CN111121560B - Rocket control surface folding and unfolding rotary driving device - Google Patents
Rocket control surface folding and unfolding rotary driving device Download PDFInfo
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- CN111121560B CN111121560B CN201911353685.7A CN201911353685A CN111121560B CN 111121560 B CN111121560 B CN 111121560B CN 201911353685 A CN201911353685 A CN 201911353685A CN 111121560 B CN111121560 B CN 111121560B
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- actuating cylinder
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/14—Stabilising arrangements using fins spread or deployed after launch, e.g. after leaving the barrel
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Abstract
The invention discloses a rocket control surface folding and unfolding rotary driving device which comprises an actuating cylinder with the functions of an initial lock and an in-place lock, a rack and gear mechanism, a rotary locking mechanism, a rotating mechanism and a linear steering engine, wherein the actuating cylinder is provided with a first locking mechanism and a second locking mechanism; the peripheral equipment comprises an arrow body, a control surface and a control surface rotating shaft; the actuating cylinder is fixed on the inner wall of the arrow body, a piston rod of the actuating cylinder is connected with a rack and pinion mechanism through a pin, the rack and pinion mechanism is rotatably connected with the control surface through a rotation locking mechanism, and an inner control surface rotating shaft is fixedly connected with the rotation locking mechanism. The invention saves the radial installation space in the rocket, is miniaturized and light, and can adapt to the folding and unfolding of the control surface with large load.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a rocket control surface folding and unfolding rotation driving device.
Background
With the development of the aerospace activities of human beings, the return technology of the rocket is more and more emphasized by people, on one hand, the returned real object can be detected to directly know the working condition of the returned real object in flight, on the other hand, the returned real object can be repeatedly used after being tested and repaired, so that a large amount of manpower and material resources can be saved, and time is won for model development. The control surface is an important part on the rocket, plays a role in stabilizing the rocket body and can realize operation, so that the problem of flight stability when the rocket returns is firstly solved by researching the return technology of the rocket, namely a reliable control surface folding and unfolding rotary driving device is developed.
The existing control surface folding and unfolding rotary driving device mainly comprises a spring force type, a compressed air actuating cylinder type, a gas actuating cylinder type and a hydraulic actuating cylinder type. The spring force type control surface folding and unfolding rotary driving device adopts a spring as a power source for unfolding movement of the control surface, and the spring is in a stressed state for a long time and is easy to generate permanent deformation, so that the reliability of the device is reduced. The actuating cylinder type rudder surface folding and unfolding rotary driving device adopts an actuating cylinder as a power source for the unfolding motion of the rudder surface, the actuating cylinder only outputs linear motion with a certain stroke and does not provide the functions of an initial lock and an in-place lock, the locking of the initial folding state and the locking of the unfolding and in-place state of the rudder surface are realized by other locking mechanisms, the locking mechanism of the initial folding state generally adopts a mode of locking a shear pin, the locking mechanism of the unfolding and in-place state generally adopts a mode of locking a spring lock pin, the whole device is complex, the shear pin of the locking mechanism of the initial folding state is required to be firstly sheared to drive the rudder surface to unfold when the actuating cylinder moves, the shear torque of the shear pin is generally 1.5 times of the maximum aerodynamic load of the rudder surface, the thrust of the actuating cylinder is generally 1.5 times of the thrust converted by the shear torque of the shear pin, namely the thrust of the actuating cylinder is generally 2.25 times of the thrust converted by the maximum aerodynamic load of the rudder surface, therefore, the safety factor is continuously accumulated, so that the required value of the output thrust of the actuating cylinder is larger, the volume of the actuating cylinder is larger, and the volume of the whole device is larger. In addition, the locking effect of the locking mechanism in the unfolding-to-position state is closely related to the in-position angular velocity of the control surface, and when the in-position angular velocity of the control surface is larger than a certain value, the locking mechanism in the unfolding-to-position state fails due to the fact that the response of the spring is not timely, and disastrous results are caused. The existing control surface folding and unfolding rotary driving device usually adopts a rotary steering engine to realize the rotary motion of the control surface after being unfolded in place, however, when the pneumatic load requirement value of the control surface is larger, the diameter and the length of the steering engine for driving the control surface to rotate are also greatly increased, and because the steering engine adopts an installation mode of being uniformly distributed and arranged along the radial direction of an arrow body in the arrow body, the occupied size of the radial installation space in the arrow body is larger, and the diameter of the whole rocket is increased finally. Therefore, the existing rudder surface folding and unfolding rotary driving device has the defects of complex structure, larger occupied radial space size and larger weight, is not suitable for the requirement of a return rocket, and is necessary to develop a rudder surface folding and unfolding driving device which can save the radial installation space in the rocket body, is miniaturized and lightened, and can adapt to large loads in order to reduce the transverse size of the rocket, save the storage and transportation space of the rocket, and improve the carrying capacity of vehicles, ships and airplanes.
Disclosure of Invention
In view of the above, the invention provides a rocket control surface folding and unfolding rotation driving device, which saves the radial installation space in the rocket, is small and light, and can adapt to the control surface folding and unfolding of a large load.
The technical scheme adopted by the invention is as follows:
a rocket control surface folding and unfolding rotary driving device comprises an actuating cylinder with the functions of an initial lock and an in-place lock, a rack and gear mechanism, a rotary locking mechanism, a rotating mechanism and a linear steering engine; the peripheral equipment comprises an arrow body, a control surface and a control surface rotating shaft;
the actuating cylinder is fixed on the inner wall of the arrow body, a piston rod of the actuating cylinder is connected with a rack and gear mechanism through a pin, the rack and gear mechanism is rotationally connected with the control surface through a rotation locking mechanism, and a control surface rotating shaft in the control surface is fixedly connected with the rotation locking mechanism; in the initial state, the actuating cylinder is in the initial lock locking state, the control surface is locked by itself under the action of the rotary locking mechanism, the actuating cylinder works, and a piston rod of the actuating cylinder drives the rack-and-pinion mechanism to move, so that the control surface rotates by 90 degrees around the axis of the gear shaft to complete the unfolding; after the control surface is unfolded in place, the actuator cylinder in-place lock is locked, the rotation locking mechanism is unlocked, the control surface can rotate around the control surface rotation shaft, meanwhile, the control surface and the rotating mechanism are locked, and the linear steering engine drives the rotating mechanism to rotate to drive the control surface to rotate around the control surface rotation shaft.
Further, the rotation locking mechanism comprises a control surface support, a hook, a spring, a pressure plate and a thread plug;
the control surface support is L-shaped, the horizontal part of the control surface support faces outwards, and the vertical part of the control surface support is arranged in the control surface and is fixedly connected with the control surface rotating shaft; the hook is L-shaped, a guide groove is processed in the control surface support, the hook can move along the guide groove, the spring is limited between the top end of the vertical part of the hook and the thread plug, and the vertical part of the hook is limited in a groove at a corresponding position in the control surface under the action of the spring, so that the rotary locking between the control surface and the control surface rotating shaft in the unfolding process is realized; the clamp plate is fixed at the arrow body inner wall, and after the control surface expanded in place, the contact of couple horizontal part bottom and clamp plate made the spring compression, made the couple vertical part throw off from the recess and realized the unblock.
Furthermore, the rotating mechanism is a rocker arm, a sliding groove is formed in the rocker arm, an output shaft of the linear steering engine is connected with the rocker arm through a pin shaft, and the pin shaft can move along the sliding groove.
Further, the rack and pinion mechanism comprises a helical rack, a helical pinion shaft and a helical pinion shaft base;
the bevel rack is connected with the piston rod of the actuating cylinder through a pin, the bevel rack is in meshing transmission with a bevel gear shaft, the bevel gear shaft is installed on a bevel gear shaft base, and the bevel gear shaft base is fixedly connected with the rocket body.
Further, the locking mode of the control surface and the rotating mechanism is as follows: the bottom end of the control surface is provided with a groove, and the top end of the rotating mechanism is provided with a boss clamped with the groove.
Further, the groove is a trapezoidal groove, and the boss is a trapezoidal table.
Has the advantages that:
1. the invention can realize the folding and unfolding of the control surface, and adopts the actuating cylinder with the functions of the initial lock and the in-place lock, so that the whole device does not need to additionally design a locking mechanism in the initial folding state and a locking mechanism in the unfolding in-place state, and the whole device has simple structure, higher reliability and smaller occupied installation space; and secondly, the transmission mode of the linear steering engine for linearly driving the rotating mechanism is adopted, so that the occupied size of the radial space inside the rocket can be reduced to the maximum extent.
2. The invention adopts a locking mode of the hook lock of the hook to realize automatic locking and automatic unlocking between the control surface and the control surface rotating shaft, and has simple structure, easy realization and space saving.
3. The invention adopts the transmission mode of meshing the helical rack and the helical gear shaft, so that the whole driving device has more compact structure and smaller volume.
Drawings
FIG. 1 is a front view of the overall structure of the present invention;
FIG. 2 is a cross-sectional view A-A of FIG. 1;
FIG. 3 is a left side view of the present invention;
FIG. 4 is a bottom view of the present invention;
FIG. 5 is a cross-sectional view B-B of FIG. 2;
fig. 6 is a cross-sectional view C-C of fig. 1.
The device comprises a 1-linear steering engine, a 2-arrow body, a 3-pressing plate, a 4-rocker arm, a 5-supporting seat, a 6-base, a 7-hook, an 8-control surface support, a 9-control surface, a 10-actuating cylinder, a 11-oblique rack, a 12-oblique gear shaft, a 13-thrust ball bearing, a 14-plug, a 15-threaded pin, a 16-spring, a 17-threaded plug, a 18-control surface rotating shaft and a 19-oblique gear shaft base.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment provides a rocket control surface folding and unfolding rotary driving device, which comprises an actuating cylinder 10 with functions of an initial lock and a target lock, a helical rack 11, a helical gear shaft 12, a helical gear shaft base 19, a rotary locking mechanism, a rocker arm 4 and a linear steering engine 1, wherein the actuating cylinder has the functions of the initial lock and the target lock; the peripheral devices are an arrow body 2, a control surface 9 and a control surface rotating shaft 18.
The initial lock of the actuator cylinder 10 is a 'strong locking weak unlocking' structure, the structure adopts the cross section of a rectangular block as a shearing surface to realize 'strong locking' in the initial process, and when unlocking is needed, a piston rod of the actuator cylinder 10 can be easily unlocked only by sinking the rectangular block with small force. The in-place lock of the actuating cylinder 10 is a 'latch lock' structure, and when the piston rod of the actuating cylinder 10 moves to a specified stroke, two latches are inserted into the locking holes of the piston rod to realize in-place locking of the piston rod of the actuating cylinder 10.
The rotation locking mechanism comprises a control surface bracket 8, a hook 7, a spring 16, a pressure plate 3 and a thread plug 17; the control surface support 8 is L-shaped, the horizontal part of the control surface support 8 faces outwards, and the vertical part is arranged in the control surface 9 and is fixedly connected with the control surface rotating shaft 18; the hook 7 is L-shaped, a guide groove is processed in the control surface support 8, the hook 7 can move along the guide groove, the spring 16 is limited between the top end of the vertical part of the hook 7 and the thread plug 17, and under the action of the spring 16, the vertical part of the hook 7 is limited in a groove at a corresponding position in the control surface 9, so that the control surface 9 is rotationally locked with the control surface rotating shaft 18 in the unfolding process; the pressing plate 3 is fixedly connected to the inner wall of the arrow body 2 through bolts, after the control surface 9 is unfolded in place, the bottom end of the horizontal part of the hook 7 is in contact with the pressing plate 3 to compress the spring 16, the vertical part of the hook 7 is separated from the groove to achieve unlocking, and meanwhile, the pressing plate 3 prevents the control surface support 8 from overshooting and plays a role of a protection mechanism.
The actuator cylinder 10 is mounted on the inner wall of the rocket body 2 through bolts, a piston rod of the actuator cylinder 10 is in pin connection with the helical rack 11, the helical rack 11 is in meshing transmission with the helical gear shaft 12, the helical gear shaft 12 is mounted on the helical gear shaft base 19, the helical gear shaft base 19 is in bolt connection with the rocket body 2, the front end of the helical gear shaft 12 is provided with the thrust ball bearing 13, the thrust ball bearing can bear certain axial thrust, and the plug 14 is used for limiting the shaft end of the thrust ball bearing 13. The bevel gear shaft 12 is connected with the control surface support 8 through a threaded pin 15, the other end of the bevel gear shaft 12 penetrates into a center hole of the base 6, the base 6 plays a supporting role, and the base 6 is connected with the arrow body 2 through a bolt.
The bottom end of the control surface 9 is provided with a trapezoidal groove, and the top end of the rocker arm 4 is provided with a trapezoidal boss clamped with the trapezoidal groove. The rocker arm 4 is provided with a sliding groove, the output shaft of the linear steering engine 1 is connected with the rocker arm 4 through a pin shaft, the pin shaft can move along the sliding groove, and the linear steering engine 1 is connected with the arrow body 2 through a bolt. The lower end of the rocker arm 4 is limited in a groove of the supporting seat 5, the supporting seat 5 is connected with the base 6 through a bolt, and the rocker arm 4 can rotate in the groove of the supporting seat 5 under the driving of the linear steering engine 1.
The working process is as follows: initially, the actuator cylinder 10 is in the initial lock locked state and the control surface 9 is in the initial folded locked state. After an ignition instruction is sent by an electrical system on the rocket, gunpowder inside the actuating cylinder 10 starts to burn and generates high-temperature and high-pressure gas to unlock the initial lock of the actuating cylinder 10, and a piston rod of the actuating cylinder 10 starts to move. The piston rod of the actuating cylinder 10 pushes the helical rack 11 to move forwards. The helical rack 11 drives the helical gear shaft 12 to rotate, and the helical gear shaft 12 drives the control surface support 8 to rotate together and drives the control surface 9 to unfold for 90 degrees around the axis of the helical gear shaft 12. During the unfolding process, under the action of the spring 16, the horizontal part of the hook 7 is limited in a groove at a corresponding position in the control surface 9, so that the rotation locking between the control surface 9 and the control surface rotation shaft 18 is kept, and the control surface 9 is prevented from rotating around the control surface rotation shaft 18.
When the control surface 9 is unfolded to the proper position, the actuating cylinder 10 is locked by the proper position lock, and the control surface 9 is in the unfolded to proper position locking state. At this time, the bottom end of the hook 7 collides with the pressure plate 3, the hook 7 retracts in the guide groove in the control surface support 8, meanwhile, the spring 16 is compressed, when the horizontal part of the hook 7 is completely separated from the groove in the corresponding position in the control surface 9, the rotation locking mechanism is unlocked, the rotation locking between the control surface 9 and the control surface rotating shaft 18 is released, the control surface 9 can rotate around the control surface rotating shaft 18, and at this time, the trapezoidal groove of the control surface 9 is meshed with the trapezoidal boss of the rocker arm 4. The lower end of the rocker arm 4 is embedded in a recess of the bearing block 5 and is rotatable in the recess. After the linear steering engine 1 receives a motion instruction, the linear steering engine 1 drives the rocker arm 4 to rotate, and the rocker arm 4 further drives the control surface 9 to rotate around the control surface rotating shaft 18, so that the posture of the rocket during flying is adjusted, and the stability of the rocket during flying is ensured.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A rocket control surface folding and unfolding rotary driving device is characterized by comprising an actuating cylinder with functions of an initial lock and a target locking, a rack and gear mechanism, a rotary locking mechanism, a rotating mechanism and a linear steering engine; the peripheral equipment comprises an arrow body, a control surface and a control surface rotating shaft;
the actuating cylinder is fixed on the inner wall of the arrow body, a piston rod of the actuating cylinder is connected with a rack and gear mechanism through a pin, the rack and gear mechanism is rotationally connected with the control surface through a rotation locking mechanism, and a control surface rotating shaft in the control surface is fixedly connected with the rotation locking mechanism; in the initial state, the actuating cylinder is in the initial lock locking state, the control surface is locked by itself under the action of the rotary locking mechanism, the actuating cylinder works, and a piston rod of the actuating cylinder drives the rack-and-pinion mechanism to move, so that the control surface rotates by 90 degrees around the axis of the gear shaft to complete the unfolding; after the control surface is unfolded in place, the actuator cylinder in-place lock is locked, the rotation locking mechanism is unlocked, the control surface can rotate around a control surface rotation shaft, meanwhile, the control surface and the rotation mechanism are locked, and the linear steering engine drives the rotation mechanism to rotate to drive the control surface to rotate around the control surface rotation shaft;
the rotary locking mechanism comprises a control surface support, a hook, a spring, a pressure plate and a thread plug;
the control surface support is L-shaped, the horizontal part of the control surface support faces outwards, and the vertical part of the control surface support is arranged in the control surface and is fixedly connected with the control surface rotating shaft; the hook is L-shaped, a guide groove is processed in the control surface support, the hook can move along the guide groove, the spring is limited between the top end of the vertical part of the hook and the thread plug, and the vertical part of the hook is limited in a groove at a corresponding position in the control surface under the action of the spring, so that the rotary locking between the control surface and the control surface rotating shaft in the unfolding process is realized; the clamp plate is fixed at the arrow body inner wall, and after the control surface expanded in place, the contact of couple horizontal part bottom and clamp plate made the spring compression, made the couple vertical part throw off from the recess and realized the unblock.
2. A rocket rudder surface folding and unfolding rotary driving device as claimed in claim 1, wherein the rotating mechanism is a rocker arm, a chute is arranged on the rocker arm, an output shaft of the linear steering engine is connected with the rocker arm through a pin shaft, and the pin shaft can move along the chute.
3. A rocket rudder surface folding and unfolding rotary driving device as recited in claim 1, wherein said rack and pinion mechanism includes a helical rack, a helical pinion shaft and a helical pinion shaft base;
the bevel rack is connected with the piston rod of the actuating cylinder through a pin, the bevel rack is in meshing transmission with a bevel gear shaft, the bevel gear shaft is installed on a bevel gear shaft base, and the bevel gear shaft base is fixedly connected with the rocket body.
4. A rocket rudder surface folding and unfolding rotary driving device as recited in claim 1, wherein the locking manner of the rudder surface and the turning mechanism is: the bottom end of the control surface is provided with a groove, and the top end of the rotating mechanism is provided with a boss clamped with the groove.
5. A rocket rudder surface folding and unfolding rotary drive device as claimed in claim 4, wherein said grooves are trapezoidal grooves and said bosses are trapezoidal platforms.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911353685.7A CN111121560B (en) | 2019-12-25 | 2019-12-25 | Rocket control surface folding and unfolding rotary driving device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911353685.7A CN111121560B (en) | 2019-12-25 | 2019-12-25 | Rocket control surface folding and unfolding rotary driving device |
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| CN111121560A CN111121560A (en) | 2020-05-08 |
| CN111121560B true CN111121560B (en) | 2022-08-09 |
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| CN201911353685.7A Active CN111121560B (en) | 2019-12-25 | 2019-12-25 | Rocket control surface folding and unfolding rotary driving device |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114136157A (en) * | 2020-09-04 | 2022-03-04 | 北京恒星箭翔科技有限公司 | Guidance projectile body that 40mm rocket tube sought with general strapdown |
| CN112173073B (en) * | 2020-09-25 | 2023-05-26 | 中国直升机设计研究所 | Single steering engine control double vertical fin control structure |
| CN112665468B (en) * | 2020-12-21 | 2023-08-15 | 兰州空间技术物理研究所 | Novel strong locking and weak unlocking mechanism |
| CN112829924B (en) * | 2020-12-31 | 2022-12-13 | 上海机电工程研究所 | Retractable duck steering mechanism |
| CN113639595A (en) * | 2021-09-09 | 2021-11-12 | 陕西航天时代导航设备有限公司 | Steering engine system |
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| US8933383B2 (en) * | 2010-09-01 | 2015-01-13 | The United States Of America As Represented By The Secretary Of The Army | Method and apparatus for correcting the trajectory of a fin-stabilized, ballistic projectile using canards |
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| CN102407939A (en) * | 2011-09-30 | 2012-04-11 | 北京航空航天大学 | Variable flat plate type bionic leading edge flap device |
| RU2520846C1 (en) * | 2013-03-29 | 2014-06-27 | Открытое акционерное общество "Военно-промышленная корпорация "Научно-производственное объединение машиностроения" | Rocket aerodynamic rudder |
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