CN208325624U - It is a kind of to realize the system for flutterring solid wing structure multi-angle accurate transformation - Google Patents
It is a kind of to realize the system for flutterring solid wing structure multi-angle accurate transformation Download PDFInfo
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- CN208325624U CN208325624U CN201821025266.1U CN201821025266U CN208325624U CN 208325624 U CN208325624 U CN 208325624U CN 201821025266 U CN201821025266 U CN 201821025266U CN 208325624 U CN208325624 U CN 208325624U
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Abstract
The utility model discloses a kind of systems realized and flutter solid wing structure multi-angle accurate transformation, it solves the problems, such as that the prior art is not suitable for the bionics fiber of large-scale flying bird, mostly dependent on dedicated landing runway, with can be realized flapping wing take off, fixed-wing cruise, can cruising phase neatly change fixed-wing angle effect；Its technical solution are as follows: including driving device and control system, driving device connects gear wheel by transmission mechanism, and gear wheel two sides are respectively equipped with a concentric sliding slot, and sliding slot two sides pass through the fixed axis connection control system of trigonometric expression；The center two sides of gear wheel connect wing main spar by crank and rocker mechanism respectively, and wing main spar and fuselage girder are rotatablely connected；The amplitude of swatting of wing main spar is detected by the angular transducer for being installed on fuselage girder side, and angular transducer will test signal and reach control system, and control system control trigonometric expression fixing axle is matched with matching hole a certain in sliding slot, and solid wing conversion is flutterred in realization.
Description
Technical field
The utility model relates to bionic flapping-wing flying vehicle field more particularly to a kind of realization, to flutter solid wing structure multi-angle accurate
The system of conversion.
Background technique
Flapping wing aircraft is a kind of new concept aircraft for imitating flying bird or principle of insect flight design and manufacture.With fixed-wing
Aircraft is different, and fixed wing aircraft is to generate lift by wing, generates the power that moves ahead by the thrust or traction of engine, and flapping wing
The lift and thrust of aircraft are generated by a sized flap wings system.Flapping flight has special aerodynamic characteristic, it is easier to
Miniaturization.Bionics Study show when size it is small to a certain extent after, flapping flight have irreplaceable characteristic.
Furthermore flapping wing aircraft also has the characteristics that size is small, light-weight and good concealment, based on this important strategic importance, extensively by
To the attention of military field, rapidly developed in recent decades.
The wing of flying bird and insect has a common movement characteristic in entire flight course --- swat, swat be around
The angular movement for patting axis identical with its heading.Under different state of flights, swatting angle is variation.Flying bird and elder brother
Worm swats the optimal aeroperformance of angle realization at angle by changing.Gliding, which is able to lasting condition, is: weight/speed=movement
Distance/mistake is high, thus the ratio of lift and resistance is higher, gliding when swat the angle at angle and be cured hour, the speed of sinking is also slower,
To obtain farther away horizontal gliding distance.It can be seen that the distance that angle angle directly affects gliding is swatted when gliding, however simultaneously
Always gliding distance is not the bigger the better, and needs according to the actual situation by swatting the variation of angle angle, to adjust gliding distance.Such as
Imitative albatross morphing aerodynamic optimization shape angle when switching to land by gliding is about -5 °, is switching to anti-bow of dashing forward by gliding
Aerodynamic optimization shape angle is about 30 ° when rushing, and the angle of aerodynamic optimization shape is about -15 ° in cruise.
It is current on the low side for the bionical research of large-scale flying bird full offline mode mechanism transformation progress mechanism both at home and abroad, it is only
Hybrid motion formula bionic Aircraft structure is mostly to flutter rotor mode, i.e. flapping wing and rotor matches, the bionical object of such aircraft
For winged insect and small-sized flying bird, the bionics fiber to large-scale flying bird is not suitable for.Therefore, one kind need to be designed and flutter solid wing motor pattern
Aircraft to solve the above problems.
And a critical issue is exactly how to realize that flapping flight mode and fixed-wing fly in flutterring solid rotor aircraft design
Steady, accurate conversion between row mode.The conversion is not only the single conversion of flapping wing and fixed interplane, need to also be flown in fixed-wing
Under row mode, the angle of the dynamic adjusting machine wing, to realize that aircraft reaches optimum pneumatic performance in varied situations.Therefore urgently
A kind of realize need to be designed and flutter the Mechatronic Systems that solid wing structure multi-angle is accurately converted.
Utility model content
In order to overcome the deficiencies of the prior art, the utility model provides, and a kind of realization is flutterred solid wing structure multi-angle and is accurately turned
The system changed, have can be realized flapping wing take off, fixed-wing cruise, high-efficient, cruising speed is fast, can cruising phase spirit
Change the effect of the angle of fixed-wing livingly.
The utility model adopts the following technical solutions:
It is a kind of to realize the system for flutterring solid wing structure multi-angle accurate transformation, including driving device and control system, driving dress
It sets and a gear wheel is connected by transmission mechanism, gear wheel two sides are respectively equipped with a concentric sliding slot, and sliding slot two sides are logical
Cross the fixed axis connection control system of trigonometric expression；
The center two sides of gear wheel connect wing main spar, wing main spar and fuselage master by crank and rocker mechanism respectively
Beam rotation connection, the rotation of gear wheel drive the realization of wing main spar to swat operation；
The amplitude of swatting of wing main spar is detected by the angular transducer for being installed on fuselage girder side, and angular transducer will
Detection signal reaches control system, and control system control trigonometric expression fixing axle is matched with matching hole a certain in sliding slot, and realization is flutterred solid
Wing conversion；
Further, interval set distance is arranged multiple matching holes in the sliding slot, trigonometric expression fixing axle and different cooperations
Angle difference is swatted when hole connects.
Further, the gear wheel center is fixed with central axis, and central axis both ends are separately connected crank and rocker mechanism；
The crank and rocker mechanism includes crank and transmission rocking bar, and crank one end is connected with central axis, the crank other end and
It is hinged to be driven rocking bar one end；The transmission rocking bar other end is divided into two sections, and it turns with being set on the outside of wing girder frame
Dynamic bearing is hinged；
Further, the trigonometric expression fixing axle includes two groups, and each group of trigonometric expression fixing axle includes first connecting rod and the
Two connecting rods；First connecting rod is connected with the end of second connecting rod by connecting shaft compatible with sliding slot；
Further, first connecting rod and second connecting rod head end are rotatablely connected with control system respectively, and pass through stepper motor
Driving is to change fixed angles size；
Further, fuselage body frame two sides are separately installed with rotating base, and the wing main spar passes through rotary shaft
It is connected with rotating base, rotating base side fixed angle sensor；
Further, the driving device be driving motor, driving motor be connected be meshed with the gear wheel it is small
Gear；
Further, the control system includes cabinet, and controller is arranged in box house, and the bottom of box passes through shaft and three
Angie type fixing axle is connected.
Realize the operating method for flutterring the system of solid wing structure multi-angle accurate transformation, comprising the following steps:
Step (1) takeoff phase, motor pattern are flapping mode, and driving motor drive gear wheel rotates, and gear wheel passes through
Crank handle turns are driven rocking bar and swing, and transmission rocking bar drives wing main spar to swat up and down around rotating base by rolling bearing；This
When trigonometric expression fixing axle it is hanging, do not contacted with canine tooth wheel side sliding slot.
Step (2) cruising phase, control system judgement swat whether frequency meets given threshold, and swat angle according to current
Degree information swats frequency, to obtain the shaft hole matching time；Fixed angles are changed to by controlling initial angle, axis hole is made to start to match
It closes, and control system judges whether axis hole successfully cooperates；After axis hole successfully cooperates, it is converted to fixed-wing state.
Step (3) landing phases are changed to initial angle by controlling fixed angles, keep trigonometric expression fixing axle and matching hole de-
From；Start driving motor when axis hole completely disengages, is converted to flapping wing state.
Further, when swatting frequency greater than given threshold, control system control driving motor, which is decelerated to, swats frequency
Less than given threshold.
Compared with prior art, the utility model has the beneficial effects that
(1) the utility model is smoothly and precisely to realize aircraft wing flapping flight and more in the case where difference swats speed
Free switching between angle fixed-wing offline mode, while can be in the case where flapping wing speed is effectively reduced and crosses high state, flapping flight
Be converted to the damage that fixed-wing flies to aircraft mechanical component.
(2) the utility model setting wing amplitude calculates module, and the signal of angular transducer detection is calculated by wing amplitude
Module calculates and analysis, improves the accuracy for flutterring solid wing conversion；Have the effect of that accuracy is high, adaptable.
Detailed description of the invention
The accompanying drawings constituting a part of this application is used to provide further understanding of the present application, and the application's shows
Meaning property embodiment and its explanation are not constituted an undue limitation on the present application for explaining the application.
Fig. 1 is the axonometric drawing of the utility model；
The axonometric drawing that Fig. 2 is the utility model wing angle when being 30 ° under fixed-wing mode；
Fig. 3 be the utility model wing angle be -5 ° when fixed-wing mode under axonometric drawing；
Fig. 4 be the utility model wing angle be -15 ° when fixed-wing mode under axonometric drawing；
Fig. 5 connect axonometric drawing with trigonometric expression fixing axle for the utility model control system；
Fig. 6 is the utility model control system and the fixed axis connection main view of trigonometric expression；
Fig. 7 is the partial enlarged view of Fig. 6；
Fig. 8 is the gear wheel structural schematic diagram of the utility model；
Fig. 9 is the angular transducer scheme of installation of the utility model；
Connection figure when Figure 10 is the utility model trigonometric expression fixing axle and control system is in initial angle；
Connection figure when Figure 11 is the utility model trigonometric expression fixing axle and control system is in fixed angles；
Figure 12 is the utility model control system flow chart.
Wherein, 1- fuselage body frame；2- gear wheel；3- driving motor；4A, 4B- crank；5A, 5B- are driven rocking bar；6A,6B-
Wing main spar；7A, 7B- rolling bearing；8A, 8B- rotating base；9- cabinet；10- trigonometric expression fixing axle；11A,11B,11C-
Matching hole；12- angular transducer；13- stepper motor；14- first connecting rod；15- second connecting rod；16- connecting shaft；17- shaft；
18- sliding slot.
Specific embodiment
It is noted that following detailed description is all illustrative, it is intended to provide further instruction to the application.Unless another
It indicates, all technical and scientific terms used herein has usual with the application person of an ordinary skill in the technical field
The identical meanings of understanding.
It should be noted that term used herein above is merely to describe specific embodiment, and be not intended to restricted root
According to the illustrative embodiments of the application.As used herein, unless the context clearly indicates otherwise, otherwise singular
Also it is intended to include plural form, additionally, it should be understood that, when in the present specification using term "comprising" and/or " packet
Include " when, indicate existing characteristics, step, operation, device, component and/or their combination.
As background technique is introduced, exist in the prior art be not suitable for large-scale flying bird bionics fiber, mostly according to
The deficiency of the dedicated landing runway of Lai Yu, in order to solve technical problem as above, present applicant proposes a kind of realizations to flutter solid wing structure
The system of multi-angle accurate transformation.
In a kind of typical embodiment of the application, as shown in Figure 1-Figure 11, provides a kind of realize and flutter solid wing structure
The system of multi-angle accurate transformation, including driving device, control system, gear wheel 2, trigonometric expression fixing axle 10, fuselage body frame 1,
Crank and rocker mechanism and wing main spar 6A (6B).
The center of gear wheel 2 is fixed with central axis, and the both ends of central axis are separately connected a crank and rocker mechanism, crank rocker
Mechanism includes crank 4A (4B) and transmission rocking bar 5A (5B), and the one end crank 4A (4B) is connected with central axis, and crank 4A (4B) is another
End and transmission one end rocking bar 5A (5B) are hinged；Transmission rocking bar 5A (5B) other end is divided into two sections, forms y-type structure.
The two sides of fuselage body frame 1 are rotatablely connected with a wing main spar 6A (6B) respectively.
Preferably, the two sides of fuselage body frame 1 are respectively mounted rotating base 8A (8B), and rotating base 8A (8B) includes two mutual
Parallel riser passes through rotation axis connection wing main spar 6A (6B) between two risers.
Angular transducer 12 is fixed with (far from the side wing main spar 6A (6B)) on the outside of one of riser.
Wing main spar 6A (6B) outer circumferential is arranged with rolling bearing 7A (7B), the two sides (7B) rolling bearing 7A point
The two sections of ends that do not set up separately with transmission rocking bar 5A (5B) are hinged.
Driving device is connected by transmission mechanism with gear wheel 2.
Preferably, the transmission mechanism is a pinion gear, and the driving device is driving motor 3.
The pinion gear is installed on the motor shaft of driving motor 3, pinion gear engaged with gear wheel 2 (herein, it is large and small only
For relative concept, gear specific size is not defined), 3 driving pinion of driving motor rotation, to realize gear wheel
2 rotation, gear wheel 2 are swung up and down by crank 4A, crank 4B driving transmission rocking bar 5A, the transmission rocking bar 5B of its two sides.
2 two sides of gear wheel are respectively equipped with the sliding slot 18 of circular ring shape close to endface position, and sliding slot 18 and gear wheel are concentric
It is arranged and there is certain depth；Three matching holes of setting spaced apart in sliding slot 18, i.e. matching hole 11A, matching hole 11B,
Matching hole 11C enables aircraft to respectively reach three different fixation wing angles by three matching holes, i.e. ,-
15 °, -5 ° and 30 °.
Above-mentioned cooperation bore dia is equal with 18 width of sliding slot, to guarantee the connecting shaft 16 of trigonometric expression fixing axle 10 along sliding slot
18 slidings.
Wherein, wing angle is determined by formula (1):
In formula (1), θ is that wing main spar 6A (6B) swats angle, and R is crank 4A (4B) length, and w is 2 jiaos of speed of gear wheel
Degree, l are crank 4A (4B) to 2 centre distance of gear wheel, and rolling bearing 7A (7B) is to the distance of wing main spar 6A (6B)
For l.
The symmetrical two trigonometric expression fixing axles 10 in 2 two sides of gear wheel, the trigonometric expression fixing axle 10 include first connecting rod
14, second connecting rod 15 and connecting shaft 16, first connecting rod 14 are connected with one end of second connecting rod 15, connect at the tie point of the two with one
Spindle 16 is connected；The diameter of the connecting shaft 16 is adapted with 18 size of sliding slot.
Angle between first connecting rod 14 and second connecting rod 15 is 60 °, and connecting shaft 16 connects perpendicular to first connecting rod 14, second
The tie point of bar 15；Connecting shaft 16 can cooperate with matching hole, and 16 diameter of connecting shaft is equal with cooperation bore dia, reach fixed big
The effect of gear 2.
First connecting rod 14 is connected with control system respectively with the other end of second connecting rod 15.
Wherein, the control system includes cabinet 9, and controller is installed inside cabinet 9, and the controller includes four controls
Module is motor control module, status check module, fixed shaft hole cooperation control module, the control of shaft hole matching time respectively
Molding block.
Preferably, the cabinet 9 is rectangular parallelepiped structure.
First connecting rod 14 is connected with 9 bottom end of cabinet respectively with the other end of second connecting rod 15；As shown in Figure 6 and Figure 7,
Cabinet 9 bottom four angle is respectively fixed with connector, one end rotation connection of the connector and shaft 17,17 other end of shaft
It is connected with first connecting rod 14 (second connecting rod 15) other end.
Trigonometric expression fixing axle 10 acts on lower swing in stepper motor 13, and each trigonometric expression fixing axle 10 is at least connected with 1 step
Into motor 13,2 stepper motors 13 are at most connected；The motor shaft and shaft 17 of stepper motor 13 are fixed, and stepper motor 13 is installed
In connector side.
Total 13 installation number of stepper motor is at least 2 in the application, is at most 4, depending on aircraft weight, respectively
Stepper motor cooperates.
The motor control module is realized by program, controls the rotation of driving motor 3.
The stepper motor 13 that fixed shaft hole cooperates control module control described, stepper motor 13 control trigonometric expression fixing axle 10
Rotation angle, and then realize adjusting to connecting shaft 13 and 2 distance of gear wheel.
The initial angle that shaft 17 of the trigonometric expression fixing axle 10 around 9 lower section of cabinet rotates is 0 °, and defining the angle is initial angle,
As shown in Figure 10, connecting shaft 16 and matching hole are not connected at this time；When mated condition, the folder of trigonometric expression fixing axle 10 and vertical direction
Angle is arc-tangent value of the sliding slot depth value divided by first connecting rod 14 (second connecting rod 15) length value, and defining the angle is fixed angles, such as
Shown in Figure 11.
The status check module includes an angular transducer, for detecting the cooperation shape of connecting shaft 16 Yu matching hole
State, i.e. the rotation angle of shaft 16；Angular transducer will test signal and be sent to controller, and controller controls 3 He of driving motor
Stepping electricity 13 rotates.
Wing amplitude measuring and calculating module includes the angular transducer 12 of the side wing main spar 6A (6B), as shown in figure 9, angle
The tool of sensor 12 is fixed on rotating base 8A (8B) there are two fixation hole by fixed screw, wing main spar 6A (6B) with
The rotary shaft of rotating base 8A (8B) passes through the axis hole of angular transducer 12, and rotary shaft is revolved together with wing main spar 6A (6B)
Turn, drives the rotor rotation of angular transducer 12.
Wing amplitude measuring and calculating module is swatted the measurement of angle to wing main spar 6A (6B) by program realization and is in real time flutterred
Play the calculating of frequency.
The angular transducer 12 can convert angle signal to the voltage signal of 0~5V, by A/D converter by mould
Analog quantity is converted into digital quantity and uses for measuring and calculating module.
It is poor by the angle work to six points before and after certain point to swat frequency, calculates instantaneous angular frequency, thus calculates one
A frequency for swatting the period.
The specific method is as follows:
The instantaneous angular frequency of i-th moment point is denoted as ωiIt indicates are as follows:
Ai-3~Ai+2Indicate that the angle value of i-th -3~i+2 moment point, f indicate sample frequency, calculate instantaneous angular frequency
ωiAfterwards, can be swatted according to the angular frequency a cycle (above flutter and under flutter maximum angular and be denoted as θmax) time, Jin Erji
Swatting frequency is denoted as F in real time for calculatingi:
Takeoff phase, motor pattern are flapping mode, and 3 drive gear wheel 2 of driving motor makees turnover movement, and gear wheel 2 is logical
Crossing crank 4A (4B) drives transmission rocking bar 5A (5B) to swing, and transmission rocking bar 5A (5B) drives wing master by rolling bearing 7A (7B)
Spar 6A (6B) is swatted up and down around rotating base 8A (8B)；Trigonometric expression fixing axle 10 is hanging at this time, not with the cunning on 2 face of gear wheel
18 inner wall of slot contacts (position-limiting action is played to connecting shaft 16 in 18 two sidewalls of sliding slot at this time), and gear wheel 2 is made normally to have enough to meet the need movement.
Cruising phase, the signal that control system receives are the fixed-wing mode signal that flapping wing is converted to predetermined angular, machine
The angular transducer 12 of the side the wing main spar 6A (6B) detects flapping wing aircraft and swats frequency, is greater than setting threshold when swatting frequency
Value, motor control module are decelerated to driving motor 3 to swat frequency less than given threshold.
Then, wing amplitude measuring and calculating module obtains current airfoils and swats angle information, swats frequency signal, and send
Shaft hole matching time control module is given, it is poor that shaft hole matching time control module makees current angular with the conversion angle received
Value calculates the time that starting fixed shaft hole cooperates control module further according to frequency is currently swatted.
Its calculation method are as follows:
In formula (4), tstartFor the delay time for starting shaft hole matching, tkIt is rotated for trigonometric expression fixing axle 10 from initial angle
Time needed for fixed angles, θg、θcPredetermined angular and current airfoils angle, ω when respectively indicating fixed-wing are indicated when anterior angle speed
Degree.
After delay time reaches, the operation of shaft hole matching control module is directly fixed；Firstly, fixed shaft hole cooperation control
Module control initial angle is changed to fixed angles, i.e. 10 bottom of trigonometric expression fixing axle is rotated around cabinet 9 to trigonometric expression fixing axle 10
Connecting shaft 16 can be slided along the sliding slot 18 on canine tooth wheel face, and axis hole (connecting shaft 16 and matching hole) starts to cooperate at this time.
Then, whether status check module detection axis hole successfully cooperates, and wing amplitude calculates module measurement wing angle simultaneously
Judge whether it is consistent with the conversion angle received, if cooperated successfully, motor control module controls driving motor 3
It shuts down rapidly, completes conversion.
Cooperate successfully includes following three kinds of situations:
If as shown in Fig. 2, when trigonometric expression fixing axle is fixed to position shown in matching hole 11A, the fixation of wing angle is about
30 °, shaft hole matching success achievees the purpose that lock gear wheel 2.
If wing angle is fixed about as shown in figure 3, when trigonometric expression fixing axle is fixed to position shown in matching hole 11B-
5 °, shaft hole matching success achievees the purpose that lock gear wheel 2.
If wing angle is fixed about as shown in figure 4, when trigonometric expression fixing axle is fixed to position shown in matching hole 11C-
15 °, shaft hole matching success achievees the purpose that lock gear wheel 2.
If cooperation is unsuccessful, control signal is back to fixed shaft hole cooperation control module, continues to operate by original process,
Until shaft hole matching success.
Landing phases, the signal that control system receives are that fixed-wing is converted to flapping mode signal, fixed shaft hole cooperation
Control module passes through control fixed angles first and is changed to initial angle, to cancel the cooperation of connecting shaft 16 Yu matching hole；It is specific to execute
Mode are as follows: 10 bottom end of trigonometric expression fixing axle turns to 10 liang of connecting shafts 16 of trigonometric expression fixing axle and 2 thickness of gear wheel around cabinet 9
It is identical, cancel the cooperation of connecting shaft 16 Yu matching hole with this.
Then, whether status check module detection axis hole successfully discharges, if discharged successfully, driving motor control is opened rapidly
Dynamic driving motor 3, pinion gear and gear wheel 2 make gear motion, and gear wheel 2 drives crank 4A (4B) to make circumference turnover movement, into
And transmission rocking bar 5A (5B) is driven to swing；It is driven rocking bar 5A (5B) and wing main spar 6A (6B) is driven by rolling bearing 7A (7B)
It is swatted up and down around rotating base 8A (8B), completes conversion.
If release is unsuccessful, control signal is back to fixed shaft hole cooperation control module, continues to operate by original process,
Until axis hole discharges successfully.
The application can be realized flapping wing take off, fixed-wing cruise, to reach in small place, the quick landing of complex condition,
It gets rid of the dependence to dedicated landing runway, in addition has both the advantage of fixed wing aircraft again in cruising phase, i.e., high-efficient, cruise speed
Degree is fast；It is different with completion to adapt to different flight environment of vehicle that the angle of fixed-wing can neatly be changed in cruising phase simultaneously
Aerial mission.
The foregoing is merely preferred embodiment of the present application, are not intended to limit this application, for the skill of this field
For art personnel, various changes and changes are possible in this application.Within the spirit and principles of this application, made any to repair
Change, equivalent replacement, improvement etc., should be included within the scope of protection of this application.
Claims (8)
1. a kind of realize the system for flutterring solid wing structure multi-angle accurate transformation, which is characterized in that including driving device and control system
System, driving device connect a gear wheel by transmission mechanism, and gear wheel two sides are respectively equipped with a concentric sliding slot, sliding
Slot two sides pass through the fixed axis connection control system of trigonometric expression；
The center two sides of gear wheel connect wing main spar by crank and rocker mechanism respectively, and wing main spar and fuselage girder turn
Dynamic connection, the rotation of gear wheel drive the realization of wing main spar to swat operation；
The amplitude of swatting of wing main spar is detected by the angular transducer for being installed on fuselage girder side, and angular transducer will test
Signal reaches control system, and control system control trigonometric expression fixing axle is matched with matching hole a certain in sliding slot, and realization is flutterred the solid wing and turned
It changes.
2. a kind of the system for flutterring solid wing structure multi-angle accurate transformation is realized according to claim 1, which is characterized in that institute
It states interval set distance in sliding slot and multiple matching holes is set, swat angle not when trigonometric expression fixing axle is connected from different matching holes
Together.
3. a kind of the system for flutterring solid wing structure multi-angle accurate transformation is realized according to claim 1, which is characterized in that institute
It states gear wheel center and is fixed with central axis, central axis both ends are separately connected crank and rocker mechanism；
The crank and rocker mechanism includes crank and transmission rocking bar, and crank one end is connected with central axis, the crank other end and transmission
Rocking bar one end is hinged；The transmission rocking bar other end is divided into two sections, and itself and the rotation axis that is set on the outside of wing girder frame
It holds hinged.
4. a kind of the system for flutterring solid wing structure multi-angle accurate transformation is realized according to claim 1, which is characterized in that institute
Stating trigonometric expression fixing axle includes two groups, and each group of trigonometric expression fixing axle includes first connecting rod and second connecting rod；First connecting rod and
The end of two connecting rods is connected by connecting shaft compatible with sliding slot.
5. a kind of the system for flutterring solid wing structure multi-angle accurate transformation is realized according to claim 4, it is characterised in that
One connecting rod and second connecting rod head end are rotatablely connected with control system respectively, and are driven by stepper motor big to change fixed angles
It is small.
6. a kind of the system for flutterring solid wing structure multi-angle accurate transformation is realized according to claim 1, which is characterized in that institute
It states fuselage body frame two sides and is separately installed with rotating base, the wing main spar is connected by rotary shaft with rotating base, is rotated
Side of base fixed angle sensor.
7. a kind of the system for flutterring solid wing structure multi-angle accurate transformation is realized according to claim 1, which is characterized in that institute
Stating driving device is driving motor, and driving motor is connected with the pinion gear being meshed with the gear wheel.
8. a kind of the system for flutterring solid wing structure multi-angle accurate transformation is realized according to claim 1, which is characterized in that institute
Stating control system includes cabinet, and controller is arranged in box house, and the bottom of box is connected by shaft with trigonometric expression fixing axle.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821025266.1U CN208325624U (en) | 2018-06-29 | 2018-06-29 | It is a kind of to realize the system for flutterring solid wing structure multi-angle accurate transformation |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201821025266.1U CN208325624U (en) | 2018-06-29 | 2018-06-29 | It is a kind of to realize the system for flutterring solid wing structure multi-angle accurate transformation |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750105A (en) * | 2018-06-29 | 2018-11-06 | 山东大学 | It is a kind of to realize the system and method for flutterring solid wing structure multi-angle accurate transformation |
| CN111013192A (en) * | 2019-12-31 | 2020-04-17 | 江苏高科制药设备有限公司 | Supercritical carbon dioxide extraction method for pharmacy |
-
2018
- 2018-06-29 CN CN201821025266.1U patent/CN208325624U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108750105A (en) * | 2018-06-29 | 2018-11-06 | 山东大学 | It is a kind of to realize the system and method for flutterring solid wing structure multi-angle accurate transformation |
| CN111013192A (en) * | 2019-12-31 | 2020-04-17 | 江苏高科制药设备有限公司 | Supercritical carbon dioxide extraction method for pharmacy |
| CN111013192B (en) * | 2019-12-31 | 2021-12-03 | 江苏高科制药设备有限公司 | Supercritical carbon dioxide extraction method for pharmacy |
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Granted publication date: 20190104 Termination date: 20200629 |