CN107244412A - A kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity - Google Patents
A kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity Download PDFInfo
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- CN107244412A CN107244412A CN201710439688.7A CN201710439688A CN107244412A CN 107244412 A CN107244412 A CN 107244412A CN 201710439688 A CN201710439688 A CN 201710439688A CN 107244412 A CN107244412 A CN 107244412A
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- main
- undercarriage
- elasticity
- main reed
- spring piece
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- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The present invention proposes a kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity, is made up of main reed and auxiliary spring piece；There is block respectively on the upside of the two-arm of main elasticity of spring leaf direction；Secondary elasticity of spring leaf direction two ends have the hollow fastener above turned over；Auxiliary spring piece is on the downside of main reed, and the hollow fastener at secondary elasticity of spring leaf direction two ends is enclosed in the two-arm of main elasticity of spring leaf direction, and is in the outside of block on the upside of the two-arm of main elasticity of spring leaf direction；When the hollow fastener of auxiliary spring piece is enclosed in the two-arm of main elasticity of spring leaf direction, and main reed and auxiliary spring piece are when being in free state, have gap between the hollow fastener of auxiliary spring piece and the main reed block of homonymy.Using the undercarriage of the present invention when bearing relatively low impact energy, only main reed is deformed, and two reeds is all deformed by mechanically connecting fit structure when bearing compared with HI high impact energy, thus can effectively be reduced the load peaks of undercarriage.
Description
Technical field
Present invention design unmanned plane landing gear structure technical field is specially a kind of for lifting UAV Landing resiliency
The undercarriage plate spring structure of energy.
Background technology
Unmanned plane is in flight, and undercarriage is not involved in bearing the flight load of full machine, but in the take-off and landing of most critical
The two stages, especially landing period, the safety of unmanned plane carry out effective buffering energy-absorbing mainly by undercarriage.Buffer is modern
The indispensable universal component of unmanned plane undercarriage, its function is the kinetic energy during absorbing UAV Landing and sliding, its buffering energy-absorbing
Ability the overload for acting on unmanned plane structure should be made to be reduced to a certain tolerable injury level.Unmanned plane has light weight, speed low
Feature, its undercarriage is typically non-retractable, and because leaf spring buffer has simple in construction, reliability is high, the features such as maintainability is good,
Thus it is widely used on the undercarriage of unmanned plane, this undercarriage is referred to as leaf spring undercarriage.
Existing unmanned plane is using buffer of traditional plate spring structure as undercarriage.Traditional plate spring structure is all
Reed is all clamped with U bolt, or only one of which reed, as shown in figure 1, operationally, leaf spring can integrally be deformed, i.e., simultaneously
Make the less kinetic energy of application, can also produce higher active force, if applied on unmanned plane undercarriage, unmanned plane can be born
Larger overload.Often bear larger overload and infringement had to unmanned plane, in order that the overload born of unmanned plane reduce, it is necessary to
Leaf spring has more preferable shock-absorbing capacity, i.e. leaf spring when bearing identical impact energy, produces lower active force.
The content of the invention
Unmanned plane undercarriage in the case of most of landing is solely subjected to the relatively low kinetic energy (speed of less quality/relatively low
Degree), and it is harmful to unmanned plane often to produce larger overload, therefore now more desirable undercarriage fuselage is only produced it is relatively low
Active force.Due to traditional plate spring structure operationally, leaf spring can integrally be deformed simultaneously, even if applying less impact energy
Amount, leaf spring can also produce higher active force.For the problem, the present invention proposes a kind of for lifting UAV Landing resiliency
The undercarriage plate spring structure of energy, can prevent all reeds from being deformed simultaneously in the case where applying relatively low kinetic energy, and the present invention is proposed
Undercarriage plate spring structure there is one by one the ability of reaction deformation (step by step), to be produced in the case where applying relatively low kinetic energy
Raw less reaction force.
The technical scheme is that：
A kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity, with main reed, the master
It can be connected in the middle part of reed with unmanned aerial vehicle body, main elasticity of spring leaf direction two ends can be connected with unmanned plane gear tyre；Its
It is characterised by：There is block respectively on the upside of the main elasticity of spring leaf direction two-arm；The undercarriage plate spring structure also has auxiliary spring
Piece, the secondary elasticity of spring leaf direction two ends have the hollow fastener above turned over；The auxiliary spring piece is on the downside of main reed, and auxiliary spring piece
The hollow fastener at elastic direction two ends is enclosed in the two-arm of main elasticity of spring leaf direction, and is on the upside of the two-arm of main elasticity of spring leaf direction
The outside of block；When the hollow fastener of auxiliary spring piece is enclosed in the two-arm of main elasticity of spring leaf direction, and main reed and auxiliary spring piece be in from
By state when, have gap between the hollow fastener of auxiliary spring piece and the main reed block of homonymy.
Further preferred scheme, a kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity,
It is characterized in that：When main reed stress is outwards deployed, the gap energy between the hollow fastener of auxiliary spring piece and the main reed block of homonymy
It is enough to diminish until the hollow fastener of auxiliary spring piece is contacted with the main reed block of homonymy；When the hollow fastener of auxiliary spring piece and the main reed block of homonymy
After contact, auxiliary spring piece and the common stress of main reed.
Beneficial effect
In most cases unmanned plane is when landing, undercarriage be solely subjected to relatively low impact energy (less quality/compared with
Low speed), in this case, in order to reduce the overload that unmanned plane is born, it is undesirable to which undercarriage produces larger load.This
The new plate spring structure that invention is proposed solves this problem using new mechanical connection fit structure.Undercarriage is being born
During relatively low impact energy, only main reed is deformed, when bearing compared with HI high impact energy by mechanically connecting fit structure
Two reeds is all deformed, thus can effectively reduce the load peaks of undercarriage.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Brief description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become from description of the accompanying drawings below to embodiment is combined
Substantially and be readily appreciated that, wherein：
Fig. 1：Traditional plate spring structure schematic diagram；(a) all reeds are clamped by U bolt；(b) single reed structure.
Fig. 2：The schematic layout pattern of substep energy absorption leaf spring；(a) exploded view；(b) installation diagram；
Fig. 3：Mechanically connect fit structure schematic diagram；
Fig. 4：Mechanically connect fit structure partial enlarged drawing；
Fig. 5：The decomposing schematic representation of substep energy absorption leaf spring in embodiment；
Fig. 6：The installation diagram of substep energy absorption leaf spring in embodiment；
Fig. 7：Three kinds of comparison structure schematic diagrames in embodiment；
Fig. 8：During Vo=0.5m/s, the vertical displacement time history of three kinds of comparison structures；
Fig. 9：During Vo=3m/s, the vertical displacement time history of three kinds of comparison structures；
Figure 10：During Vo=0.5m/s, the vertical load history of three kinds of comparison structures；
Figure 11：During Vo=3m/s, the vertical load history of three kinds of comparison structures..
Embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning to end
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and be not considered as limiting the invention.
As shown in Fig. 2 the undercarriage leaf spring in the present embodiment is substep energy absorption leaf spring, structure is divided into two parts：It is main
The auxiliary spring piece of reed and substep energy absorption.It can be connected in the middle part of the main reed with unmanned aerial vehicle body, main elasticity of spring leaf side
It can be connected to two ends with unmanned plane gear tyre.As shown in figure 3, having respectively on the upside of the main elasticity of spring leaf direction two-arm
Block, the secondary elasticity of spring leaf direction two ends have the hollow fastener above turned over.Main reed and auxiliary spring timing on chip, the auxiliary spring piece
On the downside of main reed, and the hollow fastener at secondary elasticity of spring leaf direction two ends is enclosed in the two-arm of main elasticity of spring leaf direction, and is located
The outside of block on the upside of the two-arm of main elasticity of spring leaf direction；The hollow fastener at auxiliary spring piece two ends and the block of main reed both sides composition
Substep energy absorption bindiny mechanism.
As shown in figure 3, when the hollow fastener of auxiliary spring piece is enclosed in the two-arm of main elasticity of spring leaf direction, and main reed and auxiliary spring piece are equal
During in free state, there is gap between the hollow fastener of auxiliary spring piece and the main reed block of homonymy, have between hollow fastener and block
Certain gap can be such that fastener is slided in certain scope.Auxiliary spring piece is linked on main reed by fastener, and block plays limitation card
The function of part range of movement.When main reed stress outwards deploys deformation, the hollow fastener of auxiliary spring piece and the main reed block of homonymy it
Between gap can diminish until the hollow fastener of auxiliary spring piece contacted with the main reed block of homonymy；When the hollow fastener of auxiliary spring piece and homonymy
After main reed block contact, auxiliary spring piece and the common stress of main reed, auxiliary spring piece is together with main reed common eigenvector.
The present invention is deformed by main reed, and the clamping lock function of hollow fastener and block realizes two step deformation stages：
First stage is main reed deformation, if the impact energy applied to Landing Gear System is not enough to main reed
Being deformed to makes fastener contact blocks, then only main reed deformation；
Second stage is that main reed and substep energy absorption reed (auxiliary spring piece) are all deformed, if applied to Landing Gear System
Plus impact energy be enough to make main reed to produce enough deformations so that hollow fastener slips over gap-contact to block, then main spring
Piece and substep energy absorption reed are all deformed, i.e. leaf spring system overall deformation.
The present embodiment selects a frame unmanned plane to carry out experimental study.Unmanned plane quality is 300kg, and undercarriage is fixed straight panel
Type, as shown in Figure 5 and Figure 6, material uses 7075-T6 aluminium alloys to size, and its density is 2810kg/m3, Young's modulus is
71.7GPa, stretching yield stress is 503MPa, and ultimate tensile stress is 572MPa, and Poisson's ratio is 0.33.Construct finite element mould
Type carries out emulation comparison to three kinds of systems：1) only main reed, such as Fig. 7 (a)；(2) Novel leaf spring proposed by the present invention is distribution energy
Amount absorbs leaf spring, such as Fig. 7 (b)；3) quality and the equivalent leaf spring of Novel leaf spring identical are traditional leaf spring, such as Fig. 7 (c).
Comparative studies load peaks and dominant bit of undercarriage in the case where initial velocity is respectively 0.5m/s, 3m/s
Move.Wherein Fig. 8,9 are shown in the case of 0.5m/s and 3m/s, the displacement-time curve on unmanned plane undercarriage.Figure 10,11
Show in the case of 0.5m/s and 3m/s, load-time graph on unmanned plane undercarriage.
Such as Fig. 8 and Fig. 9 shows only have the leaf spring undercarriage and substep energy absorption plate of main reed in the case of 0.5m/s
The shift value of spring undercarriage is closer；Substep energy absorption leaf spring undercarriage and equivalent leaf spring undercarriage in the case of 3m/s
Shift value is closer.In rushing under speed for 0.5m/s, the impact energy that undercarriage is born is smaller, and substep energy absorption leaf spring rises and falls
It is mainly main reed deformation in frame and enters row buffering, therefore the displacement of its shift value and the undercarriage of only main reed to absorb kinetic energy
Value is closer；Under 3m/s impact velocity, the impact energy that undercarriage is born is larger, in substep energy absorption leaf spring undercarriage
Main reed and auxiliary spring piece is all deformed entering row buffering, therefore the displacement of its shift value and equivalent leaf spring undercarriage to absorb kinetic energy
Value is closer.
Such as Figure 10 and Figure 11 is shown, in the case of 0.5m/s, and leaf spring undercarriage and the substep energy of only main reed are inhaled
The load peaks for receiving leaf spring undercarriage are closer, in the case of 3m/s, substep energy absorption leaf spring undercarriage and equivalent leaf spring
The load peaks of undercarriage are closer.Also, in the case of 0.5m/s, the load that substep energy absorption leaf spring undercarriage is produced
Peak value (10416kN) reduces 40.92% compared with the load peaks (14678kN) of equivalent leaf spring undercarriage.0.5m/s's
Rush under speed, the impact energy that undercarriage is born is smaller, be mainly main reed deformation in substep energy absorption leaf spring undercarriage and come
Absorb kinetic energy and enter row buffering, therefore the load that the load of its generation and the undercarriage of only main reed are produced is closer, load peak
Value is also closer；Under 3m/s impact velocity, the impact energy that undercarriage is born is larger, substep energy absorption leaf spring undercarriage
Middle main reed and auxiliary spring piece are all deformed entering row buffering to absorb kinetic energy, therefore the load produced is produced with equivalent leaf spring undercarriage
Raw load is closer, and load peaks are also closer.Also, under 0.5m/s impact velocity, due to substep energy absorption plate
Spring undercarriage is bigger than the displacement stroke of equivalent leaf spring undercarriage, and the time that arrival maximum displacement stroke is undergone is than equivalent leaf spring
The time that undercarriage arrival maximum displacement stroke is undergone is long, therefore when bearing same impact, substep energy absorption leaf spring
The load peaks of undercarriage are smaller than the load peaks of equivalent leaf spring undercarriage.
Equivalent leaf spring undercarriage is traditional leaf spring undercarriage in experiment.Substep energy proposed by the present invention is understood by experiment
When absorbing leaf spring and meeting unmanned plane and bear relatively low impact energy in the case of most of land, the load of undercarriage is more traditional
The load of leaf spring undercarriage is small.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from the principle and objective of the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (2)
1. a kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity, with main reed, in the main reed
Portion can be connected with unmanned aerial vehicle body, and main elasticity of spring leaf direction two ends can be connected with unmanned plane gear tyre；Its feature exists
In：There is block respectively on the upside of the main elasticity of spring leaf direction two-arm；The undercarriage plate spring structure also has auxiliary spring piece, described
Secondary elasticity of spring leaf direction two ends have the hollow fastener above turned over；The auxiliary spring piece is on the downside of main reed, and secondary elasticity of spring leaf side
It is enclosed on to the hollow fastener at two ends in the two-arm of main elasticity of spring leaf direction, and is in block on the upside of the two-arm of main elasticity of spring leaf direction
Outside；When the hollow fastener of auxiliary spring piece is enclosed in the two-arm of main elasticity of spring leaf direction, and main reed and auxiliary spring piece are in free state
When, there is gap between the hollow fastener of auxiliary spring piece and the main reed block of homonymy.
2. a kind of according to claim 1 be used to lift the undercarriage plate spring structure of UAV Landing shock-absorbing capacity, its feature
It is：When main reed stress is outwards deployed, the gap between the hollow fastener of auxiliary spring piece and the main reed block of homonymy can diminish
Until the hollow fastener of auxiliary spring piece is contacted with the main reed block of homonymy；When the main reed block of the hollow fastener of auxiliary spring piece and homonymy is contacted
Afterwards, auxiliary spring piece and the common stress of main reed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710439688.7A CN107244412B (en) | 2017-06-12 | 2017-06-12 | It is a kind of for promoting the undercarriage plate spring structure of UAV Landing cushion performance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710439688.7A CN107244412B (en) | 2017-06-12 | 2017-06-12 | It is a kind of for promoting the undercarriage plate spring structure of UAV Landing cushion performance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107244412A true CN107244412A (en) | 2017-10-13 |
| CN107244412B CN107244412B (en) | 2019-06-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710439688.7A Expired - Fee Related CN107244412B (en) | 2017-06-12 | 2017-06-12 | It is a kind of for promoting the undercarriage plate spring structure of UAV Landing cushion performance |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108516079A (en) * | 2018-04-18 | 2018-09-11 | 佛山论剑科技有限公司 | A kind of unmanned plane buffering undercarriage |
| CN108930743A (en) * | 2018-08-29 | 2018-12-04 | 沈阳航空航天大学 | The double arches overlapping variation rigidity leaf spring and production method being staggered using the perpendicular paving of horizontal paving |
| CN111645853A (en) * | 2020-06-08 | 2020-09-11 | 中航飞机起落架有限责任公司 | Aircraft undercarriage |
| CN112478144A (en) * | 2020-12-04 | 2021-03-12 | 西北工业大学 | Flexible undercarriage damping device |
| CN113428348A (en) * | 2021-07-16 | 2021-09-24 | 中国科学院国家空间科学中心 | Unmanned aerial vehicle undercarriage |
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| FR2364165A1 (en) * | 1976-09-08 | 1978-04-07 | Wassmer Aviat Ste Nle | Undercarriage component for a light aircraft - comprises an arched spring blade with wheel(s) fitted inside the curve |
| US4852829A (en) * | 1987-09-14 | 1989-08-01 | Marvin Garfinkle | Undercarriage apparatus for vertical-lift aircraft |
| RU2123961C1 (en) * | 1997-01-29 | 1998-12-27 | Открытое акционерное общество "Авиационный комплекс им.С.В.Ильюшина" | Aircraft nose undercarriage leg |
| KR20100066244A (en) * | 2008-12-08 | 2010-06-17 | 정만희 | The equipment that eliminates rolling of car |
| CN203486136U (en) * | 2013-07-20 | 2014-03-19 | 中国特种飞行器研究所 | Variable cross-section spring steel plate type landing gear |
| CN204278970U (en) * | 2014-11-18 | 2015-04-22 | 郑州日产汽车有限公司 | The few plate spring of CDV car variation rigidity |
| CN104696403A (en) * | 2015-01-06 | 2015-06-10 | 成都客车股份有限公司 | Composite spring structure realizing equal offset frequency of variable stiffness |
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2017
- 2017-06-12 CN CN201710439688.7A patent/CN107244412B/en not_active Expired - Fee Related
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2364165A1 (en) * | 1976-09-08 | 1978-04-07 | Wassmer Aviat Ste Nle | Undercarriage component for a light aircraft - comprises an arched spring blade with wheel(s) fitted inside the curve |
| US4852829A (en) * | 1987-09-14 | 1989-08-01 | Marvin Garfinkle | Undercarriage apparatus for vertical-lift aircraft |
| RU2123961C1 (en) * | 1997-01-29 | 1998-12-27 | Открытое акционерное общество "Авиационный комплекс им.С.В.Ильюшина" | Aircraft nose undercarriage leg |
| KR20100066244A (en) * | 2008-12-08 | 2010-06-17 | 정만희 | The equipment that eliminates rolling of car |
| CN203486136U (en) * | 2013-07-20 | 2014-03-19 | 中国特种飞行器研究所 | Variable cross-section spring steel plate type landing gear |
| CN204278970U (en) * | 2014-11-18 | 2015-04-22 | 郑州日产汽车有限公司 | The few plate spring of CDV car variation rigidity |
| CN104696403A (en) * | 2015-01-06 | 2015-06-10 | 成都客车股份有限公司 | Composite spring structure realizing equal offset frequency of variable stiffness |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108516079A (en) * | 2018-04-18 | 2018-09-11 | 佛山论剑科技有限公司 | A kind of unmanned plane buffering undercarriage |
| CN108930743A (en) * | 2018-08-29 | 2018-12-04 | 沈阳航空航天大学 | The double arches overlapping variation rigidity leaf spring and production method being staggered using the perpendicular paving of horizontal paving |
| CN111645853A (en) * | 2020-06-08 | 2020-09-11 | 中航飞机起落架有限责任公司 | Aircraft undercarriage |
| CN112478144A (en) * | 2020-12-04 | 2021-03-12 | 西北工业大学 | Flexible undercarriage damping device |
| CN113428348A (en) * | 2021-07-16 | 2021-09-24 | 中国科学院国家空间科学中心 | Unmanned aerial vehicle undercarriage |
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