CN113734428A - A simple and easy skid formula rear landing gear for solar energy unmanned aerial vehicle - Google Patents
A simple and easy skid formula rear landing gear for solar energy unmanned aerial vehicle Download PDFInfo
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- CN113734428A CN113734428A CN202111006855.1A CN202111006855A CN113734428A CN 113734428 A CN113734428 A CN 113734428A CN 202111006855 A CN202111006855 A CN 202111006855A CN 113734428 A CN113734428 A CN 113734428A
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- landing gear
- aerial vehicle
- unmanned aerial
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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
- B64C25/52—Skis or runners
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/06—Undercarriages fixed
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
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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
- B64C2025/325—Alighting gear characterised by elements which contact the ground or similar surface specially adapted for helicopters
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Vibration Dampers (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a simple skid type rear landing gear for a solar unmanned aerial vehicle, which comprises a landing gear main body with an L-shaped rod structure, a fixed sleeve, an upper plug, a lower plug and a fixed belt. The vertical section of the landing gear main body is connected with the vertical tail main beam of the unmanned aerial vehicle through a fixing sleeve sleeved on the landing gear main body, and the connection mode is that carbon filaments pre-impregnated with epoxy resin are buried between the vertical section of the landing gear main body and the vertical tail main beam and are bound and fixed by a fixing band. The longitudinal positioning of the fixed sleeve on the undercarriage main body is limited by an upper plug arranged at the top end of the undercarriage main body and a lower plug arranged below the fixed sleeve. The fixing mode of the lower plug is realized by embedding carbon wires presoaked with epoxy resin between the lower plug and the landing gear main body and binding the carbon wires by fixing belts; and finally, the up-down movement of the undercarriage main body relative to the unmanned aerial vehicle is limited by the upper plug and the lower plug. The simple skid type rear landing gear for the solar unmanned aerial vehicle is small in structural weight, simple in form and capable of buffering.
Description
Technical Field
The invention belongs to the field of aircraft design, and relates to a simple skid type rear landing gear for a solar unmanned aerial vehicle, in particular to a simple skid type rear landing gear which is small in structure weight, simple in form and capable of buffering.
Background
For an adjacent space solar unmanned aerial vehicle, a front landing gear is generally used as a main landing gear, and a rear landing gear is used as an auxiliary landing gear. At present, the rear landing gear of the solar unmanned aerial vehicle at home and abroad mainly has two types: one is to arrange the auxiliary wheel under the vertical fin, the advantage of this kind of form is high in reliability, the disadvantage is that the structural weight is large, and because the auxiliary wheel diameter of the rear landing gear is smaller, so the ground requirement to the runway is higher; another form is local reinforcement under the vertical fin represented by Zephyr series, and the bottom of the vertical fin rubs when taking off and landing, and the form has the advantages of small structural weight, but has the defects of poor reliability, and can cause local abrasion and even structural damage after multiple taking off and landing. In addition, the existing rear landing gear form of the solar unmanned aerial vehicle does not have buffering capacity, and when the ground speed of the aircraft is high, the impact load easily causes structural damage. Therefore, for the solar unmanned aerial vehicle, a new structural form of the rear landing gear is required to meet the requirements of small structural weight, high reliability and buffer capacity.
Disclosure of Invention
In order to overcome the defects of the structural form of the rear landing gear of the existing solar unmanned aerial vehicle, the invention provides a novel simple skid type rear landing gear for the solar unmanned aerial vehicle.
The invention discloses a simple skid type rear landing gear for a solar unmanned aerial vehicle.
The undercarriage main part is L type carbon fiber return bend, and the cover has the fixed sleeve on the vertical section, and the fixed sleeve links firmly between unmanned aerial vehicle vertical fin girder. The axial displacement of the fixed sleeve along the longitudinal section is limited by an upper plug arranged at the top end of the longitudinal section and a lower plug arranged at the lower end of the longitudinal section.
The fixed mode of above-mentioned end cap down to and the fixed mode between the fixed sleeve and the unmanned aerial vehicle main girder that hangs down all adopt carbon fiber sizing yarn cooperation to fill preimpregnation epoxy's carbon silk realization.
The landing gear main body is provided with only one degree of freedom rotating around the axis of the longitudinal section in the mounting mode, and the remaining degree of freedom is favorable for turning of the unmanned aerial vehicle in the transition and take-off and landing processes. Meanwhile, when the unmanned aerial vehicle lands, the lower plug transmits impact load generated when the unmanned aerial vehicle lands to the vertical tail main beam; and at unmanned aerial vehicle descending in-process, the horizontal section in the undercarriage main part contacts with ground, and the undercarriage main part receives load and takes place deformation, and horizontal section reduces with vertical intersegmental contained angle this moment to absorb the impact when partly aircraft fall to the ground.
The invention has the advantages that:
1. the simple skid type rear landing gear for the solar unmanned aerial vehicle is of a pure carbon fiber structure, is light in weight, and only 10g of the weight of one set of product, while the single weight of the existing small wheel type rear landing gear is usually more than 50g, and compared with the structure weight of the simple skid type rear landing gear, the structure weight of the simple skid type rear landing gear is only 20% of that of the small wheel type rear landing gear.
2. The simple skid type rear landing gear for the solar unmanned aerial vehicle is simple in structural form, and 5 components are simple in appearance and low in manufacturing cost.
3. The simple skid type rear landing gear for the solar unmanned aerial vehicle is high in reliability, and loading tests prove that the simple skid type rear landing gear can not be structurally damaged under the impact load of the vertical grounding speed of 1 m/s.
4. The L-shaped landing gear body has a special structural form, and can elastically deform under the load condition, so that part of impact generated when an airplane lands on the ground is absorbed.
Drawings
Fig. 1 is a schematic structural view of a simple skid type rear landing gear for a solar unmanned aerial vehicle according to the present invention.
FIG. 2 is an exploded view of the simple skid rear landing gear for a solar drone according to the present invention.
FIG. 3 shows the lower plug and landing gear of the simple skid type rear landing gear for a solar unmanned aerial vehicle according to the present invention
The fixing mode of the main body is schematically shown.
FIG. 4 shows a simple skid-mounted rear landing gear middle fixing sleeve and an aircraft for a solar unmanned aerial vehicle according to the present invention
The fixing mode of the vertical tail main beam is shown schematically.
FIG. 5 shows a simple skid-mounted rear landing gear middle fixing sleeve and an aircraft for a solar unmanned aerial vehicle according to the present invention
Fixed position cross-sectional view of the vertical tail girder.
FIG. 6 shows the simple skid type rear landing gear for solar unmanned aerial vehicle of the present invention when long-endurance is in a certain altitude
Application schematic diagram in solar energy unmanned aerial vehicle.
Fig. 7 is an equivalent stress cloud diagram of the simple skid-type rear landing frame for a solar unmanned aerial vehicle in a stopped and static state.
Fig. 8 is a local displacement cloud diagram of the simple skid-type rear landing frame for a solar unmanned aerial vehicle in a stopped and static state.
FIG. 9 illustrates a conventional small wheel type rear landing gear and a simple skid type rear lift for a solar unmanned aerial vehicle according to the present invention
And comparing the impact load of the landing frame when the landing frame is landed.
In the figure:
1-landing gear body 2-fixed sleeve 3-upper plug
4-lower plug 5-fixing band 6-unmanned aerial vehicle vertical tail main beam
7-carbon filament
Detailed Description
The invention will be further explained with reference to the drawings.
The invention discloses a simple skid type rear landing gear for a solar unmanned aerial vehicle, which is arranged on a vertical tail main beam of the unmanned aerial vehicle and comprises a landing gear main body 1, a fixed sleeve 2, an upper plug 3, a lower plug 4 and a fixed belt 5, wherein the landing gear main body is shown in figures 1 and 2.
The landing gear main body 1 is an L-shaped carbon fiber bent pipe and is provided with a transverse section, a longitudinal section and a bending transition section between the transverse section and the longitudinal section, and two ends of the bending transition section are respectively connected with the tail end of the transverse section and the bottom end of the longitudinal section.
The fixing sleeve 2 is made of carbon fiber materials and is used for realizing connection between the landing gear main body 1 and the vertical tail main beam 6 of the unmanned aerial vehicle. The fixing sleeve 2 is coaxially sleeved on the longitudinal section of the landing gear main body 1, the inner diameter of the fixing sleeve is designed to be larger than the outer diameter of the landing gear main body 1 by 0.2mm, and a circumferential 0.1mm assembly gap is formed between the fixing sleeve 2 and the longitudinal section so that the landing gear main body 1 can rotate relative to the fixing sleeve 2 conveniently.
The axial displacement of the fixed sleeve 2 along the longitudinal section is limited by an upper plug 3 arranged at the top end of the longitudinal section and a lower plug 4 arranged at the lower end of the longitudinal section. The upper plug 3 is of a carbon fiber material columnar structure, and a columnar mounting hole is coaxially formed in the bottom of the upper plug; the mounting hole external diameter equals with the fixed sleeve external diameter, and the internal diameter design is 5.2mm, is greater than undercarriage main part 1 external diameter 0.2mm, makes 3 accessible columnar mounting holes of upper end cap and vertical section top clearance fit peg graft to glue between fixed with vertical section top, and clearance fit between 3 bottom surfaces of upper end cap and 2 top end faces of fixed sleeve. Therefore, the upper plug 3 limits the upward displacement of the fixing sleeve 2, and the landing gear main body 1 is prevented from vertically falling down after the landing gear and the vertical tail main beam 6 of the unmanned aerial vehicle are installed. The vertical downward falling force of the landing gear body 1 is the gravity of the landing gear body 1, the size of the landing gear body is only 0.1N, the specification of the upper plug 2 is small, and the depth of the columnar mounting hole is only designed to be 5 mm.
The lower plug 4 is a circular carbon fiber sheet, and the lower plug 4 is sleeved on the longitudinal section of the undercarriage main body 1 and is vertically arranged and fixed with the longitudinal section, so that the top surface of the lower plug 4 is in clearance fit with the bottom end of the fixed sleeve 2. Because the structure, material and size of the lower plug 4 and the landing gear main body 1 are limited, the fixing between the lower plug 4 and the longitudinal section cannot be realized by common fixing methods such as welding or screws, the fixing between the lower plug 4 and the longitudinal section is realized by adopting the fixing band 5 to match and fill the carbon filaments 7 pre-impregnated with epoxy resin, the fixing band 5 is carbon fiber sizing yarn, and as shown in fig. 3, the specific method is as follows:
firstly, carbon wires 7 pre-impregnated with epoxy resin are circumferentially embedded at the corner between the bottom surface of the lower plug 4 and the longitudinal section, and the width of an embedded area is at least 5 mm.
And then, winding a fixing belt 5 pre-impregnated with epoxy resin along the circumferential direction of the lower plug 4, so that the fixing belt 5 circumferentially wraps the carbon wire 7 embedded in the pad and the lower plug, and also wraps the outer edge part of the top surface of the lower plug 4 and a section of the landing gear main body 1 connected with the carbon wire below the lower plug 4.
Finally, the fixing band 5, the carbon wire 7, the lower plug 4 and the longitudinal section are fixed together through curing at normal temperature to form a whole.
Because the force causing the landing gear main body 1 to vertically move upwards is the gravity at the rear part of the airplane and the impact force during landing, the maximum force can reach more than 100N, the sectional area of the lower plug 4 is large, and the outer diameter of the sectional area is at least 6 times of the outer diameter of the longitudinal section, so that the structural damage caused by overlarge local stress is prevented; and the contact area of the lower plug 4 and the carbon wire 8 is larger, and at least occupies 43% of the area of the bottom surface of the lower plug, so that the bonding strength is increased.
The undercarriage main part 1 of above-mentioned structure passes through fixing sleeve 2 to be installed on unmanned aerial vehicle vertical tail girder 6, owing to receive undercarriage main part 1, fixing sleeve 2's size and material and with both area of contact restrictions for columnar structure, can't adopt fixed mode such as welding or screw commonly used to realize fixed between fixing sleeve 2 and unmanned aerial vehicle vertical tail girder 6. Therefore, the fixing band 5 (carbon fiber sizing yarn) can be matched with the carbon filament 7 filled with the epoxy resin to fix the two, as shown in fig. 4, 5 and 6, the specific method is as follows:
firstly, arranging a fixing sleeve 2 in an axial direction parallel to a vertical tail main beam 6 of the unmanned aerial vehicle, and attaching the fixing sleeve and the vertical tail main beam;
then, longitudinally filling carbon filaments 7 pre-impregnated with epoxy resin at the gap between the binding surfaces of the fixing sleeve 2 and the vertical tail main beam 6 of the unmanned aerial vehicle, so that the carbon filaments 7 are outwards stacked to reach or exceed the plane position tangent to the fixing sleeve 2 and the vertical tail main beam of the unmanned aerial vehicle at the same time, and a gap between the fixing band 5 and the carbon filaments 8 after winding is avoided; fix band 5 twines outside in fixed sleeve 2 and unmanned aerial vehicle vertical tail girder this moment, by the carbon silk 7 of fixed band 5 parcel fixed sleeve 2, unmanned aerial vehicle vertical tail girder 6 and landfill between the two.
Finally, the fixing band 5, the carbon wire 7, the fixing sleeve 2 and the unmanned aerial vehicle vertical tail main beam 6 are fixed together through curing at normal temperature, and a whole body is formed.
Because impact load is the horizontal section that is used in undercarriage main part 1 when unmanned aerial vehicle descends, the direction is vertical upwards, consequently, through when fixed sleeve 2 is installed with unmanned aerial vehicle vertical fin girder 6, will descend 4 upper surfaces of end cap and unmanned aerial vehicle vertical fin bottommost wing rib lower surface and the setting of laminating simultaneously of unmanned aerial vehicle vertical fin girder 6 bottom terminal surface, through down end cap 4 can transmit the impact load that produces when unmanned aerial vehicle descends to vertical fin girder 6 on.
When the skid type rear landing gear with the structure is assembled, firstly, the lower plug 4 is sleeved on the longitudinal section from the top of the longitudinal section of the landing gear main body 1, and the lower plug 4 is fixed on the longitudinal section according to the fixing mode. Then the fixed sleeve 2 is sleeved on the longitudinal section from the top end of the longitudinal section; then, the upper plug 3 is inserted at the top end of the longitudinal section and is fixedly bonded with the longitudinal section; and finally, fixing the fixing sleeve 2 on the vertical tail main beam 6 of the unmanned aerial vehicle by the method. After the assembly is completed according to the method, the vertical movement of the undercarriage main body 1 is limited by the upper plug 3 and the lower plug 4; the horizontal movement of the landing gear body 1 is limited by the fixing sleeve 2, so that the landing gear body 1 only has one degree of freedom rotating around the axis of the longitudinal section, and the remaining degree of freedom is beneficial to turning of the unmanned aerial vehicle during transition and taking off and landing.
At unmanned aerial vehicle descending in-process, horizontal section and ground contact in the undercarriage main part 1, the undercarriage main part 1 receives load to take place deformation, and horizontal section reduces with vertical intersegmental contained angle this moment to absorb the impact when partly aircraft fall to the ground. Each parameter (external diameter, internal diameter, horizontal section and longitudinal segment length, changeover portion curvature radius and bending angle of undercarriage main part 1) specifically adjusts the affirmation according to the unmanned aerial vehicle model among the above-mentioned undercarriage main part 1, guarantees that horizontal section and longitudinal segment contained angle reduction number of degrees are unanimous with unmanned aerial vehicle shut down angle under unmanned aerial vehicle machine-down state to guarantee undercarriage main part 1 and ground area of contact the biggest.
The invention is subjected to structural finite element simulation, as shown in fig. 7 and 8, in the shutdown static state, the maximum equivalent stress of the invention is 217.5MPa, the maximum local displacement is 4.332mm, the maximum equivalent stress is located in the bending section of the landing gear body 1, the maximum local displacement is located at the tail end of the transverse section of the landing gear body 1, and the bending angle of the landing gear body is about 2 degrees according to the conversion of the geometric shape. As shown in fig. 9, the impact load of the existing small wheel type rear landing gear and the impact load of the rear landing gear of the invention during landing are compared, and simulation results show that the maximum impact load of the rear landing gear of the invention is about 64% of that of the existing small wheel type rear landing gear, which proves that the invention can effectively reduce the maximum impact load during landing and has important significance for improving the structural performance of the solar unmanned aerial vehicle.
Claims (8)
1. The utility model provides a simple and easy skid formula undercarriage for solar energy unmanned aerial vehicle which characterized in that: the landing gear comprises a landing gear main body, a fixed sleeve, an upper plug, a lower plug and a fixed belt;
the landing gear main body is an L-shaped carbon fiber bent pipe, a fixing sleeve is sleeved on the longitudinal section of the landing gear main body, and the fixing sleeve is fixedly connected with the main girder of the vertical tail of the unmanned aerial vehicle; the fixed sleeve is limited by an upper plug arranged at the top end of the longitudinal section and a lower plug arranged at the lower end of the longitudinal section along the axial displacement of the longitudinal section;
the fixed mode of above-mentioned end cap down to and the fixed mode between fixed sleeve and the unmanned aerial vehicle vertical tail girder all adopt carbon fiber sizing yarn cooperation to fill preimpregnation epoxy's carbon silk realization.
2. The simple skid-mounted rear landing gear for a solar drone of claim 1, wherein: the landing gear main body, the fixing sleeve, the upper plug, the lower plug and the fixing band are all made of carbon fiber materials.
3. The simple skid-mounted rear landing gear for a solar drone of claim 1, wherein: the upper plug is of a columnar structure, the bottom of the upper plug is provided with a hole, the bottom of the upper plug is connected with the top end of the longitudinal section in an inserting mode, and the depth of the inserting section is designed to be 5 mm.
4. The simple skid-mounted rear landing gear for a solar drone of claim 1, wherein: lower end cap is ring shape carbon fiber thin slice, sets up with vertical section is perpendicular, and lower end cap upper surface and unmanned aerial vehicle vertical fin bottommost wing rib lower surface and unmanned aerial vehicle vertical fin girder bottom terminal surface laminate simultaneously and set up.
5. The simple skid-mounted rear landing gear for a solar drone of claim 1, wherein: the specific fixing method of the lower plug comprises the following steps:
firstly, carbon wires pre-impregnated with epoxy resin are circumferentially embedded at the included angle between the bottom surface of the lower plug and the longitudinal section, and the width of an embedded area is at least 5 mm;
then, winding a fixing band pre-impregnated with epoxy resin along the circumferential direction of the lower plug, so that the fixing band circumferentially wraps the carbon wire embedded in the dwelling mat and the lower plug, and also wraps the outer edge part of the top surface of the lower plug and a section of landing gear main body connected with the carbon wire below the lower plug;
finally, the fixing band, the carbon wire, the lower plug and the longitudinal section are fixed together through curing at normal temperature to form a whole.
6. The simple skid-mounted rear landing gear for a solar unmanned aerial vehicle of claim 5, wherein: the outer diameter of the section of the lower plug is at least 6 times of the outer diameter of the longitudinal section; and the contact area of the lower plug and the carbon wire at least accounts for 43 percent of the area of the bottom surface of the lower plug.
7. The simple skid-mounted rear landing gear for a solar drone of claim 1, wherein: the fixing method between the fixing sleeve and the vertical tail main beam of the unmanned aerial vehicle comprises the following steps:
firstly, arranging a fixing sleeve in an axial direction parallel to a vertical tail main beam of the unmanned aerial vehicle, and attaching the fixing sleeve and the vertical tail main beam;
then, longitudinally filling carbon filaments pre-impregnated with epoxy resin at a gap between the binding surfaces of the fixing sleeve and the vertical tail main beam of the unmanned aerial vehicle, so that the carbon filaments are outwards stacked to reach or exceed a plane position tangent to the fixing sleeve and the vertical tail main beam of the unmanned aerial vehicle at the same time, and a gap between the fixing band and the carbon filaments after being wound is avoided; at the moment, the fixing belt is wound outside the fixing sleeve and the vertical tail main beam of the unmanned aerial vehicle, and the fixing sleeve, the vertical tail main beam of the unmanned aerial vehicle and the carbon wire buried between the fixing sleeve and the vertical tail main beam are wrapped by the fixing belt;
and finally, the fixing band, the carbon wire, the fixing sleeve and the vertical tail main beam of the unmanned aerial vehicle are fixed together through curing at normal temperature to form a whole.
8. The simple skid-mounted rear landing gear for a solar drone of claim 1, wherein: at unmanned aerial vehicle descending in-process, horizontal section and ground contact in the undercarriage main part, the undercarriage main part receives the load and takes place deformation, and horizontal section reduces with vertical intersegmental contained angle this moment, absorbs the impact when partial aircraft lands, and under unmanned aerial vehicle shutdown state, horizontal section reduces the number of degrees with vertical section contained angle and unmanned aerial vehicle shuts down the angle unanimously.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111006855.1A CN113734428B (en) | 2021-08-30 | 2021-08-30 | Simple skid type rear landing gear for solar unmanned aerial vehicle |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111006855.1A CN113734428B (en) | 2021-08-30 | 2021-08-30 | Simple skid type rear landing gear for solar unmanned aerial vehicle |
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| CN113734428A true CN113734428A (en) | 2021-12-03 |
| CN113734428B CN113734428B (en) | 2023-05-26 |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB357476A (en) * | 1930-03-06 | 1931-09-24 | Fiat Spa | Improvements in or relating to landing gear for aeroplanes |
| GB446509A (en) * | 1934-10-25 | 1936-04-27 | Noel Pemberton Billing | Improvements in or relating to aircraft |
| US5897077A (en) * | 1996-08-02 | 1999-04-27 | Mcdonnell Douglas Helicopter Co. | Quick-change skid landing gear |
| JP2004249942A (en) * | 2003-02-21 | 2004-09-09 | Yamaha Motor Co Ltd | Unmanned helicopter |
| CN202896876U (en) * | 2012-11-08 | 2013-04-24 | 广州金海航空技术有限公司 | Ultra-light high-strength carbon filament winded undercarriage for aircraft |
| CN203666974U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Remote sensing remote metering fixed wing unmanned air vehicle |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
| US20210122461A1 (en) * | 2019-10-25 | 2021-04-29 | Robert G. Watkins | Relocatable main landing gear |
-
2021
- 2021-08-30 CN CN202111006855.1A patent/CN113734428B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB357476A (en) * | 1930-03-06 | 1931-09-24 | Fiat Spa | Improvements in or relating to landing gear for aeroplanes |
| GB446509A (en) * | 1934-10-25 | 1936-04-27 | Noel Pemberton Billing | Improvements in or relating to aircraft |
| US5897077A (en) * | 1996-08-02 | 1999-04-27 | Mcdonnell Douglas Helicopter Co. | Quick-change skid landing gear |
| JP2004249942A (en) * | 2003-02-21 | 2004-09-09 | Yamaha Motor Co Ltd | Unmanned helicopter |
| CN202896876U (en) * | 2012-11-08 | 2013-04-24 | 广州金海航空技术有限公司 | Ultra-light high-strength carbon filament winded undercarriage for aircraft |
| CN203666974U (en) * | 2013-11-20 | 2014-06-25 | 天津三爻航空航天科技发展有限公司 | Remote sensing remote metering fixed wing unmanned air vehicle |
| CN106628130A (en) * | 2016-12-26 | 2017-05-10 | 中国航空工业集团公司西安飞机设计研究所 | Unmanned aerial vehicle nose landing gear shock absorption and steering mechanism |
| US20210122461A1 (en) * | 2019-10-25 | 2021-04-29 | Robert G. Watkins | Relocatable main landing gear |
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| CN113734428B (en) | 2023-05-26 |
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