CN107576228A - A kind of high synchronism rudder face folding and expanding mechanism - Google Patents
A kind of high synchronism rudder face folding and expanding mechanism Download PDFInfo
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- CN107576228A CN107576228A CN201710696098.2A CN201710696098A CN107576228A CN 107576228 A CN107576228 A CN 107576228A CN 201710696098 A CN201710696098 A CN 201710696098A CN 107576228 A CN107576228 A CN 107576228A
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- rudder face
- rudderpost
- rudder
- claw
- rack
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Abstract
The invention discloses a kind of high synchronism rudder face folding and expanding mechanism, rudder face folding and expanding mechanism employs an actuator while promotes four rack motions, pass through the gear motion of rack pinion again, four rudder faces of drive are reliable, synchronously deploy, rudder face expansion makes its positive lock by wedge structure afterwards in place, then four rudder face rotations are driven by four steering wheels, realizes the stability control to missile flight.The present invention can make rudder face expansion have higher synchronism, and compact-sized, in light weight, transmission efficiency.
Description
Technical field
The present invention relates to field of aerospace technology, and in particular to a kind of high synchronism rudder face folding and expanding mechanism.
Background technology
Existing rudder face folding and expanding mechanism, it is most of using torsion spring type, connecting-rod mechanism type, worm drive formula driver
Structure, and the expansion of four rudder faces needs four independent actuator as power source, therefore, existing rudder face folding and expanding mechanism
Rudder face expansion synchronism is poor, in addition, torsion spring is chronically at stress, easily produces stress failures, elastic potential energy is reduced, made
Rudder face expansion is not in place, and mechanical stability is poor；The installation of connecting-rod mechanism type rudder face folding and expanding mechanism needs larger installation empty
Between, general volume is larger, heavier mass；Although the space that worm drive formula rudder face folding and expanding mechanism takes is small, in light weight,
It is that transmission efficiency is low.At present, a kind of miniaturization, lightweight, transmission efficiency and the high rudder face of expansion synchronism is developed to fold
Development mechanism be the development of China missilery there is an urgent need to.
The content of the invention
In view of this, the invention provides a kind of high synchronism rudder face folding and expanding mechanism so that rudder face expansion have compared with
High synchronism, and compact-sized, in light weight, transmission efficiency.
Specific embodiments of the present invention are as follows：
A kind of high synchronism rudder face folding and expanding mechanism, the rudder face folding and expanding mechanism include gear mechanism, claw and lock
Determine block, ancillary equipment is rudder face, rudderpost and steering wheel；
Gear mechanism is locked with claw by shear pin, and gear shaft forms screw auxiliary structure, claw and rudderpost with claw
Engaging；Rudder face is arranged in clamping block by rudderpost, and the axis direction of rudderpost is interference fitted perpendicular to rudder face, rudderpost with rudder face；
Gear mechanism driving claw rotates, and makes rudderpost drive rudder face to rotate expansion, and rudder face expansion passes through clamping block afterwards in place
Locking；After gear mechanism continues to move, and cuts shear pin, and claw separates with rudderpost, clamping block rotation, rotation are driven by steering wheel
Rotor shaft direction is vertical with rudderpost axis direction, rudder face is realized rotation.
Further, the gear mechanism uses rack pinion, rack Tong Guo " Swastika " shape connector and external impetus
Mechanism connects, and rack Gu is scheduled on " Swastika " end of shape connector, the direction of motion Yu the " Swastika of rack " plane where shape connector is mutual
Perpendicular, rack and pinion engages, and the rotation direction of gear is consistent with rudderpost rotation direction.
Further, the clamping block is provided with the wedge-shaped slot being engaged with rudder face, is locked in place for rudder face expansion.
Further, the clamping block is connected by shaft coupling with steering wheel.
Beneficial effect：
1st, the present invention drives rudder face expansion using gear mechanism, and fast response time, reliable and synchronism is high, and gear movement passes
Efficiency of movement is high, compact-sized.
2nd, gear mechanism of the present invention uses rack pinion, rack Tong Guo " Swastika " shape connector and external impetus mechanism connect
Connect, the rudder face of folded state and gear drive are staggered placement, space-consuming position is small.
3rd, clamping block of the invention is provided with the wedge-shaped slot being engaged with rudder face so that the mode letter that rudder face expansion locks in place
It is single reliable.
Brief description of the drawings
Fig. 1 is overall structure diagram of the present invention；
Fig. 2 is the top view of the present invention；
Fig. 3 is the upward view of the present invention；
Fig. 4 is the schematic diagram of servo driving rudder face of the present invention；
Fig. 5 is the initial position figure of rudder face expansion of the present invention.
Wherein, 1- top covers, 2- bomb bodys, 3- actuator, 4- racks, 5- gears, 6- " Swastika " shape connectors, 7- claws, 8- are cut
Cut pin, 9- rudderposts, 10- rudder faces, 11- clamping blocks, 12- shaft couplings, 13- steering wheels.
Embodiment
The present invention will now be described in detail with reference to the accompanying drawings and examples.
The present invention principle be：Rudder face folding and expanding mechanism employs an actuator while promotes four rack motions,
Again by the gear motion of rack pinion, four rudder faces of drive are reliable, synchronously deploy, and rudder face expansion passes through wedge shape and tied afterwards in place
Structure makes its positive lock, then drives four rudder face rotations by four steering wheels, realizes the stability control to missile flight.
High synchronism rudder face folding and expanding mechanism provided by the invention include rack 4, the, " Swastika of gear 5 " shape connector 6, card
Pawl 7, clamping block 11 and shaft coupling 12, ancillary equipment are rudder face 10, rudderpost 9, steering wheel 13, top cover 1, bomb body 2 and actuator 3, such as
Shown in Fig. 1, Fig. 2.
Top cover 1 is bolted with bomb body 2, and actuator 3 is installed on , " Swastika on top cover 1 " shape connector 6 and actuator 3
Piston rod be fixedly connected, four Gu of rack 4 are scheduled on " Swastika " four ends of shape connector 6, the direction of motion Yu " Swastika of rack 4 "
The place plane of shape connector 6 is orthogonal, four gears 5 and four engaged transmissions of rack 4.As shown in figure 3, four claws 7 are logical
Cross shear pin 8 to lock with four gears 5, screw auxiliary structure is formed between claw 7 and gear shaft.Rudderpost 9 has four on end face
Individual groove, four projections and four grooves on the end face of rudderpost 9 of the end face of claw 7 are held tightly, rotation direction and the gear 5 of rudderpost 9
Rotation direction is consistent.Rudder face 10 is arranged in clamping block 11 by rudderpost 9, and the axis direction of rudderpost 9 is perpendicular to rudder face 10, rudderpost
9 are interference fitted with rudder face 10, are connected between four clamping blocks 11 and four steering wheels 13 by four shaft couplings 12, as shown in Figure 4.
As shown in figure 5, the confined planes of rudder face 10 are wedge-shaped block structure, the confined planes of clamping block 11 are wedge-shaped groove structure, should
Fit structure can make the positive lock after expansion in place of rudder face 10.
Specific work process is：When initial, the piston rod of actuator 3 is in the lock state, and four rudder faces 10, which are in, to be folded
State.After the electric igniter of actuator 3 is under fire, the piston rod of actuator 3 unblock, and drive " Swastika " shape connector 6 is moved downward, entered
And drive four racks 4 to move downward, rotated by the gear motion drive claw 7 of rack 4 and gear 5, due to it is initial when block
Locked by shear pin 8 between pawl 7 and gear 5, therefore when shear pin 8 is not cut, can be seen between claw 7 and gear 5
Holding state is in as being rigidly connected, when four projections on the end face of claw 7 and initial four grooves on the end face of rudderpost 9,
With the rotation of gear 5, claw 7 drives rudderpost 9 to move together, due to being interference fit, rudderpost 9 between rudderpost 9 and rudder face 10
Rudder face 10 is driven to deploy in place, rudder face 10 and the positive lock of clamping block 11.
After rudder face 10 locks, rack 4 continues band moving gear 5 and moved, when four raised enclasping forces are more than on the end face of claw 7
During the shearing force of shear pin 8, shear pin 8 is cut, the latch-release between claw 7 and gear 5.Due to claw 7 and gear shaft
Between be worm drive, with being rotated further for gear 5, four projections on the end face of claw 7 and four on the end face of rudderpost 9 are recessed
Groove is gradually disengaged.When completely isolated after, four steering wheels 13 drive four clamping blocks 11 to rotate by four shaft couplings 12, and then
Drive four rudder faces 10 to rotate, realize the stability control to missile flight.
In summary, presently preferred embodiments of the present invention is these are only, is not intended to limit the scope of the present invention.
Within the spirit and principles of the invention, any modification, equivalent substitution and improvements made etc., it should be included in the present invention's
Within protection domain.
Claims (4)
- A kind of 1. high synchronism rudder face folding and expanding mechanism, it is characterised in that the rudder face folding and expanding mechanism include gear mechanism, Claw and clamping block, ancillary equipment are rudder face, rudderpost and steering wheel；Gear mechanism is locked with claw by shear pin, and gear shaft forms screw auxiliary structure with claw, and claw engages with rudderpost； Rudder face is arranged in clamping block by rudderpost, and the axis direction of rudderpost is interference fitted perpendicular to rudder face, rudderpost with rudder face；Gear mechanism driving claw is rotated, and makes rudderpost drive rudder face to rotate expansion, and rudder face expansion is locked by clamping block afterwards in place； After gear mechanism continues to move, and cuts shear pin, and claw separates with rudderpost, clamping block rotation, rotary shaft are driven by steering wheel Direction is vertical with rudderpost axis direction, rudder face is realized rotation.
- 2. high synchronism rudder face folding and expanding mechanism as claimed in claim 1, it is characterised in that the gear mechanism uses tooth Rack-driving is taken turns, rack led to " Swastika " shape connector and is connected with external impetus mechanism, and rack is scheduled on the end of " Swastika " shape connector admittedly Plane where portion, the direction of motion Yu the " Swastika of rack " shape connectors is orthogonal, rack and pinion engagement, the rotation direction of gear It is consistent with rudderpost rotation direction.
- 3. high synchronism rudder face folding and expanding mechanism as claimed in claim 1, it is characterised in that the clamping block is provided with and rudder The wedge-shaped slot that face is engaged, locked in place for rudder face expansion.
- 4. high synchronism rudder face folding and expanding mechanism as claimed in claim 1, it is characterised in that the clamping block passes through shaft coupling Device is connected with steering wheel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710696098.2A CN107576228B (en) | 2017-08-15 | 2017-08-15 | A kind of high synchronism rudder face folding and expanding mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710696098.2A CN107576228B (en) | 2017-08-15 | 2017-08-15 | A kind of high synchronism rudder face folding and expanding mechanism |
Publications (2)
| Publication Number | Publication Date |
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| CN107576228A true CN107576228A (en) | 2018-01-12 |
| CN107576228B CN107576228B (en) | 2019-06-18 |
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|---|---|---|---|
| CN201710696098.2A Active CN107576228B (en) | 2017-08-15 | 2017-08-15 | A kind of high synchronism rudder face folding and expanding mechanism |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110155307A (en) * | 2018-04-02 | 2019-08-23 | 北京机电工程研究所 | A kind of inertia unlock rudder face device for ejecting |
| CN110230954A (en) * | 2019-05-30 | 2019-09-13 | 上海宇航***工程研究所 | A kind of space transportation device grid rudder transmission mechanism |
| CN110733630A (en) * | 2019-10-25 | 2020-01-31 | 北京机电工程研究所 | steering engine for miniature aircraft |
| CN111121560A (en) * | 2019-12-25 | 2020-05-08 | 兰州空间技术物理研究所 | Rocket control surface folding and unfolding rotary driving device |
| CN111306996A (en) * | 2020-01-23 | 2020-06-19 | 西安现代控制技术研究所 | Ammunition flight resistance device |
| CN112141349A (en) * | 2020-11-27 | 2020-12-29 | 成都云鼎智控科技有限公司 | Control system of unmanned aerial vehicle engine |
| CN112659011A (en) * | 2020-11-12 | 2021-04-16 | 北京星航机电装备有限公司 | Control surface folding and releasing tool and control surface folding and releasing method |
| CN114408224A (en) * | 2021-12-20 | 2022-04-29 | 中国航天科工集团八五一一研究所 | Space-recyclable folding mechanism |
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| GB634090A (en) * | 1946-07-15 | 1950-03-15 | William Alexander Onslow Marti | Improvements in and connected with stabilizing fins for projectiles |
| DE1703052A1 (en) * | 1968-03-26 | 1971-12-09 | Dichl Fa | Tail unit for projectiles |
| CN202092524U (en) * | 2011-05-26 | 2011-12-28 | 浙江理工大学 | Longitudinal expanding mechanism of redundancy locking type folding wing |
| CN203350014U (en) * | 2013-07-15 | 2013-12-18 | 中国航天空气动力技术研究院 | Resonance excitation device |
| CN104089547A (en) * | 2014-06-30 | 2014-10-08 | 中国航天时代电子公司 | Unfolding and locking device for foldable rudder face |
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB634090A (en) * | 1946-07-15 | 1950-03-15 | William Alexander Onslow Marti | Improvements in and connected with stabilizing fins for projectiles |
| DE1703052A1 (en) * | 1968-03-26 | 1971-12-09 | Dichl Fa | Tail unit for projectiles |
| CN202092524U (en) * | 2011-05-26 | 2011-12-28 | 浙江理工大学 | Longitudinal expanding mechanism of redundancy locking type folding wing |
| CN203350014U (en) * | 2013-07-15 | 2013-12-18 | 中国航天空气动力技术研究院 | Resonance excitation device |
| CN104089547A (en) * | 2014-06-30 | 2014-10-08 | 中国航天时代电子公司 | Unfolding and locking device for foldable rudder face |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110155307B (en) * | 2018-04-02 | 2021-04-02 | 北京机电工程研究所 | Inertia unblock control surface pops out device |
| CN110155307A (en) * | 2018-04-02 | 2019-08-23 | 北京机电工程研究所 | A kind of inertia unlock rudder face device for ejecting |
| CN110230954B (en) * | 2019-05-30 | 2021-11-16 | 上海宇航***工程研究所 | Grid rudder transmission mechanism for spaceflight carrier |
| CN110230954A (en) * | 2019-05-30 | 2019-09-13 | 上海宇航***工程研究所 | A kind of space transportation device grid rudder transmission mechanism |
| CN110733630A (en) * | 2019-10-25 | 2020-01-31 | 北京机电工程研究所 | steering engine for miniature aircraft |
| CN110733630B (en) * | 2019-10-25 | 2021-11-02 | 北京机电工程研究所 | Micro aircraft steering engine |
| CN111121560A (en) * | 2019-12-25 | 2020-05-08 | 兰州空间技术物理研究所 | Rocket control surface folding and unfolding rotary driving device |
| CN111121560B (en) * | 2019-12-25 | 2022-08-09 | 兰州空间技术物理研究所 | Rocket control surface folding and unfolding rotary driving device |
| CN111306996A (en) * | 2020-01-23 | 2020-06-19 | 西安现代控制技术研究所 | Ammunition flight resistance device |
| CN111306996B (en) * | 2020-01-23 | 2022-07-05 | 西安现代控制技术研究所 | Ammunition flight resistance device |
| CN112659011A (en) * | 2020-11-12 | 2021-04-16 | 北京星航机电装备有限公司 | Control surface folding and releasing tool and control surface folding and releasing method |
| CN112141349A (en) * | 2020-11-27 | 2020-12-29 | 成都云鼎智控科技有限公司 | Control system of unmanned aerial vehicle engine |
| CN114408224A (en) * | 2021-12-20 | 2022-04-29 | 中国航天科工集团八五一一研究所 | Space-recyclable folding mechanism |
| CN114408224B (en) * | 2021-12-20 | 2024-05-17 | 中国航天科工集团八五一一研究所 | Space-recoverable folding mechanism |
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| Publication number | Publication date |
|---|---|
| CN107576228B (en) | 2019-06-18 |
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