CN204461240U - Twice-folded aerofoil horizontal spreading mechanism - Google Patents
Twice-folded aerofoil horizontal spreading mechanism Download PDFInfo
- Publication number
- CN204461240U CN204461240U CN201520041735.9U CN201520041735U CN204461240U CN 204461240 U CN204461240 U CN 204461240U CN 201520041735 U CN201520041735 U CN 201520041735U CN 204461240 U CN204461240 U CN 204461240U
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- wing
- hole
- centre section
- locking
- wing root
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Abstract
The utility model discloses twice-folded aerofoil horizontal spreading mechanism.Existing aerofoil folding and expanding mechanism is disposable folding, and guided missile volume is comparatively large, storing and transmitting inconvenience.Pressurized strut of the present utility model and wing root are fixed; Piston rod is connected with pressurized strut sliding pair; The two ends of screw rod and two of wing root wing root joints 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, the other end and wing centre section hinged at wing centre section pin-and-hole place; Outer wing is provided with two outer wing joints; Hinge is passed through in two top connections of two outer wing joints and wing centre section; One end of connecting rod and wing root by hinge, the other end and outer wing hinged at outer wing pin-and-hole place; Two spring release mechanism are arranged symmetrically with, and are all connected by sliding pair with wing root, and are connected with the spiral of screw rod side respectively.When aerofoil of the present utility model folds, body lateral dimension is little, is the dead-centre position of mechanism when aerofoil launches completely, separately arranges spring release mechanism and carries out redundancy locking.
Description
Technical field
The utility model belongs to field of aerospace technology, relates to a kind of Missile Folding aerofoil development mechanism, is 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, extensively need adopt folded surface.The function of folded surface development mechanism is that aerofoil is folded before transmission, 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 comparatively large, causes storing and launch inconvenience.Existing folding and expanding mechanism all can realize disposable expansion locking, comparatively large to ballistic impact when duration of run is short, expansion puts in place, affects the flight stability of guided missile.
Summary of the invention
The purpose of this utility model is for the deficiencies in the prior art, and provide a kind of twice-folded aerofoil horizontal spreading mechanism, this mechanism can effectively reduce the lateral dimension of body when aerofoil folds, thus it is volume required with transmitting to reduce projectile storage and transportation; Can the span be increased after expansion, improve aerodynamic lift during missile flight; Dead-centre position just for mechanism when aerofoil launches completely, separately arranging spring release mechanism carries out redundancy locking, to ensure that folded surface launches positive lock when putting in place, reduces aerofoil and locks the impact caused body, ensure the flight stability of guided missile.
The utility model comprises wing root, pressurized strut, piston rod, auricle, wing centre section, outer wing, connecting rod, screw rod and spring release 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 contrary spiral of rotation direction; The two ends of described screw rod and two wing root joints 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, the other end and wing centre section 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; Hinge is passed through in two top connections of two outer wing joints and wing centre section; One end of described connecting rod and wing root by hinge, the other end and outer wing hinged at outer wing pin-and-hole place; Two spring release mechanism are arranged symmetrically with, and are all connected by sliding pair with wing root, and are connected with the spiral of screw rod 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; Bearing saddle bore is vertical with the outer face of wing root with the axis place plane in locking bushing hole, 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 hinged at bearing saddle bore place; Described wing centre section offers wing centre section groove and wing centre section blind slot, and under launching lock-out state completely, 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 lock the side that taper pin-hole is arranged on close wing root outer face.
Two spring release mechanism are arranged symmetrically with; Described spring release mechanism comprises spring, lock nut, locking bushing and locking taper pin; The lock nut rotation direction of two spring release mechanism 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 complete lock-out state, locking taper pin embeds in locking taper pin-hole.
The beneficial effects of the utility model:
1, crank block and double-crank combined mechanism form is adopted, simple and compact for structure, be easy to realize launching lock function;
2, missile airfoil is divided into three sections to fold, the radial dimension of body when can effectively reduce folding, meets envelope size design minimization principle;
3, when aerofoil launches, can the span be increased, effectively improve aerodynamic lift during missile flight;
Dead-centre position when 4, utilizing mechanism deploying to put in place and spring release mechanism realize redundancy positive lock, reduce the impact to body when aerofoil launches to put in place, ensure that 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 collapsible solar wing, deployable antenna and relevant ground mechanism.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram that the utility model launches lock-out state completely;
Fig. 2 is the schematic diagram of mechanism of the utility model folded state;
Fig. 3 is the overall structure schematic diagram of the utility model folded state;
Fig. 4 is wing root structural perspective of the present utility model;
Fig. 5 is wing centre section structural perspective of the present utility model;
Fig. 6 is the cross-sectional schematic of the utility model folded state lower spring locking mechanism.
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 release 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 utility model is described further.
As shown in Figure 1,2 and 3, 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 release mechanism 7; The outer end of wing root 1 is provided with two wing root joint 1-1, and pressurized strut 4 is fixed 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 contrary spiral of rotation direction; The two ends of screw rod 6 and two wing root joint 1-1 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 and the piston rod 3 of auricle 5 are hinged, the other end and wing centre section 10 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 pass through hinge; One end of connecting rod 9 and wing root 1 hinged by bearing pin 2, the other end and outer wing 8 hinged at outer wing pin-and-hole 8-1 place; Two spring release mechanism 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 side 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; Bearing saddle bore 1-3 is vertical with the outer face of wing root 1 with the axis place plane of locking bushing hole 1-4, 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 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, and under launching lock-out state completely, 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 lock the side that taper pin-hole 10-3 is arranged on close wing root 1 outer face.
As shown in Figure 6, two spring release mechanism 7 are arranged symmetrically with; Spring release 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 release mechanism 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 complete lock-out state, locking taper pin 7-4 embeds in locking taper pin-hole 10-3.
The operation principle of this twice-folded aerofoil horizontal spreading mechanism:
Missile airframe surface is pressed close to when folded state by this twice-folded aerofoil horizontal spreading mechanism, relies on emitter to retrain, and after MISSILE LAUNCHING goes out cylinder, constraint release, mechanism deploying is to predetermined angular and lock, for missile flight provides lift.
As Fig. 2,3, shown in 5 and 6, body is pressed close to by this twice-folded aerofoil horizontal spreading mechanism in a folded configuration aerofoil (aerofoil comprises wing root 1, wing centre section 10 and outer wing 8), locking taper pin 7-4 is arranged in locking bushing hole 1-4.During work, pressurized strut 4 action, promotes piston rod 3 and moves linearly along wing root 1, drive 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 outer wing 8 is driven to relatively rotate around wing centre section 10.Limit because locking bushing 7-3 is locked sleeve hole 1-4, therefore nut 7-2 can only move linearly along screw rod 6.After wing centre section 10 turns over 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.Being rotated further now along with aerofoil, spring 7-1 is compressed, when 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 mechanism to be locked.Meanwhile, locking taper pin 7-4 drops in locking taper pin-hole 10-3 under spring force, realizes locking the redundancy of mechanism.
As shown in Figure 1, when 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, achieves the locking of expansion completely of twice-folded aerofoil horizontal spreading mechanism.
Claims (3)
1. 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 release 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 contrary spiral of rotation direction; The two ends of described screw rod and two wing root joints 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, the other end and wing centre section 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; Hinge is passed through in two top connections of two outer wing joints and wing centre section; One end of described connecting rod and wing root by hinge, the other end and outer wing hinged at outer wing pin-and-hole place; Two spring release mechanism are arranged symmetrically with, and are all connected by sliding pair with wing root, and are connected with the spiral of screw rod side respectively.
2. twice-folded aerofoil horizontal spreading mechanism according to claim 1, it is characterized in that: the outer end of described wing root is provided with wing root lug, wing root joint offers bearing saddle bore and locking bushing hole; Bearing saddle bore is vertical with the outer face of wing root with the axis place plane in locking bushing hole, 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 hinged at bearing saddle bore place; Described wing centre section offers wing centre section groove and wing centre section blind slot, and under launching lock-out state completely, 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 lock the side that taper pin-hole is arranged on close wing root outer face.
3. twice-folded aerofoil horizontal spreading mechanism according to claim 2, is characterized in that: two spring release mechanism are arranged symmetrically with; Described spring release mechanism comprises spring, lock nut, locking bushing and locking taper pin; The lock nut rotation direction of two spring release mechanism 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 complete lock-out state, locking taper pin embeds in locking taper pin-hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520041735.9U CN204461240U (en) | 2015-01-21 | 2015-01-21 | Twice-folded aerofoil horizontal spreading mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520041735.9U CN204461240U (en) | 2015-01-21 | 2015-01-21 | Twice-folded aerofoil horizontal spreading mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204461240U true CN204461240U (en) | 2015-07-08 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520041735.9U Expired - Fee Related CN204461240U (en) | 2015-01-21 | 2015-01-21 | Twice-folded aerofoil horizontal spreading mechanism |
Country Status (1)
| Country | Link |
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| CN (1) | CN204461240U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104677200A (en) * | 2015-01-21 | 2015-06-03 | 浙江理工大学 | Secondary folded-wing-surface transverse unfolding mechanism |
| CN105782159A (en) * | 2016-04-27 | 2016-07-20 | 南京航空航天大学 | Hydraulic rotary actuator |
| EP3254957A1 (en) * | 2016-06-09 | 2017-12-13 | Airbus Operations GmbH | Latching device for a foldable wing arrangement |
| CN110108170A (en) * | 2019-04-23 | 2019-08-09 | 浙江理工大学 | A kind of two-way locking device and its locking means for lateral Missile folded wing |
-
2015
- 2015-01-21 CN CN201520041735.9U patent/CN204461240U/en not_active Expired - Fee Related
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104677200A (en) * | 2015-01-21 | 2015-06-03 | 浙江理工大学 | Secondary folded-wing-surface transverse unfolding mechanism |
| CN105782159A (en) * | 2016-04-27 | 2016-07-20 | 南京航空航天大学 | Hydraulic rotary actuator |
| EP3254957A1 (en) * | 2016-06-09 | 2017-12-13 | Airbus Operations GmbH | Latching device for a foldable wing arrangement |
| US10597139B2 (en) | 2016-06-09 | 2020-03-24 | Airbus Operations Limited | Latching device for a foldable wing arrangement |
| CN110108170A (en) * | 2019-04-23 | 2019-08-09 | 浙江理工大学 | A kind of two-way locking device and its locking means for lateral Missile folded wing |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150708 Termination date: 20170121 |