CN107253527B - Composite fixed wing unmanned aerial vehicle capable of vertically taking off - Google Patents
Composite fixed wing unmanned aerial vehicle capable of vertically taking off Download PDFInfo
- Publication number
- CN107253527B CN107253527B CN201710315903.2A CN201710315903A CN107253527B CN 107253527 B CN107253527 B CN 107253527B CN 201710315903 A CN201710315903 A CN 201710315903A CN 107253527 B CN107253527 B CN 107253527B
- Authority
- CN
- China
- Prior art keywords
- power unit
- unmanned aerial
- aerial vehicle
- fixed wing
- wing unmanned
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/22—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Toys (AREA)
Abstract
The invention relates to a composite fixed wing unmanned aerial vehicle capable of vertically taking off, belonging to the technical field of unmanned aerial vehicles; a driving connecting mechanism and a signal receiving mechanism are arranged in the machine body; the two wings are symmetrically arranged on two sides of the fuselage; the wings are provided with power unit connecting rods; the front end and the rear end of the power unit connecting rod are respectively provided with two symmetrical power unit supporting rods; an upper power unit is arranged above the power unit supporting rod; a lower power unit is arranged below the power unit supporting rod; universal rotating shafts are arranged at the joints of the upper power unit, the lower power unit and the power unit supporting rod; the combined type aircraft wing aircraft has the advantages of reasonable structural design, convenience in operation, good flexibility, high stability, capability of vertically taking off and good taking-off stability, the fixed wings are in a composite form, the combined type power unit can select a combined form according to needs, the combined form is diversified, and the improvement of the flying stability is facilitated.
Description
Technical Field
The invention relates to a composite fixed wing unmanned aerial vehicle capable of vertically taking off, and belongs to the technical field of unmanned aerial vehicles.
Background
With the gradual deepening of Chinese reform and the rapid development of economic construction, the landform of each region is changed greatly. The existing aerial remote sensing technical means cannot meet the requirement of economic development. New remote sensing technologies serve increasingly evolving economic construction and cultural career. The technology of taking the unmanned aircraft as the aerial remote sensing platform is a novel application technology developed to meet the requirement.
The aerial photo of the unmanned aerial vehicle has the advantages of large scale, wide visual angle and the like, and at present, the unmanned aerial vehicle is widely applied to the fields of military reconnaissance, national ecological environment protection, mineral resource exploration, marine environment monitoring, land utilization investigation, water resource development, crop growth, natural disaster monitoring and assessment and the like, and has relatively wide market demand.
The unmanned aerial vehicle aerial photography uses an unmanned aerial vehicle as an aerial platform, uses airborne remote sensing equipment such as a high-resolution CCD digital camera, a light optical camera, an infrared scanner, a laser scanner, a magnetic measuring instrument and the like to acquire information, processes image information by using a computer, and makes the image according to certain precision requirements. The whole system has outstanding characteristics in the aspects of design and optimal combination, and is a novel application technology integrating high-altitude shooting, remote control, remote measuring technology, video image microwave transmission and computer image information processing.
The unmanned aerial vehicle is used for carrying out the small-area remote sensing aerial photography technology, and obvious effect and experience are obtained in practice. The micro aerial remote sensing technology with the unmanned aerial vehicle as the aerial remote sensing platform adapts to the requirements of national economic and cultural construction development, and provides an effective remote sensing technology service means for economic and cultural construction of small and medium-sized cities, particularly cities, towns, counties, villages and other areas. The remote sensing aerial photography technology has an important promotion effect on the development of the economy of China.
The existing fixed-wing vertical take-off and landing unmanned aerial vehicle is divided into three forms: the combined wing vertical take-off and landing scheme is based on a conventional fixed wing aircraft, a multi-shaft power unit is added, the aircraft flies in a multi-shaft mode in vertical take-off and landing and low-speed states, and upward tension is generated by a plurality of propellers to overcome gravity; and in a high-speed state, the aircraft flies in a fixed wing mode, the lift force is started through the wings to overcome the gravity, and the propeller with forward pulling force overcomes the aerodynamic resistance. Compared with other modes, the composite wing vertical take-off and landing scheme does not need an additional mechanism and is simple in structure, but the existing fixed wing unmanned aerial vehicle capable of taking off vertically is poor in stability and serious in shaking phenomenon when taking off.
Disclosure of Invention
The invention aims to provide a composite fixed wing unmanned aerial vehicle capable of vertically taking off, which has the advantages of simple structure, reasonable design and convenient use, and aims to overcome the defects and shortcomings of the prior art.
In order to achieve the purpose, the invention adopts the technical scheme that: the aircraft comprises an aircraft body, wings, a power unit connecting rod, an empennage, a power unit supporting rod, an upper power unit, a lower power unit, a driving connecting mechanism and a signal receiving mechanism; a driving connecting mechanism and a signal receiving mechanism are arranged in the machine body; the two wings are symmetrically arranged on two sides of the fuselage; the wings 2 are provided with power unit connecting rods; the front end and the rear end of the power unit connecting rod are respectively provided with two symmetrical power unit supporting rods; an upper power unit is arranged above the power unit supporting rod; a lower power unit is arranged below the power unit supporting rod; and universal rotating shafts are arranged at the joints of the upper power unit, the lower power unit and the power unit supporting rod.
Preferably, the power unit connecting rod is inserted at the bottom of the wing and fixedly connected with the wing.
Preferably, the power unit connecting rod and the wing form an included angle of 90 degrees.
Preferably, the power unit connecting rods and the wings are arranged at a certain included angle of-20 degrees to-20 degrees, and the angles of the unit connecting rods on the two sides are symmetrical.
Preferably, the tail end of the power unit connecting rod connected with the tail wing is perpendicular to the wing.
Preferably, the outer port of the power unit support rod is connected with the centers of the upper power unit and the lower power unit.
Preferably, the joints of the upper power unit and the lower power unit are provided with damping mechanisms.
Preferably, the upper power unit and the lower power unit are propellers, and the propellers are provided with outward-diffused grains.
Preferably, the empennage is trapezoidal, and the edges of the front end and the rear end are sharp-angled edges.
Preferably, the upper power unit and the lower power unit are aligned vertically.
Preferably, the upper power unit and the lower power unit are staggered up and down, and the edges of the upper propeller and the lower propeller are tangent.
The principle of the invention is as follows: the wings are in a composite form and diversified in form, the power units are in a combined form, the combined power units can be combined and matched at will to operate, the flight direction of the airplane can be changed through the combination of the power units in different forms, and the tail wings in a trapezoidal form and connected with the power unit connecting rods can reduce the wind resistance.
In the invention, the power unit connecting rod is fixedly connected with two ends of the tail wing, so that the integral stability is improved, the front end edge and the rear end edge of the tail wing are sharp corner edges, the resistance to wind can be effectively reduced, the upper power unit and the lower power unit which are in an up-and-down mode are adopted, the flexibility of takeoff and flight can be improved, and the joints of the upper power unit and the lower power unit are respectively provided with a universal rotating shaft, so that the direction can be changed at any angle, the direction can be randomly changed in the process of flight, the balance of takeoff can also be adjusted, the vibration is reduced, and the stability is improved; in addition, the power unit connecting rod is obliquely arranged in the horizontal direction, so that the power unit power-spreading area can be enlarged, and the takeoff stability can be improved.
After adopting the structure, the invention has the beneficial effects that: the composite fixed wing unmanned aerial vehicle capable of vertically taking off is reasonable in structural design, convenient to operate, good in flexibility, high in stability, capable of vertically taking off and good in taking-off stability, the fixed wings are in a composite form, the combined power unit can select a combined form according to needs, the combined form is diversified, and the stability of flight is improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic illustration of the upper and lower power units of the present invention;
FIG. 3 is a schematic view of a second embodiment of the present invention;
FIG. 4 is a schematic view of a third embodiment of the present invention;
description of reference numerals:
The unit 6, the lower power unit 7, the driving connection mechanism 8, the signal receiving mechanism 9 and the universal rotating shaft 10.
Detailed Description
The invention will be further described with reference to the accompanying drawings.
The first embodiment is as follows:
referring to fig. 1 and 2, the present embodiment includes a fuselage 1, a wing 2, a power unit connecting rod 3, a tail fin 4, a power unit supporting rod 5, an upper power unit 6, a lower power unit 7, a driving connection mechanism 8 and a signal receiving mechanism 9; a driving connecting mechanism 8 and a signal receiving mechanism 9 are arranged in the machine body 1; the two wings 2 are symmetrically arranged on two sides of the fuselage 1; the wings 2 are provided with power unit connecting rods 3; the front end and the rear end of the power unit connecting rod 3 are respectively provided with two symmetrical power unit supporting rods 5; an upper power unit 6 is arranged above the power unit support rod 5; a lower power unit 7 is arranged below the power unit support rod 5; the joints of the upper power unit 6, the lower power unit 7 and the power unit support rod 5 are provided with universal rotating shafts 10; the power unit connecting rod 3 is inserted at the bottom of the wing 2 and fixedly connected with the wing 2, and the power unit connecting rod 3 and the wing 2 form an included angle of 90 degrees; the tail end of the power unit connecting rod 3 connected with the tail wing 4 is vertical to the wing 2; the outer port of the power unit support rod 5 is connected with the centers of the upper power unit 6 and the lower power unit 7; the joints of the upper power unit 6 and the lower power unit 7 are provided with damping mechanisms; the upper power unit 6 and the lower power unit 7 are propellers, and the propellers are provided with outward-diffused grains; the tail wing 4 is trapezoidal, and the edges of the front end and the rear end are sharp corner edges; the upper power unit 6 and the lower power unit 7 are aligned up and down;
the second embodiment is as follows:
referring to fig. 3 and 2, the present embodiment differs from the first embodiment in that: the power unit connecting rods 3 and the wings 2 are arranged at a certain included angle, and the angles presented by the unit connecting rods 3 on the two sides are symmetrical;
the third concrete implementation mode:
referring to fig. 3 and 4, the present embodiment differs from the first embodiment in that: the power unit connecting rods 3 and the wings 2 are arranged at a certain included angle, the angles of the unit connecting rods 3 on the two sides are symmetrical, the upper power unit 6 and the lower power unit 7 are staggered up and down, and the edges of the upper propeller and the lower propeller are tangent; other structures and connection relations are the same as those of the first embodiment.
Principle of the above-described embodiment: the wings are in a composite form and diversified in form, the power units are in a combined form, the combined power units can be combined and matched at will to operate, the flight direction of the airplane can be changed through the combination of the power units in different forms, and the tail wings in a trapezoidal form and connected with the power unit connecting rods can reduce the wind resistance.
In the above specific embodiment, the power unit connecting rod 3 is fixedly connected with two ends of the tail fin 4, so that the overall stability is improved, the front end and the rear end of the tail fin 4 are sharp-angled edges, so that the resistance to wind can be effectively reduced, the upper power unit 6 and the lower power unit 7 which are in an up-and-down form are adopted, so that the flexibility of takeoff and flight can be improved, and the joints of the upper power unit 6 and the lower power unit 7 are provided with universal rotating shafts 10, so that the direction can be changed at any angle, the direction can be changed at will in the process of flight, the balance of takeoff can be adjusted, the vibration is reduced, the stability is improved, wherein the upper power unit 6 and the lower power unit 7 can be in a staggered form, so that the upper power unit 6 and the lower power unit 7 can act simultaneously, and only a single operation (the operation of the upper power unit 6 or; in addition, the power unit connecting rod 3 is obliquely arranged in the horizontal direction, so that the power unit power-spreading area can be enlarged, and the takeoff stability can be improved.
The vertical take-off composite fixed wing unmanned aerial vehicle has the advantages of reasonable structural design, convenient operation, good flexibility, high stability, vertical take-off and good take-off stability, the fixed wings are in a composite form, the combined power unit can select a combined form according to needs, the combined form is diversified, and the improvement of the flying stability is facilitated
The above description is only for the purpose of illustrating the technical solutions of the present invention and not for the purpose of limiting the same, and other modifications or equivalent substitutions made by those skilled in the art to the technical solutions of the present invention should be covered within the scope of the claims of the present invention without departing from the spirit and scope of the technical solutions of the present invention.
Claims (9)
1. The utility model provides a can take off compound fixed wing unmanned aerial vehicle perpendicularly which characterized in that: the aircraft comprises an aircraft body, wings, a power unit connecting rod, an empennage, a power unit supporting rod, an upper power unit, a lower power unit, a driving connecting mechanism and a signal receiving mechanism; a driving connecting mechanism and a signal receiving mechanism are arranged in the machine body; the two wings are symmetrically arranged on two sides of the fuselage; the wings are provided with power unit connecting rods; the front end and the rear end of the power unit connecting rod are respectively provided with two symmetrical power unit supporting rods; an upper power unit is arranged above the power unit supporting rod; a lower power unit is arranged below the power unit supporting rod; and universal rotating shafts are arranged at the joints of the upper power unit, the lower power unit and the power unit supporting rod.
2. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: the power unit connecting rod is inserted at the bottom of the wing and fixedly connected with the wing.
3. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: the power unit connecting rod and the wing form an included angle of 90 degrees.
4. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: the power unit connecting rods and the wings are arranged at a certain included angle which is-20 degrees to 20 degrees, and the angles of the power unit connecting rods on the two sides are symmetrical.
5. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: the tail end of the power unit connecting rod connected with the empennage is perpendicular to the wing.
6. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: the outer port of the power unit supporting rod is connected with the centers of the upper power unit and the lower power unit.
7. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: and the joints of the upper power unit and the lower power unit are provided with damping mechanisms.
8. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: the upper power unit and the lower power unit are propellers, and outward-diffused grains are arranged on the propellers.
9. The vertical takeoff composite fixed wing unmanned aerial vehicle as claimed in claim 1, wherein: the empennage is trapezoidal, and the edges of the front end and the rear end are sharp-angled edges.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710315903.2A CN107253527B (en) | 2017-05-08 | 2017-05-08 | Composite fixed wing unmanned aerial vehicle capable of vertically taking off |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710315903.2A CN107253527B (en) | 2017-05-08 | 2017-05-08 | Composite fixed wing unmanned aerial vehicle capable of vertically taking off |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107253527A CN107253527A (en) | 2017-10-17 |
| CN107253527B true CN107253527B (en) | 2020-10-09 |
Family
ID=60027372
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710315903.2A Active CN107253527B (en) | 2017-05-08 | 2017-05-08 | Composite fixed wing unmanned aerial vehicle capable of vertically taking off |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107253527B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111196346A (en) * | 2019-11-20 | 2020-05-26 | 湖北航天飞行器研究所 | Distributed electric propulsion tilt rotor unmanned aerial vehicle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2264951C1 (en) * | 2004-02-24 | 2005-11-27 | Дуров Дмитрий Сергеевич | Hydroconverti ground-effect craft |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN105984581A (en) * | 2015-02-01 | 2016-10-05 | 范磊 | Modularized compound multi-rotor hybrid power aircraft |
| CN206125423U (en) * | 2016-11-02 | 2017-04-26 | 北京航空航天大学 | VTOL fixed wing uavs with power device verts |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9623967B2 (en) * | 2014-02-01 | 2017-04-18 | Aero Machining, LLC | Tiltrotor unmanned aerial vehicle |
-
2017
- 2017-05-08 CN CN201710315903.2A patent/CN107253527B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2264951C1 (en) * | 2004-02-24 | 2005-11-27 | Дуров Дмитрий Сергеевич | Hydroconverti ground-effect craft |
| CN105984581A (en) * | 2015-02-01 | 2016-10-05 | 范磊 | Modularized compound multi-rotor hybrid power aircraft |
| CN204489181U (en) * | 2015-03-10 | 2015-07-22 | 广州天翔航空科技有限公司 | Variable motor angle four axle vertical takeoff and landing fixed-wing compound unmanned plane |
| CN206125423U (en) * | 2016-11-02 | 2017-04-26 | 北京航空航天大学 | VTOL fixed wing uavs with power device verts |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107253527A (en) | 2017-10-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN206273678U (en) | The unmanned plane that a kind of variable empennage is controlled with folded wing | |
| CN203294313U (en) | Police quadrotor type unmanned aerial vehicle | |
| CN204750564U (en) | Three rotor VTOL unmanned aerial vehicle on Y type | |
| CN108688803A (en) | It is a kind of can VTOL aircraft | |
| CN204452934U (en) | The double mode aircraft of rotor, fixed-wing | |
| CN205076045U (en) | Combined type aircraft of varistructure | |
| CN206012982U (en) | A kind of small-sized electric fixed-wing unmanned plane for oblique photograph | |
| Moschetta | The aerodynamics of micro air vehicles: technical challenges and scientific issues | |
| CN106828916A (en) | Unmanned vehicle | |
| CN208102309U (en) | Three-surface configuration VTOL general-purpose aircraft | |
| CN205998126U (en) | A kind of unmanned plane during flying system | |
| CN204979211U (en) | Unmanned aerial vehicle | |
| CN2868845Y (en) | Vertical launching-landing fixed-wing man-free special aircraft | |
| CN204279947U (en) | The unmanned prior-warning plane of a kind of novel long-range | |
| CN107253527B (en) | Composite fixed wing unmanned aerial vehicle capable of vertically taking off | |
| CN208134595U (en) | A kind of 20 feather weight long endurance unmanned aircraft of load | |
| CN206719540U (en) | Tilting rotor type VUAV based on Flying-wing | |
| CN206394880U (en) | Unmanned vehicle | |
| CN103863561A (en) | Vertical take-off and landing unmanned aerial vehicle with foldable aerofoils | |
| CN103803057B (en) | Row's wing sun power UAV aerodynamic layout structure | |
| CN202953178U (en) | Minitype electric unmanned helicopter aerial photo system based on proposed triple axel type cloud platform | |
| CN212313298U (en) | Small-sized solar unmanned aerial vehicle | |
| CN2772962Y (en) | Special aerobat with circular wing | |
| CN204368414U (en) | A kind of novel double-layer rotor wing unmanned aerial vehicle | |
| CN204473134U (en) | Arrow formula aircraft |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |