CN108069023A - Aircraft damping undercarriage and aircraft - Google Patents
Aircraft damping undercarriage and aircraft Download PDFInfo
- Publication number
- CN108069023A CN108069023A CN201611025473.2A CN201611025473A CN108069023A CN 108069023 A CN108069023 A CN 108069023A CN 201611025473 A CN201611025473 A CN 201611025473A CN 108069023 A CN108069023 A CN 108069023A
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- Prior art keywords
- aircraft
- damping
- support plate
- link
- support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000013016 damping Methods 0.000 title claims abstract description 72
- 230000035939 shock Effects 0.000 claims abstract description 8
- 230000000694 effects Effects 0.000 claims description 13
- 238000005516 engineering process Methods 0.000 abstract description 3
- 229910000831 Steel Inorganic materials 0.000 description 9
- 239000010959 steel Substances 0.000 description 9
- 230000003139 buffering effect Effects 0.000 description 8
- 239000000463 material Substances 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000010276 construction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 229920001651 Cyanoacrylate Polymers 0.000 description 1
- 239000004830 Super Glue Substances 0.000 description 1
- 230000008901 benefit Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 230000008439 repair process Effects 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The present invention relates to vehicle technology fields, disclose a kind of aircraft damping undercarriage and aircraft, wherein, aircraft damping undercarriage include be used for for aircraft lands in support is provided on external object support plate, the link for connecting support plate and aircraft, and the damping for aircraft lands to be carried out with bumper and absorbing shock, the damping is arranged between link and support plate, and link is flexibly connected with damping.Aircraft damping undercarriage and aircraft proposed by the present invention; it is used to be aircraft lands in the support plate for providing support on external object and link for connecting support plate and aircraft by setting; and damping is set between link and support plate; on the premise of structural strength is ensured; damping performance is improved, is effectively protected carry-on Aerial Electronic Equipment and load.
Description
Technical field
The present invention relates to vehicle technology field more particularly to a kind of aircraft damping undercarriages and aircraft.
Background technology
At present, the undercarriage of rotor wing unmanned aerial vehicle generally use is divided to two kinds, a kind of cantilever knot being bent to form for elastic wire
Structure, another kind are by the molding fixing bracket of rigid member.Although the former has certain buffering, support strength is not enough and stability
Deficiency；Although the latter solves the problems, such as strength and stability, but do not possess cushioning effect.There is a kind of bottom containing strip on the market
The undercarriage in portion, which ensure that the intensity of undercarriage, and the undercarriage material of elasticity is employed, although playing to a certain extent
Damping effect, but for large-scale gyroplane, the damping effect unobvious, and intensity is difficult to ensure that, has been seriously affected big
Type gyroplane safety.
The content of the invention
It is an object of the invention to provide a kind of aircraft damping undercarriage and aircraft, it is intended to it solves in the prior art,
The problem of existing gyroplane undercarriage cushioning effect unobvious, intensity are difficult to ensure that.
An embodiment of the present invention provides a kind of aircraft damping undercarriage, including being used to be aircraft lands in external object
There is provided the support plate of support, for the link that connects the support plate and the aircraft and for the aircraft
It lands and carries out the damping of bumper and absorbing shock, the damping is arranged between the link and the support plate, and institute
Link is stated to be flexibly connected with the damping.
Further, the damping includes lead and spring, and the lead is fixed on the support plate top surface
On, the link is movably set on the lead, and the spring pocket is arranged on the lead and positioned at the connection
Between frame and the support plate, and the both ends of the spring abut the link and the support plate respectively.
Further, the both ends of the spring are fixedly connected respectively with the link and the support plate.
Further, the damping further includes to limit the locating part that the link departs from the lead,
The locating part is arranged on the outer end of the lead and keeps out cooperation with the link activity.
Further, the locating part is nut, and the lead outer end has the outer spiral shell being connected with the nut
Line.
Further, the damping further includes the buffering for bumper and absorbing shock being arranged on the support plate bottom surface
Pad.
Preferably, the cushion pad is rubber pad.
Further, the link includes being symmetrically disposed on the support plate top surface first support and second support, institute
It states and the damping is both provided between first support and the second support and the support plate.
Further, the first support offers to be fixedly connected with the aircraft with second support top
Screw hole.
The embodiment of the present invention additionally provides a kind of aircraft, and including fuselage, the aircraft further includes the aircraft
Damping undercarriage, the aircraft damping undercarriage are fixedly connected with the fuselage.
Based on aircraft damping undercarriage and aircraft that above-mentioned technical proposal, the embodiment of the present invention propose, pass through setting
For being aircraft lands in the support plate that support is provided on external object and link for connecting support plate and aircraft, and
Damping between link and support plate is set, on the premise of structural strength is ensured, improves damping performance, effectively
Protect carry-on Aerial Electronic Equipment and load.
Description of the drawings
Fig. 1 is structure diagram of the aircraft damping undercarriage when standing in the embodiment of the present invention；
Fig. 2 is structure diagram of the aircraft damping undercarriage in landing in the embodiment of the present invention.
Specific embodiment
In order to make the purpose , technical scheme and advantage of the present invention be clearer, with reference to the accompanying drawings and embodiments, it is right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.
It should be noted that when element is referred to as " being fixed on " or " being arranged at " another element, it can be directly another
On one element or it may be simultaneously present centering elements.When an element is known as " being connected to " another element, it can be with
It is directly to another element or may be simultaneously present centering elements.
Only it is phase each other in addition, it should also be noted that, the orientation term such as left and right, upper and lower in the embodiment of the present invention
To concept or using the normal operating condition of product as reference, and should not be regarded as restrictive.Below in conjunction with tool
The realization of the present invention is described in detail in body embodiment.
As shown in Figure 1 to Figure 2, the embodiment of the present invention proposes a kind of aircraft damping undercarriage, which can be rotation
Wing machine will be described in detail in Examples below by taking gyroplane as an example, two groups of flights are connected under the fuselage of the gyroplane
Device damping undercarriage.Specifically, which may include support plate 1, link 2 and damping 3, wherein,
Support plate 1 is used to provide support when on external object or ground for gyroplane landing, and here, which is high intensity tablet,
It can be the composite panel of hollow steel plate or carbon fiber board or other high-strength lights, and herein, the support plate 1 is excellent
Elect hollow steel plate as；In addition, link 2 is used to connect support plate 1 and gyroplane (being not drawn into attached drawing), and here, the link 2
The preferably flat steel pipe of high intensity is alternatively the material member of other high intensity；Damping 3 be used for gyroplane
Reliction row buffering damping, the damping 3 are arranged between link 2 and support plate 1, and link 2 and 3 activity of damping
Connection, in this way, during gyroplane (especially large-scale gyroplane) landing is landed, the support plate 1 of high intensity is first
Ground, the gyroplane fuselage being then connected with link 2 push damping 3 and it are caused to deform upon, occur in damping 3
The landing buffer to gyroplane fuselage is realized in the case of deformation.
The aircraft damping undercarriage that the embodiment of the present invention proposes has following features：
The aircraft damping undercarriage that the embodiment of the present invention proposes is used to be aircraft lands in external object by setting
The support plate 1 of the high intensity of support and the link 2 for connecting the high intensity of support plate 1 and aircraft are provided, and connected
Damping 3 between frame 2 and support plate 1 is set, both ensure that undercarriage overall construction intensity, meanwhile, when gyroplane lands
Effective bumper and absorbing shock is realized using the deformation of damping 3, improves damping performance, the avionics being effectively protected on gyroplane
Equipment and load.
Further, in embodiments of the present invention, above-mentioned damping 3 may include the spring 32 of lead 31 and hard,
Specifically, lead 31 is perpendicularly fixed on the top surface of above-mentioned support plate 1, and above-mentioned 2 bottom of link is movably set in lead
On 31, meanwhile, spring 32 is also set on lead 31, and the spring 32 is between link 2 and support plate 1, the spring
32 both ends are connected to the bottom surface of link 2 and the top surface of support plate 1 respectively.In this way, link 2 is under downward active force, energy
Enough to be relatively moved towards support plate 1, at the same time, link 2, which pushes damping 3, to be made it send deformation and then generates slow
Punching acts on.In the present embodiment, by setting lead 31, both can retaining spring 32, can also be link 2 be oriented to, ensure
The stability of buffering.According to actual conditions and specific requirements, in other embodiments of the invention, above-mentioned damping 3 is also
It can be other structural forms, not limit uniquely herein.
Further, in embodiments of the present invention, the both ends of above-mentioned spring 32 are fixed respectively with link 2 and support plate 1
Connection.Herein, above-mentioned 31 preferably cylindrical steel bar of lead, bottom and 1 top surface of support plate of the lead 31 are welded and fixed,
Meanwhile 32 one end of spring and the bottom surface of link 2 are welded and fixed, 32 other end of spring and the top surface of support plate 1 are welded and fixed.Such as
This, by the way that the both ends of spring 32 are welded and fixed respectively with link 2 and support plate 1, both ensure that the stabilization that spring 32 connects
Property, simultaneously, it is ensured that the reliability buffered between link 2 and support plate 1 by spring 32.
Further, in embodiments of the present invention, above-mentioned damping 3 may also include locating part 33, which uses
Depart from above-mentioned lead 31 in limiting above-mentioned link 2, specifically, the locating part 33 be arranged on the outer end of lead 31 and with
Cooperation is kept out in the top surface activity of above-mentioned link 2.Herein, since the bottom of lead 31 is fixedly connected with above-mentioned support plate 1, together
When, locating part 33 is fixed on the outer end of lead 31, and 2 bottom of link is movably set on lead 31 and positioned at locating part
Between 33 and support plate 1, in this way, link 2 can move linearly along the length direction of lead 31, and the pole to move linearly
Range line from for 33 bottom surface of locating part with a distance from 1 top surface of support plate with the difference of 2 bottom thickness of link.As described above, pass through
Locating part 33 is set so that link 2 can not depart from lead 31, and so that the buffer distance of link 2 is adjustable, i.e., by changing
Become locating part 33 to can be realized in the position of lead 31, so so that 3 integral shock-absorbing effect of damping can obtain further
Improve, particularly with large-scale gyroplane, meet the shock attenuation needs of different weight machine.Certainly, according to actual conditions and specifically
Demand, in other embodiments of the invention, above-mentioned damping 3 can be also other structural forms, not limit uniquely herein
It is fixed.
Further, in embodiments of the present invention, above-mentioned locating part 33 is preferably nut, accordingly, above-mentioned lead 31
On the outer wall of outer end there is the external screw thread (being not drawn into attached drawing) for adapting to the nut, be connected through a screw thread cooperation so that nut
It is fixed adjustably to 31 outer end of lead.Certainly, according to actual conditions and specific requirements, in the other embodiment of the present invention
In, above-mentioned locating part 33 can be also other forms component, and be adjusted and be fixedly connected with lead 31, not limit uniquely herein
It is fixed.
Further, in embodiments of the present invention, above-mentioned damping 3 may also include the cushion pad for bumper and absorbing shock
34, which is fixed on the bottom surface of above-mentioned support plate 1.By the way that buffering is fixedly installed on the bottom surface of support plate 1
On the one hand pad 34 can directly contact with hard ground to avoid support plate 1, and have certain buffering effect, avoided so as to play
On the other hand the effect that support plate 1 wrecks, is equal to the intensity for adding support plate 1.Certainly, according to actual conditions and
Specific requirements, in other embodiments of the invention, above-mentioned damping 3 can be also other structural forms, not make herein only
One limits.
Further, in embodiments of the present invention, above-mentioned cushion pad 34 is preferably the rubber pad of hard, existing certain hard
Degree, and have certain cushioning effect.Herein, cushion pad 34 can be bonded by super glue and above-mentioned support plate 1.Certainly, at this
In invention other embodiment, above-mentioned cushion pad 34 can be also other kinds of bolster, can also pass through its other party with support plate 1
Formula is fixedly connected, and is not limited uniquely herein.
In embodiments of the present invention, since gyroplane requirement system dead weight is small, it just can guarantee that take-off weight is light, it requires
Support plate 1 is light-weight, while also to ensure its intensity.If support plate 1 directly selects steel plate, weight is too big, therefore examines
Consider hollow steel plate, it is so light-weight, while stick in 1 bottom of support plate the rubber (i.e. cushion pad 34) of hard, it can be to avoid
Hollow steel plate is directly contacted with hard ground, and has certain buffering effect, plays the work that hollow steel plate is avoided to wreck
With from another viewpoint, being equal to the intensity for adding hollow steel plate.In addition, the support plate 1 is it is also contemplated that using hollow
Carbon fiber board or other composite panel, not only lightweight but also high-strength.
Further, in embodiments of the present invention, above-mentioned link 2 may include first support 21 and second support 22, this
In, first support 21 and second support 22 are symmetrically distributed on the top surface of above-mentioned support plate 1, and first support 21 and second support
Above-mentioned damping 3 is both provided between 22 and support plate 1.Specifically, it is preferably provided with one between first support 21 and support plate 1
To parallel lead 31, a pair of of spring 32 and a pair of of locating part 33；A pair is preferably provided between second support 22 and support plate 1
Parallel lead 31, a pair of of spring 32 and a pair of of locating part 33.Certainly, according to actual conditions and demand, the present invention other
In embodiment, above-mentioned link 2 can be also other structural forms, not limit uniquely herein.
Further, in embodiments of the present invention, the outer profile of above-mentioned first support 21 and above-mentioned second support 22 is excellent
Elect " Z " font as, the two is symmetrical.Shape design not only conforms with intensity requirement, also reduces materials, alleviates dead weight.
Certainly, according to actual conditions and demand, in other embodiments of the present invention, above-mentioned first support 21 and second support 22 can also be
Other shapes do not limit uniquely herein.
Further, in embodiments of the present invention, the top of above-mentioned first support 21 and second support 22 opens up useful
In screw hole 20, it is detachably fixed and is connected using screw formation with the fuselage of above-mentioned gyroplane by the screw hole 20.It here, can basis
The type size of gyroplane and load-bearing and increase screw hole 20 and screw quantity.Certainly, according to actual conditions and demand, in the present invention
In other embodiment, above-mentioned first support 21 and second support 22 can also be fixed with the fuselage of gyroplane and connected by other means
It connects, does not limit uniquely herein.
As shown in Figure 1 to Figure 2, the embodiment of the present invention also proposed a kind of aircraft, which includes fuselage (in attached drawing
It is not drawn into), which further includes above-mentioned aircraft damping undercarriage, which is detachably fixed with fuselage
Connection.When aircraft lands, above-mentioned cushion pad 34 contacts ground first, generates miniature deformation and buffer portion impact force, connects
Above-mentioned spring 32 compressed, so as to buffer the impact force of the overwhelming majority, and then protection aircraft Aerial Electronic Equipment and negative
The effect of load.
Based on above-mentioned technical proposal, compared with prior art, the aircraft that the embodiment of the present invention proposes, aircraft damping
Undercarriage is aided with spring 32 and vulcanie (i.e. cushion pad 34), is ensureing to rise and fall by using the high-strength material of main part of hard
On the premise of frame overall construction intensity, the buffering effect of undercarriage is effectively improved, is navigated so as to play on protection aircraft
Electric equipment and the effect of load.
Embodiment described above is only the specific embodiment of the invention, but protection scope of the present invention is not limited thereto,
Any one skilled in the art in the technical scope disclosed by the present invention, can readily occur in various equivalent repair
Change, replace and improve etc., these modifications, replacement and improvement should be covered by the protection scope of the present invention.Therefore, this hair
Bright protection domain should be subject to the protection scope in claims.
Claims (10)
1. a kind of aircraft damping undercarriage, which is characterized in that including being used to be aircraft lands in providing support on external object
Support plate, for the link that connects the support plate and the aircraft and for being carried out to the aircraft lands
The damping of bumper and absorbing shock, the damping are arranged between the link and the support plate, and the link
It is flexibly connected with the damping.
2. aircraft damping undercarriage as described in claim 1, which is characterized in that the damping includes lead and bullet
Spring, the lead are fixed in the support plate top surface, and the link is movably set on the lead, the spring
It is sheathed on the lead and between the link and the support plate, and the both ends of the spring abut institute respectively
State link and the support plate.
3. aircraft damping undercarriage as claimed in claim 2, which is characterized in that the both ends of the spring respectively with the company
Frame is connect to be fixedly connected with the support plate.
4. aircraft damping undercarriage as claimed in claim 2, which is characterized in that the damping further includes to limit
The link departs from the locating part of the lead, the locating part be arranged on the outer end of the lead and with the company
It connects frame activity and keeps out cooperation.
5. aircraft damping undercarriage as claimed in claim 4, which is characterized in that the locating part be nut, the guiding
Column outer end has the external screw thread being connected with the nut.
6. such as aircraft damping undercarriage described in any one of claim 1 to 5, which is characterized in that the damping also wraps
Include the cushion pad for bumper and absorbing shock being arranged on the support plate bottom surface.
7. aircraft damping undercarriage as claimed in claim 6, which is characterized in that the cushion pad is rubber pad.
8. such as aircraft damping undercarriage described in any one of claim 1 to 5, which is characterized in that the link includes pair
Title is arranged at the support plate top surface first support and second support, the first support and the second support and the support
The damping is both provided between plate.
9. aircraft damping undercarriage as claimed in claim 8, which is characterized in that the first support and the second support
Top offers to be fixedly connected with the screw hole of the aircraft.
10. a kind of aircraft, including fuselage, which is characterized in that the aircraft is further included described in any one of claim 1 to 9
Aircraft damping undercarriage, the aircraft damping undercarriage is fixedly connected with the fuselage.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611025473.2A CN108069023A (en) | 2016-11-17 | 2016-11-17 | Aircraft damping undercarriage and aircraft |
| PCT/CN2017/107969 WO2018090810A1 (en) | 2016-11-17 | 2017-10-27 | Landing gear and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611025473.2A CN108069023A (en) | 2016-11-17 | 2016-11-17 | Aircraft damping undercarriage and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108069023A true CN108069023A (en) | 2018-05-25 |
Family
ID=62160784
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611025473.2A Pending CN108069023A (en) | 2016-11-17 | 2016-11-17 | Aircraft damping undercarriage and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108069023A (en) |
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2016
- 2016-11-17 CN CN201611025473.2A patent/CN108069023A/en active Pending
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB533076A (en) * | 1939-06-03 | 1941-02-06 | Aircraft Components Ltd | Improvements relating to aircraft alighting gear |
| CN102505206A (en) * | 2011-10-28 | 2012-06-20 | 福兴织造（苏州）有限公司 | Shock-absorbing leg of spinning frame |
| CN105880246A (en) * | 2014-12-15 | 2016-08-24 | 广西大学 | Damping supporting mechanism for rotary arm type tank cleaning device |
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