CN107364572B - Fixed wing vector unmanned plane - Google Patents
Fixed wing vector unmanned plane Download PDFInfo
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- CN107364572B CN107364572B CN201710684839.5A CN201710684839A CN107364572B CN 107364572 B CN107364572 B CN 107364572B CN 201710684839 A CN201710684839 A CN 201710684839A CN 107364572 B CN107364572 B CN 107364572B
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- steering engine
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- vector
- fixed wing
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- 239000013598 vector Substances 0.000 title claims abstract description 43
- 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 14
- 230000003014 reinforcing effect Effects 0.000 claims description 8
- 239000003351 stiffener Substances 0.000 claims 1
- 238000000926 separation method Methods 0.000 abstract description 2
- 230000000875 corresponding effect Effects 0.000 description 6
- 230000007246 mechanism Effects 0.000 description 6
- 238000011161 development Methods 0.000 description 5
- 238000011160 research Methods 0.000 description 3
- WHXSMMKQMYFTQS-UHFFFAOYSA-N Lithium Chemical compound [Li] WHXSMMKQMYFTQS-UHFFFAOYSA-N 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 230000006870 function Effects 0.000 description 2
- 229910052744 lithium Inorganic materials 0.000 description 2
- 230000036544 posture Effects 0.000 description 2
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 241001330002 Bambuseae Species 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 239000011425 bamboo Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
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- 238000004519 manufacturing process Methods 0.000 description 1
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- 238000012544 monitoring process Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
Classifications
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- 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
- B64C27/28—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft with forward-propulsion propellers pivotable to act as lifting rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/32—Wings specially adapted for mounting power plant
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/24—Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U50/00—Propulsion; Power supply
- B64U50/10—Propulsion
- B64U50/19—Propulsion using electrically powered motors
Abstract
The invention provides a fixed wing vector unmanned aerial vehicle, which comprises a body, a steering engine, a flight control system, a propeller and a brushless motor, wherein the body consists of a wing plate and upper and lower body side plates, the front end of the body is fixedly provided with a motor fixing seat, a rotary support ring is arranged on the motor fixing seat through a rotary support, the rotary support ring rotates around the radial axis of the motor fixing seat, a cross rotary support is arranged in the rotary support ring, the brushless motor is arranged on the cross rotary support, the propeller is arranged on a brushless motor shaft, a left and right deflection steering engine and an upper and lower deflection steering engine are arranged in the body, each steering engine is respectively connected with the rotary support ring and the cross rotary support through a ball head pull rod to control the deflection of the axis of the propeller and the brushless motor, and the flight control system comprises a remote control ground remote controller, a remote control receiver on the body and an APM flight controller, and the flight control system is electrically connected with the left and right deflection steering engines and the upper and lower deflection steering engines. The vector of the invention can rotate adaptively, provide a timely pulling force for different actions, reduce the ground separation and grounding speed of the airplane, shorten the running distance of the airplane and save the power consumption.
Description
Technical Field
The invention belongs to unmanned plane technology, and particularly relates to a fixed wing vector unmanned plane.
Background
In 1903, the american Latt brothers successfully developed the first human-historic manned aircraft. The exploration of aircraft has also begun from this point. Later, due to the lag of science and technology and the restriction of theoretical knowledge, the research of the vector power aircraft has not been well developed. In recent years, with the progress of scientific and technological theory, the united states has made a great breakthrough in the aspect of vector thrust technology, and has long led to various countries in the world, and has become a country in the world where vector power aircrafts are successfully developed. The well-known vector powered aircraft in the united states is represented by F-35B.
The foreign vector power aircraft is a model version of a U.S. military aircraft F-35B, but the aircraft version F35-B only has strong ornamental value, has poor maneuverability and stability, has low practicability, and has a fuselage structure which is completely made of ultra-light materials and high cost.
The X-Hound developed at present by the 'Aoyi science and technology' of unmanned aerial vehicle enterprises in China is also a vector unmanned aerial vehicle, and consists of four rotors.
China is still in the primary stage of development in the aspect of vector power technology. Because the starting is late, the core technology is not mastered yet, and the learning and reference are required to be continued. In the face of the core technology, the problem is overcome, and the reverse research and development are needed, so that the innovation is more important.
With the development of aviation industry, the breakthroughs of scientific technology and aviation knowledge, various innovative aeromodelling such as spring bamboo shoots after rain are various. At present, the research on the aircraft, whether domestic or foreign, is mainly performed on the aspects of conventional fixed wings and multiaxis, such as: four-axis, six-axis, eight-axis and other aircrafts are marketed and commercialized, and compared with a multi-axis model airplane, the fixed wing model airplane has the advantages of long range, stable posture and high energy efficiency. The fixed wing model airplane is gradually a novel and stable flying product with various excellent performances in development, so that the development of the model airplane is brought into a new research field.
However, due to the above obstacles in design and manufacture, no vector unmanned aerial vehicle has yet appeared in the model airplane at present, and in particular, a fixed wing unmanned aerial vehicle with a vector that can be changed according to flight needs has restricted the improvement of the performance of the model airplane in this aspect.
Disclosure of Invention
Therefore, the invention provides the fixed wing vector unmanned aerial vehicle, which overcomes the defect that the traditional fixed wing unmanned aerial vehicle power motor only has the tension in a fixed direction, and the vector mechanism can self-adapt to the rotating power motor, so that the accurate tension in different directions in time is provided for the aircraft to finish different actions, the ground leaving and grounding speeds of the aircraft are reduced, the running distance of the aircraft is shortened, and the power consumption is saved.
The invention provides a fixed wing vector unmanned aerial vehicle, which comprises a machine body, a steering engine, a flight control system, a propeller and a brushless motor, and is characterized in that the machine body is composed of wing plates and upper and lower machine body side plates, a motor fixing seat is fixed at the front end of the machine body, a rotary support ring is arranged on the motor fixing seat through a rotary support, the rotary support ring rotates around the radial axis of the motor fixing seat, a cross rotary support is arranged in the rotary support ring, the brushless motor is arranged on the cross rotary, the propeller is arranged on a brushless motor shaft, a left and right deflection steering engine and an upper and lower deflection steering engine are arranged in the machine body, the left and right deflection steering engines and the upper and lower deflection steering engines are respectively connected with the rotary support ring and the cross rotary support through ball head pull rods, deflection of the propeller and the brushless motor shaft axis is controlled, the flight control system comprises a remote control ground remote controller, a remote control receiver on the machine body and an APM flight controller, and the flight control system is electrically connected with the left and right deflection steering engines and the upper and lower deflection steering engines.
The machine body is provided with a middle reinforcing plate for reinforcing the connection strength between the wing plate and the upper machine body side plate and the lower machine body side plate.
The motor fixing seat is a cross fork inserted and sleeved on the middle reinforcing plate and the upper and lower machine body side plates.
A connecting cross is arranged between the motor fixing seat and the rotating bracket to strengthen the fixing.
The rotary support is a pair of right-angle supports, and the connection between the right-angle supports and the rotary support ring is pin shaft connection.
The rotary support ring is also connected with the cross rotary support through a pin shaft.
The ball head pull rods of the left-right deflection steering engine are arranged on the left side and the right side of the upper side plate of the machine body, and the ball head pull rods of the up-down deflection steering engine are arranged on the upper side and the lower side of the wing plate.
Rudder plates on the wing plates are connected with corresponding steering engines.
The lower part of the machine body is provided with a sliding wheel.
The working principle of the invention is as follows:
after the propeller is started, the flight control system automatically adjusts the elevation angle of the propeller, provides forward and upward vector pulling force for the airframe, and the air flow difference on the upper side and the lower side of the wing plate generates lifting force for the airframe, so that the aircraft flies to the sky. When the steering is needed, the left-right deflection steering engine pulls the rotary support ring to rotate around the radial axis through the ball head pull rod, the vectors on the axes of the motor and the propeller rotate left or right, and when the steering is needed to ascend or descend, the up-down deflection steering engine pulls the cross rotary support to rotate around the axis through the ball head pull rod, and the vectors on the axes of the motor and the propeller tilt up or tilt down. When the left deflection steering engine, the right deflection steering engine and the up and down deflection steering engine act simultaneously, vectors on the axis of the motor and the propeller rotate within the range of the deflection cone angle allowed by the front according to the requirements, so that different postures and different actions are realized.
The fixed wing vector unmanned aerial vehicle provided by the invention is used as a new product of fixed wing development, and breaks through the characteristic that a fixed wing power motor only has a fixed tension direction. The unique design of the vector rotating mechanism ensures that the vector rotating system can realize synchronization for the aircraft to complete corresponding actions, and provides accurate pulling forces in different directions for the flight of the unmanned aerial vehicle. The annular lifting force of the airplane using the vector power technology is beneficial to reducing the ground separation and grounding speed of the airplane in the lifting direction and shortening the running distance of the airplane. For places with thinner air (such as Tibet plateau areas), a common aircraft needs great speed and power for making various series of flight actions, energy is wasted, and the aircraft with the new vector rotation mechanism can directly change the tension direction of the motor to make corresponding actions. The vector rotating system is combined with the novel machine body to carry out innovative design, so that the unmanned aerial vehicle has a double-mode flight function, namely, the trick flight of four ailerons and the high-speed flight of delta wings, the vector rotating mechanism controls the front, back, left and right rotation of the power motor to respectively replace the horizontal tail wing and the vertical tail wing of the aircraft under the four aileron mode, a series of actions of fixing the wings can be made, and two flight modes of the unmanned aerial vehicle are realized.
In a word, the invention overcomes the defect that the traditional fixed wing unmanned aerial vehicle power motor only has the tension in a fixed direction, and the vector mechanism can self-adapt to the rotating power motor, so that accurate tension in different directions in time is provided for the aircraft to finish different actions, the ground clearance and ground connection speed of the aircraft are reduced, the running distance of the aircraft is shortened, and the power consumption is saved.
Drawings
Fig. 1 is a schematic perspective view of the present invention.
Fig. 2 is an integrated perspective view of a brushless motor, a left-right deflection steering engine, an up-down deflection steering engine, a rotary support ring and a motor fixing seat.
Fig. 3 is an integrated perspective view of a brushless motor, a cross-shaped rotating bracket, a rotating support ring, a rotating support and a motor fixing seat.
Fig. 4 is a front view of the cross-shaped rotating bracket.
Fig. 5 is a left side view of the cross-shaped rotating bracket.
Fig. 6 is a top view of a cross-shaped rotating bracket.
Fig. 7 is a front view (partially cut-away) of the rotary support ring.
Fig. 8 is a left side view (partially cut-away) of the rotary support ring.
FIG. 9 is a diagram showing the connection relationship of the components of the present invention.
The vector deflection steering engine 1 and the vector deflection steering engine 2 in fig. 9 represent a left-right deflection steering engine and an up-down deflection steering engine, respectively.
The parts of the figures 1-8 are numbered as follows:
1-a propeller; 2-brushless motor; 3-rotating the support ring; 4-rotating the support; 5-connecting a cross; 6-an upper side plate of the machine body; 7-wing plates; 8-a lower side plate of the machine body; 9-wing rudder plates; 10-left and right deflection steering engines; 11-steering engine rocker arms; 12-a ball head pull rod; 13-a motor fixing seat; 14-an intermediate reinforcing plate; 15-universal ball head; 16-cross rotary support; 17-deflection steering engine up and down.
In fig. 1-3, the reference numeral ball-end tie represents the ball-end tie of all steering engines; the rotary support with the reference number 4 represents an upper rotary support and a lower rotary support; the steering engine rocker arm numbered 11 represents all steering engine rocker arms.
Detailed Description
The invention is further illustrated in the following with reference to the figures and examples.
The parts of the wing plate 7, the upper side plate 6, the lower side plate 8, and the middle reinforcing plate 14 constituting the body are substantially the same as those of the conventional mold machine, as are the rudder plates 9 on the wing plate. The modified place mainly is that the mounting positions of the left and right deflection steering engines 10 and the up and down deflection steering engines 17 are left on the machine body. Specifically, a left deflection steering engine and a right deflection steering engine are arranged in the middle of the machine body, and an up deflection steering engine and a down deflection steering engine are arranged in the middle and the front of the machine body. Of course, steering engines driving rudder plates, flight control systems not shown, etc. are installed on board similar to the case of a normal model airplane. The table is not fine here.
Because the upper and lower side plates of the machine body and the middle reinforcing plate form a cross shape, the motor fixing seat 13 is made into a corresponding cross sleeve structure, so that the motor fixing seat can be firmly inserted on the middle reinforcing plate and the upper and lower side plates of the machine body and is fixedly connected by bolts and the like.
The front end of the motor fixing seat is provided with a connecting cross 5 which is fixed with the motor fixing seat into a whole, and the upper and lower branches of the connecting cross bracket are longer, so that the rotary support 4 is convenient to install.
As described above, the rotary support is a part of two right-angle structures, one side of the part is fixed on the connecting cross, the other side is perforated, and the rotary support ring 3 is installed through the pin shaft. The rotary support ring is a circular ring, and the ring is provided with an upper pair of mounting holes, a lower pair of mounting holes, a left pair of mounting holes and a right pair of mounting holes. The pair of mounting holes corresponds to the rotary support, the pair of mounting holes corresponds to the cross rotary support 16, and the mounting mode of the cross rotary support and the rotary support ring is also a pin shaft. The brushless motor 2 is mounted on a cross-shaped rotating bracket. After the brushless motor is installed, the propeller 1 is installed on the brushless motor shaft. Therefore, the axes of the brushless motor and the propeller can deflect on the rotary supporting ring, and the vector direction change of the unmanned aerial vehicle head is formed.
The left and right deflection steering gears and the rotary support ring and the upper and lower deflection steering gears and the rotary support are connected through respective steering gear rocker arms 11 and ball head connecting rods 12. Of course, the two ends of the ball connecting rod are respectively provided with a universal ball 15.
The power utilization of the brushless motor, each steering engine, the flight control system and the like is uniformly provided by a lithium battery, the lithium battery and corresponding accessories, a remote control receiver and an APM flight controller in the flight control system are also installed on the machine body, and the flight control system is electrically connected with the left-right deflection steering engine and the upper-lower deflection steering engine, and comprises a sliding wheel and the like under the machine body and is the same as the existing fixed wing model airplane.
The APM flight controller is an existing model airplane controller, is provided with a fixed wing program, can realize self-stabilizing control of an airplane, reduces the accident rate of flight, can manually control and mobilize motor vector rotation for each steering engine through a ground remote controller, and rapidly and accurately makes tensile forces in different directions for each series of actions for the airplane. And the conversion between the delta wing mode and the four-pair wing mode is controlled by a two-section switch of the ground remote controller. The ground station has the main functions of realizing real-time monitoring and parameter adjustment on the whole flight condition of the fixed wing vector unmanned aerial vehicle through the data transmission module.
The program on the APM flight controller can be designed or adjusted by the user himself or by the delegated relevant developer according to specific needs.
The parameters of the fuselage, the brushless motor, the power specification size of the propeller and the like of the invention are determined according to textbooks of the existing aircraft design. The brushless motor of the example is a Langyu 2814/1450Kv motor, the propeller is a 9060 propeller with the diameter of 9 inches and the pitch of 6 inches, and the reduction ratio is 0.6. The shape and dimensions of the corresponding cross-shaped swivel mount and swivel support ring are shown in fig. 4-8.
The fixed wing vector unmanned aerial vehicle has stable flight attitude, high flight speed, timely and accurate vector adjustment, small turning radius and short take-off and taxiing distance, and obtains the praise of related mechanisms.
Claims (7)
1. The fixed wing vector unmanned aerial vehicle is provided with a body, a steering engine, a flight control system, a propeller and a brushless motor, and is characterized in that the body is composed of a wing plate and upper and lower body side plates, a motor fixing seat is fixed at the front end of the body, a rotary support ring is arranged on the motor fixing seat through a rotary support, the rotary support ring rotates around the radial axis of the motor fixing seat, a cross rotary support is arranged in the rotary support ring, the brushless motor is arranged on the cross rotary support, the propeller is arranged on a brushless motor shaft, a left and right deflection steering engine and an upper and lower deflection steering engine are arranged in the body, the left and right deflection steering engine and the upper and lower deflection steering engine are respectively connected with the rotary support ring and the cross rotary support through ball head pull rods, the deflection of the propeller and the axis of the brushless motor is controlled, the flight control system comprises a remote control ground remote controller, a remote control receiver on the body and an APM flight controller, and the flight control system are electrically connected with the left and right deflection steering engines and the upper and lower deflection steering engines;
the motor fixing seat is a cross fork plug and is sleeved on the middle reinforcing plate and the upper and lower machine body side plates;
the ball head pull rods of the left-right deflection steering engine are arranged on the left side and the right side of the upper side plate of the machine body, and the ball head pull rods of the up-down deflection steering engine are arranged on the upper side and the lower side of the wing plate.
2. The fixed wing vector drone of claim 1, wherein the fuselage has an intermediate stiffener.
3. The fixed wing vector drone of claim 1, wherein a connecting cross is provided between the motor mount and the rotating frame.
4. The fixed wing vector drone of claim 1, wherein the swivel mount is a pair of right angle mounts, the connection between the right angle mounts and the swivel support ring being a pin connection.
5. The fixed wing vector unmanned aerial vehicle of claim 1, wherein the rotary support ring is in pin connection with the cross rotary support.
6. The fixed wing vector drone of claim 1, wherein rudder plates on the wing plates have corresponding steering engine connections.
7. A fixed wing vector drone according to any one of claims 1 to 6, characterised in that the lower part of the fuselage is fitted with runner wheels.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710684839.5A CN107364572B (en) | 2017-08-11 | 2017-08-11 | Fixed wing vector unmanned plane |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710684839.5A CN107364572B (en) | 2017-08-11 | 2017-08-11 | Fixed wing vector unmanned plane |
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| Publication Number | Publication Date |
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| CN107364572A CN107364572A (en) | 2017-11-21 |
| CN107364572B true CN107364572B (en) | 2024-01-30 |
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| CN201710684839.5A Active CN107364572B (en) | 2017-08-11 | 2017-08-11 | Fixed wing vector unmanned plane |
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| CN108298071A (en) * | 2018-03-14 | 2018-07-20 | 长沙市云智航科技有限公司 | A kind of more rotor flying vehicles of manned duct |
| CN108639331A (en) * | 2018-06-29 | 2018-10-12 | 长沙市云智航科技有限公司 | One kind is verted double-rotor aerobat |
| CN109263868A (en) * | 2018-09-28 | 2019-01-25 | 上海歌尔泰克机器人有限公司 | A kind of unmanned plane rotor structure and unmanned plane during flying device |
| CN109606680A (en) * | 2018-12-26 | 2019-04-12 | 李昊泽 | The multi-modal aircraft of a kind of pair of hair full vector and flight system |
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