CN113428348A - Unmanned aerial vehicle undercarriage - Google Patents
Unmanned aerial vehicle undercarriage Download PDFInfo
- Publication number
- CN113428348A CN113428348A CN202110807243.6A CN202110807243A CN113428348A CN 113428348 A CN113428348 A CN 113428348A CN 202110807243 A CN202110807243 A CN 202110807243A CN 113428348 A CN113428348 A CN 113428348A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- aerial vehicle
- energy absorber
- landing gear
- buffering energy
- 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
Images
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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Vibration Dampers (AREA)
Abstract
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an unmanned aerial vehicle undercarriage, which comprises a plurality of support legs, wherein any support leg comprises a buffering energy absorber and a foot rest; one end of the buffering energy absorber is connected with the unmanned aerial vehicle, and the other end of the buffering energy absorber is connected with the foot rest; the buffering energy absorber comprises elastic pieces and a damping layer, and the damping layer is clamped between the two elastic pieces. The invention has simple process, low cost, light weight and better buffer and energy absorption characteristics, and can be applied to vertical take-off and landing light unmanned aerial vehicles in a large scale.
Description
Technical Field
The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to a light small-sized landing gear of a vertical take-off and landing unmanned aerial vehicle.
Background
The main functions of the landing gear of the vertical take-off and landing type unmanned aerial vehicle comprise 2 points: 1) the ground support when the unmanned aerial vehicle is parked; 2) buffering and absorption descending energy when unmanned aerial vehicle descends, reduce the descending overload, protection unmanned aerial vehicle organism and internal plant.
At present, light unmanned aerial vehicle adopts the stereoplasm undercarriage that carbon fiber tube or working of plastics were made usually in order to reduce structure weight, reduction in manufacturing cost, and with fuselage rigid connection, the support frame is close to the function. Although the landing gear is simple in process and light in weight, when the landing speed is too high, an unmanned aerial vehicle can be subjected to large impact load, and the unmanned aerial vehicle and airborne equipment are easily damaged.
To the light small-size unmanned aerial vehicle of VTOL, develop simple process, lightweight to the undercarriage that has buffering energy-absorbing ability helps improving unmanned aerial vehicle's safety in utilization, promotes unmanned aerial vehicle's popularization.
In order to simplify the process or reduce the weight of the existing light and small unmanned aerial vehicle, the landing gear usually adopts a carbon fiber tube or an injection-molded plastic part, and the landing gear is rigid, has poor buffering and energy-absorbing characteristics and has the problem of large landing impact load.
Disclosure of Invention
The invention aims to provide the landing gear of the unmanned aerial vehicle, which has the advantages of simple process, low cost, light weight and better buffering and energy absorbing characteristics and can be applied to the existing light unmanned aerial vehicle for vertical take-off and landing on a large scale.
In order to achieve the purpose, the invention adopts the following technical scheme:
an unmanned aerial vehicle landing gear comprises a plurality of landing legs, wherein each landing leg comprises a buffering energy absorber and a foot rest; one end of the buffering energy absorber is connected with the unmanned aerial vehicle, and the other end of the buffering energy absorber is connected with the foot rest; the buffering energy absorber comprises elastic pieces and a damping layer, the damping layer is clamped between the two elastic pieces, and the upper layer and the lower layer of the buffering energy absorber are the elastic pieces.
Preferably, the energy absorber is curved. Further preferably, for the arc of upwards arching, when unmanned aerial vehicle descends, deformation can take place for this arc structure, and then cushion unmanned aerial vehicle's descending dynamics, makes unmanned aerial vehicle avoid impaired.
Preferably, a plurality of landing legs are circumference equipartition and connect in unmanned aerial vehicle, and the landing leg is connected on unmanned aerial vehicle's fuselage promptly, and is horizontal circumference evenly distributed on the fuselage, makes the even condition that can not produce the slope and drop of unmanned aerial vehicle atress when descending.
Preferably, one end of the foot rest is connected with the buffering energy absorber, and the other end of the foot rest is connected with the upwards bent supporting foot.
Preferably, the undercarriage further comprises a mounting seat, the mounting seat is provided with support arms equal to the support legs in number, when the undercarriage is provided with the mounting seat, the center of the mounting seat is connected to the lower bottom surface of the body of the unmanned aerial vehicle, and the support legs with the buffering energy absorbers are connected to the support arms.
Preferably, four cross-shaped support arms are arranged on the mounting base. One skilled in the art can also arrange other numbers of arms, such as six arms, in a star-shaped distribution, as desired.
Preferably, the elastic sheet is made of a metal material, such as 65Mn spring steel, the damping layer is made of a high polymer damping material, polyvinyl chloride rubber, or the like, the foot rest is made of carbon fiber or plastic, and the support arm is made of carbon fiber or plastic.
Compared with the prior art, the invention has the following beneficial effects:
according to the invention, the low-cost and light-weight buffering energy absorber is arranged on the light unmanned aerial vehicle undercarriage, and the buffering energy absorber utilizes the better elastic deformation capacity of a metal material and the energy absorption capacity of a damping material during deformation, so that the good buffering energy absorption effect can be achieved when the unmanned aerial vehicle lands.
According to the invention, the metal sheet and the damping material are compounded to form a sandwich structure which is applied to the vertical take-off and landing light unmanned aerial vehicle, so that the buffering and energy-absorbing effects can be better played when the unmanned aerial vehicle lands, and the unmanned aerial vehicle body and airborne equipment are protected. The landing gear is simple in process, low in cost, free of maintenance in the service life period, and suitable for large-scale application of the small light unmanned aerial vehicle.
Drawings
Figure 1 is a schematic view of the structure of the landing gear of the present invention;
FIG. 2 is a schematic structural view of a energy absorber according to the present invention;
FIG. 3 is a cross-sectional schematic view of a energy absorber of the present invention;
reference numerals:
1. a support arm; 2. a buffer energy absorber; 2-1 and 2-3, an elastic sheet; 2-2, a damping layer; 3. a foot rest; 4. a supporting foot.
Detailed Description
The invention is described in further detail below with reference to the figures and the detailed description.
Example 1
As shown in fig. 1, the landing gear of the unmanned aerial vehicle comprises four support legs, wherein the four support legs are connected to the body of the unmanned aerial vehicle in a cross shape; any one of the supporting legs comprises a buffering energy absorber 2 and a foot rest 3; one end of the buffering energy absorber 2 is connected with the unmanned aerial vehicle, and the other end of the buffering energy absorber is connected with the foot rest 3;
as shown in figures 2 and 3, the buffering energy absorber 2 comprises elastic sheets 2-1 and 2-3 and a damping layer 2-2, wherein the damping layer is clamped between the two elastic sheets, and the upper layer and the lower layer of the buffering energy absorber are elastic sheets.
The buffering energy absorber is in an upward arched arc shape. A plurality of landing legs are circumference equipartition and connect in unmanned aerial vehicle. One end of the foot rest 3 is connected with the buffering energy absorber 2, and the other end is connected with the supporting foot 4 which is bent upwards.
The elastic sheet is made of a metal material, the damping layer is made of a high polymer damping material, and the foot rest is made of carbon fiber or plastic.
The buffering energy absorber in the embodiment can be directly fixed on the machine body, and the foot rest can be processed by carbon fiber tubes and plastics.
In the buffer energy absorber, a high polymer damping material is clamped between two layers of elastic metal sheets, and the metal sheets and the damping material are bonded to obtain the buffer energy absorber with a laminated structure.
When unmanned aerial vehicle descends, the arm-brace 4 of foot rest contacts ground earlier, transmits impact load to buffering energy absorber 2 on, and elastic bending deformation appears in the elastic metal piece on the buffering energy absorber, warp by the metal piece and drive damping material viscoelastic layer and appear shearing motion, falls energy consumption, provides great damping, suppresses the bounce-back, realizes the buffering and the energy-absorbing of undercarriage.
Through the thickness of adjusting the flexure strip, the interval between the two-layer flexure strip, select for use different damping material and can carry out the rigidity and the damping adjustment of undercarriage to the unmanned aerial vehicle that adapts to different weight of taking off uses.
Example 2
An unmanned aerial vehicle undercarriage comprises a mounting seat and four support legs, wherein the mounting seat is provided with four support arms 1 distributed in a cross shape, the mounting seat is connected to an unmanned aerial vehicle, and any support leg comprises a buffering energy absorber 2 and a foot rest 3; one end of the buffering energy absorber 2 is connected with the support arm 1, and the other end of the buffering energy absorber is connected with the foot rest 3;
as shown in figures 2 and 3, the buffering energy absorber 2 comprises elastic sheets 2-1 and 2-3 and a damping layer 2-2, wherein the damping layer is clamped between the two elastic sheets, and the upper layer and the lower layer of the buffering energy absorber are elastic sheets.
The buffering energy absorber is in an upward arched arc shape. A plurality of landing legs are circumference equipartition and connect in unmanned aerial vehicle. One end of the foot rest 3 is connected with the buffering energy absorber 2, and the other end is connected with the supporting foot 4 which is bent upwards.
The elastic sheet is made of a metal material, the damping layer is made of a high polymer damping material, and the foot rest is made of carbon fiber or plastic.
The vertical take-off and landing light and small unmanned aerial vehicle undercarriage mainly comprises a support arm, a buffering energy absorber and a foot rest. The mount pad with the support arm is fixed on the unmanned aerial vehicle fuselage, and the buffering energy absorber passes through the bolt and is connected with support arm, foot rest.
Conventional technical knowledge in the art can be used for the details which are not described in the present invention.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and are not limited. Although the present invention has been described in detail with reference to the embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (8)
1. An unmanned aerial vehicle landing gear is characterized by comprising a plurality of landing legs, wherein any landing leg comprises a buffering energy absorber and a foot rest; one end of the buffering energy absorber is connected with the unmanned aerial vehicle, and the other end of the buffering energy absorber is connected with the foot rest; the buffering energy absorber comprises elastic pieces and a damping layer, and the damping layer is clamped between the two elastic pieces.
2. The unmanned landing gear of claim 1, wherein the energy absorber is arcuate.
3. An unmanned landing gear according to claim 1, wherein the legs are circumferentially equispaced about the unmanned aerial vehicle.
4. An unmanned landing gear according to claim 1, wherein the foot rest is connected at one end to a buffer energy absorber and at the other end to an upwardly curved foot brace.
5. An unmanned landing gear according to claim 1, wherein the landing gear further comprises a mounting base, wherein a number of arms equal to the number of legs are provided on the mounting base, the mounting base is connected to the unmanned aerial vehicle, and the legs are connected to the arms.
6. An unmanned landing gear according to claim 5, wherein four arms are provided on the mounting base in a cruciform arrangement.
7. An unmanned aircraft landing gear according to any of claims 1 to 6, wherein the resilient tab is made of a metal material, the damping layer is made of a high polymer damping material, and the foot rest is made of carbon fibre or plastic.
8. An unmanned landing gear according to claim 5 or 6, wherein the arm is made of carbon fibre or plastics.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110807243.6A CN113428348A (en) | 2021-07-16 | 2021-07-16 | Unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110807243.6A CN113428348A (en) | 2021-07-16 | 2021-07-16 | Unmanned aerial vehicle undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN113428348A true CN113428348A (en) | 2021-09-24 |
Family
ID=77760774
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110807243.6A Pending CN113428348A (en) | 2021-07-16 | 2021-07-16 | Unmanned aerial vehicle undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113428348A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194383A (en) * | 2021-12-07 | 2022-03-18 | 中电科芜湖通用航空产业技术研究院有限公司 | Unmanned aerial vehicle undercarriage and unmanned aerial vehicle |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4645143A (en) * | 1983-11-02 | 1987-02-24 | Aerospatiale Societe Nationale Industrielle | Flexible girder with high energy absorption, and landing gear and tail skid for an aircraft equipped with such a girder |
| US20060222837A1 (en) * | 2005-03-31 | 2006-10-05 | The Boeing Company | Multi-axial laminate composite structures and methods of forming the same |
| CN101092166A (en) * | 2007-07-20 | 2007-12-26 | 南京航空航天大学 | Crow plate type undercarriage of helicopter |
| CN107244412A (en) * | 2017-06-12 | 2017-10-13 | 西北工业大学 | A kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity |
| CN109278991A (en) * | 2017-07-19 | 2019-01-29 | 中国空空导弹研究院 | Collision prevention girders and the undercarriage and aircraft for using the collision prevention girders |
| CN210455191U (en) * | 2019-08-27 | 2020-05-05 | 盐城市翔盛碳纤维科技有限公司 | Undercarriage for gyroplane |
| CN211033002U (en) * | 2019-10-12 | 2020-07-17 | 天津凌智飞航科技有限公司 | Unmanned aerial vehicle undercarriage structure with adjustable stability is good |
| CN111470036A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Anti single leg buffer structure and leg formula undercarriage that hit that weigh down |
-
2021
- 2021-07-16 CN CN202110807243.6A patent/CN113428348A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4645143A (en) * | 1983-11-02 | 1987-02-24 | Aerospatiale Societe Nationale Industrielle | Flexible girder with high energy absorption, and landing gear and tail skid for an aircraft equipped with such a girder |
| US20060222837A1 (en) * | 2005-03-31 | 2006-10-05 | The Boeing Company | Multi-axial laminate composite structures and methods of forming the same |
| CN101092166A (en) * | 2007-07-20 | 2007-12-26 | 南京航空航天大学 | Crow plate type undercarriage of helicopter |
| CN107244412A (en) * | 2017-06-12 | 2017-10-13 | 西北工业大学 | A kind of undercarriage plate spring structure for being used to lift UAV Landing shock-absorbing capacity |
| CN109278991A (en) * | 2017-07-19 | 2019-01-29 | 中国空空导弹研究院 | Collision prevention girders and the undercarriage and aircraft for using the collision prevention girders |
| CN210455191U (en) * | 2019-08-27 | 2020-05-05 | 盐城市翔盛碳纤维科技有限公司 | Undercarriage for gyroplane |
| CN211033002U (en) * | 2019-10-12 | 2020-07-17 | 天津凌智飞航科技有限公司 | Unmanned aerial vehicle undercarriage structure with adjustable stability is good |
| CN111470036A (en) * | 2020-04-30 | 2020-07-31 | 中国飞机强度研究所 | Anti single leg buffer structure and leg formula undercarriage that hit that weigh down |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114194383A (en) * | 2021-12-07 | 2022-03-18 | 中电科芜湖通用航空产业技术研究院有限公司 | Unmanned aerial vehicle undercarriage and unmanned aerial vehicle |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113428348A (en) | Unmanned aerial vehicle undercarriage | |
| CN101559833A (en) | Passive vibration isolation device of main speed reduction box of helicopter | |
| CN206841708U (en) | A kind of vapour-pressure type multi-rotor unmanned aerial vehicle undercarriage | |
| CN210881582U (en) | Vehicle suspension shock absorber with adjustable damping | |
| CN209945161U (en) | Landing buffer device for rocket vertical recovery | |
| CN211844888U (en) | Helicopter is with effectual support that rises and falls of buffering | |
| CN211253002U (en) | Unmanned aerial vehicle rises and falls and uses shock absorber support | |
| CN109050914A (en) | Unmanned plane support device is sent in a kind of take-away with charge free | |
| CN213566443U (en) | Helicopter wheel landing buffer device | |
| CN217300337U (en) | Impact-resistant tempered glass piece with buffer structure | |
| CN215554099U (en) | Unmanned aerial vehicle undercarriage of combatting earthquake | |
| CN205239153U (en) | Overarm brace shock attenuation module is put to rear overhang | |
| CN106593050A (en) | Stereo garage damping and feeding mechanism | |
| CN202243998U (en) | Planing boat structure | |
| CN202255605U (en) | Novel buffer type electronic scale | |
| CN218704019U (en) | Unmanned aerial vehicle buffering undercarriage | |
| CN201610343U (en) | Elevator buffer | |
| CN218720355U (en) | A shock attenuation supporting seat for mechanical equipment | |
| CN218377499U (en) | Front pillar upper connecting piece | |
| JPS565211A (en) | Composite coil spring for suspension of vehicle | |
| CN214241222U (en) | Unmanned aerial vehicle falls buffering fender bracket | |
| CN217778952U (en) | Vertical lifting undercarriage for helicopter | |
| CN221233876U (en) | Front auxiliary frame collision energy absorbing device | |
| CN215707112U (en) | Unmanned aerial vehicle descending protection device | |
| CN104827842A (en) | Suspension system and vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20210924 |