CN206407111U - A kind of contraction type depopulated helicopter undercarriage - Google Patents
A kind of contraction type depopulated helicopter undercarriage Download PDFInfo
- Publication number
- CN206407111U CN206407111U CN201720014502.9U CN201720014502U CN206407111U CN 206407111 U CN206407111 U CN 206407111U CN 201720014502 U CN201720014502 U CN 201720014502U CN 206407111 U CN206407111 U CN 206407111U
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- fixedly connected
- fuselage
- unmanned plane
- supporting leg
- rotating shaft
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Abstract
The utility model discloses a kind of contraction type depopulated helicopter undercarriage, including fuselage, the bottom of fuselage offers rotary axis groove, supporting leg groove, cross bar groove and bottom tub respectively, the inner bottom wall of fuselage is fixedly connected with motor, the output shaft of motor is fixedly connected with rotating shaft by shaft coupling, and the inner bottom wall of fuselage is fixedly connected with bearing block, and the inside of bearing block is fixedly connected with bearing, the inner ring of bearing is fixedly connected with the surface of rotating shaft, and rotating shaft runs through rotary axis groove and extends to the side of fuselage interior.The utility model, which has reached, at utmost reduces effect of the unmanned plane undercarriage to unmanned plane during flying resistance, so as to which the effect of buffering can be reached to fuselage when reaching and unmanned plane being landed, supporting leg is enabled to open the effect that it can be fixed on the positioning when to a certain extent, when landing so as to effectively solve unmanned plane undercarriage to unmanned plane during flying resistance and unmanned plane, rigid contact in face of unmanned plane cause damage the problem of.
Description
Technical field
The utility model is related to technical field of aerospace, specially a kind of contraction type depopulated helicopter undercarriage.
Background technology
In the past, because the flying speed of aircraft is low, the requirement to Aerodynamic Configuration of Aireraft is not very strict, therefore aircraft
Undercarriage is all made up of fixed support and wheel, need not there is very high technology so for manufacture.When aircraft in the air
During flight, undercarriage is remained exposed to outside fuselage.With the continuous improvement of aircraft flight speed, aircraft spans sound soon
The obstacle of speed, because the resistance of flight is sharply increased with the increase of flying speed, at this moment, the undercarriage of exposure outside is just tight
The aeroperformance of aircraft is have impact on again, hinders the further raising of flying speed.
Therefore, people just have devised retractable undercarriage, and undercarriage just is received into machine when aircraft flight in the air
Within the wing or fuselage, to obtain good aeroperformance, will gear down it come again during aircraft landing.However, have to lose,
The weak point so done is due to the extension and retraction system that undercarriage adds complexity so that the gross weight increase of aircraft.But in a word
Being that what is gained is more than what is lost, therefore present generation aircraft whether military aircraft or aircarrier aircraft, their the undercarriage overwhelming majority is all
The undercarriage of fixed form can still be used with folding and unfolding, only sub-fraction ultra light aircraft.Undercarriage is airborne vehicle bottom
For taking off landing or support airborne vehicle and accessories apparatus mobile for ground (or water surface) when ground (or water surface) is slided.Rise
Fall the part that frame is a kind of unique support whole airplane, therefore it is the inseparable scarce some of aircraft；Without it, aircraft is just not
Can be in ground moving.After taking off, undercarriage can be withdrawn depending on aeroplane performance.
A kind of depopulated helicopter disclosed in Chinese invention patent application prospectus CN201520645478 rises and falls
Frame, is connected by undercarriage with unmanned plane, and landing approach is simple, safe and reliable, by setting polyurethane sleeve on skid, in nothing
During man-machine landing, polyurethane sleeve lands in advance, can more effectively play damping effect；Pass through device roller mount and rolling on skid
Wheel, can be achieved to promote mobile unmanned plane；Simple in construction, practical, easy to maintain and maintenance.Although although this patent solves
Existing undercarriage is not the problem of damping effect is good when unmanned plane static state, dynamic, load, protecting against shock, but with section
Technology is continued to develop, and the flying speed of depopulated helicopter will be increasingly faster, to each part requirement of depopulated helicopter also more next
Higher, for depopulated helicopter, in flight course, air drag is smaller, and the flying speed of unmanned aerial vehicle is faster, and nobody
Helicopter landing gear awing can also bring resistance to depopulated helicopter, and this air drag can be with depopulated helicopter speed
It is faster and become bigger, and when helicopter lands with ground carry out be rigid contact, so being badly in need of a kind of contraction type
Depopulated helicopter undercarriage.
Utility model content
The purpose of this utility model is to provide a kind of contraction type depopulated helicopter undercarriage possess motor and drive rotating shaft,
Rotating shaft drives supporting leg to rotate, so that reach that whole undercarriage is shunk, the effect of expansion link adjustable spring in telescopic cavity
Under base is stretched, so as to reach the advantage of buffering when landing to unmanned plane, solve unmanned plane undercarriage to unmanned plane
Flight resistance and unmanned plane landing when, rigid contact in face of unmanned plane cause damage the problem of.
To achieve the above object, the utility model provides following technical scheme：A kind of contraction type depopulated helicopter undercarriage,
Including fuselage, the bottom of the fuselage offers rotary axis groove, supporting leg groove, cross bar groove and bottom tub respectively, the fuselage it is interior
Bottom wall is fixedly connected with motor, and the output shaft of the motor is fixedly connected with rotating shaft, the inner bottom wall of the fuselage by shaft coupling
Bearing block is fixedly connected with, the inside of the bearing block is fixedly connected with bearing, and the inner ring of the bearing and the surface of rotating shaft are solid
Fixed connection, the rotating shaft runs through rotary axis groove and extends to the side of fuselage interior.
The surface of the rotating shaft is fixedly connected with supporting leg, and one end of the supporting leg is located at the inside of rotary axis groove, described
One end of supporting leg is fixedly connected with locating piece, and the surface of the supporting leg is fixedly connected with cross bar, the supporting leg it is another
End offers telescopic cavity, and one end of the telescopic cavity is fixedly connected with adjustable spring, and one end of the adjustable spring is fixedly connected
There is expansion link, the expansion link runs through and extends to the outside of telescopic cavity, and one end of the expansion link is fixedly connected with base.
It is preferred that, the top of the rotary axis groove and the bottom of bottom tub are fixedly connected with limit switches, described spacing to open
Pass is electrically connected with motor.
It is preferred that, the junction of the rotating shaft and rotary axis groove is provided with seal washer, and the quantity of the rotating shaft is two, institute
The quantity for stating rotary axis groove and bearing block is four.
It is preferred that, the bottom of the base is fixedly connected with anti-skidding salient point, and the anti-skidding salient point is in cone shape.
Compared with prior art, the beneficial effects of the utility model are as follows：
1st, the utility model is by setting rotary axis groove, supporting leg groove, cross bar groove and bottom tub, countershaft, supporting leg, cross bar
Shunk with base, reached and at utmost reduced effect of the unmanned plane undercarriage to unmanned plane during flying resistance, by flexible
Bar is stretched in telescopic cavity in the presence of adjustable spring to base, so as to can be reached when landing to unmanned plane to fuselage slow
The effect of punching.
2nd, the utility model enables to supporting leg to be carried out when opening to a certain extent to it by setting locating piece
Fixed effect is positioned, by setting limit switch, supporting leg can be prevented effectively from and inordinate rotation contraction occur, so as to fuselage
Cause damage, by setting seal washer, can effectively strengthen the air-tightness of unmanned plane, by setting the anti-skidding convex of cone-shaped
Point, can effectively reduce unstability during unmanned plane landing, and unmanned plane is flown so as to effectively solve unmanned plane undercarriage
Row resistance and unmanned plane landing when, rigid contact in face of unmanned plane cause damage the problem of.
Brief description of the drawings
Fig. 1 is the utility model structural representation；
Fig. 2 is the utility model undercarriage figure；
Fig. 3 is the utility model fuselage bottom upward view；
Fig. 4 is the utility model bearing block schematic diagram.
In figure：1 fuselage, 2 rotary axis grooves, 3 supporting leg grooves, 4 cross bar grooves, 5 bottom tubs, 6 motors, 7 rotating shafts, 8 bearing blocks, 9 axles
Hold, 10 supporting legs, 11 locating pieces, 12 cross bars, 13 telescopic cavities, 14 adjustable springs, 15 expansion links, 16 bases, 17 limit switches, 18
Seal washer, 19 anti-skidding salient points.
Embodiment
Below in conjunction with the accompanying drawing in the utility model embodiment, the technical scheme in the utility model embodiment is carried out
Clearly and completely describe, it is clear that described embodiment is only a part of embodiment of the utility model, rather than whole
Embodiment.Based on the embodiment in the utility model, those of ordinary skill in the art are not under the premise of creative work is made
The every other embodiment obtained, belongs to the scope of the utility model protection.
Fig. 1-4, a kind of contraction type depopulated helicopter undercarriage, including fuselage 1 are referred to, the bottom of fuselage 1 is opened up respectively
There are rotary axis groove 2, supporting leg groove 3, cross bar groove 4 and bottom tub 5, the top of rotary axis groove 2 and the bottom of bottom tub 5 have been fixedly connected with
Limit switch 17, limit switch 17 is electrically connected with motor 6, by setting limit switch 17, can be prevented effectively from supporting leg 10 and be gone out
Existing inordinate rotation is shunk, so as to be caused damage to fuselage 1, by setting rotary axis groove 2, supporting leg groove 3, cross bar groove 4 and bottom tub
5, countershaft 7, supporting leg 10, cross bar 12 and base 16 are shunk, and have been reached and have at utmost been reduced unmanned plane undercarriage to nothing
The effect of man-machine flight resistance, the inner bottom wall of fuselage 1 is fixedly connected with motor 6, and the output shaft of motor 6 is fixed by shaft coupling
Rotating shaft 7 is connected with, rotating shaft 7 and the junction of rotary axis groove 2 are provided with seal washer 18, by setting seal washer 18, Neng Gouyou
The air-tightness of effect enhancing unmanned plane, the quantity of rotating shaft 7 is two, and the quantity of rotary axis groove 2 and bearing block 8 is four, fuselage 1
Inner bottom wall is fixedly connected with bearing block 8, and the inside of bearing block 8 is fixedly connected with bearing 9, the inner ring of bearing 9 and the surface of rotating shaft 7
It is fixedly connected, rotating shaft 7 runs through rotary axis groove 2 and the side extended to inside fuselage 1.
The surface of rotating shaft 7 is fixedly connected with supporting leg 10, and one end of supporting leg 10 is located at the inside of rotary axis groove 2, supporting leg
10 one end is fixedly connected with locating piece 11, by setting locating piece 11, when enabling to the supporting leg 10 to open to a certain extent
The effect that it can be fixed on the positioning, the surface of supporting leg 10 is fixedly connected with cross bar 12, and the other end of supporting leg 10 is opened
Provided with telescopic cavity 13, one end of telescopic cavity 13 is fixedly connected with adjustable spring 14, and one end of adjustable spring 14, which is fixedly connected with, stretches
Contracting bar 15, is stretched by expansion link 15 in telescopic cavity 13 in the presence of adjustable spring 14 to base 16, so as to nobody
Machine can reach the effect of buffering when landing to fuselage 1, and expansion link 15 runs through and extends to the outside of telescopic cavity 13, expansion link
15 one end is fixedly connected with base 16, and the bottom of base 16 is fixedly connected with anti-skidding salient point 19, and anti-skidding salient point 19 is in cone-shaped
Shape, by setting the anti-skidding salient point 19 of cone-shaped, can effectively reduce unstability during unmanned plane landing, so as to effectively solve
When unmanned plane undercarriage of having determined lands to unmanned plane during flying resistance and unmanned plane, face unmanned plane hurtful rigid contact
Problem.
Operation principle：During work, connection power supply, the control by Remote to motor 6, when unmanned plane lands, remotely
Start motor 6 to rotate forward, motor 6 drives rotating shaft 7 to rotate, so as to drive supporting leg 10 to rotate, when the locating piece of the one end of supporting leg 10
11 when the interior rotation of rotary axis groove 2 touches limit switch 17, and motor 6 stops, and undercarriage is propped up, when base 16 is contacted with ground,
Expansion link 15 in telescopic cavity 13 causes adjustable spring 14 to compress, and plays buffering to unmanned plane landing, during unmanned plane during flying, far
Journey remote-control motor 6 is inverted, and base 16 is liftoff, and the adjustable spring 14 in telescopic cavity 13 gos up, and the return of expansion link 15, motor 6 drives
Rotating shaft 7 is rotated, so that drive supporting leg 10 to rotate, when base 16, which is turned to, touches limit switch 17 in bottom tub 5, electricity
Machine 6 stops, and undercarriage shrinks.
In summary：The contraction type depopulated helicopter undercarriage, rotating shaft 7 is driven by motor 6, and rotating shaft 7 drives supporting leg
10 rotate, so as to reach that whole undercarriage is shunk, expansion link 15 is in telescopic cavity 13 bottom of in the presence of adjustable spring 14
Seat 16 is stretched, so as to reach the advantage of buffering when landing to unmanned plane, solves unmanned plane undercarriage to unmanned plane during flying
Resistance and unmanned plane landing when, rigid contact in face of unmanned plane cause damage the problem of.
While there has been shown and described that embodiment of the present utility model, for the ordinary skill in the art,
It is appreciated that these embodiments can be carried out in the case where not departing from principle of the present utility model and spirit a variety of changes, repaiies
Change, replace and modification, scope of the present utility model is defined by the appended claims and the equivalents thereof.
Claims (4)
1. a kind of contraction type depopulated helicopter undercarriage, including fuselage (1), it is characterised in that：The bottom difference of the fuselage (1)
Rotary axis groove (2), supporting leg groove (3), cross bar groove (4) and bottom tub (5) are offered, the inner bottom wall of the fuselage (1) is fixedly connected
There is motor (6), the output shaft of the motor (6) is fixedly connected with rotating shaft (7), the inner bottom wall of the fuselage (1) by shaft coupling
Be fixedly connected with bearing block (8), the inside of the bearing block (8) is fixedly connected with bearing (9), the inner ring of the bearing (9) with
The surface of rotating shaft (7) is fixedly connected, and the rotating shaft (7) is through rotary axis groove (2) and extends to the internal side of fuselage (1)；
The surface of the rotating shaft (7) is fixedly connected with supporting leg (10), and one end of the supporting leg (10) is located at rotary axis groove (2)
Inside, one end of the supporting leg (10) is fixedly connected with locating piece (11), and the surface of the supporting leg (10) is fixedly connected with
Cross bar (12), the other end of the supporting leg (10) offers telescopic cavity (13), and one end of the telescopic cavity (13) is fixedly connected
There is adjustable spring (14), one end of the adjustable spring (14) is fixedly connected with expansion link (15), and the expansion link (15) is run through
And the outside of telescopic cavity (13) is extended to, one end of the expansion link (15) is fixedly connected with base (16).
2. a kind of contraction type depopulated helicopter undercarriage according to claim 1, it is characterised in that：The rotary axis groove (2)
Top and the bottom of bottom tub (5) be fixedly connected with limit switches (17), the limit switch (17) is electrically connected with motor (6)
Connect.
3. a kind of contraction type depopulated helicopter undercarriage according to claim 1, it is characterised in that：The rotating shaft (7) with
The junction of rotary axis groove (2) is provided with seal washer (18), and the quantity of the rotating shaft (7) is two, the rotary axis groove (2) and axle
The quantity of bearing (8) is four.
4. a kind of contraction type depopulated helicopter undercarriage according to claim 1, it is characterised in that：The base (16)
Bottom is fixedly connected with anti-skidding salient point (19), and the anti-skidding salient point (19) is in cone shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720014502.9U CN206407111U (en) | 2017-01-06 | 2017-01-06 | A kind of contraction type depopulated helicopter undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720014502.9U CN206407111U (en) | 2017-01-06 | 2017-01-06 | A kind of contraction type depopulated helicopter undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206407111U true CN206407111U (en) | 2017-08-15 |
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ID=59553540
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720014502.9U Expired - Fee Related CN206407111U (en) | 2017-01-06 | 2017-01-06 | A kind of contraction type depopulated helicopter undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN206407111U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674638A (en) * | 2018-06-14 | 2018-10-19 | 西安爱生无人机技术有限公司 | A kind of unmanned plane extendible sled retracting device |
| CN108945444A (en) * | 2018-08-30 | 2018-12-07 | 无锡莱特杰米科技发展有限公司 | A kind of unmanned aerial photography machine of the wedding celebration with landing protection structure |
| CN112373678A (en) * | 2020-11-23 | 2021-02-19 | 中国人民解放军军事科学院国防科技创新研究院 | Many rotor unmanned aerial vehicle aid landing gear |
-
2017
- 2017-01-06 CN CN201720014502.9U patent/CN206407111U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108674638A (en) * | 2018-06-14 | 2018-10-19 | 西安爱生无人机技术有限公司 | A kind of unmanned plane extendible sled retracting device |
| CN108674638B (en) * | 2018-06-14 | 2024-03-15 | 西安爱生无人机技术有限公司 | Unmanned aerial vehicle receive and releases formula skid recovery unit |
| CN108945444A (en) * | 2018-08-30 | 2018-12-07 | 无锡莱特杰米科技发展有限公司 | A kind of unmanned aerial photography machine of the wedding celebration with landing protection structure |
| CN112373678A (en) * | 2020-11-23 | 2021-02-19 | 中国人民解放军军事科学院国防科技创新研究院 | Many rotor unmanned aerial vehicle aid landing gear |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20170815 Termination date: 20200106 |
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| CF01 | Termination of patent right due to non-payment of annual fee |