CN218288111U - Anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle - Google Patents
Anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle Download PDFInfo
- Publication number
- CN218288111U CN218288111U CN202222289172.8U CN202222289172U CN218288111U CN 218288111 U CN218288111 U CN 218288111U CN 202222289172 U CN202222289172 U CN 202222289172U CN 218288111 U CN218288111 U CN 218288111U
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- rotor
- guide rail
- aerial vehicle
- unmanned aerial
- rail device
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- 238000005303 weighing Methods 0.000 claims abstract description 7
- 239000003638 chemical reducing agent Substances 0.000 claims description 15
- CPBQJMYROZQQJC-UHFFFAOYSA-N helium neon Chemical compound [He].[Ne] CPBQJMYROZQQJC-UHFFFAOYSA-N 0.000 claims description 10
- 238000005259 measurement Methods 0.000 claims description 5
- 230000009977 dual effect Effects 0.000 claims 1
- 230000005012 migration Effects 0.000 abstract 1
- 238000013508 migration Methods 0.000 abstract 1
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 abstract 1
- 238000000034 method Methods 0.000 description 5
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 3
- 239000000555 dodecyl gallate Substances 0.000 description 3
- 229910001069 Ti alloy Inorganic materials 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 2
- 239000000956 alloy Substances 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000000926 separation method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 210000003141 lower extremity Anatomy 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
- 230000001012 protector Effects 0.000 description 1
- 230000008054 signal transmission Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/02—Gyroplanes
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Abstract
The utility model provides a tandem bispin wing unmanned aerial vehicle prevents weighing down rotor guide rail device, including girder, rotor structure, rotor guide rail device, self-lock device, sensing device. The rotor guide rail device is a horizontal guide rail and a vertical guide rail which are arranged on the inner wall of the main beam, and a guide rail electromagnetic turning switch is arranged between the horizontal guide rail and the vertical guide rail. The rotor structure passes through rotor rail set and distributes in the front and back end of girder, the rotor pedestal mounting is on rotor rail set, along rotor rail set level or vertical migration to lock through self-lock device. The utility model discloses can not only use on unmanned aerial vehicle rotor trouble crash-proof, can also be in bad weather, under the extremely unfavorable environment of flight like typhoon, through adjustment rotor position change organism atress to reach the balance.
Description
Technical Field
The utility model relates to an unmanned aerial vehicle protector technical field specifically is a tandem type bispin wing unmanned aerial vehicle prevents weighing down rotor guide rail device.
Background
The front and the back of the fuselage of the tandem double-rotor unmanned helicopter are respectively provided with a rotor tower seat, two pairs of rotors are respectively arranged on the two tower seats, the two pairs of rotors are completely the same, but the rotating directions are opposite, and the reaction torques of the rotors can be balanced mutually. The helicopter of this type has the great advantage of a large longitudinal center of gravity range, so that the fuselage can be designed to be relatively large. It is suitable for middle-sized and large-sized helicopters.
Tandem formula two rotor unmanned aerial vehicle can lead to the organism to be unbalanced because of the atress is unbalanced under rotor fault state to the crash. The parachute is used in the traditional method, but in a low-altitude flight state, the parachute has a small descending buffering effect on the unmanned aerial vehicle, and the body falls to the ground and is greatly damaged.
SUMMERY OF THE UTILITY MODEL
The utility model discloses a solve prior art's problem, provide a tandem type bispin wing unmanned aerial vehicle prevents weighing down rotor guide rail device, can not only use on unmanned aerial vehicle rotor trouble prevents weighing down, can also be at bad weather, under the extremely unfavorable environment of flight like typhoon, through adjustment rotor position change organism atress to reach the balance.
The utility model provides a tandem type bispin wing unmanned aerial vehicle prevents weighing down rotor rail device, including girder, rotor structure, rotor rail device, self-lock device, sensing device.
The rotor guide rail device is a horizontal guide rail and a vertical guide rail which are arranged on the inner wall of the main beam, and a guide rail electromagnetic turning switch is arranged between the horizontal guide rail and the vertical guide rail.
The rotor wing structure is distributed at the front end and the rear end of the main beam through a rotor wing guide rail device, the rotor wing structure comprises a rotor wing base and a speed reducer fixed on the rotor wing base, the speed reducer is connected with a rotor wing through a rotating shaft, an engine is fixed in the middle of the main beam, and the engine is respectively connected with the speed reducer at the front end and the rear end of the main beam through a telescopic universal shaft; the rotor base is installed on the rotor guide rail device, moves horizontally or vertically along the rotor guide rail device and is locked through the self-locking device.
The improved rotary wing sensor is characterized in that the sensing device comprises a laser measuring system and a rotary wing rotating speed magnetic measuring sensor, and the sensing device is connected with a rotary wing rotating speed signal processor. The laser measuring system comprises a small helium-neon laser and an E312 type digital frequency meter, the digital frequency meter is fixed at the top of the rotor wing and forms a 45-degree angle with the rotating shaft, the helium-neon laser is installed on the main beam, and the angle of the helium-neon laser corresponds to that of the laser. The rotor rotation speed magnetic measurement sensor comprises two magnetic coils which are respectively arranged on two reducer boxes.
The further improvement is that the ball bearings arranged on the rotor wing guide rail and the rotor wing base are made of high-strength titanium alloy materials
In a further improvement, the rotor wing rotating speed signal processor is arranged inside the machine body
Further improved, the direction-changing switch of the rotor wing guide rail is an electromagnetic switch, and the separation and the connection are controlled by a flight control system.
Further improved, the rotor rotation speed magnetic measurement sensor needs to work by means of a sound wheel in the speed reducer.
A working method of a vertical double-rotor unmanned aerial vehicle anti-crash rotor guide rail device comprises the following steps:
1) When the signals collected by the sensing device are abnormal, judging the rotor wing structure fault at the abnormal collection point;
2) Starting a rotor wing guide rail system, closing a rotor wing base self-locking device at the side with the fault, and moving a rotor wing to the vicinity of an engine along a horizontal guide rail through the guide rail;
3) Starting a guide rail electromagnetic direction-changing switch, and moving the rotor wing downwards to the lower edge part of the main beam along the vertical guide rail;
4) The rotor self-locking device on one side of the normal flight state is closed, the rotor self-locking device moves to the position near the engine through the horizontal guide rail, and the middle self-locking device is opened.
The utility model discloses beneficial effect lies in:
1. rotor guide rail system can protect organism security in the at utmost, and this system can not only use on unmanned aerial vehicle rotor trouble crash-proof, can also be in bad weather, like under the extremely unfavorable environment of flight such as typhoon, through adjustment rotor position change organism atress to reach the balance.
2. The rotor structure staggers from top to bottom when concentrating, and prevents the interference that two rotors concentrated in the middle part of the body and took place.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without creative efforts.
FIG. 1 is an overall view of a tandem double-rotor main structure
FIG. 2 is an overall view of the rotor guide rail crash prevention system when the rotor fails to start
FIG. 3 is a schematic view of a guide rail electromagnetic direction-changing switch
In the figure, 1-main beam, 2-self-locking device, 3-speed reducer, 4-rotating shaft, 5-engine, 6-E312 type digital frequency meter, 7-small helium neon laser, 8-telescopic universal shaft, 9-guide rail, 10-rotor base and 11-guide rail electromagnetic change-direction switch.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
The utility model provides a tandem bispin wing unmanned aerial vehicle prevents weighing down rotor rail device, as shown in figure 1, including girder 1, rotor structure, rotor rail device, self-lock device 2, sensing device.
The rotor guide rail device is a guide rail 9 arranged on the inner wall of the main beam and comprises a horizontal guide rail and a vertical guide rail, and a guide rail electromagnetic direction changing switch 11 is arranged between the horizontal guide rail and the vertical guide rail.
The rotor wing structure is distributed at the front end and the rear end of the main beam through a rotor wing guide rail device, the rotor wing structure comprises a rotor wing base 10 and a speed reducer 3 fixed on the rotor wing base, the speed reducer 3 is connected with a rotor wing through a rotating shaft 4, an engine 5 is fixed in the middle of the main beam, and the engine 5 is respectively connected with the speed reducers 3 at the front end and the rear end of the main beam through a telescopic universal shaft 8; the rotor base is arranged on the rotor guide rail device, moves horizontally or vertically along the rotor guide rail device and is locked by the self-locking device 2.
The improved rotary wing sensor is characterized in that the sensing device comprises a laser measuring system and a rotary wing rotating speed magnetic measuring sensor, and the sensing device is connected with a rotary wing rotating speed signal processor. The laser measuring system comprises a small helium-neon laser 7 and an E312 type digital frequency meter 6, the digital frequency meter is fixed at the top of the rotor wing and forms a 45-degree angle with the rotating shaft, the helium-neon laser is arranged on the girder, and the angle of the helium-neon laser corresponds to that of the laser. The rotor rotation speed magnetic measurement sensor comprises two magnetic coils which are respectively arranged on two reducer boxes.
Further improved, the ball arranged on the rotor wing guide rail and the rotor wing base is made of high-strength titanium alloy material
In a further improvement, the rotor speed signal processor is arranged inside the machine body
The improved structure is characterized in that the rotor guide rail direction changing switch is an electromagnetic switch, and the separation and the connection are controlled by a flight control system.
Further improved, the rotor rotation speed magnetic measurement sensor needs to work by means of a sound wheel in the speed reducer.
When a rotor wing on one side of an unmanned aerial vehicle breaks down, the gravity center needs to be concentrated at the middle part for keeping the stress balance of the engine body, so that the guide rail devices are installed on the rotor wings on the two sides during design, and the rotor wings on the two sides move to the middle part of the engine body through the guide rails to achieve the stress balance.
As shown in fig. 2, the working method of the present invention is: when the unmanned aerial vehicle flies abnormally, judge the unusual type of flight and confirm the trouble unit, give rotor speed signal processor with signal transmission when two sets of rotor speed detecting system of unmanned aerial vehicle, when deciding rotor speed sudden drop or stall by the flight control system, then start the rotor guide rail system. The rotor base self-lock device of the side that breaks down closes, moves near the engine through the guide rail with the rotor along horizontal guide rail to start guide rail electromagnetism diversion switch and again with the rotor along vertical guide rail downwardly moving to the girder lower limb part, as shown in figure 3, this design purpose is for preventing two rotors from concentrating on the organism middle part and the interference that takes place.
The rotor self-lock device on one side of the normal flight state is closed, the rotor self-lock device moves to the position near the engine through the horizontal guide rail, and the middle self-lock device is opened.
The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, the above description of the apparatus embodiment is only a preferred embodiment of the present invention, and since it is substantially similar to the method embodiment, it is relatively simple to describe, and reference may be made to the partial description of the method embodiment for relevant points. The above description is only the specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto, and any person skilled in the art can easily think of the changes or substitutions within the technical scope of the present invention, without departing from the principle of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (4)
1. The utility model provides a tandem formula bispin wing unmanned aerial vehicle prevents weighing down rotor rail device which characterized in that: comprises a main beam, a rotor wing structure, a rotor wing guide rail device, a self-locking device and a sensing device;
the rotor wing guide rail device is a horizontal guide rail and a vertical guide rail which are arranged on the inner wall of the main beam, and a guide rail electromagnetic direction changing switch is arranged between the horizontal guide rail and the vertical guide rail;
the rotor wing structure is distributed at the front end and the rear end of the main beam through a rotor wing guide rail device, the rotor wing structure comprises a rotor wing base and a speed reducer fixed on the rotor wing base, the speed reducer is connected with a rotor wing through a rotating shaft, an engine is fixed in the middle of the main beam, and the engine is respectively connected with the speed reducer at the front end and the rear end of the main beam through a telescopic universal shaft; the rotor base is arranged on the rotor guide rail device, moves horizontally or vertically along the rotor guide rail device and is locked by the self-locking device.
2. The anti-crash rotor rail device of tandem twin rotor unmanned aerial vehicle of claim 1, wherein: the sensing device comprises a laser measuring system and a rotor rotation speed magnetic measuring sensor, and is connected with a rotor rotation speed signal processor.
3. The tandem dual rotor unmanned aerial vehicle anti-crash rotor rail device of claim 2, wherein: the laser measuring system comprises a helium-neon laser and a digital frequency meter, the digital frequency meter is fixed at the top of the rotor wing and forms a 45-degree angle with the rotating shaft, the helium-neon laser is installed on the girder, and the angle of the helium-neon laser corresponds to that of the laser.
4. The anti-crash rotor rail device of the tandem twin-rotor unmanned aerial vehicle of claim 2, wherein: the rotor rotation speed magnetic measurement sensor comprises two magnetic coils which are respectively arranged on two reducer boxes.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222289172.8U CN218288111U (en) | 2022-08-30 | 2022-08-30 | Anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle |
| PCT/CN2023/097484 WO2024045724A1 (en) | 2022-08-30 | 2023-05-31 | Anti-crash rotor wing guide rail device for tandem dual-rotor wing unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222289172.8U CN218288111U (en) | 2022-08-30 | 2022-08-30 | Anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218288111U true CN218288111U (en) | 2023-01-13 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222289172.8U Active CN218288111U (en) | 2022-08-30 | 2022-08-30 | Anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN218288111U (en) |
| WO (1) | WO2024045724A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024045724A1 (en) * | 2022-08-30 | 2024-03-07 | 南京壮大智能科技研究院有限公司 | Anti-crash rotor wing guide rail device for tandem dual-rotor wing unmanned aerial vehicle |
Family Cites Families (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102187063B1 (en) * | 2020-07-13 | 2020-12-04 | 김인헌 | Drone with Sub rotor |
| CN214690166U (en) * | 2021-03-01 | 2021-11-12 | 南昌航空大学 | Fixed wing unmanned aerial vehicle focus adjusting device can take off and land perpendicularly |
| CN114476045B (en) * | 2022-04-07 | 2022-08-02 | 西安工业大学 | Variable-centroid coaxial dual-rotor aircraft and control method thereof |
| CN218288111U (en) * | 2022-08-30 | 2023-01-13 | 南京壮大智能科技研究院有限公司 | Anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle |
| CN115503943A (en) * | 2022-08-30 | 2022-12-23 | 南京壮大智能科技研究院有限公司 | Working method of anti-crash rotor guide rail device of tandem type double-rotor unmanned aerial vehicle |
-
2022
- 2022-08-30 CN CN202222289172.8U patent/CN218288111U/en active Active
-
2023
- 2023-05-31 WO PCT/CN2023/097484 patent/WO2024045724A1/en unknown
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2024045724A1 (en) * | 2022-08-30 | 2024-03-07 | 南京壮大智能科技研究院有限公司 | Anti-crash rotor wing guide rail device for tandem dual-rotor wing unmanned aerial vehicle |
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| Publication number | Publication date |
|---|---|
| WO2024045724A1 (en) | 2024-03-07 |
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