CN107187595B - VTOL fixed wing unmanned aerial vehicle with moment-changing screw - Google Patents
VTOL fixed wing unmanned aerial vehicle with moment-changing screw Download PDFInfo
- Publication number
- CN107187595B CN107187595B CN201710389959.2A CN201710389959A CN107187595B CN 107187595 B CN107187595 B CN 107187595B CN 201710389959 A CN201710389959 A CN 201710389959A CN 107187595 B CN107187595 B CN 107187595B
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- unmanned aerial
- aerial vehicle
- connecting rod
- tail
- hinged
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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
- B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
- B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
- B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C17/00—Aircraft stabilisation not otherwise provided for
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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
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- 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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U70/00—Launching, take-off or landing arrangements
- B64U70/80—Vertical take-off or landing, e.g. using rockets
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Toys (AREA)
Abstract
The invention relates to a vertical take-off and landing fixed wing unmanned aerial vehicle with variable-torque propellers, which comprises a body, wherein wings and an empennage are respectively fixedly arranged at the middle part and the tail part of the body, an engine is arranged at the head part of the body, two groups of variable-torque propellers are arranged on an output shaft of the engine, the rotating directions of the two groups of variable-torque propellers are opposite when the unmanned aerial vehicle runs, a buffering lifting mechanism is arranged on the empennage, and the buffering lifting mechanism comprises: one end of the connecting rod is hinged to the tail wing, the other end of the connecting rod is hinged to the roller, and the middle of the connecting rod is hinged to the buffer device fixedly arranged in the tail wing. Carry out VTOL, park through buffering take-off and landing mechanism, make its flight speed that has possessed fixed wing unmanned aerial vehicle on the one hand, on the other hand can take off and land perpendicularly like rotor unmanned aerial vehicle, hover, reduced unmanned aerial vehicle's dependence to place runway by a wide margin, unmanned aerial vehicle's fin all sets up the gyro wheel, the gyro wheel is at the flight in-process, is driven high-speed the rotation by the air current to make unmanned aerial vehicle have better stability at the gesture of flight in-process.
Description
The technical field is as follows:
the invention relates to the technical field of unmanned aerial vehicles, in particular to a vertical take-off and landing fixed-wing unmanned aerial vehicle with a variable-pitch propeller.
Background art:
with the change of times, although the popularity of piloted aircraft is not reduced, the piloted aircraft gradually exposes a plurality of disadvantages, such as too high cost of the aircraft, and the loss of the aircraft threatens the life of the pilot, so that the safety and technical requirements of the piloted aircraft are continuously improved, and the cost of the aircraft is also continuously improved. In order to reduce the cost of piloted airplanes and meet the development requirements of modern war and society, unmanned airplanes, called unmanned planes for short, are developed among countries in succession. In recent years, in global local wars, military forces use unmanned aerial vehicles to attack terrorists, reconnaissance and survey battlefields, test missiles as target drone, attract enemy fire as bait, and the like; in daily life, utilize unmanned aerial vehicle to shoot the photograph, meteorological reconnaissance begins to utilize unmanned aerial vehicle to transport express delivery etc. even gradually, and unmanned aerial vehicle is playing more and more important role.
The existing unmanned aerial vehicle has the following problems: 1. the fixed-wing unmanned aerial vehicle mostly needs to run and take off and land by means of a runway, so that the fixed-wing unmanned aerial vehicle has higher requirements on a field; 2. many rotor unmanned aerial vehicle can carry out VTOL, but flying speed is lower, and the condition that can not satisfy unmanned aerial vehicle fast flight and mobility are relatively poor.
Therefore, there is a need to design a more suitable VTOL fixed wing UAV with a variable-pitch propeller to solve the above problems.
The invention content is as follows:
the invention aims to provide a vertical take-off and landing fixed wing unmanned aerial vehicle with a variable-pitch propeller, which can perform vertical take-off and landing and has higher stability in flight.
In order to achieve the purpose, the invention adopts the following technical scheme:
the invention provides a vertical take-off and landing fixed wing unmanned aerial vehicle with variable-torque propellers, which comprises a body, wherein wings and an empennage are respectively and fixedly arranged at the middle part and the tail part of the body, an engine is arranged at the head part of the body, two groups of variable-torque propellers are arranged on an output shaft of the engine, the rotating directions of the two groups of variable-torque propellers are opposite when the unmanned aerial vehicle runs, a buffering lifting mechanism is arranged on the empennage, and the buffering lifting mechanism comprises: the connecting rod is hinged to the tail wing, one end of the connecting rod is hinged to the tail wing, the other end of the connecting rod is hinged to the roller, and the middle of the connecting rod is hinged to the buffer device fixedly installed in the tail wing.
The flight has three at least, and the contained angle between two adjacent flight is less than 180 degrees, and the flight symmetry that distributes in fuselage both sides sets up.
Under the restriction of the buffer device, the connecting rod rotates in the plane of the tail wing.
An included angle is formed between the connecting rod and the central shaft of the unmanned aerial vehicle body, so that the connecting rod can slide along with the roller when the unmanned aerial vehicle descends.
The idler wheel comprises two large wheels, a small wheel is clamped between the two large wheels, the two large wheels and the small wheel are coaxially arranged, and teeth are arranged on the outer edge of the small wheel.
The trailing edge of the wing is hinged with an aileron.
The tail wing is hinged with a tail vane.
The variable-pitch propeller adjusts a pitch angle through the variable-pitch shaft, the unmanned aerial vehicle adopts vector thrust generated by the variable-pitch propeller to control pitching and course postures of the unmanned aerial vehicle in a low-speed stage of take-off and landing, and the relative rotating speed of the propeller is adjusted through the differential mechanism to control the rolling posture of the unmanned aerial vehicle.
The vertical take-off and landing fixed wing unmanned aerial vehicle with the variable-pitch propeller has the beneficial effects that: carry out VTOL, park through buffering take-off and landing mechanism, make its flight speed that has possessed fixed wing unmanned aerial vehicle on the one hand, on the other hand can take off and land perpendicularly like rotor unmanned aerial vehicle, hover, reduced unmanned aerial vehicle's dependence to place runway by a wide margin, unmanned aerial vehicle's fin all sets up the gyro wheel, the gyro wheel is at the flight in-process, is driven high-speed the rotation by the air current to make unmanned aerial vehicle have better stability at the gesture of flight in-process.
Description of the drawings:
FIG. 1 is a schematic structural view of a VTOL fixed wing UAV with a variable-pitch propeller of the present invention;
FIG. 2 is a schematic view of the tail section;
FIG. 3 is a schematic structural view of a roller;
FIG. 4 is a schematic diagram of a state when the UAV is parked;
in the figure: 1-fuselage, 2-wing, 3-empennage, 4-roller, 5-engine, 6-variable-pitch propeller, 7-aileron, 8-tail rudder, 9-hinge mechanism, 10-connecting rod, 11-buffer device, 12-big wheel and 13-small wheel.
The specific implementation mode is as follows:
the present invention will be described in further detail with reference to examples.
According to the drawings of fig. 1, fig. 2 and fig. 4, a vertical take-off and landing fixed wing unmanned aerial vehicle with variable torque propellers comprises a body 1, wherein wings 2 and empennages 3 are fixedly arranged at the middle part and the tail part of the body 1 respectively, the empennages 3 are provided with at least three pieces, the included angle between every two adjacent empennages 3 is less than 180 degrees, the empennages 3 distributed at two sides of the body are symmetrically arranged, ailerons 7 are hinged at the rear edges of the wings 2, tail rudders 8 are hinged on the empennages 3, in the flight process, the ailerons 7 are adjusted to control the roll of the unmanned aerial vehicle, the pitch and the yaw of the unmanned aerial vehicle are controlled through the tail rudders 8, an engine 5 is arranged at the head part of the body 1, two groups of variable torque propellers 6 are arranged on an output shaft of the engine 5, the pitch angle of the variable torque propellers 6 is adjusted through adjusting the variable torque shaft, and the pitch and the course attitude, unmanned aerial vehicle operation, two sets of 6 direction of rotation of torque conversion screw are opposite, and then adjusts the relative speed control unmanned aerial vehicle's of screw 6 roll-over gesture through differential mechanism, be provided with the buffering landing gear on the fin 3, the buffering landing gear includes: the connecting rod 10 is hinged to the tail wing 3 at one end, the roller 1 is hinged to the other end of the connecting rod 10, the middle of the connecting rod 10 is hinged to the buffer device 11 fixedly installed in the tail wing 3, and the connecting rod 10 rotates in the plane of the tail wing 3 under the limit of the buffer device 11.
Form the contained angle between the center pin of connecting rod 10 and fuselage 1, make unmanned aerial vehicle connecting rod can follow when descending gyro wheel 4 slides, and when unmanned aerial vehicle takes off and lands, unmanned aerial vehicle is perpendicular to ground, and if the connecting rod is on a parallel with the center pin of fuselage, it is 4 slides to probably be difficult to drive gyro wheel, has certain inclination on the contrary, can let connecting rod 10 drive gyro wheel 4 slide subaerial easily, and then unmanned aerial vehicle jolts when reducing the descending.
As shown in fig. 3, the roller 4 includes two large wheels 12, a small wheel 13 is sandwiched between the two large wheels 12, the two large wheels 12 and the small wheel 13 are coaxially arranged, teeth are arranged on the outer edge of the small wheel 13, and when the unmanned aerial vehicle flies, the small wheel 13 is driven to rotate under the action of air flow, so as to drive the roller 4 to rotate.
The invention relates to a vertical take-off and landing fixed wing unmanned aerial vehicle with a variable-pitch propeller, which is used for one time, and is described in the following with the accompanying drawings:
when the unmanned aerial vehicle takes off: the engine 5 is started, the engine 5 rotates to generate strong downward airflow, the lift force of the unmanned aerial vehicle is gradually larger than gravity, meanwhile, the connecting rod 10 is drawn by the buffer device 11 and slowly approaches the tail wing 3 under the rolling of the roller 4 until the buffer device 11 is contracted to a minimum tension state, the engine 5 drives the torque-variable propeller 6 to rotate, and when the unmanned aerial vehicle leaves the ground, the downward airflow generated by the engine 5 drives the roller 4 to rotate, so that the unmanned aerial vehicle has higher stability;
in the flight process, the engine 5 is used for controlling the variable-torque propeller 6 to generate vector thrust, so that the unmanned aerial vehicle is changed from a vertical takeoff state to a parallel flight state, the ailerons 7 are operated to control the rolling of the unmanned aerial vehicle, the tail rudder 8 is operated to control the pitching and yawing of the unmanned aerial vehicle, and meanwhile, the rollers 4 rotate under the action of airflow, so that the unmanned aerial vehicle flies more stably;
when landing, control unmanned aerial vehicle through engine 5, make it hover aloft, reduce unmanned aerial vehicle's lift gradually, lift until unmanned aerial vehicle is less than gravity, unmanned aerial vehicle's gyro wheel 4 and ground contact, under the effect of the frictional force that gyro wheel 4 received, gyro wheel 4 drives pull rod 10 to the direction motion of keeping away from fin 3, simultaneously under buffer 11's effect, make gyro wheel 4's movement strength weaken, and then unmanned aerial vehicle's jolt when reducing the descending, close the engine, accomplish whole landing process.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting the same, and although the present invention is described in detail with reference to the above embodiments, those of ordinary skill in the art should understand that: modifications and equivalents may be made to the embodiments of the invention without departing from the spirit and scope of the invention, which is to be covered by the claims.
Claims (1)
1. The utility model provides a VTOL fixed wing unmanned aerial vehicle with moment-changing screw which characterized in that: including the fuselage, fuselage middle part and afterbody are equipped with wing and fin respectively admittedly, the engine is installed to the fuselage head, is equipped with two sets of torque conversion screws on the output shaft of engine unmanned aerial vehicle operation, and is two sets of torque conversion screw rotation opposite direction, be provided with the buffering mechanism of rising and falling on the fin, the buffering mechanism of rising and falling includes: one end of the connecting rod is hinged to the tail wing, the other end of the connecting rod is hinged to the roller, and the middle of the connecting rod is hinged to the buffer device fixedly arranged in the tail wing;
the number of the tail wings is at least three, the included angle between every two adjacent tail wings is less than 180 degrees, and the tail wings distributed on the two sides of the fuselage are symmetrically arranged;
under the limit of the buffer device, the connecting rod rotates in the plane of the tail wing;
an included angle is formed between the connecting rod and a central shaft of the unmanned aerial vehicle body, so that the connecting rod can slide along with the roller when the unmanned aerial vehicle lands;
the rolling wheels comprise two large wheels, a small wheel is clamped between the two large wheels, the two large wheels and the small wheel are coaxially arranged, and teeth are arranged on the outer edge of the small wheel;
the trailing edge of the wing is hinged with an aileron;
a tail rudder is hinged on the tail wing;
the variable-torque propeller adjusts a pitch angle through a variable-torque shaft, the unmanned aerial vehicle adopts vector thrust generated by the variable-torque propeller to control the pitching and course postures of the unmanned aerial vehicle in the low-speed stages of take-off and landing, and the relative rotating speed of the propeller is adjusted through a differential mechanism to control the rolling posture of the unmanned aerial vehicle;
when the unmanned aerial vehicle takes off, the connecting rod is drawn by the buffer device and slowly approaches the tail wing under the rolling of the roller until the buffer device is contracted to a minimum tension state; after the unmanned aerial vehicle leaves the ground, the rollers rotate under the action of airflow in the flying process, so that the unmanned aerial vehicle flies more stably; when landing, unmanned aerial vehicle's gyro wheel and ground contact, under the effect of the frictional force that the gyro wheel received, the gyro wheel drives the pull rod to the direction motion of keeping away from the fin, simultaneously under buffer's effect for the kinematic strength of gyro wheel weakens, and then reduces jolting of unmanned aerial vehicle when descending.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710389959.2A CN107187595B (en) | 2017-05-27 | 2017-05-27 | VTOL fixed wing unmanned aerial vehicle with moment-changing screw |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710389959.2A CN107187595B (en) | 2017-05-27 | 2017-05-27 | VTOL fixed wing unmanned aerial vehicle with moment-changing screw |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107187595A CN107187595A (en) | 2017-09-22 |
| CN107187595B true CN107187595B (en) | 2020-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710389959.2A Expired - Fee Related CN107187595B (en) | 2017-05-27 | 2017-05-27 | VTOL fixed wing unmanned aerial vehicle with moment-changing screw |
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| Country | Link |
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| CN (1) | CN107187595B (en) |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107985589B (en) * | 2017-10-18 | 2022-02-01 | 沈阳航空航天大学 | Take VTOL unmanned aerial vehicle of vector thrust duct engine |
| CN108545182A (en) * | 2018-03-09 | 2018-09-18 | 中国科学院长春光学精密机械与物理研究所 | A kind of VTOL fixed-wing unmanned plane |
| CN111216902B (en) * | 2020-03-11 | 2022-08-02 | 沈阳航空航天大学 | Energy efficiency optimization method suitable for electric propulsion system of electric aircraft |
| CN114348245B (en) * | 2022-03-14 | 2022-07-05 | 中国人民解放军空军工程大学 | Unmanned plane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2387762A (en) * | 1941-01-25 | 1945-10-30 | Lloyd H Leonard | Aircraft |
| US5062587A (en) * | 1990-07-27 | 1991-11-05 | Wernicke Kenneth G | Landing gear for a tail sitting airplane |
| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| CN103287576A (en) * | 2013-05-24 | 2013-09-11 | 北京航空航天大学 | Tailless layout single tail seat type vertical take-off and landing aircraft |
| CN205854492U (en) * | 2016-06-17 | 2017-01-04 | 北京航空航天大学 | A kind of dismountable tailstock formula VUAV |
-
2017
- 2017-05-27 CN CN201710389959.2A patent/CN107187595B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2387762A (en) * | 1941-01-25 | 1945-10-30 | Lloyd H Leonard | Aircraft |
| US5289994A (en) * | 1989-10-10 | 1994-03-01 | Juan Del Campo Aguilera | Equipment carrying remote controlled aircraft |
| US5062587A (en) * | 1990-07-27 | 1991-11-05 | Wernicke Kenneth G | Landing gear for a tail sitting airplane |
| CN103287576A (en) * | 2013-05-24 | 2013-09-11 | 北京航空航天大学 | Tailless layout single tail seat type vertical take-off and landing aircraft |
| CN205854492U (en) * | 2016-06-17 | 2017-01-04 | 北京航空航天大学 | A kind of dismountable tailstock formula VUAV |
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| Publication number | Publication date |
|---|---|
| CN107187595A (en) | 2017-09-22 |
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