CN110803280A - Pure electric manned vehicle - Google Patents
Pure electric manned vehicle Download PDFInfo
- Publication number
- CN110803280A CN110803280A CN201911260941.8A CN201911260941A CN110803280A CN 110803280 A CN110803280 A CN 110803280A CN 201911260941 A CN201911260941 A CN 201911260941A CN 110803280 A CN110803280 A CN 110803280A
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- pair
- underframe
- nacelle
- pure electric
- manned vehicle
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- 230000035939 shock Effects 0.000 claims abstract description 20
- 238000013016 damping Methods 0.000 claims abstract description 13
- 238000010521 absorption reaction Methods 0.000 claims abstract description 7
- 230000009471 action Effects 0.000 claims abstract description 4
- 230000007246 mechanism Effects 0.000 claims description 14
- 239000006096 absorbing agent Substances 0.000 claims description 9
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 3
- 239000004917 carbon fiber Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 239000007769 metal material Substances 0.000 claims description 3
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 6
- 238000010276 construction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
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- 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
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Wind Motors (AREA)
Abstract
The invention relates to a pure electric manned aircraft which comprises a rotor wing, a nacelle and a damping bracket; the rotor wing is arranged at the top of the nacelle, and the bottom of the nacelle is provided with a damping bracket; the rotor wing comprises two spiral arms which are connected into a whole, and the two spiral arms are of a symmetrical structure; each spiral arm is composed of a connecting part and two propeller connecting parts which are integrally formed, the connecting part is positioned in the middle of each spiral arm, and the connecting parts of the two spiral arms are connected together through a connecting piece; every screw connecting portion all adopts Y type structure, and the bottom and the connecting portion integrated into one piece of Y type structure are located two forked parts of Y type structure and are provided with screw and drive arrangement respectively, and the screw bottom is provided with drive arrangement, and drive arrangement installs in the forked part of Y type structure, drives the screw action by drive arrangement. The invention has better shock absorption effect and higher safety performance.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a pure electric manned aircraft.
Background
With the development of science and technology, the application of multi-rotor aircrafts in various industry fields is more and more extensive, so that the multi-rotor aircrafts are favored by consumers and enterprises. Most of the existing aircrafts are applied to scientific research, are not suitable for the public and cannot realize manned functions. With the popularization of aircrafts, some manned aircrafts are born, but the existing manned aircrafts have poor performance, poor damping effect during landing and certain problems in rescue of flight personnel during emergency accidents, for example, after the aircraft is in fault, the existing manned aircrafts on the upper parts of multiple rotors cannot immediately rescue the flight personnel because the multiple rotors rotate for a certain time under the inertia effect.
Disclosure of Invention
Aiming at the problems, the invention aims to provide a pure electric manned aircraft which is good in damping effect and high in safety performance.
In order to achieve the purpose, the invention adopts the following technical scheme: a pure electric manned aircraft comprises a rotor wing, a nacelle and a damping bracket; the rotor wing is arranged at the top of the nacelle, and the damping bracket is arranged at the bottom of the nacelle; the rotor wing comprises two spiral arms which are connected into a whole, and the two spiral arms are of a symmetrical structure; each spiral arm is composed of a connecting part and two propeller connecting parts which are integrally formed, the connecting part is positioned in the middle of the spiral arm, and the connecting parts of the two spiral arms are connected together through a connecting piece; every screw connecting portion all adopt Y type structure, the bottom of Y type structure with connecting portion integrated into one piece is located two forked branches of Y type structure are provided with screw and drive arrangement respectively, the screw bottom is provided with drive arrangement, drive arrangement installs Y type structure forked branch portion, by drive arrangement drives the screw action.
Further, the spiral arm adopts carbon fiber material to make, the connecting piece is pre-buried in the connecting portion, just the connecting piece adopts metal material to make.
Further, the propeller connecting part of the Y-shaped structure adopts a hollow structure.
Further, a battery bin is arranged at the bottom of the Y-shaped structure of the propeller connecting part, and a power supply battery is arranged in the battery bin and used for supplying power to the driving device.
Furthermore, a connecting frame is embedded in the top of the nacelle, and the connecting frame is connected with the bottom of the connecting part of the spiral arm through a first embedded part arranged at the bottom of the connecting part.
Furthermore, the nacelle adopts a semi-closed structure, handrails are arranged on two sides of a seat arranged in the nacelle, and the two handrails are movably connected with two sides of the seat.
Further, the damping support comprises an underframe, a first connecting seat, a first connecting shaft, a lower support arm, a skid plate, a second connecting seat, a third connecting seat, an air damper and a spring; the top of the underframe is provided with a third embedded part used for being connected with the bottom of the pod, the underframe is provided with four support arms, two support arms positioned at the rear part of the underframe are of a reducing structure, and a connecting plate integrally formed with the reducing structure is arranged at the end part of the reducing structure; the reducing structure and the two support arms positioned at the front part of the underframe are arranged in a triangular shape, and the inner sides of the end parts of the two support arms at the front part are both provided with the first connecting seats; the front end of the middle part of the underframe is provided with two first connecting shafts; the lower support arms are respectively arranged below the two support arms at the front end of the underframe, and the top end of each lower support arm is movably connected with the first connecting shaft; the bottom of each lower support arm is provided with the skid plate, the middle part of the skid plate is pre-embedded with the second connecting seat, the bottom of the lower support arm is coaxially connected with the second connecting seat through a second connecting shaft, and the second connecting shaft is provided with a limiting screw for limiting the front position and the rear position of the air damper; the third connecting seat is arranged on the inner side of the lower part of the lower support arm, and a through hole is formed in the lower support arm at the third connecting seat; one end of the air damper is connected with the third connecting seat shaft, the other end of the air damper penetrates through the through hole to be connected with the first connecting seat shaft on the underframe, and a limit screw of the air damper is arranged on the shaft; and connecting wings which are integrally formed with the lower support arm are further arranged on two sides of the lower portion of the lower support arm, one end of the spring is connected with the connecting wings, and the other end of the spring is connected with the side wall of the second connecting seat on the skid plate.
Furthermore, the damping support also comprises a rear support rod and a connecting mechanism; the rear support rods are arranged in two numbers, one end of one rear support rod is connected with the bottom of the rear end of the underframe, one end of the other rear support rod is connected with the rear wall of the nacelle, the other ends of the two rear support rods are connected with the middle of the skid plate through the connecting mechanism, and the air shock absorber is further arranged between the connecting mechanism and the skid plate.
Further, the connecting mechanism comprises a first pair of vertical connecting plates, a pair of parallel frames, a second pair of vertical connecting plates and a support piece; the first pair of connecting vertical plates are embedded in the middle of the skid plate, three third connecting shafts are arranged on the first pair of connecting vertical plates, the third connecting shafts positioned in the middle of the first pair of connecting vertical plates are used for being connected with one end of the air damper, and the third connecting shafts positioned at two ends of the first pair of connecting vertical plates are respectively used for being connected with one ends of the two parallel frames; a fourth connecting shaft is arranged at two ends of one side of the second pair of connecting vertical plates respectively and is used for being connected with the other ends of the two parallel frames, and the fourth connecting shaft positioned at the upper part of the second pair of connecting vertical plates is also connected with the other end of the air damper; the supporting piece is arranged on the other side of the second pair of vertical connecting plates, the supporting piece is connected with a connecting plate between two support arms which are of a reducing structure and arranged at the rear part of the underframe, and the other ends of the two rear support rods are respectively connected with two ends of the supporting piece.
Furthermore, the two parallel frames, the first pair of connecting vertical plates and the second pair of connecting vertical plates form a quadrilateral shock absorption structure, and the air shock absorber is positioned on the diagonal line of the quadrilateral shock absorber structure.
Due to the adoption of the technical scheme, the invention has the following advantages: 1. according to the invention, the rotor wing is arranged at the top of the nacelle, so that when the aircraft breaks down, a mechanic can be timely rescued, and the safety of the mechanic is effectively ensured. 2. The rotor wing adopts a symmetrical combined structure, and the two spiral arms are connected into a whole through the metal piece, so that the strength of the rotor wing can be effectively enhanced. 3. The nacelle of the invention adopts a semi-closed structure, thereby effectively reducing the overall weight of the aircraft. 4. The damping support greatly improves the damping effect through the air damper and the quadrilateral damper structure, and can effectively ensure the stability of the aircraft during landing. In conclusion, the invention can be widely applied in the field of aviation.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention;
figure 2 is a schematic view of a rotor of the present invention;
FIG. 3 is a schematic view of the pod construction of the present invention;
FIG. 4 is a schematic view of the shock mount structure of the present invention;
FIG. 5 is an exploded view of the shock bracket of the present invention;
FIG. 6 is a rear view of the shock bracket of the present invention;
fig. 7 is a schematic view of the connection mechanism of the present invention.
Detailed Description
The invention is described in detail below with reference to the figures and examples.
As shown in fig. 1, the object of the present invention is to provide a pure electric manned vehicle comprising a rotor 1, a nacelle 2 and a shock-absorbing cradle 3. The rotor 1 is arranged on the top of the nacelle 2, and the bottom of the nacelle 2 is provided with a damping bracket 3.
Wherein:
as shown in fig. 2, the rotor 1 includes two spiral arms 4, the two spiral arms 4 are integrally connected, and the two spiral arms 4 have a symmetrical structure. Each spiral arm 4 is constituted by a connecting portion 41 and two propeller connecting portions 42 which are integrally formed; the connecting part 41 is positioned in the middle of the spiral arms 4, and the connecting parts 41 of the two spiral arms 4 are connected together through a connecting piece; every screw connecting portion 42 all adopts Y type structure, and the bottom and the connecting portion integrated into one piece of Y type structure are located two forked parts of Y type structure and are provided with screw 5 and drive arrangement 6 respectively, and screw 5 bottom is provided with drive arrangement 6, and drive arrangement 6 installs in the forked part of Y type structure, is driven screw 5 action by drive arrangement 6.
In a preferred embodiment, the spiral arms 4 are made of carbon fiber material, so as to effectively reduce the overall weight of the aircraft; the connecting piece is pre-buried in connecting portion 41, and the connecting piece adopts metal material to make, preferably, adopts aluminium to make.
In a preferred embodiment, the propeller connecting portion 42 of the Y-shaped structure is a hollow structure, that is, the bifurcations of the Y-shaped structure are all provided with hollow structures, which effectively increases the wind field of the rotor 1.
In a preferred embodiment, the drive means 6 is an electric motor. The driving device 6 can also adopt other power mechanisms according to actual needs.
In a preferred embodiment, a battery compartment 7 is provided at the bottom of the Y-shaped structure at the propeller connection 42, and a power supply battery is provided in the battery compartment 7 for supplying power to the driving device 6.
As shown in fig. 3, the nacelle 2 is intended for a carrier engineer and a control device is provided inside the nacelle 2, which control device may be of a prior art construction and will not be described in detail here. A connecting frame 8 is embedded on the top of the nacelle 2, and the connecting frame 8 is connected with the bottom of the connecting part 41 of the spiral arm 4 through a first embedded part 43 arranged on the bottom of the connecting part 41.
In a preferred embodiment, the nacelle 2 is of a semi-enclosed structure, that is, the nacelle 2 only has a front wall and a rear wall, and is composed of an upper frame and a lower frame, and the upper frame and the lower frame are connected into a whole through a second embedded part. Armrests 91 are arranged on two sides of a seat 9 arranged in the nacelle 2, the two armrests 91 are movably connected with two sides of the seat 9, and safety of an engineer can be effectively protected through the armrests 91.
As shown in fig. 4 to 6, the shock absorbing bracket 3 includes a base frame 10, a first connecting base 11, a first connecting shaft 12, a lower arm 14, a skid plate 15, a second connecting base 16, a third connecting base 17, an air damper 18, a spring 19, a rear lever 20, and a connecting mechanism.
The top of the underframe 10 is provided with a third embedded part 102 used for being connected with the bottom of the nacelle 2, the underframe 10 is provided with four support arms 101, the two support arms 101 positioned at the rear part of the underframe 10 are of a reducing structure, and the end part of the reducing structure is provided with a connecting plate integrally formed with the reducing structure; the reducing structure and two support arms 101 positioned at the front part of the underframe 10 are arranged in a triangle, and the inner sides of the end parts of the two support arms 101 at the front part are both provided with a first connecting seat 11; two first connecting shafts 12 are provided at the front end of the middle portion of the base frame 10.
A lower support arm 14 is respectively arranged below the two support arms 101 at the front end of the underframe 10, the top end of each lower support arm 14 is movably connected with the first connecting shaft 12, and the support arms 101 limit the outward extending movement of the lower support arms 14. The bottom of each lower support arm 14 is provided with a skid plate 15, a second connecting seat 16 is embedded in the middle of the skid plate 15, the bottom of the lower support arm 14 is coaxially connected with the second connecting seat 16 through a second connecting shaft, and a limiting screw for limiting the front position and the rear position of the air damper 18 is arranged on the second connecting shaft.
A third connecting seat 17 is arranged on the inner side of the lower part of the lower support arm 14, and a through hole is arranged on the lower support arm 14 at the third connecting seat 17; one end of the air damper 18 is connected with the third connecting seat 17 through a shaft, the other end of the air damper 18 penetrates through the through hole to be connected with the first connecting seat 11 on the underframe 10 through a shaft, and a limit screw of the air damper 18 is arranged on the shaft. The two sides of the lower part of the lower support arm 14 are also provided with connecting wings 21 which are integrally formed with the lower support arm, one end of the spring 19 is connected with the connecting wings 21, and the other end of the spring 19 is connected with the side wall of the second connecting seat 16 on the skid plate 15; when the aircraft is used, no matter how the skid plate 15 is stressed, the spring 19 can effectively ensure that the bottom surface of the skid plate 15 is parallel to the ground in a static state, and the skid plate 15 can keep a smaller angle with the horizontal plane in a take-off state, so that the aircraft is ensured that the skid is stressed by the spring and cannot be disturbed by the influence of air flow in the flying process.
The number of the rear supporting rods 20 is two, one end of one of the rear supporting rods 20 is connected with the bottom of the rear end of the underframe 10, one end of the other rear supporting rod 20 is connected with the rear wall of the nacelle 2, the other ends of the two rear supporting rods 20 are connected with the middle of the skid plate 15 through a connecting mechanism, and an air damper 18 is further arranged between the connecting mechanism and the skid plate 15.
As shown in fig. 7, the connecting mechanism includes a first pair of vertical connecting plates 22, a pair of parallel frames 23, a second pair of vertical connecting plates 24 and a supporting member 25. A first pair of connecting vertical plates 22 are embedded in the middle of the skid plate 15, three third connecting shafts are arranged on the first pair of connecting vertical plates 22, the third connecting shafts located in the middle of the first pair of connecting vertical plates 22 are used for being connected with one end of the air damper 18, and the third connecting shafts located at two ends of the first pair of connecting vertical plates 22 are respectively used for being connected with one ends of the two parallel frames 23. A fourth connecting shaft is arranged at each of two ends of one side of the second pair of connecting vertical plates 24 and is used for connecting with the other ends of the two parallel frames 23, and the fourth connecting shaft positioned at the upper part of the second pair of connecting vertical plates 24 is also connected with the other end of the air damper 18; the two parallel frames 23, the first pair of connecting vertical plates 22 and the second pair of connecting vertical plates 24 form a quadrilateral shock absorption structure, the air shock absorber 18 is located on a diagonal line of the quadrilateral shock absorber structure, a shock absorption effect is further improved, the bottom surface of the skid plate 15 is effectively guaranteed to be parallel to the ground in a static state, the skid plate 15 can keep a small angle with a horizontal plane in a take-off state, and therefore the situation that the skid of the aircraft is influenced by the force of a spring in the flying process and cannot be disturbed by airflow is guaranteed. The other side of the second pair of vertical connecting plates 24 is provided with a supporting member 25, the supporting member 25 is connected to the connecting plate between the two arms 101 of the rear portion of the chassis 10 in a tapered structure, and the other ends of the two rear supporting rods 20 are connected to two ends of the supporting member 25 respectively.
In the description of the present invention, it is to be understood that the terms "upper", "lower", "front", "back", "top", "bottom", "inner", "outer", and the like, indicate orientations and positional relationships based on the orientations and positional relationships shown in the drawings, are used for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," and the like are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
Although the embodiments of the present invention have been shown and described, it is understood that the embodiments are illustrative and not restrictive, and that those skilled in the art may make changes, modifications, substitutions and alterations to the embodiments without departing from the scope of the present invention.
Claims (10)
1. The utility model provides a pure electric manned vehicle which characterized in that: the device comprises a rotor wing, a nacelle and a damping bracket; the rotor wing is arranged at the top of the nacelle, and the damping bracket is arranged at the bottom of the nacelle;
the rotor wing comprises two spiral arms which are connected into a whole, and the two spiral arms are of a symmetrical structure; each spiral arm is composed of a connecting part and two propeller connecting parts which are integrally formed, the connecting part is positioned in the middle of the spiral arm, and the connecting parts of the two spiral arms are connected together through a connecting piece; every screw connecting portion all adopt Y type structure, the bottom of Y type structure with connecting portion integrated into one piece is located two forked branches of Y type structure are provided with screw and drive arrangement respectively, the screw bottom is provided with drive arrangement, drive arrangement installs Y type structure forked branch portion, by drive arrangement drives the screw action.
2. The pure electric manned vehicle of claim 1, characterized in that: the spiral arm adopts carbon fiber material to make, the connecting piece is pre-buried in the connecting portion, just the connecting piece adopts metal material to make.
3. The pure electric manned vehicle of claim 1, characterized in that: the propeller connecting part of the Y-shaped structure is of a hollow structure.
4. The pure electric manned vehicle of claim 1, characterized in that: the bottom of the Y-shaped structure of the propeller connecting part is provided with a battery bin, and a power supply battery is arranged in the battery bin and used for supplying power for the driving device.
5. The pure electric manned vehicle of claim 1, characterized in that: the top of the nacelle is embedded with a connecting frame, and the connecting frame is connected with the bottom of the connecting part of the spiral arm through a first embedded part arranged at the bottom of the connecting part.
6. The pure electric manned vehicle of claim 1, characterized in that: the nacelle adopts a semi-closed structure, handrails are arranged on two sides of a seat arranged in the nacelle, and the two handrails are movably connected with two sides of the seat.
7. The pure electric manned vehicle of claim 1, characterized in that: the shock absorption support comprises an underframe, a first connecting seat, a first connecting shaft, a lower support arm, a skid plate, a second connecting seat, a third connecting seat, an air shock absorber and a spring;
the top of the underframe is provided with a third embedded part used for being connected with the bottom of the pod, the underframe is provided with four support arms, two support arms positioned at the rear part of the underframe are of a reducing structure, and a connecting plate integrally formed with the reducing structure is arranged at the end part of the reducing structure; the reducing structure and the two support arms positioned at the front part of the underframe are arranged in a triangular shape, and the inner sides of the end parts of the two support arms at the front part are both provided with the first connecting seats; the front end of the middle part of the underframe is provided with two first connecting shafts;
the lower support arms are respectively arranged below the two support arms at the front end of the underframe, and the top end of each lower support arm is movably connected with the first connecting shaft; the bottom of each lower support arm is provided with the skid plate, the middle part of the skid plate is pre-embedded with the second connecting seat, the bottom of the lower support arm is coaxially connected with the second connecting seat through a second connecting shaft, and the second connecting shaft is provided with a limiting screw for limiting the front position and the rear position of the air damper;
the third connecting seat is arranged on the inner side of the lower part of the lower support arm, and a through hole is formed in the lower support arm at the third connecting seat; one end of the air damper is connected with the third connecting seat shaft, the other end of the air damper penetrates through the through hole to be connected with the first connecting seat shaft on the underframe, and a limit screw of the air damper is arranged on the shaft; and connecting wings which are integrally formed with the lower support arm are further arranged on two sides of the lower portion of the lower support arm, one end of the spring is connected with the connecting wings, and the other end of the spring is connected with the side wall of the second connecting seat on the skid plate.
8. The pure electric manned vehicle of claim 7, characterized in that: the shock absorption bracket also comprises a rear support rod and a connecting mechanism; the rear support rods are arranged in two numbers, one end of one rear support rod is connected with the bottom of the rear end of the underframe, one end of the other rear support rod is connected with the rear wall of the nacelle, the other ends of the two rear support rods are connected with the middle of the skid plate through the connecting mechanism, and the air shock absorber is further arranged between the connecting mechanism and the skid plate.
9. The pure electric manned vehicle of claim 8, characterized in that: the connecting mechanism comprises a first pair of vertical connecting plates, a pair of parallel frames, a second pair of vertical connecting plates and a support piece; the first pair of connecting vertical plates are embedded in the middle of the skid plate, three third connecting shafts are arranged on the first pair of connecting vertical plates, the third connecting shafts positioned in the middle of the first pair of connecting vertical plates are used for being connected with one end of the air damper, and the third connecting shafts positioned at two ends of the first pair of connecting vertical plates are respectively used for being connected with one ends of the two parallel frames; a fourth connecting shaft is arranged at two ends of one side of the second pair of connecting vertical plates respectively and is used for being connected with the other ends of the two parallel frames, and the fourth connecting shaft positioned at the upper part of the second pair of connecting vertical plates is also connected with the other end of the air damper; the supporting piece is arranged on the other side of the second pair of vertical connecting plates, the supporting piece is connected with a connecting plate between two support arms which are of a reducing structure and arranged at the rear part of the underframe, and the other ends of the two rear support rods are respectively connected with two ends of the supporting piece.
10. The pure electric manned vehicle of claim 9, characterized in that: the two parallel frames, the first pair of vertical connecting plates and the second pair of vertical connecting plates form a quadrilateral shock absorption structure, and the air shock absorber is positioned on the diagonal line of the quadrilateral shock absorber structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911260941.8A CN110803280A (en) | 2019-12-10 | 2019-12-10 | Pure electric manned vehicle |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911260941.8A CN110803280A (en) | 2019-12-10 | 2019-12-10 | Pure electric manned vehicle |
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| CN110803280A true CN110803280A (en) | 2020-02-18 |
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| CN201911260941.8A Pending CN110803280A (en) | 2019-12-10 | 2019-12-10 | Pure electric manned vehicle |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113568433A (en) * | 2021-08-12 | 2021-10-29 | 广东新创华科环保股份有限公司 | Multi-rotor unmanned aerial vehicle cluster measurement and control system and method |
| CN114013231A (en) * | 2021-11-25 | 2022-02-08 | 广东汇天航空航天科技有限公司 | Propeller fixing device and flight equipment |
| CN116119024A (en) * | 2023-04-17 | 2023-05-16 | 成都沃飞天驭科技有限公司 | Aircraft test platform and design method thereof |
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