CN205366062U - Change axial device of rotor craft - Google Patents
Change axial device of rotor craft Download PDFInfo
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- CN205366062U CN205366062U CN201620116009.3U CN201620116009U CN205366062U CN 205366062 U CN205366062 U CN 205366062U CN 201620116009 U CN201620116009 U CN 201620116009U CN 205366062 U CN205366062 U CN 205366062U
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- axial device
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- rotating shaft
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Abstract
The utility model discloses a change axial device of rotor craft, including the pivot, during the bearing frame on aircraft fuselage was installed in the pivot, the rotor was connected to the one end of pivot, and it is continuous with the fixing base on the aircraft fuselage that the other end passes through reset spring, the transfer line is connected on the axle body of pivot, and the staff is connected perpendicularly to the other end of transfer line, and the ejector tie rod is distinguished at the both ends of staff, and the push rod is continuous with the action mechanism on the aircraft fuselage. The utility model discloses a manned vehicle driver's operating handle can be regarded as to change axial device, and two left and right change axial devices are controlled respectively to two hands of aircraft driver, realize the action of ging forward, retreating, turning left, turn right of aircraft, and simple structure, easy manufacturing and maintenance, control mode convenience are applicable to large -scale installation and popularization in the manned vehicle in a flexible way.
Description
Technical field
This utility model relates to rotor craft, is specifically related to the change axial device of a kind of rotor craft.
Background technology
Existing rotor craft, is all use change of flight device engine output, or changes blade pitch so that there is lift difference or difference in torque between multiple electromotors to realize attitude of flight vehicle change.So that aircraft smooth flight, when adjusting each flight attitude, specifically how to change the output of electromotor or change the pitch of blade, need to utilize computer process, accurately calculate, process is loaded down with trivial details, be difficult to popularize, and not easily deals with flight environment of vehicle complicated and changeable in real time.And use existing method of adjustment, in the process that flight attitude changes, the situation that aircraft fuselage tilts often occurs, be unfavorable for carrying on board the aircraft video recording equipment or observation instrument.
The applicant is once a kind of disclosed in Chinese patent CN201520276807.8 becomes axial multi-rotor aerocraft, this aircraft is by becoming axial device, can realize only by changing the axial of each rotor, the attitude that aircraft is made advance, retreated, moves to left, moves to right and turn left, turns right can be made, it is possible to make aircraft remain level in the process of flight.But the change axial device that in above-mentioned patent, aircraft uses, its structure is complex, controls and operates relatively complicated, is not appropriate for for needing simple and flexible to control in the manned vehicle of function, it is impossible to meet large-scale production and promote requirement.
Utility model content
In order to solve the problems referred to above, the utility model discloses the change axial device of a kind of rotor craft.
The technical solution of the utility model is as follows:
The change axial device of a kind of rotor craft, including rotating shaft, described rotating shaft is arranged in the bearing block on aircraft fuselage, and the outer end of rotating shaft connects rotor；Connecting drive link on the axle body of described rotating shaft, the other end of described drive link is vertical with little axle to be connected, and the two ends of described little axle connect one or more push rod respectively, and described push rod is connected with the actuating mechanism on aircraft fuselage.
Its further technical scheme is: at least includes two and becomes axial device, controls left side rotor and the right side rotor of aircraft respectively.
Its further technical scheme is: one or more change axial device can be connected on same steering wheel.
Its further technical scheme is: described actuating mechanism is steering wheel, motor, Pneumatic Liquid press or manual operation mechanism.
Its further technical scheme is: also include return to neutral mechanism, and described return to neutral mechanism includes the back-moving spring being arranged on rotating shaft inner end and the fixing seat being arranged on aircraft fuselage, and described rotating shaft is connected with fixing seat by back-moving spring.
Advantageous Effects of the present utility model is:
Change axial device of the present utility model can as the operation handle of manned vehicle driver, and two handss of aircraft pilot control left and right two respectively and become axial device, it is achieved the advance of aircraft, retrogressing, left-hand rotation, right-hand rotation action；And aircraft is for the control of height and translation, still by flight control system by the balance of each Rotor thrust size is realized.After an operation completes, if driver does not continue to operation, then becoming axial device can set back under the effect of return to neutral mechanism.This utility model simple in construction, easily fabricated with safeguard, control mode convenient, flexible, it is adaptable to large-scale in manned vehicle install and promote.
Accompanying drawing explanation
Fig. 1 is the structural representation of a kind of embodiment of change axial device described in the utility model.
Fig. 2 is the structure chart after Fig. 1 removes the first half.
Fig. 3 is the structure chart of return to neutral mechanism of the present utility model.
Fig. 4 is the structure chart after Fig. 3 removes fixing seat.
Detailed description of the invention
Below in conjunction with accompanying drawing, detailed description of the invention of the present utility model is described further.
Fig. 1 and Fig. 2 is the structural representation of a kind of aircraft adopting change axial device of the present utility model.This aircraft fuselage is provided with 4 rotors, including rotor behind left front rotor, right front rotor, left back rotor, the right side.In this embodiment, having two to become axial device, the two becomes axial device and controls rotor before left front rotor and the right side respectively.
In Fig. 1 and embodiment illustrated in fig. 2 two become axial device, control rotor before the left front rotor of aircraft and the right side respectively.Obviously, the two becomes axial device and can also be installed to behind left back rotor and the right side on rotor, controls rotor behind left back rotor and the right side respectively, and at this moment its type of drive is similar with embodiment illustrated in fig. 1.Further, Fig. 1 becomes two push rods 9 of axial device after being connected with steering wheel 10, it is also possible to continue to extend back, be connected with rotor behind left back rotor, the right side, now one become axial device with regard to Synchronization Control two rotors of aircraft homonymy.By that analogy, in other embodiments, it is possible to become axial device by two, it is possible to control all rotors on the left of aircraft and all rotors on the right side of aircraft respectively.
The structure of each change axial device into: including a rotating shaft 1, this rotating shaft 1 is arranged in the bearing block 3 on aircraft fuselage 2, and one end of rotating shaft 1 connects rotor 4, and the other end is connected with the fixing seat 6 on aircraft fuselage 2 by back-moving spring 5.A piece drive link 7 is connected on the axle body of rotating shaft 1, and the other end of drive link 7 vertically connects a little axle 8, and the two ends of little axle 8 connect two push rods 9 respectively, and two push rods 9 be arranged in parallel, is connected with the steering wheel 10 on aircraft fuselage 2.Push rod 9 is except can being controlled by steering wheel 10, it is also possible to be controlled by motor, Pneumatic Liquid press, it is also possible to being Artificial Control, namely the relative telescoping movement of push rod 9 can by different control modes.
Above-mentioned change axial device can as the operation handle of aircraft pilot, and two handss of aircraft pilot control left and right two respectively and become axial device, and the mode adjusted at this point for the flight attitude of aircraft is as follows.If with the propeller of each rotor be in horizontal plane time for initial position, then have:
A, simultaneously promote forward left change axial device and right change axial device when two handss of aircraft pilot, then before left front rotor and the right side, rotor turns forward, and aircraft advances；
B, simultaneously promote left change axial device and right change axial device backward when two handss of aircraft pilot, then before left front rotor and the right side, rotor tilts backwards, and aircraft retreats；
C, when the left hand of aircraft pilot promotes forward left change axial device, the right hand promotes right change axial device backward, then left front rotor turn forward, right before rotor tilt backwards, aircraft turns to the left；
D, when the right hand of aircraft pilot promotes forward right change axial device, left hand promotes left change axial device backward, then before right, rotor turns forward, left front rotor tilts backwards, and aircraft turns to the right.
This change axial device only realizes the advance of aircraft, retrogressing, left-hand rotation, right-hand rotation；And aircraft is for the control of height and translation, still by flight control system by the balance of each Rotor thrust size is realized.
After an operation of above-mentioned a, b, c, d completes, if driver does not continue to operation, then becoming axial device can set back under the active force returning middle device that back-moving spring 5 and fixing seat form.As shown in Figure 3 and Figure 4, wherein Fig. 4 is the view after removing fixing seat on the basis of Fig. 3, it is therefore an objective in order to show the position of back-moving spring.
Above-described is only preferred implementation of the present utility model, and this utility model is not limited to above example.It is appreciated that the oher improvements and changes that those skilled in the art directly derive under the premise without departing from spirit of the present utility model and design or associate, is all considered as being included within protection domain of the present utility model.
Claims (5)
1. the change axial device of a rotor craft, it is characterised in that: including rotating shaft, described rotating shaft is arranged in the bearing block on aircraft fuselage, and the outer end of rotating shaft connects rotor；Connecting drive link on the axle body of described rotating shaft, the other end of described drive link is vertical with little axle to be connected, and the two ends of described little axle connect one or more push rod respectively, and described push rod is connected with the actuating mechanism on aircraft fuselage.
2. the change axial device of rotor craft according to claim 1, it is characterised in that: at least include two and become axial device, control left side rotor and the right side rotor of aircraft respectively.
3. the change axial device of rotor craft according to claim 1, it is characterised in that: one or more change axial device can be connected on same steering wheel.
4. the change axial device of rotor craft according to claim 1, it is characterised in that: described actuating mechanism is steering wheel, motor, Pneumatic Liquid press or manual operation mechanism.
5. the change axial device of rotor craft according to claim 1, it is characterized in that: also include return to neutral mechanism, described return to neutral mechanism includes the back-moving spring being arranged on rotating shaft inner end and the fixing seat being arranged on aircraft fuselage, and described rotating shaft is connected with fixing seat by back-moving spring.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620116009.3U CN205366062U (en) | 2016-02-04 | 2016-02-04 | Change axial device of rotor craft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620116009.3U CN205366062U (en) | 2016-02-04 | 2016-02-04 | Change axial device of rotor craft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205366062U true CN205366062U (en) | 2016-07-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201620116009.3U Active CN205366062U (en) | 2016-02-04 | 2016-02-04 | Change axial device of rotor craft |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298071A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | A kind of more rotor flying vehicles of manned duct |
| CN111216885A (en) * | 2020-01-20 | 2020-06-02 | 张世栋 | Tilting rotor craft |
-
2016
- 2016-02-04 CN CN201620116009.3U patent/CN205366062U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108298071A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | A kind of more rotor flying vehicles of manned duct |
| CN111216885A (en) * | 2020-01-20 | 2020-06-02 | 张世栋 | Tilting rotor craft |
| CN111216885B (en) * | 2020-01-20 | 2021-10-22 | 张世栋 | Tilting rotor craft |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 214000 room 411-414, A1 tower 999, Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Patentee after: Jiangsu digital Eagle Polytron Technologies Inc Address before: 214000 room 411-414, A1 tower 999, Gao Lang Dong Road, Binhu District, Wuxi, Jiangsu. Patentee before: Jiangsu numeral Accipitridae skill Development Co., Ltd |
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| CP01 | Change in the name or title of a patent holder |