CN108016610B - Aircraft with buffer structure and working method - Google Patents
Aircraft with buffer structure and working method Download PDFInfo
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- CN108016610B CN108016610B CN201711324851.1A CN201711324851A CN108016610B CN 108016610 B CN108016610 B CN 108016610B CN 201711324851 A CN201711324851 A CN 201711324851A CN 108016610 B CN108016610 B CN 108016610B
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- driven gear
- electromagnetic element
- assembly
- control unit
- aircraft
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000001514 detection method Methods 0.000 claims abstract description 16
- 230000003139 buffering effect Effects 0.000 claims description 36
- 230000007246 mechanism Effects 0.000 claims description 22
- 230000009471 action Effects 0.000 claims description 4
- 230000000694 effects Effects 0.000 abstract description 11
- 230000002035 prolonged effect Effects 0.000 abstract description 2
- 230000007547 defect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000011835 investigation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
Images
Classifications
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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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/60—Take-off or landing of UAVs from a runway using their own power
Abstract
The invention relates to an aircraft and a working method thereof. When the support contacts the ground, the pressure sensor transmits a pressure signal to the control unit, the control unit starts the power supply module according to the detection signal result, the power supply module supplies power to the first electromagnetic element and the second electromagnetic element to generate magnetic force, the first electromagnetic element and the second electromagnetic element repel each other to form a buffer structure, the closer the distance between the first electromagnetic element and the second electromagnetic element is, the larger the repulsive force is, the buffer effect of the repulsive force and the buffer effect of the elastic piece are fused together, the buffer effect is remarkably improved, the damage effect on the part is very small, and the service life of the elastic piece is also prolonged.
Description
Technical Field
The invention belongs to the field of aircrafts, and particularly relates to an aircraft with a buffer structure and a working method.
Background
Aircraft (drones) have developed rapidly in recent years. It has been used in many fields such as express delivery, investigation, cruise to different degrees.
When the aircraft is landing, for example when parked on the ground, the feet need to be in contact with the ground, which is generally a rigid contact or a simple cushioned contact (for example with springs).
However, the existing buffering mode still has the defects, and the buffering effect is insufficient, so that the service life of the aircraft can be seriously damaged. In addition, the existing buffering mode is too single, and gradient adjustment cannot be performed in the buffering process, so that the buffering effect is more stable.
Disclosure of Invention
In order to solve the defects of the prior art, the invention aims to provide an aircraft capable of improving the buffering effect of the aircraft and a working method thereof.
The invention idea of the invention is as follows: through the circular telegram repulsion effect between first electromagnetic element and the second electromagnetic element, form another kind of buffer structure, it cooperates with the elastic component, forms two kinds of cushioning effects that fuse together, and when the aircraft parked on the holding surface, the cushioning effect was obviously promoted.
An aircraft with a buffer structure comprises a rack, a buffer assembly and a first pushing assembly, wherein the rack is provided with an accommodating groove; the buffer assembly is arranged in the accommodating groove; the first pushing assembly is arranged on the rack, a first end of the first pushing assembly is connected with the rack, a second end of the first pushing assembly is connected with the buffering assembly, the first pushing assembly is provided with a telescopic structure, and the telescopic structure is used for driving the buffering assembly to move; the buffer assembly comprises a first connecting block, an elastic piece, a second connecting block and an elastic supporting leg which are sequentially connected, the first connecting block is provided with a first electromagnetic element, the second connecting block is provided with a second electromagnetic element, the first electromagnetic element and the second electromagnetic element are oppositely arranged, and the elastic supporting leg is provided with a pressure sensor; the buffer assembly further comprises a control unit and a power supply module, the control unit is connected with the pressure sensor and the power supply module respectively, and the power supply module is connected with the first electromagnetic element and the second electromagnetic element respectively.
The invention has the beneficial effects that: when the support contacts the ground, the pressure sensor transmits a pressure signal to the control unit, the control unit starts the power supply module according to the detection signal result, the power supply module supplies power to the first electromagnetic element and the second electromagnetic element to generate magnetic force, the first electromagnetic element and the second electromagnetic element repel each other to form a buffer structure, the closer the distance between the first electromagnetic element and the second electromagnetic element is, the larger the repulsive force is, the buffer effect of the repulsive force and the buffer effect of the elastic piece are fused together, the buffer effect is remarkably improved, the damage effect on the part is very small, and the service life of the elastic piece is also prolonged.
According to a preferable scheme, the first pushing assembly comprises a hydraulic assembly and a telescopic structure which are sequentially connected, and the telescopic structure is connected with the buffering assembly.
The first pushing assembly comprises a first motor, a driving gear, a first driven gear, a second driven gear and a first screw rod which are sequentially connected, the first screw rod is connected with the first buffering assembly, and when the second driven gear rotates, the first screw rod moves along the axis direction of the second driven gear; the first pushing assembly further comprises a third driven gear, a fourth driven gear and a second lead screw which are sequentially connected, the second lead screw is connected with the second buffering assembly, when the fourth driven gear rotates, the second lead screw moves along the axis direction of the second driven gear, and the driving gear is meshed with the third driven gear.
The aircraft also comprises a wing and a power mechanism, wherein the power mechanism is connected with the wing, and the control unit is connected with the power mechanism; the control unit is provided with a comparison module, the comparison module is used for comparing whether the ratio of the pressure detection value of the pressure sensor to the set pressure value exceeds the set range, and when the ratio of the pressure detection value to the set pressure value exceeds the set range, the control unit improves the power of the power mechanism.
Method for operating an aircraft with a buffer structure, comprising the following steps:
s1: the aircraft flies to a designated area and is prepared to land on a supporting surface of the designated area;
s2: the first pushing assembly pushes the buffering assembly out of the accommodating groove, so that the buffering assembly is firstly contacted with the supporting surface;
s3: the elastic support legs are in contact with the supporting surface, and meanwhile, the pressure sensor senses the pressure of the supporting surface and transmits detected pressure signals to the control unit in real time;
s4: the elastic piece gives a first buffering effect, meanwhile, the control unit judges the pressure signal, and when the judgment result shows that the pressure signal exceeds a set threshold value, the power supply module is started to supply power to the first electromagnetic element and the second electromagnetic element;
s5: the first electromagnetic element and the second electromagnetic element generate electromagnetic force in the energized state, and a repulsive force is generated between the first electromagnetic element and the second electromagnetic element;
s6: a second buffer action is generated between the first connecting block and the second connecting block;
s7: the control unit judges the pressure signal, and when the judgment result shows that the pressure signal is lower than the set threshold value, the power supply module is closed to supply power to the first electromagnetic element and the second electromagnetic element, and the repulsive force between the first connecting block and the second connecting block disappears.
The first pushing assembly comprises a first motor, a driving gear, a first driven gear, a second driven gear and a first screw rod which are sequentially connected, the first screw rod is connected with the first buffering assembly, and when the second driven gear rotates, the first screw rod moves along the axis direction of the second driven gear; the first pushing assembly further comprises a third driven gear, a fourth driven gear and a second lead screw which are sequentially connected, the second lead screw is connected with the second buffering assembly, when the fourth driven gear rotates, the second lead screw moves along the axis direction of the second driven gear, and the driving gear is meshed with the third driven gear.
The working method comprises the following steps:
y1: the aircraft flies to a designated area and is prepared to land on a supporting surface of the designated area;
y2: the first motor works to drive the driving gear to rotate, the first driven gear and the second driven gear sequentially rotate, when the second driven gear rotates, the first screw rod moves along the axis direction of the second driven gear, and the first screw rod drives the first buffer assembly to be pushed out of the accommodating groove; meanwhile, when the driving wheel rotates, the third driven gear and the fourth driven gear are sequentially driven to rotate, and the second screw rod drives the second buffer assembly to be pushed out from the accommodating groove.
The aircraft also comprises a wing and a power mechanism, wherein the power mechanism is connected with the wing, and the control unit is connected with the power mechanism;
the control unit is provided with a comparison module, the comparison module is used for comparing whether the ratio of the pressure detection value of the pressure sensor to the set pressure value exceeds the set range, and when the ratio of the pressure detection value to the set pressure value exceeds the set range, the control unit improves the power of the power mechanism.
The working method also comprises the following steps:
t1: when the comparison module compares that the ratio of the pressure detection value of the pressure sensor to the set pressure value exceeds the set range, the control unit improves the power of the power mechanism;
t2: when the comparison module compares that the ratio of the pressure detection value of the pressure sensor to the set pressure value is in the set range, the control unit stops the work of the power mechanism.
Drawings
Fig. 1 is a schematic structural view of a first embodiment of the aircraft with a buffer structure according to the invention.
Fig. 2 is a cross-sectional structural view of a portion of an assembly of a first embodiment of the aircraft having a cushioning structure of the present invention.
Figure 3 is a schematic view of the first pusher assembly and the buffer assembly of the first embodiment of the aircraft with a buffer structure according to the invention.
Figure 4 is a schematic view of the first pusher assembly and the buffer assembly of the second embodiment of the aircraft with a buffer structure according to the invention.
Wherein the reference numerals are: 10. frame, 11, holding tank, 13, rotor wing, 20, buffer unit, 21, first connecting block, 22, elastic component, 23, second connecting block, 24, elasticity stabilizer blade, 30, first propelling movement subassembly, 31, hydraulic assembly, 32, extending structure, 41, first motor, 42, driving gear, 44, first driven gear, 45, head rod, 46, second driven gear, 47, first lead screw, 51, third driven gear, 52, second connecting rod, 53, fourth driven gear, 54, the second lead screw.
Detailed Description
The first embodiment:
as shown in fig. 1 to 3, the aircraft with a buffer structure of the present embodiment includes a frame 10, a buffer assembly 20, and a first pushing assembly 30.
The frame 10 has a receiving groove 11. Buffering subassembly 20 sets up in holding tank 11, and first propelling movement subassembly 30 sets up on frame 10, and the first end and the frame 10 of first propelling movement subassembly 30 are connected, and the second end and the buffering subassembly 20 of first propelling movement subassembly 30 are connected, and first propelling movement subassembly 30 has extending structure, and extending structure is used for driving buffering subassembly 20 and removes.
Specifically, the first pushing assembly 30 includes a hydraulic assembly 31 and a telescopic structure 32 connected in sequence, and the telescopic structure 32 is connected with the buffering assembly 20. The buffering assembly 20 comprises a first connecting block 21, an elastic member 22, a second connecting block 23 and an elastic supporting leg 24 which are sequentially connected, wherein the first connecting block 21 is provided with a first electromagnetic element, the second connecting block is provided with a second electromagnetic element, the first electromagnetic element and the second electromagnetic element are oppositely arranged, and the elastic supporting leg 24 is provided with a pressure sensor. The buffer assembly further comprises a control unit and a power supply module, the control unit is connected with the pressure sensor and the power supply module respectively, and the power supply module is connected with the first electromagnetic element and the second electromagnetic element respectively.
Two sides of the frame are respectively provided with a rotary wing 13, the rotary wings 13 are driven to rotate under the action of a power mechanism, and an upward force is provided to enable the aircraft to move upwards.
The method of operating an aircraft having a cushioning structure of the present embodiment includes the steps of:
s1: the aircraft flies to a designated area and is prepared to land on a supporting surface of the designated area;
s2: the first pushing assembly 30 pushes the buffering assembly 20 out of the accommodating groove 11, so that the buffering assembly 20 is firstly contacted with the supporting surface;
s3: the elastic support legs 24 are in contact with the supporting surface, and meanwhile, the pressure sensor senses the pressure of the supporting surface and transmits a detected pressure signal to the control unit in real time;
s4: the elastic part 22 gives a first buffering function, meanwhile, the control unit judges the pressure signal, and when the judgment result shows that the pressure signal exceeds a set threshold value, the power supply module is started to supply power to the first electromagnetic element and the second electromagnetic element;
s5: the first electromagnetic element and the second electromagnetic element generate electromagnetic force in the energized state, and a repulsive force is generated between the first electromagnetic element and the second electromagnetic element;
s6: a second buffer action is generated between the first connecting block 21 and the second connecting block 23;
s7: the control unit judges the pressure signal, and when the judgment result shows that the pressure signal is lower than the set threshold value, the power supply module is closed to supply power to the first electromagnetic element and the second electromagnetic element, and the repulsive force between the first connecting block and the second connecting block disappears.
Second embodiment:
the aircraft of this embodiment is substantially the same as the first embodiment described above, and only the differences will be described in detail below.
As shown in fig. 4, the first pushing assembly 30 of the present embodiment includes a first motor 41, a driving gear 42, a first driven gear 44, a first connecting rod 45, a second driven gear 46, and a first lead screw 47, which are connected in sequence, wherein the first lead screw 47 is connected to the buffering assembly 20 (with reference to the first embodiment), and when the second driven gear 46 rotates, the first lead screw 47 moves along the axial direction of the second driven gear 46. The first pushing assembly 30 further includes a third driven gear 51, a second connecting rod 52, a fourth driven gear 53, and a second lead screw 54 connected in sequence, wherein the second lead screw 54 is connected to another buffer assembly 20 (structure refer to the first embodiment), when the fourth driven gear 53 rotates, the second lead screw 54 moves along the axial direction of the second driven gear 46, and the driving gear 42 is also engaged with the third driven gear 51.
The working method of the embodiment comprises the following steps:
y1: the aircraft flies to a designated area and is prepared to land on a supporting surface of the designated area;
y2: the first motor works to drive the driving gear 42 to rotate, the first driven gear 44 and the second driven gear 46 sequentially rotate, when the second driven gear 46 rotates, the first screw rod 47 moves along the axis direction of the second driven gear 46, and the first screw rod 47 drives the first buffer assembly 20 to be pushed out of the accommodating groove; meanwhile, when the driving gear 42 rotates, the third driven gear 51 and the fourth driven gear 53 are sequentially driven to rotate, and the second screw 54 drives the second buffer assembly 20 to be pushed out from the accommodating groove.
The third embodiment:
the aircraft of this embodiment is substantially the same as the first embodiment described above, and only the differences will be described in detail below.
The aircraft also comprises a wing and a power mechanism, the power mechanism is connected with the wing, and the control unit is connected with the power mechanism; the control unit is provided with a comparison module, the comparison module is used for comparing whether the ratio of the pressure detection value of the pressure sensor to the set pressure value exceeds the set range, and when the ratio of the pressure detection value to the set pressure value exceeds the set range, the control unit improves the power of the power mechanism.
The working method of the embodiment further comprises the following steps:
t1: when the comparison module compares that the ratio of the pressure detection value of the pressure sensor to the set pressure value exceeds the set range, the control unit improves the power of the power mechanism;
t2: when the comparison module compares that the ratio of the pressure detection value of the pressure sensor to the set pressure value is in the set range, the control unit stops the work of the power mechanism.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (5)
1. An aircraft having a cushioning structure, comprising:
a frame having an accommodating groove;
the buffer assembly is arranged in the accommodating groove;
the first pushing assembly is arranged on the rack, a first end of the first pushing assembly is connected with the rack, a second end of the first pushing assembly is connected with the buffering assembly, the first pushing assembly is provided with a telescopic structure, and the telescopic structure is used for driving the buffering assembly to move;
the buffer assembly comprises a first connecting block, an elastic piece, a second connecting block and an elastic supporting leg which are sequentially connected, the first connecting block is provided with a first electromagnetic element, the second connecting block is provided with a second electromagnetic element, the first electromagnetic element and the second electromagnetic element are oppositely arranged, and the elastic supporting leg is provided with a pressure sensor;
the buffer assembly further comprises a control unit and a power supply module, the control unit is respectively connected with the pressure sensor and the power supply module, and the power supply module is respectively connected with the first electromagnetic element and the second electromagnetic element;
the power mechanism is connected with the wing, and the control unit is connected with the power mechanism;
the control unit is provided with a comparison module, the comparison module is used for comparing whether the ratio of the pressure detection value of the pressure sensor to the set pressure value exceeds a set range, and when the ratio of the pressure detection value to the set pressure value exceeds the set range, the control unit improves the power of the power mechanism.
2. The aircraft with a cushioning structure of claim 1,
the first pushing assembly comprises a hydraulic assembly and a telescopic structure which are sequentially connected, and the telescopic structure is connected with the buffering assembly.
3. The aircraft with a cushioning structure of claim 1,
the first pushing assembly comprises a first motor, a driving gear, a first driven gear, a second driven gear and a first screw rod which are sequentially connected, the first screw rod is connected with the first buffering assembly, and when the second driven gear rotates, the first screw rod moves along the axis direction of the second driven gear;
the first pushing assembly further comprises a third driven gear, a fourth driven gear and a second lead screw which are sequentially connected, the second lead screw is connected with the second buffering assembly, when the fourth driven gear rotates, the second lead screw moves along the axis direction of the second driven gear, and the driving gear is meshed with the third driven gear.
4. Method of operating an aircraft with a buffer structure according to claim 1,
the method comprises the following steps:
s1: the aircraft flies to a designated area and is prepared to land on a supporting surface of the designated area;
s2: the first pushing assembly pushes the buffering assembly out of the accommodating groove, so that the buffering assembly is firstly contacted with the supporting surface;
s3: the elastic support leg is in contact with the supporting surface, and meanwhile, the pressure sensor senses the pressure of the supporting surface and transmits a detected pressure signal to the control unit in real time;
s4: the elastic piece gives a first buffering effect, meanwhile, the control unit judges the pressure signal, and when the judgment result shows that the pressure signal exceeds a set threshold value, the control unit starts a power supply module to supply power to the first electromagnetic element and the second electromagnetic element;
s5: the first electromagnetic element and the second electromagnetic element generate electromagnetic force in the electrified state, and a repulsive force is generated between the first electromagnetic element and the second electromagnetic element;
s6: a second buffer action is generated between the first connecting block and the second connecting block;
s7: the control unit judges the pressure signal, and when the judgment result shows that the pressure signal is lower than a set threshold value, the power supply module is closed to supply power to the first electromagnetic element and the second electromagnetic element, and the repulsive force between the first connecting block and the second connecting block disappears;
the working method also comprises the following steps:
t1: when the comparison module compares that the ratio of the pressure detection value of the pressure sensor to the set pressure value exceeds a set range, the control unit improves the power of the power mechanism;
t2: when the comparison module compares that the ratio of the pressure detection value of the pressure sensor to the set pressure value is in the set range, the control unit stops the work of the power mechanism.
5. Method of operating an aircraft with a buffer structure according to claim 4,
the first pushing assembly comprises a first motor, a driving gear, a first driven gear, a second driven gear and a first screw rod which are sequentially connected, the first screw rod is connected with the first buffering assembly, and when the second driven gear rotates, the first screw rod moves along the axis direction of the second driven gear;
the first pushing assembly further comprises a third driven gear, a fourth driven gear and a second lead screw which are sequentially connected, the second lead screw is connected with the second buffering assembly, when the fourth driven gear rotates, the second lead screw moves along the axis direction of the second driven gear, and the driving gear is meshed with the third driven gear
The working method comprises the following steps:
y1: the aircraft flies to a designated area and is prepared to land on a supporting surface of the designated area;
y2: the first motor works to drive the driving gear to rotate, the first driven gear and the second driven gear sequentially rotate, when the second driven gear rotates, the first lead screw moves along the axis direction of the second driven gear, and the first lead screw drives the first buffer assembly to be pushed out of the accommodating groove; simultaneously, when the driving gear rotated, drive third driven gear, fourth driven gear rotation in proper order, the second lead screw drives second buffering subassembly and is released in by the holding tank.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711324851.1A CN108016610B (en) | 2017-12-13 | 2017-12-13 | Aircraft with buffer structure and working method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711324851.1A CN108016610B (en) | 2017-12-13 | 2017-12-13 | Aircraft with buffer structure and working method |
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| CN108016610A CN108016610A (en) | 2018-05-11 |
| CN108016610B true CN108016610B (en) | 2020-12-29 |
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| CN111366694A (en) * | 2020-02-06 | 2020-07-03 | 河北泰斯汀检测技术服务有限公司 | Detection device and detection method for heavy metals in flour |
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| CN206068140U (en) * | 2016-08-29 | 2017-04-05 | 桂阳县浩丰科技有限公司 | A kind of vicariouss unmanned plane damping undercarriage |
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| CN105882986B (en) * | 2016-06-30 | 2018-11-13 | 江苏科力斯通新材料有限公司 | A kind of boat-carrying unmanned plane fall protection mechanism |
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2017
- 2017-12-13 CN CN201711324851.1A patent/CN108016610B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB530388A (en) * | 1939-06-10 | 1940-12-11 | Armstrong Whitworth Co Eng | Improvements relating to the landing-gear of aeroplanes |
| CN106103274A (en) * | 2015-07-02 | 2016-11-09 | 深圳市大疆创新科技有限公司 | Unmanned plane, its control system and method, and unmanned plane landing control method |
| CN205707305U (en) * | 2016-06-28 | 2016-11-23 | 滨州学院 | A kind of pint-sized airplane undercarriage |
| CN105882986B (en) * | 2016-06-30 | 2018-11-13 | 江苏科力斯通新材料有限公司 | A kind of boat-carrying unmanned plane fall protection mechanism |
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Effective date of registration: 20201216 Address after: 313000 north side of National Road 318 and east side of sewage treatment plant in Dongjiao, Zhili Town, Wuxing District, Huzhou City, Zhejiang Province Applicant after: Zhejiang Lisheng New Material Technology Co.,Ltd. Address before: 056900 43 Yucai Road, Daming County, Handan, Hebei Applicant before: Ren Hongye |
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Denomination of invention: An aircraft with buffer structure and its working method Effective date of registration: 20211228 Granted publication date: 20201229 Pledgee: Huzhou Wuxing Rural Commercial Bank Co.,Ltd. high tech Zone Green sub branch Pledgor: Zhejiang Lisheng New Material Technology Co.,Ltd. Registration number: Y2021330002697 |
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