screw and installing hole, along circumferencial direction also uniform multiple groove 101 of matrix 1, further groove 101 of the present invention is 4.As shown in Figure 1 and Figure 2, above-mentioned spacing ring 3 is also circular, formed multiple for coordinating the second boss 301 of matrix 1 at the inner circumferential extension of spacing ring 3, second boss 301 is directly proportional to the quantity of groove 101, spacing ring 3 can be made by the second boss 301 to do to move freely axially along matrix 1 with coordinating of groove 101.Each second boss 301 is along the circumferential direction uniform.As shown in Figure 1, in the periphery of model 8, along the uniform lattice fin mounting groove 801 of circumferencial direction of model 8, the groove depth of lattice fin mounting groove 801 is identical with the thickness of lattice fin 2, and the quantity of described lattice fin mounting groove 801 is directly proportional to the quantity of lattice fin 2.
Specific embodiment of the invention process is as follows:
When model 8 is in launching tube, each lattice fin 2 is all folded in the lattice fin mounting groove 801 of model 8, each lattice fin 2 maximum outside diameter be after folding no more than model 8 diameter (namely the periphery of each lattice fin 2 and model 8 periphery be in same periphery), now torque spring 6 is in impaction state, there is certain tension force, after model 8 moves out of cylinder, four lattice fins 2 synchronous expansion under torque spring 6 and hydrodynamic comprehensive function, because each lattice fin 2 is all connected with spacing ring 3 by connecting rod 5, therefore spacing ring 3 is driven to do axially movable along the groove 101 of matrix 1, also therefore ensure that the synchronous expansion of four lattice fins 2, thus realize the control of lattice fin 2 pairs of model trajectories.
More than describing is explanation of the invention, and be not the restriction to invention, limited range of the present invention is see claim, and when without prejudice to basic structure of the present invention, the present invention can do any type of amendment.
Claims (4)
1. lattice fin synchronous expansion mechanism, it is characterized in that: comprise matrix (1), described matrix (1) is affixed with one end of model (8), spacing ring (3) is also coordinated in the periphery of described matrix (1), one end of many connecting rods (5) is hinged by pitman shaft (4) and described spacing ring (3), the other end of described connecting rod (5) is flexibly connected with multiple lattice fin (2) by lattice fin axle (7), all be socketed torque spring (6) in the periphery of each lattice fin axle (7), each lattice fin (2) is along the circumferential direction distributed in the periphery of matrix (1).
2. lattice fin synchronous expansion mechanism as claimed in claim 1, it is characterized in that: described matrix (1) is for circular, circumferencial direction along described matrix (1) stretches out and forms multiple first boss (102), each first boss (102) is connected with one end of described model (8) by securing member and installing hole, along circumferencial direction also uniform multiple groove (101) of described matrix (1).
3. lattice fin synchronous expansion mechanism as claimed in claim 1, it is characterized in that: described spacing ring (3) is also for circular, formed multiple for coordinating second boss (301) of matrix (1) at the inner circumferential extension of described spacing ring (3), each second boss (301) is along the circumferential direction uniform.
4. lattice fin synchronous expansion mechanism as claimed in claim 1, it is characterized in that: the periphery in described model (8), the uniform lattice fin mounting groove (801) of the circumferencial direction along model (8), the groove depth of described lattice fin mounting groove (801) is identical with the thickness of described lattice fin (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510252313.0A CN104833276B (en) | 2015-05-18 | 2015-05-18 | Lattice fin synchronous expansion mechanism |
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|---|---|---|---|
| CN201510252313.0A CN104833276B (en) | 2015-05-18 | 2015-05-18 | Lattice fin synchronous expansion mechanism |
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| CN104833276A true CN104833276A (en) | 2015-08-12 |
| CN104833276B CN104833276B (en) | 2016-09-14 |
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| CN201510252313.0A Active CN104833276B (en) | 2015-05-18 | 2015-05-18 | Lattice fin synchronous expansion mechanism |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292410A (en) * | 2015-10-30 | 2016-02-03 | 北京精密机电控制设备研究所 | Pop-up decelerating wing system driven by initiating explosive device and provided with locking function |
| CN105730678A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Foldable grid control plane |
| CN106143911A (en) * | 2016-07-13 | 2016-11-23 | 西藏长源动力科技有限公司 | A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched |
| CN106382860A (en) * | 2016-11-11 | 2017-02-08 | 万耀东 | Folding type ground drilling bomb |
| CN106781830A (en) * | 2016-12-28 | 2017-05-31 | 哈尔滨工业大学 | A kind of two degrees of freedom simulator of grid rudder aircraft |
| CN109595997A (en) * | 2019-01-02 | 2019-04-09 | 西安微电子技术研究所 | The synchronization four-way folding wings locking unfolding mechanism and its method of anti high overload impact |
| CN110127037A (en) * | 2019-06-09 | 2019-08-16 | 西北工业大学 | A kind of cylindric vertically taking off and landing flyer using foldable single screw and grid fin |
| CN110230958A (en) * | 2019-07-22 | 2019-09-13 | 哈尔滨工业大学 | A kind of expandable type Wei Qun mechanism |
| CN112902769A (en) * | 2021-03-09 | 2021-06-04 | 华中科技大学 | Grid wing, novel rocket stage interval structure, control method and application |
| CN113267093A (en) * | 2020-03-13 | 2021-08-17 | 北京星际荣耀空间科技股份有限公司 | Grid rudder structure and rocket with same |
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| WO2002079716A1 (en) * | 2001-03-20 | 2002-10-10 | Bofors Defence Ab | Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith |
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| US3861627A (en) * | 1972-12-30 | 1975-01-21 | Dynamit Nobel Ag | Foldable control flap unit, especially for rockets |
| US3944168A (en) * | 1973-03-14 | 1976-03-16 | Etat Francais | Artillery projectile with spreading tail assembly |
| US5048773A (en) * | 1990-06-08 | 1991-09-17 | The United States Of America As Represented By The Secretary Of The Army | Curved grid fin |
| RU2082941C1 (en) * | 1994-07-04 | 1997-06-27 | Конструкторское бюро приборостроения | Rocket with aerodynamic brake |
| WO2002079716A1 (en) * | 2001-03-20 | 2002-10-10 | Bofors Defence Ab | Method of synchronizing fin fold-out on a fin-stabilized artillery shell, and an artillery shell designed in accordance therewith |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105292410A (en) * | 2015-10-30 | 2016-02-03 | 北京精密机电控制设备研究所 | Pop-up decelerating wing system driven by initiating explosive device and provided with locking function |
| CN105730678A (en) * | 2016-02-18 | 2016-07-06 | 江西洪都航空工业集团有限责任公司 | Foldable grid control plane |
| CN105730678B (en) * | 2016-02-18 | 2018-01-30 | 江西洪都航空工业集团有限责任公司 | A kind of folding grid rudder face |
| CN106143911A (en) * | 2016-07-13 | 2016-11-23 | 西藏长源动力科技有限公司 | A kind of individual soldier carries, can cartridge type storage and the collapsible unmanned plane launched |
| CN106382860A (en) * | 2016-11-11 | 2017-02-08 | 万耀东 | Folding type ground drilling bomb |
| CN106781830A (en) * | 2016-12-28 | 2017-05-31 | 哈尔滨工业大学 | A kind of two degrees of freedom simulator of grid rudder aircraft |
| CN109595997A (en) * | 2019-01-02 | 2019-04-09 | 西安微电子技术研究所 | The synchronization four-way folding wings locking unfolding mechanism and its method of anti high overload impact |
| CN109595997B (en) * | 2019-01-02 | 2021-11-30 | 西安微电子技术研究所 | High overload impact resistant synchronous four-channel folding wing locking and unfolding mechanism and method thereof |
| CN110127037A (en) * | 2019-06-09 | 2019-08-16 | 西北工业大学 | A kind of cylindric vertically taking off and landing flyer using foldable single screw and grid fin |
| CN110230958A (en) * | 2019-07-22 | 2019-09-13 | 哈尔滨工业大学 | A kind of expandable type Wei Qun mechanism |
| CN113267093A (en) * | 2020-03-13 | 2021-08-17 | 北京星际荣耀空间科技股份有限公司 | Grid rudder structure and rocket with same |
| CN112902769A (en) * | 2021-03-09 | 2021-06-04 | 华中科技大学 | Grid wing, novel rocket stage interval structure, control method and application |
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| Publication number | Publication date |
|---|---|
| CN104833276B (en) | 2016-09-14 |
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