CN114506447A - Novel aerial survey unmanned aerial vehicle with tilting rotor - Google Patents
Novel aerial survey unmanned aerial vehicle with tilting rotor Download PDFInfo
- Publication number
- CN114506447A CN114506447A CN202210250412.5A CN202210250412A CN114506447A CN 114506447 A CN114506447 A CN 114506447A CN 202210250412 A CN202210250412 A CN 202210250412A CN 114506447 A CN114506447 A CN 114506447A
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- rotor
- unmanned aerial
- aerial vehicle
- novel
- survey unmanned
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- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 4
- 230000005540 biological transmission Effects 0.000 abstract 1
- 238000013507 mapping Methods 0.000 description 9
- 230000007774 longterm Effects 0.000 description 3
- 230000009194 climbing Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000012876 topography Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
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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
- B64C25/02—Undercarriages
- B64C25/04—Arrangement or disposition on aircraft
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/52—Tilting of rotor bodily relative to fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
- B64C29/02—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis vertical when grounded
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention discloses a novel aerial survey unmanned aerial vehicle with tilting rotors, which comprises a body, wherein a rotor shaft is arranged on the body, the rotor shaft is provided with the tilting rotors, the rotors are provided with propellers, the propellers are propellers with five blades, the cutting angles of the blades are 45 degrees, a torsion shaft for torsion is arranged at one third of the front ends of the blades, a turboshaft engine is arranged on the rotor, the turboshaft engine adopts an electric transmission flight control mode, a rotor arm is arranged in the middle of the body, a front triangular landing gear is arranged on the body, trapezoids are arranged on the left side and the right side of the bottom of the body, and hanging points for hanging observation equipment are arranged on the trapezoids, so that the range, the flight time and the load of the unmanned aerial vehicle are effectively increased under the condition that the weight of the unmanned aerial vehicle is not increased greatly, meanwhile, the requirement on a take-off and landing site can be reduced through the front triangular undercarriage.
Description
Technical Field
The invention relates to the technical field of aerial survey unmanned aerial vehicles, in particular to a novel aerial survey unmanned aerial vehicle with a tilting rotor wing.
Background
The existing aerial survey unmanned aerial vehicle in the market is roughly divided into a fixed wing type and a rotor wing type. Fixed wing unmanned aerial vehicle, it is fast, long-term on the fly, carry heavily, the observation device that can carry is many, but, when the aviation survey and drawing of complicated topography, fixed wing aerial survey unmanned aerial vehicle's take off condition requirement is very strict. Large fixed-wing aerial drones must take off at airports with horizontal runways. Although a small-sized fixed wing unmanned aerial vehicle can launch by installing an unmanned aerial vehicle launching guide rail on a vehicle, the launching can be free from the limitation of a site, the load capacity of the small-sized fixed wing unmanned aerial vehicle is greatly reduced, the cruising radius of the vehicle-mounted launching unmanned aerial vehicle is not more than 5 kilometers, the load is not more than 5 kilograms, advanced large-scale observation equipment cannot be carried, and simple equipment can only be carried. The requirements of multi-angle and multi-technology aerial survey cannot be met. Still another is exactly rotor unmanned aerial vehicle, and rotor unmanned aerial vehicle is with low costs, controls simply, and what is most important is that take off to land does not receive the place restriction and restraint. However, the load, the cruise radius and the cruise time of the rotor-wing drone are greatly reduced compared with those of a fixed wing, and the high-technology aviation mapping operation cannot be implemented. Therefore, whether fixed wing or rotor wing, there are many places where it is limited.
Disclosure of Invention
The invention aims to solve the technical problems in the prior art and provides a novel aerial surveying unmanned aerial vehicle with a tilting rotor wing.
In order to achieve the purpose, the technical scheme provided by the invention is as follows: the utility model provides a novel aerial survey unmanned aerial vehicle of rotor verts, includes the fuselage body, be provided with the rotor shaft on the fuselage body, the epaxial rotor that can vert that is provided with of rotor, be provided with the screw on the rotor, the screw is the screw of five paddles, the corner cut of paddle is 45, the third department of paddle front end is provided with and is used for torsional torsion shaft, be provided with the turboshaft engine on the rotor, the turboshaft engine adopts the control mode of teleflight control, fuselage body middle part is provided with the rotor arm, be provided with preceding triangle undercarriage on the fuselage body, fuselage body bottom left and right sides all is provided with trapezoidal stores pylon, be provided with the carry point that can be used to carry observation equipment on the trapezoidal stores pylon.
Preferably, the tail of the machine body is provided with a tail which comprises a horizontal tail, and vertical tails are arranged at two ends of the horizontal tail.
Preferably, the trapezoidal hanging rack is connected with the machine body through a supporting frame, and the number of the hanging points is four.
Preferably, the twist angle of the rotor shaft is from minus 3 degrees to plus 92 degrees.
Preferably, the front triangular undercarriage comprises an undercarriage arranged at the front part of the body and two undercarriages arranged at the rear part of the body, and tires are arranged on the undercarriage.
The invention has the beneficial effects that:
1. the invention adopts the design of the tilt rotor wing, when the angle of the rotor wing is 90 degrees, the rotor wing can vertically take off and land, and when the rotor wing is in a horizontal position state, the rotor wing becomes a fixed wing aircraft. The capacity of the aircraft during long-term flight can enlarge the area of an aerial survey area during one-time flight, and the efficiency is higher. When the rotor is the vertical position state, rotor unmanned aerial vehicle has just possessed the ability of hovering in the air. Like this, its observation equipment of carrying on just can carry out long-time single observation to certain survey and drawing region, for fixed wing aerial survey unmanned aerial vehicle, such surveying and drawing mode is more stable, accurate. Tiltrotor unmanned aerial vehicles have also inherited the large load capacity of fixed wing unmanned aerial vehicles.
2. The invention effectively increases the range, the time and the load of the unmanned aerial vehicle under the condition of small weight increase of the unmanned aerial vehicle, and simultaneously can reduce the requirements on the taking-off and landing site through the front triangular undercarriage.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
FIG. 1 is a side view of the fuselage of the present invention;
FIG. 2 is a front view of the fuselage of the present invention;
figure 3 is a top view of a rotor upper blade of the present invention.
The attached drawings are marked as follows:
1-rotor arm 2-vertical tail 3-ladder type hanging rack 4-turboshaft engine 5-rotor shaft 6-tire 7-undercarriage 8-rotor 9-propeller.
Detailed Description
Reference will now be made in detail to the present preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings, wherein like reference numerals refer to like elements throughout.
In the description of the present invention, it should be understood that the orientation or positional relationship referred to in the description of the orientation, such as the upper, lower, front, rear, left, right, etc., is based on the orientation or positional relationship shown in the drawings, and is only for convenience of description and simplification of description, and does not indicate or imply that the device or element 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.
In the description of the present invention, the meaning of a plurality of means is one or more, the meaning of a plurality of means is two or more, and larger, smaller, larger, etc. are understood as excluding the number, and larger, smaller, inner, etc. are understood as including the number. If there is a description of first and second for the purpose of distinguishing technical features only, this is not to be understood as indicating or implying a relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of technical features indicated.
In the description of the present invention, unless otherwise specifically limited, terms such as set, installation, connection and the like should be understood in a broad sense, and those skilled in the art can reasonably determine the specific meanings of the above terms in the present invention by combining the specific contents of the technical solutions.
Referring to fig. 1 to 3, in a preferred embodiment of the present invention, a novel aerial survey unmanned aerial vehicle with tilt rotors comprises a fuselage body, wherein a rotor shaft 5 is arranged on the fuselage body, the cross section of the rotor shaft 5 is trapezoidal, a tilt rotor 8 is arranged on the rotor shaft 5, a propeller 9 is arranged on the rotor 8, five blades are arranged on the propeller 9, the cutting angle of each blade is 45 °, a torsion shaft for torsion is arranged at one third of the front end of each blade to change the flight attitude in a vertical flight mode, a scroll engine 4 is arranged on the rotor 8, the scroll engine 4 adopts an electric flight control mode, a rotor arm 1 is arranged in the middle of the fuselage body, a front triangle landing gear 7 is arranged on the fuselage body, and the front triangle landing gear 7 is configured to enable the unmanned aerial vehicle to play a better buffering role during landing, fuselage body bottom left and right sides all is provided with trapezoidal stores pylon 3, be provided with the mount point that can be used to mount observation equipment on the trapezoidal stores pylon 3.
The observation equipment such as a photoelectric pod, a DMC digital aerial camera and a LIDAR laser altimeter scanner can also be carried with an IMU/DGPS system to meet the requirements of different aerial measurement means in one-time flight.
The utility model discloses a novel rotor aerial survey unmanned aerial vehicle verts adopts two rotors 8 to add two vertical tails 2 and peaceful tail overall arrangement, adopts telex flight control system, and the biggest load 300 kilograms, the time of cruising 8 hours of the biggest, the distance of cruising 300 kilometers of the biggest, the radius of cruising 120 kilometers of the biggest, the 1500 meters of biggest flight height.
The invention adopts the design of the tilting rotor wing 8, when the angle of the rotor wing 8 is 90 degrees, the vertical take-off and landing can be realized, and when the rotor wing 8 is in a horizontal position state, the fixed wing aircraft can be formed. The capacity of the aircraft during long-term flight can enlarge the area of an aerial survey area during one-time flight, and the efficiency is higher. When rotor 8 is the vertical position state, rotor unmanned aerial vehicle has just possessed the ability of hovering in the air. Like this, its observation equipment of carrying on just can carry out long-time single observation to certain survey and drawing region, for fixed wing aerial survey unmanned aerial vehicle, such surveying and drawing mode is more stable, and is accurate, has still inherited fixed wing unmanned aerial vehicle's big load capacity.
Under the condition that the weight of the unmanned aerial vehicle is not increased greatly, the range, the time and the load of the unmanned aerial vehicle are effectively increased, and the requirements on a take-off and landing place are reduced.
As a preferred embodiment of the present invention, it may also have the following additional technical features:
in this embodiment, the tail is arranged at the tail of the fuselage body, the tail comprises a horizontal tail, vertical tails 2 are arranged at two ends of the horizontal tail, and the vertical tails 2 can be properly adjusted to determine the left and right steering of the aircraft in the fixed-wing flight mode.
In this embodiment, trapezoidal stores pylon 3 through the support frame with this body coupling of fuselage, the mount point is four, through the different observation device of mount point mount, can carry out multiple aerial survey task.
In this embodiment, the torsion angle of rotor shaft 5 is 3 degrees to positive 92 degrees negatively, and rotor shaft 5 can twist 1 of rotor arm to parallel with the fuselage to reduce the shared space of unmanned aerial vehicle.
In this embodiment, the nose-triangle-shaped landing gear 7 includes one landing gear 7 disposed at the front of the body and two landing gears 7 disposed at the rear of the body, and the tires 6 are disposed on the landing gear 7.
In the invention, 60% of the fuselage material of the fuselage body is made of composite material, and the small-sized turboshaft engine 4 is selected as the turboshaft engine 4. When a field detection task is executed, ground surveying and mapping personnel fly off in a field. When taking off, the rotor wing 8 is vertical at 90 degrees, and when climbing to approximately 30 meters away from the ground, the angle of the rotor wing 8 can be properly reduced to carry out flat flight and hover for aviation mapping operation. When fixed-point mapping is needed, the rotor 8 recovers a 90-degree state in the air, and a vertical climbing mode is selected for hovering in the air. That is, when the rotor 8 vertically climbs to more than 30 meters, the rotor shaft 5 can selectively change the angle to correspond to different flight modes. When the rotor shaft 5 is close to 90 degrees, the unmanned plane can be changed into a fixed-wing unmanned plane driven by the turboshaft engine 4 from a rotorcraft, the flying speed is maximum, and the range can be greatly increased.
When observing the operation, the surveying and mapping equipment who carries under trapezoidal stores pylon 3 just can carry out corresponding survey and mapping operation, for example three-dimensional topography survey and mapping, infrared survey and mapping, three-dimensional survey and mapping of high altitude live action etc..
In unmanned aerial vehicle's transportation way, whole rotor arm 1 twists reverse 90, and rotor shaft 5 twists reverse to the horizontal direction simultaneously, can rotate the fuselage upper end with huge rotor arm 1 like this, has reduced the required space of rotor arm 1 greatly, has made things convenient for the transportation more.
The above additional technical features can be freely combined and used in superposition by those skilled in the art without conflict.
The above description is only a preferred embodiment of the present invention, and the technical solutions that achieve the objects of the present invention by basically the same means are all within the protection scope of the present invention.
Claims (5)
1. The utility model provides a novel aerial survey unmanned aerial vehicle of rotor verts which characterized in that: the aircraft comprises a fuselage body, be provided with rotor shaft (5) on the fuselage body, be provided with rotor (8) that can vert on rotor shaft (5), be provided with screw (9) on rotor (8), five paddles have on screw (9), the corner cut of paddle is 45, the third department of paddle front end is provided with and is used for torsional torsion shaft, be provided with turboshaft engine (4) on rotor (8), turboshaft engine (4) adopt the control mode of telex flight control, fuselage body middle part is provided with rotor arm (1), undercarriage (7) of preceding triangle-shaped are provided with on the fuselage body, fuselage body bottom left and right sides all is provided with trapezoidal stores pylon (3), be provided with the carry point that can be used to carry observation equipment on trapezoidal stores pylon (3).
2. The novel aerial survey unmanned aerial vehicle of tiltrotor of claim 1, characterized in that: the tail of the machine body is provided with a machine tail which comprises a horizontal tail, and vertical tails (2) are arranged at two ends of the horizontal tail.
3. The novel aerial survey unmanned aerial vehicle of tiltrotor of claim 1, characterized in that: the ladder-shaped hanging rack (3) is connected with the machine body through a supporting frame, and the number of the hanging points is four.
4. The novel aerial survey unmanned aerial vehicle of tiltrotor of claim 1, characterized in that: the torsion angle of the rotor shaft (5) is from minus 3 degrees to plus 92 degrees.
5. The novel aerial survey unmanned aerial vehicle of tiltrotor of claim 1, characterized in that: the nose triangle landing gear (7) comprises a landing gear (7) arranged at the front part of the body and two landing gears (7) arranged at the rear part of the body, and tires (6) are arranged on the landing gears (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210250412.5A CN114506447A (en) | 2022-03-15 | 2022-03-15 | Novel aerial survey unmanned aerial vehicle with tilting rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210250412.5A CN114506447A (en) | 2022-03-15 | 2022-03-15 | Novel aerial survey unmanned aerial vehicle with tilting rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114506447A true CN114506447A (en) | 2022-05-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210250412.5A Pending CN114506447A (en) | 2022-03-15 | 2022-03-15 | Novel aerial survey unmanned aerial vehicle with tilting rotor |
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| CN (1) | CN114506447A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
| US7874513B1 (en) * | 2005-10-18 | 2011-01-25 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| CN107839875A (en) * | 2016-09-19 | 2018-03-27 | 贝尔直升机德事隆公司 | Wing for tiltrotor aircraft extends winglet |
| CN109533319A (en) * | 2018-12-07 | 2019-03-29 | 湖北航天飞行器研究所 | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
-
2022
- 2022-03-15 CN CN202210250412.5A patent/CN114506447A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7874513B1 (en) * | 2005-10-18 | 2011-01-25 | Smith Frick A | Apparatus and method for vertical take-off and landing aircraft |
| CN101875399A (en) * | 2009-10-30 | 2010-11-03 | 北京航空航天大学 | Tilt rotor aircraft adopting parallel coaxial dual rotors |
| CN107839875A (en) * | 2016-09-19 | 2018-03-27 | 贝尔直升机德事隆公司 | Wing for tiltrotor aircraft extends winglet |
| CN109533319A (en) * | 2018-12-07 | 2019-03-29 | 湖北航天飞行器研究所 | A kind of tilting rotor unmanned vehicle structural system with the overlap joint wing |
| CN113697097A (en) * | 2021-09-01 | 2021-11-26 | 中国航空研究院 | Overall pneumatic layout of fixed-wing aircraft with tiltable outer wings and rotary wings |
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