CN204775993U - Wing device is folded to aircraft - Google Patents
Wing device is folded to aircraft Download PDFInfo
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- CN204775993U CN204775993U CN201520271420.3U CN201520271420U CN204775993U CN 204775993 U CN204775993 U CN 204775993U CN 201520271420 U CN201520271420 U CN 201520271420U CN 204775993 U CN204775993 U CN 204775993U
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Abstract
The utility model discloses a wing device is folded to aircraft, the device constructs (7) including last half wing (1), lower half wing (2), axis of rotation (3), locking mechanism (4), interlock mechanism (5), trigger mechanism (6) and group favourable turn, installing accessible trigger mechanism (6) and group favourable turn structure (7) drive locking mechanism (4) and changing over to lock status over to by fold condition, messenger's airfoil from top to bottom opens completely to can not reset completely through manual reversible operation ground. This device simple structure, occupation space are little, with low costs, the operation is convenient, it is quick to reset, the homonymy airfoil expand the synchronism high, and guarantee that locking back monolithic airfoil can normally bear airfoil load.
Description
Technical field
The utility model discloses a kind of folding wings device, belong to aviation machine technical field.
Background technology
Along with the development of missilery, canister launch, feedway miniaturization become main flow, and for aircraft, the size of aerofoil is the parts that space availability ratio is minimum, are also to reduce aircraft store and launch volume required topmostly to start with a little.Realize wing controllability folding and expanding and become design key.
Folding wings system is generally made up of these three essential parts of collapsible aerofoil, fold mechanism and the energy.Fold mechanism is the core of structure design, is made up of folding and expanding mechanism, location locking mechanism two essential parts.Folding and expanding mechanism is the mechanism allowing aerofoil to fold in good time and launch, and is the execution module of folding functional; And location locking mechanism is the mechanism guaranteeing normally carry after folded wing launches, it is the assurance module of wing function.The complexity of fold mechanism is relevant to factors such as the parameter of aerofoil and automatic mechanism levels.The energy is to provide the part of mechanical operation power, and the controllability of mechanism requires higher, and energy resource system is more complicated, and Large Scale Space Vehicle folding-wing structure comprises complicated sensor and control program usually.
As certain model airplane carrier fighter folded wing can auto-folder and expansion, increase the aircraft quantity that warship can load, outfit be fluid power system, except aerofoil being equipped with sensor and steering unit, in fuselage, also have Hydraulic Elements and control loop; In addition certain rocket projectile adopts gaseous-pressure formula folding wings system, utilizes gaseous-pressure as unwind force, although mechanism construction is complicated, unwind force comparatively greatly, can push-jump area, aerofoil that quality is larger; Also have the air-ground bomb of certain model, bomb body diameter 200mm is about the longitudinal folding mode that 1m aerofoil adopts income bomb body, launches reduced nearly 1/2.
The scheme of current folding wings has multiple, but because wing is the main force-summing element of aircraft, to accuracy rate, the reliability of folding wing mechanism, launching the aspects such as the intensity of rear aerofoil requires harsh, cause often complex structure, development difficulty is large, and development cost is high, is not suitable for usability and the cost-effectiveness requirement of middle-size and small-size aircraft folding wings.If for middle-size and small-size aircraft folding wings development fold mechanism, large-scale automation equipment or the control element of complexity just will must be abandoned, replace the mechanism design of innovation, realized folding wings function.In the process of mechanism design, mainly containing following key technical problem must solve:
1) catch gear requires to lock upper and lower half wing, make it the aerodynamic loading that normally can bear design after launching, general reliable fastening combination such as Bolt Connection, riveted joint, welding, gluing etc. are all non-removable, and catch gear must disconnect when folding connection, launch time automatically connect, general fastening means can not use, and the catch gear how designing not only fastening but also good folding and unfolding is one of key issue.
2) catch gear needs timing element and accurately and reliably triggers, and locks upper and lower half wing in time when upper half wing resets.But half wing structure up and down of not yet having locked because resetted is not integrative-structure completely, more fragile, almost can not bear vertical aerofoil load, if do not locked in time, the effect of aerodynamic loading may cause aerofoil to be out of shape normally to lock or directly to destroy and not lock aerofoil.
3) after trigger mechanism work, must unlock the latching device being originally in collapsed state, how transmit rapidly the signal that timing unit transmits, how reliably to unlock latching device in time, be also ensure that upper and lower half wing connects an important ring of locking smoothly in time.
4) whole mechanism should set back under the condition not dismantling wing.Conveniently carry out structural adjustment and inspection, the interlock of sleeve mechanism should not be unidirectional, and should realize in the process of hand foldable, whole mechanism can reset into folded state, and whole process is without the need to dismantling wing, direct peripheral operation.
5) each component units of mechanism must all be fixed on wing inside, guarantee that fixed form is solid and reliable, and mechanical operation does not affect by gravity direction, all can normally work when wing attitudes vibration, aerofoil distortion.
When design folding wings mechanism, except these technical matterss above will be solved, in order to realize being applied to the transformation of existing non-collapsible aerofoil profile aircraft, mechanism must be reduced to take up room as far as possible, all parts are placed in wing inner space, and be applicable to the span about 1m, the wing carries the various common aerofoil profile of below 1000N.The purpose of this utility model solves the problems of the technologies described above exactly, provides the aircraft folding wings device that a kind of structure is simple, operation is convenient, take up room little, cost is low.
Utility model content
Based on above-mentioned purpose, the invention theory that the utility model adopts " hand foldable, Automatic-expanding are locked ", adopt the laterally folded form that folding rotary shaft is parallel with aircraft axis of symmetry, unidirectional automation full mechanical, reduce system complexity, according to Strength co-mputation and motion simulation result appropriate design transmission device, ensure structural reliability, provide a kind of folding wings device, described device comprises:
Collapsible and launch upper half wing 1, state constant lower half wing 2, for fixing upper half wing 1 and make its sway with the turning cylinder 3 changed between folded state and deployed condition, for lock the deployed condition of half wing 1 and invertibility turn again catch gear 4, for controlling trigger mechanism 6 that catch gear 4 changes between locking with release position and switch mechanism 7, and for the interlinked mechanism 5 of synchronous interlock trigger mechanism 6 and switch mechanism 7, wherein go up half wing 1 and be fixed on lower half wing 2 by turning cylinder 3.
In a preferred technical scheme, the contact surface of half wing 1 is provided with two protruding connecting arms 11 on described, described lower half wing 2 is provided with the recessed link slot 21 of two of adapting with described connecting arm 11, when described folding wings is launched completely, described connecting arm 11 is completely involutory with link slot 21; Turning cylinder 3 is arranged at the midway location of connecting arm 11 and link slot 21, and described turning cylinder 3 is driven by torsion spring group 31.The quantity of torsion spring can be two or more, but at least needs respectively to arrange one at the two ends of turning cylinder 3.In order to increase the area of contact of half aerofoil up and down, upper half wing 1 can engage in dentation with the contact surface of bottom wing on lower half wing 2.
Preferably, described catch gear 4 is arranged on the position in the middle of two link slots 21 of distribution on lower half wing 2, wherein arrange the straight trough 41 being communicated with upper half wing 1 and lower half wing 2, place locking sliding block 42 in described straight trough 41, locking sliding block 42 can slide up and down and can be fixed or discharge in straight trough 41.Slide block can be made up of steel material, and the cube configuration of homogeneous can ensure can bear the main aerodynamic loading of vertical aerofoil by the main element when upper half wing resets as the upper and lower half wing of connection.
More preferably, described straight trough 41 arranges draw-in groove 43, slide block 42 lower end is provided with the button 44 of shaft-like projection, described button 44 can come and go slip in draw-in groove 43, and slide block 42 can be fixed or discharge.Can also arrange in slide block 42 upper end one with the snap-on 47 of the mutually level arc convex of button 44, in upper half wing, the correspondence position of half straight trough has arc groove 48, to ensure slide block 42 in locking when half wing, snap-on 47 and groove 48 fasten, in case limited slip block 42 up-and-down movement.And snap-on 47 and button 44 interlock, when folding, press the button 44, snap-on 47 is also corresponding to be packed up.
More preferably, described draw-in groove 43 is parallel with straight trough dumb-bell shape structure, and upper and lower two ends are bell-shaped is configured to static stall for it, and lower end gear is folding gear, upper end gear is locking gear, and described button 44 can by sliding and entering and leave static stall in draw-in groove 43.
More preferably, be provided with compression-spring device 45 bottom slide block 42, compression-spring device 45 back is provided with compression-spring device 46, and it is by the inclination of the axle of stage clip 45 remote effect slide block.When slide block 42 is pressed into lower aerofoil 2, compression-spring device 45 is in compression storage power state, and button 44 enters folding gear, by the pressure fixing of compression-spring device 46, slide block can not be ejected.
In a preferred technical scheme, described interlinked mechanism 5 comprise be installed on gear one 51A on lower half wing 2 and gear four 51D, with gear two 51B of gear one 51A interlock and driving band one 52A, with gear three 51C of gear four 51D interlock and driving band two 52B, and connecting the couple axle 53 of gear two 51B and gear three 51C, the axle center of gear one 51A is provided with torsion spring 54.
Preferably, described trigger mechanism 6 is installed on lower half wing 2, comprises a gear snap close 61 that can be embedded in gear one 51A between cog and the contact 62 extended by snap close 61.
More preferably, described switch mechanism 7 is made up of rotary gear shaft 71 and switch sheet 72, rotary gear shaft 71 one end be fixed on gear four 51D and with its coaxial rotation, the other end is connected with switch sheet 72, switch sheet 72, drive switch sheet to rotate when gear four 51D rotates, slide block 42 bottom is pushed rearward dynamic, slide block 42 entirety rotates backward, and button 44 is deviate to unlock from draw-in groove 43.
Preferably, rotary gear shaft 71 is connected with switch sheet 72 by a short handle 73, and described switch sheet 72 is shape at right angles, before described right angle inner surface and slide block 42 and bottom surface fit.
The utility model mainly relies on transmission device, spring installation and notch to complete aerofoil folding and expanding function.Principle is after hand foldable top airfoil, and top airfoil launches around axle under torsion spring effect, triggers the upper lower aerofoil of latching device locking at the end of its reseting movement.Whole device has following innovation point:
1. locking sliding block and subsidiary thereof.In order to bear the main aerodynamic loading of vertical aerofoil, designing a high strength cube steel slide block, sliding up and down in the straight trough that the interface of upper and lower half wing is communicated with two halves aerofoil.Slide block arranges " locking " (expansion) and " folding " two gears, the draw-in groove under being of control gear on half wing and the button on slide block.Slide up and down by the Spring driving connected bottom it, when slide block is in " folding " gear, spring is in compressive state.Slide block intensity is large, and energy two grades of any switching laws, upper and lower half wing can be connected when upper half wing resets as main, bear the element of larger aerodynamic loading.
2. reset contact and interlinked mechanism thereof.Design a contact mechanism to be arranged on lower half wing, be positioned at half wing and reset on the moving line of rotation, when making it to reset, the sport of upper half wing triggers contact mechanism.The snap close of the gear structure inside contact mechanism interlock unclamps, and gear starts to rotate under the torsion spring effect of pretwist, drives interlinked mechanism to start the release mechanism of slide block.This mechanism achieves and realizes start by set date with mechanical element, can be started timely unlock lower aerofoil on slider locking by design contact position.
3. slide block release mechanism and switch mechanism.Because slide block is fixed on " folding " gear by the spring at back by gear button, the approach unlocked is that Compress Spring makes button exit from draw-in groove, on slide block slides under the action of the spring " locking " gear, (gear four 51D is the driving of release mechanism to the switch mechanism that moves around axle of design employing one, switch mechanism is driven to rotate), act on the bottom of slide block (switch structure as shown in Figure 7, the short handle be fixed on switch sheet by an one end and gear four 51D coaxial rotation one also has the switch sheet of rectangular shape to form, fit with bottom surface before the right angle inner surface of switch sheet and cube slide block).The gear one 51A interlock of gear four 51D and trigger mechanism, under the rotational load effect that trigger mechanism transmits, gear 51 4 D rotates and drives short handle then switch sheet rotation, and slide block bottom is pushed rearward dynamic, and slide block entirety rotates backward, and button is deviate to unlock from draw-in groove.Because this mechanism directly make use of the rotational load of contact mechanism, can realize with contact mechanism without time difference interlock, and separate lock slide rapidly, lock upper and lower half wing.
4. oppositely restore mechanism.All driver elements of aerofoil Automatic-expanding are all spring and torsion spring, have reversible operation; The switch sheet of slide block release mechanism can set back when slide block is taken in lower aerofoil by hand foldable under the drive of slide block, and drive interlinked mechanism to rotate and transmit rotational load until gear in contact mechanism, all elements recover original folded state.
The program is only made up of physical construction, realizes the self-driven running of folding process system by mechanism design, without the need to energy recharge, not containing electronic component or control program, simple and reliable.Realizing on the necessary function of folding wings and reliability basis, by structural complexity and cost control at reduced levels, taking up room little, can be applicable to the transformation of old model aerofoil collapsibleization.
By calculating, the utility model technology is applied to the span about 1m, and when the monolithic wing carries the middle-size and small-size aircraft of about 1000N, all elements all adopt common specification, can first aerofoil be driven to reset in 500ms after the folding constraint of releasing.And optimized by Rational structure, can ensure that homonymy two is to folding mutually the aerofoil duration of run difference of fastening in 100ms, and after ensureing locking, monolithic aerofoil can normally bear aerofoil load.
Because structure is simple, the more common aerofoil productive costs of folded surface that application the utility model technology is produced only increases by 50 ~ 80%, only account for less than 1% of general middle bug total cost, if carry out the upgrading of the non-collapsible wing, vehicle launch size is reduced about 1/3 by cost that can be lower.
Accompanying drawing explanation
The structural representation of Figure 1A, 1B. the utility model folding wings;
Fig. 2. the folded state detail view of a specific embodiments of the utility model folding wings;
Fig. 3. the locking state detail view of a kind of specific embodiments of the utility model folding wings;
Fig. 4. detail view when catch gear slides in straight trough 41
Fig. 5. trigger mechanism detail view;
Fig. 6. catch gear and the switch mechanism detail view when folded state;
Fig. 7. the operation logic figure of switch mechanism when unlocking folded state;
Fig. 8 A, 8B, 8C. catch gear and switch mechanism are from manual reset procedure figure when being locked to folded state.
Description of reference numerals:
Half wing on 1,
11 connecting arms
2 times half wings
21 link slots,
3 turning cylinders
31 torsion spring groups
4 catch gears
41 straight troughs
42 locking sliding blocks
43 draw-in grooves
44 buttons
45 compression-spring devices
46 compression-spring devices
47 snap-ons
48 grooves
5 interlinked mechanisms
51 gears (A, B, C, D)
52 driving bands (A, B)
53 couple axles
54 torsion springs
6 trigger mechanisms
61 gear snap closes
62 contacts
7 switch mechanisms
71 rotary gear shafts
72 switch sheets
73 short handles
Detailed description of the invention
Further describe the utility model below in conjunction with specific embodiment, advantage and disadvantage of the present utility model will be more clear along with description.But these embodiments are only exemplary, do not form any restriction to protection domain of the present utility model.
Embodiment
The utility model technology is applied in the fixed-wing transformation of BW III X-3 type target missile, the overall aerofoil of script fixed-wing is placed fold mechanism and spring etc. by utilizing space in the wing of 1/3, repacking common aerofoil into folding wings.
Below a specific embodiments of the present utility model:
Fig. 1 shows the sketch design drawing of this device, shows this device and comprises half wing 1, lower half wing 2, turning cylinder 3, catch gear 4, interlinked mechanism 5.Figure 1B is the section-drawing of Figure 1A, and slice location and projecting direction are as shown in the dashed cutting-line on 1A and arrow B-B, and because parts inside wing are not symmetrical, for cuing open all key components and parts, the section chosen here is not the aerofoil plane of symmetry.
What Fig. 2 showed is the detail view of folding wings when folded state, as shown in the figure, the upper half wing 1 of described device and the contact surface of lower half wing 2 are provided with two protruding connecting arms 11, described lower half wing 2 is provided with the recessed link slot 21 of two of adapting with described connecting arm 11, turning cylinder 3 is arranged at the midway location of connecting arm 11 and link slot 21, and described turning cylinder 3 is driven by torsion spring group 31.
Upper half wing 1 and lower half wing 2 intersection are provided with catch gear, the straight trough 41 being communicated with upper half wing 1 and lower half wing 2 is wherein set, locking sliding block 42 is placed in described straight trough 41, compression-spring device 45 is provided with bottom slide block 42, when folded state, slide block 42 is pressed into lower aerofoil 2, and stage clip 45 is in compression storage power state.
Comprise at the upper interlinked mechanism arranged of lower half wing (2): be installed on gear one 51A in lower half wing 2, with gear four 51D of switch mechanism interlock, with gear two 51B of gear one 51A interlock and driving band one 52A, with gear three 51C of gear four 51D interlock and driving band two 52B, and connect the couple axle 53 of gear two 51B and gear three 51C.Described trigger mechanism 6 is installed on lower half wing 2.
What Fig. 3 showed is the detail view of folding wings when locking state, and as shown in the figure, when described folding wings is launched completely, described connecting arm 11 is completely involutory with link slot 21.When folded state, a part for slide block 42 enters in top airfoil 1, and stage clip 45 extends to some extent, and still slide block is stabilized in straight trough top by remainder stress.
Fig. 4 display be the catch gear of folding wings detail view when sliding in straight trough 41.As shown in the figure, arrange the straight trough 41 being communicated with upper half wing 1 and lower half wing 2, place locking sliding block 42 in described straight trough 41, locking sliding block 42 can slide up and down in straight trough 41,
Described straight trough 41 arranges draw-in groove 43, draw-in groove 43 is vertical dumb-bell shape structure, upper and lower two ends are bell-shaped is configured to static stall for it, wherein lower end gear is folding gear, upper end gear is locking gear, described slide block 42 arranges the button 44 with shaft-like projection adapted with bell-shaped structure, and described button 44 can, by sliding in draw-in groove 43 and entering and leave static stall, make slide block 42 to be fixed or to discharge.Arrange in slide block 42 upper end one with the snap-on 47 of the mutually level arc convex of button 44, in upper half wing, the correspondence position of half straight trough has arc groove 48, to ensure slide block 42 in locking when half wing, snap-on 47 and groove 48 fasten, in case limited slip block 42 up-and-down movement.Snap-on 47 and button 44 interlock, press the button 44 when hand foldable, and snap-on 47 is also corresponding to be packed up.
Be provided with compression-spring device 45 bottom slide block 42, compression-spring device 45 back is provided with compression-spring device 46, and it is by promoting the inclination of the axle of stage clip 45 remote effect slide block.When slide block 42 is pressed into lower aerofoil 2, stage clip 45 is in compression storage power state, and button 44 enters folding gear, by the pressure fixing of compression-spring device 46, slide block can not be ejected.
Fig. 5 display be the detail view of the trigger mechanism of folding wings.Described trigger mechanism 6 comprises a gear snap close 61 that can be embedded in gear one 51A between cog and the contact 62 extended by snap close 61.The axle center of gear one 51A is provided with torsion spring 54.
What Fig. 6 showed is catch gear and the switch mechanism detail view when folded state; Gear four 51D is the driven wheel of switch mechanism, and rotary gear shaft 71 is connected with switch sheet 72 with short handle 73, and switch sheet 72 contacts with slide block 42 bottom surfaces, and now slider button 44 is positioned on folding gear, and device is in folded state.
What Fig. 7 showed is the principle detail view of switch mechanism when unlocking folded state, shows the continuous action relation of rotary gear shaft 71 and short handle 73 and switch sheet 72.
Fig. 8 display be catch gear and switch mechanism from manual reset procedure figure when being locked to folded state, when Fig. 8 A display hand foldable makes slide block move downward half wing in unblock along straight trough 41, the relative position of switch sheet 72 and slide block 42, and the sense of motion of slide block 42.Through the motion process of Fig. 8 B and Fig. 8 C, final slide block device will reset to folded state.
The working mechanism of this specific embodiments is:
From folding into locking: when top airfoil 1 folds, torsion spring group 31 is in and reverses storage power state, rotating shaft 3 and top airfoil 1 connect firmly synchronous axial system, when top airfoil is released, torsion spring group 31 discharges torsion, upper half wing 1 rotates around rotating shaft 3 and launches under the effect of torsion spring group 31, on when being about to reset before half wing 1 connecting arm lower contacts to the contact 62 in the trigger mechanism being installed on lower half wing 2 and with its deflection, contact 62 drives the gear snap close 61 of coaxial rotation to untie, gear one 51A rotates under the effect of pretwist torsion spring 54, rely on interlinked mechanism rotation to be delivered on gear four 51D always, gear four 51D drives the switch mechanism of coaxial rotation to rotate, switch sheet 72 contacts with slide block 42 bottom surfaces, promote slide block 42 bottom yaw motion backward, slide block 42 is caused to tilt backwards, button 44 is released and exits from draw-in groove 43, act on sliding block at the stage clip 45 being in compressive state and slide into top along straight trough 41, slip into top airfoil 1 groove from lower aerofoil 2, its the first half enters half wing 1, lower aerofoil in connection, button 44 snaps into the gear of draw-in groove 43 upper end, pin the upper half wing resetted, realize the locking of aerofoil Automatic-expanding.
In this process, torsion spring group 31 is power units that folding wings is launched rapidly to reset, and catch gear controls the clocked flip of location and the locking launched.
From expansion (locking) to folding:
Being manual from being deployed into folding, utilizing and oppositely restoring mechanism, completing the conversion from being locked to folded state.First press the button with hand that (part that root diameter (RD) is larger can by compressing into slide block, the part that diameter above moves along draw-in groove compared with I is non-telescoping) and slide block is pressed downwards, compression press spring 45, until button arrives draw-in groove bottom, locking sliding block 42 is pressed in the lower aerofoil part of straight trough 41 completely, and unclamp hand and eject locking sliding block by button 44, now slide block exits completely from upper half wing, lower aerofoil is connected disconnect, fixedly make slide block 42 pop up by notch 41.Top airfoil 1 is folded.Now stage clip 45 is in compression storage power state.
With reference to accompanying drawing 8, when slide block M/C slips down to bottom straight trough, switch sheet 72 can be driven to restore, drive gear four 51D of coaxial rotation with it simultaneously, then gear four 51D relies on the torsion spring 54 that interlinked mechanism transmits rotation driven gear one 51A and is connected with gear one 51A, make torsion spring 54 reverse storage power, when gear one 51A rotates backward on earth, gear snap close 61 pins gear.
Claims (10)
1. an aircraft folding wings device, described device comprises upper half wing (1) that is collapsible and that launch, the lower half wing (2) of state constant, for fixing upper half wing (1) and making it sway with the turning cylinder changed between folded state and deployed condition (3), for locking the deployed condition of upper half wing (1) and the catch gear (4) that turns again of invertibility, the trigger mechanism (6) and switch mechanism (7) changed between release position is being locked for controlling catch gear (4), and for the interlinked mechanism (5) of synchronous interlock trigger mechanism (6) and switch mechanism (7), wherein go up half wing (1) to be fixed on lower half wing (2) by turning cylinder (3).
2. device according to claim 1, it is characterized in that, the contact surface of half wing (1) is provided with two protruding connecting arms (11) on described, described lower half wing (2) is provided with the recessed link slot (21) of two of adapting with described connecting arm (11), when described folding wings is launched completely, described connecting arm (11) is completely involutory with link slot (21); Turning cylinder (3) is arranged at the midway location of connecting arm (11) and link slot (21), and described turning cylinder (3) is driven by torsion spring group (31).
3. device according to claim 2, it is characterized in that, described catch gear (4) is arranged on the position in the middle of two link slots (21) of the upper distribution of lower half wing (2), the straight trough (41) being communicated with upper half wing (1) and lower half wing (2) is wherein set, place locking sliding block (42) in described straight trough (41), locking sliding block (42) can slide up and down and can be fixed or discharge in straight trough (41).
4. device according to claim 3, it is characterized in that, described straight trough (41) arranges draw-in groove (43), slide block (42) is provided with the button (44) of shaft-like projection, described button (44) can come and go slip in draw-in groove (43), and slide block (42) can be fixed or discharge.
5. device according to claim 4, it is characterized in that, described draw-in groove (43) is parallel with straight trough dumb-bell shape structure, upper and lower two ends are bell-shaped is configured to static stall for it, lower end gear is folding gear, upper end gear is locking gear, and described button (44) can slide and enter and leave static stall in draw-in groove (43).
6. device according to claim 5, it is characterized in that, slide block (42) bottom is provided with compression-spring device (45), compression-spring device (45) back is provided with compression-spring device (46), when slide block (42) press-in lower aerofoil (2), compression-spring device (45) is in compression storage power state, button (44) enters folding gear, by the pressure fixing of compression-spring device (46), slide block can not be ejected.
7. device according to claim 1, it is characterized in that, described interlinked mechanism (5) comprise be installed on gear one (51A) on lower half wing (2) and gear four (51D), with the gear two (51B) of gear one (51A) interlock and driving band one (52A), and the gear three (51C) of gear four (51D) interlock and driving band two (52B), and connecting the couple axle (53) of gear two (51B) and gear three (51C), the axle center of gear one (51A) is provided with torsion spring (54).
8. device according to claim 7, it is characterized in that, described trigger mechanism (6) is installed on lower half wing (2), comprises a gear snap close (61) that can be embedded in gear one (51A) between cog and the contact (62) extended by snap close (61).
9. device according to claim 7, it is characterized in that, described switch mechanism (7) is made up of rotary gear shaft (71) and switch sheet (72), rotary gear shaft (71) one end be fixed on gear four (51D) and with its coaxial rotation, the other end is connected with switch sheet (72), switch sheet is driven to rotate when gear four (51D) rotates, slide block (42) bottom is pushed rearward dynamic, slide block (42) entirety rotates backward, and button (44) is deviate to unlock from draw-in groove (43).
10. device according to claim 9, it is characterized in that, rotary gear shaft (71) is connected with switch sheet (72) by a short handle (73), described switch sheet (72) at right angles shape, before described right angle inner surface and slide block (42) and bottom surface fit.
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|---|---|---|---|
| CN201520271420.3U CN204775993U (en) | 2015-04-29 | 2015-04-29 | Wing device is folded to aircraft |
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|---|---|---|---|
| CN201520271420.3U CN204775993U (en) | 2015-04-29 | 2015-04-29 | Wing device is folded to aircraft |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104802978A (en) * | 2015-04-29 | 2015-07-29 | 北京威标至远科技发展有限公司 | Folding wing device of aircraft |
| CN105799914A (en) * | 2016-03-17 | 2016-07-27 | 北京昆仑凯利科技有限公司 | Rotation unfolding mechanism for aircraft wing |
| CN110758773A (en) * | 2019-11-21 | 2020-02-07 | 上海卫星工程研究所 | Spacecraft and spring pre-tightening high-rigidity locking device thereof |
| CN112046730A (en) * | 2020-09-17 | 2020-12-08 | 江苏云博智能科技有限公司 | Wing folding structure of unmanned aerial vehicle |
| CN112665468A (en) * | 2020-12-21 | 2021-04-16 | 兰州空间技术物理研究所 | Novel strong locking and weak unlocking mechanism |
| CN113665790A (en) * | 2021-08-11 | 2021-11-19 | 广东空天科技研究院 | Locking mechanism for energy storage driving folding wing folding state and folding wing |
| CN114348238A (en) * | 2021-12-23 | 2022-04-15 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pull rod type airplane folding wing tip and operation method thereof |
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- 2015-04-29 CN CN201520271420.3U patent/CN204775993U/en active Active
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104802978A (en) * | 2015-04-29 | 2015-07-29 | 北京威标至远科技发展有限公司 | Folding wing device of aircraft |
| CN104802978B (en) * | 2015-04-29 | 2017-04-12 | 北京威标至远科技发展有限公司 | Folding wing device of aircraft |
| CN105799914A (en) * | 2016-03-17 | 2016-07-27 | 北京昆仑凯利科技有限公司 | Rotation unfolding mechanism for aircraft wing |
| CN110758773A (en) * | 2019-11-21 | 2020-02-07 | 上海卫星工程研究所 | Spacecraft and spring pre-tightening high-rigidity locking device thereof |
| CN112046730A (en) * | 2020-09-17 | 2020-12-08 | 江苏云博智能科技有限公司 | Wing folding structure of unmanned aerial vehicle |
| CN112046730B (en) * | 2020-09-17 | 2022-01-04 | 江苏云博智能科技有限公司 | Wing folding structure of unmanned aerial vehicle |
| CN112665468A (en) * | 2020-12-21 | 2021-04-16 | 兰州空间技术物理研究所 | Novel strong locking and weak unlocking mechanism |
| 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 |
| CN113665790A (en) * | 2021-08-11 | 2021-11-19 | 广东空天科技研究院 | Locking mechanism for energy storage driving folding wing folding state and folding wing |
| CN113665790B (en) * | 2021-08-11 | 2023-03-17 | 广东空天科技研究院 | Locking mechanism for energy storage driving folding wing folding state and folding wing |
| CN114348238A (en) * | 2021-12-23 | 2022-04-15 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pull rod type airplane folding wing tip and operation method thereof |
| CN114348238B (en) * | 2021-12-23 | 2024-01-16 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Pull rod type aircraft folding wing tip and operation method thereof |
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