CN104677200B - One twice-folded aerofoil horizontal spreading mechanism - Google Patents
One twice-folded aerofoil horizontal spreading mechanism Download PDFInfo
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- CN104677200B CN104677200B CN201510029887.1A CN201510029887A CN104677200B CN 104677200 B CN104677200 B CN 104677200B CN 201510029887 A CN201510029887 A CN 201510029887A CN 104677200 B CN104677200 B CN 104677200B
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Abstract
The invention discloses a kind of twice-folded aerofoil horizontal spreading mechanism. Existing aerofoil folding and expanding mechanism is disposable folding, makes guided missile volume larger, storing and transmitting inconvenience. Pressurized strut of the present invention and wing root are fixed; Piston rod is connected with pressurized strut sliding pair; Two wing root joints of the two ends of screw rod and wing root are hinged; Two lower contacts of wing centre section and the two ends of screw rod are fixed; One end and the piston rod of auricle are hinged, and the other end and wing centre section are hinged at wing centre section pin-and-hole place; Outer wing is provided with two outer wing joints; Two top connections of two outer wing joints and wing centre section are hinged by bearing pin; One end of connecting rod and wing root are hinged by bearing pin, and the other end and outer wing are hinged at outer wing pin-and-hole place; Two spring locking mechanisms are arranged symmetrically with, and are all connected by sliding pair with wing root, and are connected with the spiral of screw rod one side respectively. When aerofoil of the present invention is folding, body lateral dimension is little, is the dead-centre position of mechanism when aerofoil launches completely, spring locking mechanism is separately set and carries out redundancy locking.
Description
Technical field
The invention belongs to field of aerospace technology, relate to a kind of Missile Folding aerofoil development mechanism, be specifically related to a kind of twice-folded aerofoil horizontal spreading mechanism.
Background technology
Aerofoil is the important component part of missile airframe, for adapting to modern case/cartridge type launch requirements, needs extensively to adopt folded surface. The function of folded surface development mechanism is to make aerofoil folding before transmitting, after transmitting under the effect of driving force Automatic-expanding positive lock. Currently used aerofoil folding and expanding mechanism is disposable folding, still cannot meet the demand of body radial dimension, makes guided missile volume larger, has caused storing and transmitting inconvenience. Existing folding and expanding mechanism all can realize disposable expansion locking, and duration of run is short, larger to ballistic impact while launching to put in place, affects the flight stability of guided missile.
Summary of the invention
The object of the invention is for the deficiencies in the prior art, a kind of twice-folded aerofoil horizontal spreading mechanism is provided, this mechanism can effectively reduce the lateral dimension of body in the time that aerofoil is folding, thereby it is volume required with transmitting to reduce projectile storage and transportation; After expansion, can increase the span, the aerodynamic lift while improving missile flight; The proper dead-centre position for mechanism when aerofoil launches completely, spring locking mechanism is separately set carries out redundancy locking, and the positive lock when ensureing that folded surface launches to put in place, reduces aerofoil lock the impact that body is caused the flight stability of guarantee guided missile.
The present invention includes wing root, pressurized strut, piston rod, auricle, wing centre section, outer wing, connecting rod, screw rod and spring locking mechanism; The outer end of described wing root is provided with two wing root joints, and pressurized strut and wing root are fixed; Described piston rod is connected by sliding pair with pressurized strut; The two ends of screw rod are provided with the spiral that rotation direction is contrary; The two ends of described screw rod and two wing root joints are hinged; Described wing centre section offers wing centre section pin-and-hole, and is provided with two top connections and two lower contacts; The two ends of two lower contacts and screw rod are fixed; One end and the piston rod of auricle are hinged, and the other end and wing centre section are hinged at wing centre section pin-and-hole place; Described outer wing offers outer wing pin-and-hole, and is provided with two outer wing joints; Two top connections of two outer wing joints and wing centre section are hinged by bearing pin; One end of described connecting rod and wing root are hinged by bearing pin, and the other end and outer wing are hinged at outer wing pin-and-hole place; Two spring locking mechanisms are arranged symmetrically with, and are all connected by sliding pair with wing root, and are connected with the spiral of screw rod one side respectively.
The outer end of described wing root is provided with wing root lug, and wing root joint offers bearing saddle bore and locking bushing hole; The axis place plane in bearing saddle bore and locking bushing hole is vertical with the outer face of wing root, and locking bushing hole is arranged on the side near wing root outer face; The two ends of described screw rod and two wing root joints are hinged at bearing saddle bore place; Described wing centre section offers wing centre section groove and wing centre section blind slot, launches completely under lock-out state, and auricle is embedded in wing centre section blind slot, and connecting rod is embedded in wing centre section groove; The two ends of screw rod are separately fixed in the connecting hole of a lower contact; The edge of described connecting hole offers locking taper pin slideway, and one end of locking taper pin slideway offers locking taper pin-hole; Locking taper pin-hole and connecting hole axis place plane vertical with the outer face of wing root, and locking taper pin-hole is arranged on a side of close wing root outer face.
Two spring locking mechanisms are arranged symmetrically with; Described spring locking mechanism comprises spring, lock nut, locking bushing and locking taper pin; The lock nut rotation direction of two spring locking mechanisms is contrary, is connected respectively with the spiral of screw rod one end; Described locking bushing and the end face of lock nut are fixed, and are connected by sliding pair with the locking bushing hole of wing root joint; Described spring is nested with in locking bushing, and one end and locking bushing are fixed; One end of described locking taper pin embeds in locking bushing, and fixes with the other end of spring; In locking process, locking taper pin is connected by sliding pair with locking taper pin slideway; Under lock-out state, locking taper pin embeds in locking taper pin-hole completely.
Beneficial effect of the present invention:
1, adopt crank block and double-crank combined mechanism form, simple and compact for structure, be easy to realize expansion lock function;
2, missile airfoil is divided into three sections and folds, can effectively reduce the radial dimension of body while folding, meet envelope size design minimization principle;
3,, when aerofoil launches, can increase the span, the aerodynamic lift while effectively improving missile flight;
4, the dead-centre position while utilizing mechanism deploying to put in place and spring locking winding machine redundancy positive lock, reduced the impact to body when aerofoil launches to put in place, ensured the flight stability of guided missile;
5, applied range, except being applied to folded surface, also may be used on the space development mechanisms such as the collapsible sun wing, deployable antenna and relevant ground mechanism.
Brief description of the drawings
Fig. 1 is the overall structure schematic diagram that the present invention launches lock-out state completely;
Fig. 2 is the schematic diagram of mechanism of folded state of the present invention;
Fig. 3 is the overall structure schematic diagram of folded state of the present invention;
Fig. 4 is wing root structural perspective of the present invention;
Fig. 5 is wing centre section structural perspective of the present invention;
Fig. 6 is the cross-sectional schematic of folded state lower spring locking mechanism of the present invention.
In figure: 1, wing root, 1-1, wing root joint, 1-2, wing root lug, 1-3, bearing saddle bore, 1-4, locking bushing hole, 2, bearing pin, 3, piston rod, 4, pressurized strut, 5, auricle, 6, screw rod, 7, spring locking mechanism, 7-1, spring, 7-2, lock nut, 7-3, locking bushing, 7-4, locking taper pin, 8, outer wing, 8-1, outer wing pin-and-hole, 8-2, outer wing joint, 9, connecting rod, 10, wing centre section, 10-1, wing centre section pin-and-hole, 10-2, lower contact, 10-3, locking taper pin-hole, 10-4, locking taper pin slideway, 10-5, wing centre section groove, 10-6, top connection, 10-7, wing centre section blind slot, 10-8, connecting hole, 11, bearing.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention will be further described.
As shown in Figure 1,2 and 3, a kind of twice-folded aerofoil horizontal spreading mechanism, comprises wing root 1, pressurized strut 4, piston rod 3, auricle 5, wing centre section 10, outer wing 8, connecting rod 9, screw rod 6 and spring locking mechanism 7; The outer end of wing root 1 is provided with two wing root joint 1-1, and pressurized strut 4 is fixing with wing root 1; Piston rod 3 is connected by sliding pair with pressurized strut 4; The two ends of screw rod 6 are provided with the spiral that rotation direction is contrary; The two ends of screw rod 6 and two wing root joint 1-1 are hinged; Wing centre section 10 offers wing centre section pin-and-hole 10-1, and is provided with two top connection 10-6 and two lower contact 10-2; The two ends of two lower contact 10-2 and screw rod 6 are fixed; One end of auricle 5 and piston rod 3 are hinged, and the other end and wing centre section 10 are hinged at wing centre section pin-and-hole 10-1 place; Outer wing 8 offers outer wing pin-and-hole 8-1, and is provided with two outer wing joint 8-2; Two top connection 10-6 of two outer wing joint 8-2 and wing centre section are hinged by bearing pin; One end of connecting rod 9 and wing root 1 are hinged by bearing pin 2, and the other end and outer wing 8 are hinged at outer wing pin-and-hole 8-1 place; Two spring locking mechanisms 7 are arranged symmetrically with, and are all connected by sliding pair with wing root 1, and are connected with the spiral of screw rod 6 one sides respectively.
As shown in Figures 4 and 5, the outer end of wing root 1 is provided with wing root lug 1-2, and wing root joint 1-1 offers bearing saddle bore 1-3 and locking bushing hole 1-4; The axis place plane of bearing saddle bore 1-3 and locking bushing hole 1-4 is vertical with the outer face of wing root 1, and locking bushing hole 1-4 is arranged on the side near wing root 1 outer face; The two ends of screw rod 6 and two wing root joint 1-1 are hinged at bearing saddle bore 1-3 place; Wing centre section 10 offers wing centre section groove 10-5 and wing centre section blind slot 10-7, launches completely under lock-out state, and auricle 5 is embedded in wing centre section blind slot 10-7, and connecting rod 9 is embedded in wing centre section groove 10-5; The two ends of screw rod 6 are separately fixed in the connecting hole 10-8 of a lower contact 10-2; The edge of connecting hole 10-8 offers locking taper pin slideway 10-4, and one end of locking taper pin slideway 10-4 offers locking taper pin-hole 10-3; Locking taper pin-hole 10-3 and connecting hole 10-8 axis place plane vertical with the outer face of wing root 1, and locking taper pin-hole 10-3 is arranged on a side of close wing root 1 outer face.
As shown in Figure 6, two spring locking mechanisms 7 are arranged symmetrically with; Spring locking mechanism 7 comprises spring 7-1, lock nut 7-2, locking bushing 7-3 and locking taper pin 7-4; The lock nut 7-2 rotation direction of two spring locking mechanisms 7 is contrary, is connected respectively with the spiral of screw rod 6 one end; The end face of locking bushing 7-3 and lock nut 7-2 is fixed, and is connected by sliding pair with the locking bushing hole 1-4 of wing root joint 1-1; Spring 7-1 is nested with in locking bushing 7-3, and one end and locking bushing 7-3 fix; One end of locking taper pin 7-4 embeds in locking bushing 7-3, and fixes with the other end of spring 7-1; As shown in Figure 5, in locking process, locking taper pin 7-4 is connected by sliding pair with locking taper pin slideway 10-4; Under lock-out state, locking taper pin 7-4 embeds in locking taper pin-hole 10-3 completely.
The operation principle of this twice-folded aerofoil horizontal spreading mechanism:
Missile airframe surface is pressed close in the time of folded state by this twice-folded aerofoil horizontal spreading mechanism, relies on emitter to retrain, when MISSILE LAUNCHING goes out after cylinder, and constraint release, mechanism deploying is to predetermined angular locking, for missile flight provides lift.
As shown in Fig. 2,3,5 and 6, body is pressed close at folded state lower aerofoil (aerofoil comprises wing root 1, wing centre section 10 and outer wing 8) by this twice-folded aerofoil horizontal spreading mechanism, and locking taper pin 7-4 is arranged in locking bushing hole 1-4. When work, pressurized strut 4 is moved, and promotes piston rod 3 and moves linearly along wing root 1, drives wing centre section 10 and screw rod 6 to rotate around wing root 1 by auricle 5, because wing root 1, wing centre section 10, connecting rod 9 and outer wing 8 are double-crank mechanism on mechanism form, and then drive outer wing 8 to relatively rotate around wing centre section 10. Because of the locked sleeve hole 1-4 restriction of locking bushing 7-3, therefore nut 7-2 can only move linearly along screw rod 6. When wing centre section 10 turns over after certain angle, locking taper pin 7-4 contacts with the lower contact 10-2 of wing centre section, enters locking taper pin slideway 10-4, produces relative sliding with the lower contact 10-2 of wing centre section. Now being rotated further along with aerofoil, spring 7-1 is compressed, in the time that aerofoil turns to precalculated position, pressurized strut 4 quits work, wing root 1, piston rod 3, auricle 5 are located along the same line with wing centre section 10, just be the dead-centre position of mechanism, wing root 1, wing centre section 10, connecting rod 9 and outer wing 8 are also positioned at same straight line, rely on dead-centre position that mechanism is locked. Meanwhile, locking taper pin 7-4 falls in locking taper pin-hole 10-3 at spring-force driven dual, realizes the redundancy locking to mechanism.
As shown in Figure 1, in the time that aerofoil is expanded to precalculated position, auricle 5 is also embedded in wing centre section blind slot 10-7, and connecting rod 9 is embedded in wing centre section groove 10-5, has realized the locking of expansion completely of twice-folded aerofoil horizontal spreading mechanism.
Claims (3)
1. a twice-folded aerofoil horizontal spreading mechanism, comprises wing root, pressurized strut, piston rod, auricle, wing centre section, outer wing, connecting rod, screw rod and spring locking mechanism, it is characterized in that:
The outer end of described wing root is provided with two wing root joints, and pressurized strut and wing root are fixed; Described piston rod is connected by sliding pair with pressurized strut; The two ends of screw rod are provided with the spiral that rotation direction is contrary; The two ends of described screw rod and two wing root joints are hinged; Described wing centre section offers wing centre section pin-and-hole, and is provided with two top connections and two lower contacts; The two ends of two lower contacts and screw rod are fixed; One end and the piston rod of auricle are hinged, and the other end and wing centre section are hinged at wing centre section pin-and-hole place; Described outer wing offers outer wing pin-and-hole, and is provided with two outer wing joints; Two top connections of two outer wing joints and wing centre section are hinged by bearing pin; One end of described connecting rod and wing root are hinged by bearing pin, and the other end and outer wing are hinged at outer wing pin-and-hole place; Two spring locking mechanisms are arranged symmetrically with, and are all connected by sliding pair with wing root, and are connected with the spiral of screw rod one side respectively.
2. a kind of twice-folded aerofoil horizontal spreading according to claim 1 mechanism, is characterized in that: the outer end of described wing root is provided with wing root lug, and wing root joint offers bearing saddle bore and locking bushing hole; The axis place plane in bearing saddle bore and locking bushing hole is vertical with the outer face of wing root, and locking bushing hole is arranged on the side near wing root outer face; The two ends of described screw rod and two wing root joints are hinged at bearing saddle bore place; Described wing centre section offers wing centre section groove and wing centre section blind slot, launches completely under lock-out state, and auricle is embedded in wing centre section blind slot, and connecting rod is embedded in wing centre section groove; The two ends of screw rod are separately fixed in the connecting hole of a lower contact; The edge of described connecting hole offers locking taper pin slideway, and one end of locking taper pin slideway offers locking taper pin-hole; Locking taper pin-hole and connecting hole axis place plane vertical with the outer face of wing root, and locking taper pin-hole is arranged on a side of close wing root outer face.
3. a kind of twice-folded aerofoil horizontal spreading according to claim 2 mechanism, is characterized in that: two spring locking mechanisms are arranged symmetrically with; Described spring locking mechanism comprises spring, lock nut, locking bushing and locking taper pin; The lock nut rotation direction of two spring locking mechanisms is contrary, is connected respectively with the spiral of screw rod one end; Described locking bushing and the end face of lock nut are fixed, and are connected by sliding pair with the locking bushing hole of wing root joint; Described spring is nested with in locking bushing, and one end and locking bushing are fixed; One end of described locking taper pin embeds in locking bushing, and fixes with the other end of spring; In locking process, locking taper pin is connected by sliding pair with locking taper pin slideway; Under lock-out state, locking taper pin embeds in locking taper pin-hole completely.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510029887.1A CN104677200B (en) | 2015-01-21 | 2015-01-21 | One twice-folded aerofoil horizontal spreading mechanism |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510029887.1A CN104677200B (en) | 2015-01-21 | 2015-01-21 | One twice-folded aerofoil horizontal spreading mechanism |
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| CN104677200A CN104677200A (en) | 2015-06-03 |
| CN104677200B true CN104677200B (en) | 2016-05-18 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010202A (en) * | 2017-02-28 | 2017-08-04 | 北京航空航天大学 | A kind of controllable aircraft folds wing spreading device |
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| CN106839897B (en) * | 2017-01-03 | 2019-01-15 | 北京临近空间飞行器系统工程研究所 | A kind of straight-line helix unfolded wing mechanism |
| CN107655366B (en) * | 2017-10-23 | 2023-07-28 | 贵州航天林泉电机有限公司 | Steering wheel is with folded cascade rudder piece subassembly twice |
| CN108306091B (en) * | 2018-01-30 | 2020-09-22 | 中国电子科技集团公司第三十八研究所 | Radar antenna tilting mechanism |
| CN108548457B (en) * | 2018-03-20 | 2023-12-05 | 浙江理工大学 | Single power source synchronous driving type secondary folding unfolding mechanism for guided missile |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SE331242B (en) * | 1969-05-14 | 1970-12-14 | Bofors Ab | |
| DE3838735C2 (en) * | 1988-11-15 | 1997-12-18 | Diehl Gmbh & Co | Folding wing, especially for one floor |
| DE102004039770A1 (en) * | 2004-08-16 | 2006-03-02 | Diehl Bgt Defence Gmbh & Co. Kg | wing assembly |
| RU2535789C1 (en) * | 2013-08-02 | 2014-12-20 | Открытое акционерное общество "Долгопрудненское научно-производственное предприятие" | Folding aerodynamic rudder |
| CN204461240U (en) * | 2015-01-21 | 2015-07-08 | 浙江理工大学 | Twice-folded aerofoil horizontal spreading mechanism |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010202A (en) * | 2017-02-28 | 2017-08-04 | 北京航空航天大学 | A kind of controllable aircraft folds wing spreading device |
| CN107010202B (en) * | 2017-02-28 | 2019-06-25 | 北京航空航天大学 | A kind of controllable aircraft folding wing spreading device |
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