CN112319783A - System and unmanned aerial vehicle rise and fall - Google Patents
System and unmanned aerial vehicle rise and fall Download PDFInfo
- Publication number
- CN112319783A CN112319783A CN202110000850.1A CN202110000850A CN112319783A CN 112319783 A CN112319783 A CN 112319783A CN 202110000850 A CN202110000850 A CN 202110000850A CN 112319783 A CN112319783 A CN 112319783A
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- Prior art keywords
- landing gear
- landing
- fuselage
- linear
- aerial vehicle
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Toys (AREA)
Abstract
The invention discloses a landing system and an unmanned aerial vehicle, which relate to the technical field of aviation and comprise a landing gear which is rotatably arranged on a machine body; and the extension end of the linear driving component is slidably clamped on the undercarriage, and the fixed end of the linear driving component is arranged on the undercarriage. When the landing gear system is used, when the landing gear needs to be retracted, the linear driving assembly operates in the first direction, and the retracted landing gear is adsorbed on the side face of the machine body; when it is desired to deploy the landing gear, the linear drive assembly operates in a second direction, which urges the landing gear to deploy to support the fuselage. Therefore, the landing gear can be switched to the unfolding state or the folding state by adopting the landing gear lifting system, and the unmanned aerial vehicle can be effectively supported in the taking-off and landing state in the unfolding state, so that the problem of overturning is not easy to occur, and the service life of the unmanned aerial vehicle is prolonged.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a landing and landing system and an unmanned aerial vehicle.
Background
At present, some column structure's unmanned aerial vehicle because this type of unmanned aerial vehicle's focus is on the high side, and the easy fuselage that damages is tumbled in the in-process of taking off and land to easy.
Therefore, how to reduce the overturning of the drone and prolong the service life of the drone becomes a technical problem to be solved urgently by the technical personnel in the field.
Disclosure of Invention
The invention aims to provide a landing system and an unmanned aerial vehicle, so that the unmanned aerial vehicle is prevented from overturning, and the service life of the unmanned aerial vehicle is prolonged.
To achieve the above object, the present invention provides a landing gear system, comprising:
a landing gear rotatably arranged on the fuselage; and
the extension end of the linear driving component is slidably clamped on the undercarriage, the fixed end of the linear driving component is arranged on the fuselage, and when the linear driving component operates in a first direction, the linear driving component pushes the undercarriage to be unfolded to support the fuselage; when the linear drive assembly is operated in a second direction, the landing gear is pulled to retract to be close to the side of the fuselage.
Optionally, the linear driving assembly includes a linear motor and a first power supply element for providing a power supply for the linear motor, a fixed end of the linear motor is disposed on the body, and an extending end of the linear motor is slidably clamped on the undercarriage; when the first power supply element provides positive power, the linear driving assembly operates in a first direction, and when the first power supply element provides negative power, the linear driving assembly operates in a second direction.
Optionally, linear electric motor's stiff end passes through the support setting and is in on the fuselage, the support is located the lower extreme of fuselage, just have on the support and hold linear electric motor's the end reciprocating motion that stretches out dodge the passageway.
Optionally, the landing gear comprises a plurality of landing joints and a plurality of landing legs, each landing joint being provided in part on the fuselage and in part connected to one of the landing legs.
Optionally, a clamping ball is arranged at the extending end of the linear motor, a sliding groove is arranged on the lifting support leg, and the clamping ball is slidably clamped in the sliding groove.
Optionally, the lifting joint includes a first lifting joint disposed on the fuselage and a second lifting joint coupled to the first lifting joint, and the second lifting joint is connected to the lifting support leg.
Optionally, the power supply device further comprises a controller, and the controller is electrically connected with the first power supply element.
Optionally, the controller further comprises a communication component, and the controller is in communication connection with the communication component.
The invention also discloses an unmanned aerial vehicle which comprises a fuselage and the landing gear system, wherein the landing gear of the landing gear system is rotatably arranged on the fuselage.
When the landing gear needs to be unfolded, the linear driving assembly operates in a first direction and pushes the landing gear to be unfolded to support the fuselage; when retraction of the landing gear is required, the linear drive assembly operates in a second direction to retract the landing gear to close the side of the fuselage. Therefore, the landing gear can be switched to the unfolding state or the folding state by adopting the landing gear lifting system, and the unmanned aerial vehicle can be effectively supported in the taking-off and landing state in the unfolding state, so that the problem of overturning is not easy to occur, and the service life of the unmanned aerial vehicle is prolonged. In addition, during takeoff, the landing gear can be retracted under the action of the linear driving assembly, so that the influence of the landing gear on the flight is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
Fig. 1 is a schematic perspective view of an unmanned aerial vehicle in an unfolded state according to an embodiment of the present invention;
fig. 2 is a schematic perspective view of an unmanned aerial vehicle in a stowed state according to an embodiment of the present invention;
fig. 3 is a schematic cross-sectional structural diagram of an unmanned aerial vehicle in an unfolded state according to an embodiment of the present invention;
fig. 4 is a schematic cross-sectional structural diagram of an unmanned aerial vehicle in a stowed state according to an embodiment of the present invention;
fig. 5 is a schematic view of a partially enlarged structure of an unmanned aerial vehicle in an unfolded state according to an embodiment of the present invention;
fig. 6 is a schematic view of a partially enlarged structure of an unmanned aerial vehicle in a stowed state according to an embodiment of the present invention;
FIG. 7 is a perspective view of a landing gear according to an embodiment of the present invention;
wherein: 100 is a fuselage, 101 is a battery compartment, 102 is a power compartment, 103 is a support, 1021 is a propeller, 1031 is an avoidance channel, 200 is a landing system, 201 is a landing gear, 202 is a linear driving assembly, 2011 is a landing joint, 2012 is a landing leg, 2021 is a linear motor, 2011a is a first landing joint, 2011b is a second landing joint, 2021a is an extension end, and 2021b is a fixed end.
Detailed Description
The invention provides a landing system and an unmanned aerial vehicle, which are used for reducing the overturning of the unmanned aerial vehicle and prolonging the service life of the unmanned aerial vehicle.
In order to make the technical solutions of the present invention better understood by those skilled in the art, the present invention will be further described in detail with reference to the accompanying drawings and embodiments.
Referring to fig. 1 to 7, the landing gear system 200 of the present invention includes a landing gear 201 and a linear drive assembly 202, wherein the landing gear 201 is rotatably disposed on a fuselage 100; the extended end of the linear driving assembly 202 is slidably clamped on the landing gear 201, the fixed end of the linear driving assembly 202 is arranged on the fuselage 100, and when the linear driving assembly 202 operates in a first direction, the landing gear 201 is pushed to be unfolded to support the fuselage 100; when the linear drive assembly 202 is operating in the second direction, the landing gear 201 is pulled to retract closer to the side of the fuselage 100.
In use of the landing gear system 200 of the present invention, when it is desired to deploy the landing gear 201, the linear drive assembly 202 operates in a first direction, the linear drive assembly 202 urging the landing gear 201 to deploy to support the fuselage 100; when retraction of the landing gear 201 is required, the linear drive assembly 202 operates in the second direction, retracting the landing gear 201 and approaching the side of the fuselage 100. Therefore, the landing gear 201 can be switched to the unfolding state or the folding state by adopting the landing gear system 200 provided by the invention, and the unmanned aerial vehicle can be effectively supported in the taking-off and landing state in the unfolding state, so that the problem of overturning is not easy to occur, and the service life of the unmanned aerial vehicle is prolonged. In addition, during take-off, retraction may also be provided by the linear drive assembly 202 to reduce the impact of the landing gear 201 on flight.
It should be noted that the extending end of the linear drive assembly 202 can perform a reciprocating linear motion, i.e., the extending end of the linear drive assembly 202 can operate in a first direction and a second direction, wherein the first direction and the second direction are opposite.
The linear drive assembly 202 functions as the motive force for pushing and pulling the landing gear 201 for deployment and retraction. Specifically, the linear driving assembly 202 includes a linear motor 2021 and a first power supply element for supplying power to the linear motor 2021, a fixed end 2021b of the linear motor 2021 is fixed to the body 101, and an extended end 2021a of the linear motor 2021 is slidably clamped on the landing gear; the linear drive assembly 202 operates in a first direction when the first power supply provides positive power and the linear drive assembly 202 operates in a second direction when the first power supply provides negative power. The positive and negative power may be interchanged, i.e., when the first power supply element provides negative power, the linear drive assembly 202 operates in the first direction, and when the first power supply element provides positive power, the linear drive assembly 202 operates in the second direction.
It should be noted that when the linear drive assembly 202 is operated in the first direction, the extension end 2021a of the linear motor 2021 extends, thereby pushing the landing gear 201 to deploy; when the linear drive assembly 202 is operated in the second direction, the extended end 2021a of the linear motor 2021 retracts, thereby retracting the landing gear to close the side of the fuselage 100.
The fixed end 2021b of the linear motor 2021 is directly fixed to the machine body 101, or is disposed on the machine body through the bracket 103, so long as the structure for fixing the linear motor is realized, which is within the protection scope of the present invention. Specifically, the bracket 103 is located at the upper end or the lower end of the body 101, and the bracket 103 is provided with an escape passage 1031 for accommodating the reciprocating motion of the extending end of the linear motor 2021. In order to reduce the influence of the landing gear 201 on the takeoff process of the unmanned aerial vehicle and shorten the length of the landing gear 201, the support 103 is preferably arranged at the lower end of the fuselage 101. The bracket is of a frame structure or a barrel structure as long as the linear motor 2021 can be fixed.
The landing gear 201 may be constructed in many ways, and the landing gear 201 may be understood as long as it has a function of supporting the airframe 100 of the drone. In one embodiment of the present invention, the landing gear 201 includes a plurality of landing joints 2011 and a plurality of landing legs 2012, wherein each landing joint 2011 is partially disposed on the fuselage 100 and partially connected to one landing leg 2012. According to the invention, the landing gear 201 is arranged on the airframe 100 through the lifting joint 2011, so that the landing gear 201 can be rotatably arranged on the airframe 100, and the lifting joint 2011 and the lifting support legs 2012 are of an integrated structure or a split structure.
It is within the scope of the present invention that the landing leg 2012 can be rotatably connected to the fuselage 100, for example, the landing joint 2011 includes a first landing joint 2011a disposed on the fuselage 100 and a second landing joint 2011b coupled to the first landing joint 2011a, and the second landing joint 2011b is connected to the landing leg 2012. The first lift joint 2011a and the second lift joint 2011b are connected through a rotating shaft, or the first lift joint 2011a and the second lift joint 2011b are coupled through a positioning protrusion.
The first joint 2011a that falls together is provided with the rotation hole, and second joint 2011b that rises and falls is provided with first location arch and second location arch with the position that the rotation hole corresponds, realizes that second joint 2011b that rises and falls connects on first joint 2011a that falls together through first location arch and second location arch. Alternatively, the first lift joint 2011a and the second lift joint 2011b may be provided with rotation holes through which the rotation shafts are attached. Only two connection modes for coupling the first lift joint 2011a and the second lift joint 2011b are described above, and any connection mode capable of coupling the second lift joint 2011b and the first lift joint 2011a is within the protection scope of the present invention.
To facilitate adjustment, the landing gear system 200 further includes a controller that controls the power conditions of the first power supply element. The controller can be according to unmanned aerial vehicle's the power supply situation of the first power supply element of rise and fall demand self-control. For example, after the controller obtains an electric signal for landing the drone, the controller controls the first power supply element to supply power to the linear motor 2021 so that the linear driving assembly 202 operates in the first direction, and the landing gear 201 is deployed to support the drone; when the controller obtains that the unmanned aerial vehicle is in the flight state, the controller controls the first power supply element to supply power to the linear motor 2021, so that the linear driving assembly 202 runs in the second direction, and the resistance of the landing gear 201 in the flight process is reduced. Or a timer is arranged in the controller, and the electrifying condition of the first power supply element is controlled according to the timer.
Further, the landing gear system 200 of the present invention further includes a communication component, and the controller is communicatively coupled to the communication component. That is, when unmanned aerial vehicle controls through remote controller or mobile terminal, can realize controller and remote controller or mobile terminal's communication interaction through this communication subassembly to the packing up and the expansion of artificial control undercarriage 201.
The invention also discloses an unmanned aerial vehicle which comprises a fuselage 100 and the landing gear system 200 as in any one of the above, wherein the landing gear 201 of the landing gear system 200 is rotatably arranged on the fuselage 100. Because above-mentioned landing gear system 200 has above beneficial effect, including the unmanned aerial vehicle of this landing gear system 200 also has corresponding effect, and this no longer gives redundant details here.
Above-mentioned fuselage 100 includes power compartment 102 and battery compartment 101, and wherein power compartment 102 realizes unmanned aerial vehicle's flight and control, and battery compartment 101 provides electric support for unmanned aerial vehicle, and power compartment 102 can dismantle with battery compartment 101 and be connected or integral type structure. The power cabin 102 is equipped with motor, screw 1021, flight control system and actuates the device, can realize unmanned aerial vehicle's flight and control.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (9)
1. A landing gear system, comprising:
a landing gear rotatably arranged on the fuselage; and
the extension end of the linear driving component is slidably clamped on the undercarriage, the fixed end of the linear driving component is arranged on the fuselage, and when the linear driving component operates in a first direction, the linear driving component pushes the undercarriage to be unfolded to support the fuselage; when the linear drive assembly is operated in a second direction, the landing gear is pulled to retract to be close to the side of the fuselage.
2. The landing gear system of claim 1, wherein the linear drive assembly includes a linear motor and a first power supply element for supplying power to the linear motor, a fixed end of the linear motor being disposed on the body, and an extended end of the linear motor being slidably engaged with the landing gear; when the first power supply element provides positive power, the linear driving assembly operates in a first direction, and when the first power supply element provides negative power, the linear driving assembly operates in a second direction.
3. The landing gear system of claim 2, wherein the fixed end of the linear motor is mounted to the fuselage by a bracket at the lower end of the fuselage, the bracket having an escape channel therein for receiving the reciprocating motion of the extended end of the linear motor.
4. A landing gear according to claim 3, wherein the landing gear includes a plurality of landing joints and a plurality of landing legs, each landing joint being provided in part on the fuselage and in part connected to one of the landing legs.
5. The landing gear system of claim 4, wherein the linear motor has a ball catch on an extended end thereof, and the landing leg has a slot therein, the ball catch being slidably received in the slot.
6. The landing gear system of claim 5, wherein the landing gear includes a first landing gear disposed on the fuselage and a second landing gear journaled to the first landing gear, the second landing gear being coupled to the landing leg.
7. The landing system of claim 2, further comprising a controller electrically connected to the first power supply element.
8. The landing system of claim 7, further comprising a communication assembly, wherein the controller is communicatively coupled to the communication assembly.
9. A drone comprising a fuselage and a landing gear system as claimed in any one of claims 1 to 8, the landing gear of the landing gear system being rotatably disposed on the fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110000850.1A CN112319783A (en) | 2021-01-04 | 2021-01-04 | System and unmanned aerial vehicle rise and fall |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110000850.1A CN112319783A (en) | 2021-01-04 | 2021-01-04 | System and unmanned aerial vehicle rise and fall |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112319783A true CN112319783A (en) | 2021-02-05 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110000850.1A Pending CN112319783A (en) | 2021-01-04 | 2021-01-04 | System and unmanned aerial vehicle rise and fall |
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| CN (1) | CN112319783A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230312086A1 (en) * | 2022-03-30 | 2023-10-05 | Honda Motor Co., Ltd. | Landing gear for flight vehicle |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140263833A1 (en) * | 2005-06-03 | 2014-09-18 | Airbus Operations Limited | Landing gear |
| CN207747806U (en) * | 2017-12-31 | 2018-08-21 | 滁州职业技术学院 | A kind of draw off gear of vehicle-mounted unmanned aerial vehicle |
| US20200003251A1 (en) * | 2016-07-28 | 2020-01-02 | Goodrich Corporation | Thin-skin side stay beams and landing gear assemblies |
| CN110758738A (en) * | 2019-11-26 | 2020-02-07 | 山东省地质测绘院 | Unmanned aerial vehicle for surveying and mapping |
| CN211630854U (en) * | 2020-02-19 | 2020-10-09 | 成都航空职业技术学院 | Unmanned aerial vehicle harvester |
| CN212125507U (en) * | 2020-05-26 | 2020-12-11 | 北京未来智能科技有限公司 | Shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls |
-
2021
- 2021-01-04 CN CN202110000850.1A patent/CN112319783A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140263833A1 (en) * | 2005-06-03 | 2014-09-18 | Airbus Operations Limited | Landing gear |
| US20200003251A1 (en) * | 2016-07-28 | 2020-01-02 | Goodrich Corporation | Thin-skin side stay beams and landing gear assemblies |
| CN207747806U (en) * | 2017-12-31 | 2018-08-21 | 滁州职业技术学院 | A kind of draw off gear of vehicle-mounted unmanned aerial vehicle |
| CN110758738A (en) * | 2019-11-26 | 2020-02-07 | 山东省地质测绘院 | Unmanned aerial vehicle for surveying and mapping |
| CN211630854U (en) * | 2020-02-19 | 2020-10-09 | 成都航空职业技术学院 | Unmanned aerial vehicle harvester |
| CN212125507U (en) * | 2020-05-26 | 2020-12-11 | 北京未来智能科技有限公司 | Shock attenuation formula unmanned aerial vehicle stabilizer blade mechanism that rises and falls |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20230312086A1 (en) * | 2022-03-30 | 2023-10-05 | Honda Motor Co., Ltd. | Landing gear for flight vehicle |
| US12030620B2 (en) * | 2022-03-30 | 2024-07-09 | Honda Motor Co., Ltd. | Landing gear for flight vehicle |
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Application publication date: 20210205 |