CN206187336U - Rectangle combination duct aircraft - Google Patents
Rectangle combination duct aircraft Download PDFInfo
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- CN206187336U CN206187336U CN201621287885.9U CN201621287885U CN206187336U CN 206187336 U CN206187336 U CN 206187336U CN 201621287885 U CN201621287885 U CN 201621287885U CN 206187336 U CN206187336 U CN 206187336U
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Abstract
The utility model relates to a rectangle combination duct aircraft, including the rectangle duct body (1), the rectangle duct body (1) symmetry is provided with duct (7) of two rows of the same figures, and follow in duct (7) and up set gradually reaction torque grid rudder (6), power device and power device support piece (2) down, the rectangle duct body (1) is located and still is provided with flight control equipment case (8) between two rows duct (7), the utility model discloses a rectangle combination duct aircraft simple structure, loading and unloading are convenient, can reduce aerodynamic drag and noise, and the flight safety is stable, can the quick response operation to left out balanced anti -twisting device, used the balance of the reaction torque grid rudder realization reaction torque of brand -new structure, thereby the balance has been more swift accurate, and has reduced the energy consumption of balanced needs, guaranteed that the aircraft satisfies the requirement of VTOL, smooth flight.
Description
Technical Field
The invention relates to an aircraft, belongs to the technical field of aircraft, and particularly relates to a rectangular combined duct aircraft.
Background
The unmanned aerial vehicle can be divided into a fixed wing type, a rotor type and a duct type according to functions, and the duct type aircraft is the current advanced aircraft.
Duct type aircraft is at present often mostly the monomer duct, only is applicable to low latitude low-speed flight, and is subject to single engine power and inertia scheduling problem, and monomer duct load capacity can't have great promotion, and the structure is comparatively complicated.
The ducted aircraft adopts the structure that propeller propellers (propellers for short) are arranged in a duct, the propellers rotate by the aid of power provided by an engine, thrust is generated to enable the aircraft to be separated from the ground, if a single group of propellers is adopted, the propellers can generate reverse torque when rotating at high speed, a balance anti-torque device is required to be arranged in the duct to offset the reverse torque, complexity of the system is increased, and aerodynamic efficiency in the duct is reduced. If the double-group propeller propellers are used for contrarotating and mutually offsetting self reaction torque, the propeller propulsion efficiency is reduced, and the depth size of the duct needs to be increased to meet the requirement of double-propeller installation space.
At present on the market duct aircraft is mostly single duct structure, mostly is to certain specific demand development, and task load, service environment etc. are comparatively single, can not realize the multipurpose, and a lot of structural design of current duct aircraft do not conform to the fluid design simultaneously, and not only air resistance is great during its flight, and the energy consumption is high, and because the friction that blocks of air, the noise is great, very easily damages after outside permanent use moreover.
Disclosure of Invention
Based on the technical problems, the invention provides a rectangular combined ducted aircraft, so that the technical problems of complex structure and high energy consumption of the conventional ducted aircraft are solved.
In order to solve the technical problems, the technical scheme adopted by the invention is as follows:
the utility model provides a rectangle combination duct aircraft, includes the rectangle duct body, and rectangle duct body symmetry is provided with two rows of the duct of the same number, has set gradually anti-torque grid rudder, power device and power device support piece from up down in the duct, the rectangle duct position still is provided with between two rows of ducts and flies the accuse equipment box.
Preferably, the grid slip flow rudder comprises a plurality of grid slip flow rudders which are arranged in sequence, the grid slip flow rudders are connected into a whole through a grid slip flow rudder connecting rod and realize synchronous linkage, and any one grid slip flow rudder is further connected with a driving servo steering engine.
Preferably, a plurality of grid slipstream rudders are provided with control plane rotating shafts at two ends, and the driving servo steering engine is connected to any one of the control plane rotating shafts at one end of the grid slipstream rudders.
Preferably, the number of the grid slipstream rudders is odd, and the driving servo steering engine is connected to one end of the grid slipstream rudders in the middle.
Preferably, the power device comprises a propeller and a motor or an oil engine connected with the propeller.
Preferably, the supporting piece comprises a cylinder seat and a plurality of supporting legs, a speed regulation switch assembly of a power device is arranged inside the cylinder seat, the power device is arranged at the lower end of the cylinder seat, and the supporting legs are uniformly distributed and clamped on the side face of the opening at the upper end of the duct.
Preferably, the number of the ducts is eight, and the two rows of ducts are symmetrically provided with four ducts respectively; in the four ducts in any row, the reactive torque grid rudders in the two ducts in the middle are transversely arranged, and the reactive torque grid rudders in the two ducts at the two ends are longitudinally arranged.
The rectangular combined ducted aircraft has the advantages of simple structure, convenience in loading and unloading, capability of reducing air resistance and noise, safety and stability in flight, capability of quickly responding to operation, omission of a balance anti-torsion device and realization of balance of anti-torsion by using the anti-torsion grid rudder with a brand-new structure, so that the aircraft is more quickly and accurately balanced, the energy consumption required by balance is reduced, and the aircraft is ensured to meet the requirements of vertical take-off and landing and stable flight.
Meanwhile, the invention also discloses a flight control system of the rectangular combined ducted aircraft, which comprises a ground control system and a flight control system inside the aircraft which are connected through a data chain,
wherein,
the ground control system comprises an air route planning system, a task planning system and a real-time monitoring system, wherein the air route planning system, the task planning system and the real-time monitoring system are all connected with a ground wireless data link terminal;
the flight control system comprises an anti-torque grid rudder servo system, a power device servo system and a main control system arranged in a flight control equipment box, wherein the main control system comprises an air pressure height sensor, an attitude sensor, a GPS positioning device, a wireless data chain terminal, a flight controller and a driving power supply, and the air pressure height sensor, the attitude sensor, the GPS positioning device, the wireless data chain terminal and the driving power supply are all connected with the flight controller.
The flight control system can accurately measure and control the flying height, speed, longitude and latitude, flying attitude and the like of the aircraft, can well monitor the flying state of the aircraft in real time, can accurately control and adjust the flying parameters of the aircraft, realizes the accurate positioning of the aircraft, and has quick operation response.
Finally, the invention also provides a flight control method of the rectangular combined ducted aircraft, which comprises a ground control method and a flight control method which are carried out simultaneously,
wherein,
the flight control method comprises the following steps: the GPS positioning device positions longitude and latitude coordinates and altitude of the aircraft and measures the flying speed of the aircraft during flying; the attitude sensor is used for measuring the flying attitude of the aircraft so as to meet the balance requirement during flying; the barometric altitude sensor can measure the flying barometric pressure and flying height of the aircraft, and the measured flying height and altitude height can be calibrated mutually through the flying controller;
the GPS positioning device, the attitude sensor and the air pressure height sensor transmit monitored data to the flight controller, the flight controller outputs corresponding signals to the anti-torque grid rudder servo system and the power device servo system after receiving the data, and the anti-torque grid rudder servo system and the power device servo system control the actions of the anti-torque grid rudder and the power device so as to realize the stable flight of the aircraft;
the ground control method comprises the following steps: the flight controller transmits the received data to a ground wireless data link terminal through a wireless data link terminal and a data link, and the ground wireless data link terminal transmits the data to a real-time monitoring system to realize data monitoring of the attitude, the speed, the altitude, the air pressure and the longitude and latitude of the aircraft;
meanwhile, the air route planning system can plan an air route, transmits air route data to the flight controller through a data chain, changes the flight air route through the aircraft control reaction torque grid rudder servo system and the power device servo system, and can adjust the speed, the height and the flight attitude of the aircraft; the task planning system can preset an aircraft task and set a specific flight task to realize flexible flight of the aircraft.
By the method, the invention can realize movement in any direction, is stable in operation during movement, is accurate in control, can monitor flight data and change flight paths at any time, and can ensure that the aircraft does not incline or jolt during flight or change the flight state due to continuous control, so that the balance is faster and more accurate, and the safety, stability and use of the aircraft are ensured.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an enlarged view of the structure at A in FIG. 1;
FIG. 3 is a front view of the present invention;
FIG. 4 is a side view of the present invention;
FIG. 5 is a top view of the present invention;
FIG. 6 is a diagrammatic view of the flight control system configuration of the present invention;
FIG. 7 is a schematic structural diagram of an exemplary embodiment;
the reference numerals in the drawings denote: 1. a rectangular duct body; 2. a power plant support; 3. a landing gear; 4. an electric motor or an oil engine; 5. a propeller thruster; 6. a reactive torque grid rudder; 7. a duct; 8. a flight control equipment box; 9. a cylindrical seat; 10. a support leg; 11. a grid slipstream rudder; 12. a control surface rotating shaft; 13. a grid slipstream rudder connecting rod; 14. and driving the servo steering engine.
Detailed Description
The invention will be further described with reference to the accompanying drawings. Embodiments of the present invention include, but are not limited to, the following examples.
As shown in fig. 1-5, the rectangular combined ducted aircraft comprises a rectangular ducted body 1, wherein two rows of ducts 7 with the same number are symmetrically arranged on the rectangular ducted body 1, a reactive torque grid rudder 6, a power device and a power device support 2 are sequentially arranged in the ducts 7 from bottom to top, and a flight control equipment box 8 is further arranged between the two rows of ducts 7 on the rectangular ducted body 1.
The rectangular duct body 1 is provided with symmetrical ducts, and the anti-torque grid rudder 6, the power device and the power device support 2 are arranged in the ducts, so that stable flight during flight can be ensured, the flight attitude can be conveniently adjusted, the regular appearance structure also conforms to the streamline design, the air resistance and noise can be reduced, the flight is safe and stable, meanwhile, the anti-torque grid rudder 6 is used for balancing the anti-torque of the aircraft, the balance of the aircraft is kept, the structure is simple, the structure of the aircraft is simplified, the energy consumption is lower, and the structure is simpler.
The lower end of the rectangular duct body 1 can be provided with an undercarriage 3 for safe landing and taking off of an aircraft.
To further explain the structure of the invention, the anti-torque grid rudder 6 comprises a plurality of grid slipstream rudders 11 which are sequentially arranged, the grid slipstream rudders 11 are connected into a whole through grid slipstream rudder connecting rods 13 to realize synchronous linkage, and any one grid slipstream rudder 11 is also connected with a driving servo steering engine 14. The grid slipstream rudder 6 is rotatably arranged in the duct 7 and is positioned at the lower end of the power device; the grid slipstream rudders 11 are connected into a whole through grid slipstream rudder connecting rods 13 and are synchronously linked, any one of the grid slipstream rudders 11 can be driven to rotate through driving the servo steering engine 14, the synchronous rotation of all the grid slipstream rudders 11 is realized, the downwash airflow direction passing through the grid slipstream rudders 11 is changed, the flight state of the aircraft can be changed, the reaction on the grid slipstream rudders 11 is adjusted through the deflection angle of the grid slipstream rudders, and the reaction torque of the aircraft caused by the rotation of the power device is balanced. The invention omits the existing balance anti-torque device, realizes the balance of the anti-torque by using the anti-torque grid rudder 6 with a brand new structure, thereby simplifying the structure of the aircraft, ensuring that the aircraft can quickly and accurately balance, realizing the rotation of the whole device by using one steering engine, reducing the energy consumption required by the balance, ensuring that the aircraft meets the requirements of vertical take-off and landing and stable flight, ensuring that the flight state is changed quickly, ensuring that the airflow flows smoothly and not influencing the normal flight.
Control surface rotating shafts 12 are arranged at two ends of the grid slipstream rudders 11, and the driving servo steering engine 14 is connected to the control surface rotating shaft 12 at one end of any one of the grid slipstream rudders 11. Through setting up control surface pivot 12 to can be with the rotatable grafting of whole reaction torque grid rudder 6 on the duct aircraft, and, drive servo steering wheel 14 is connected arbitrary one on the control surface pivot 12 of 11 one ends of grid slipstream rudder, thereby can set up drive servo steering wheel 14 inside the aircraft, avoid the steering wheel to expose and influence balance, utilize control surface pivot 12 to realize connecting also having made things convenient for the loading and unloading, increased the stability after 11 installation of grid slipstream rudder.
On the basis, the number of the grid slipstream rudders 11 is odd, and the driving servo steering engine 14 is connected to one end of the grid slipstream rudders 11 in the middle. In order to ensure that the grid slip flow rudders 6 can better realize balance faster when the balance reaction torque is adjusted, the grid slip flow rudders 11 are set to be odd number, and the driving servo steering engines 14 are connected to one ends of the grid slip flow rudders 11 in the middle, so that the number of the grid slip flow rudders 11 left and right of the grid slip flow rudders 11 connected with the driving servo steering engines 14 is the same, the acting force is uniform when the reaction torque is adjusted, the balance of the reaction torque can be better realized, the adjusting time and the angle are reduced, and the energy consumption is reduced.
As a further description of the present invention, the power device includes a propeller 5 and a motor or an oil engine 4 connected to the propeller 5. The propeller thruster 5 is driven by the motor or the oil engine 4 to rotate to generate downward washing airflow to provide power for the aircraft.
As a further explanation of the present invention, the supporting member 2 includes a cylindrical seat 9 and a plurality of supporting legs 10, a speed-adjusting switch assembly of a power device is disposed inside the cylindrical seat 9, the power device is disposed at the lower end of the cylindrical seat 9, and the plurality of supporting legs 10 are uniformly distributed and clamped on the side surface of the opening at the upper end of the duct 7. Design into inside hollow structure with cylinder seat 9, its inside cavity sets up the required power device speed governing switch subassembly of power device, the structure has been simplified, and through a plurality of stabilizer blades 10 evenly distributed and block with the power device chucking on 7 upper end opening sides of duct, make its loading and unloading convenient, and leave sufficient space between the stabilizer blade 10, can increase the required air current flow space of power device, make the aircraft flight more steady, can not appear cutting off, the problem that admits air is not smooth. When the power device adopts a motor, the speed regulating switch component of the power device is an electronic speed regulator and is used for switching on and switching off the motor and regulating the rotating speed of the motor; when the oil engine is adopted, the speed regulation switch component of the power device comprises a CDI igniter and an accelerator control servo steering engine, the CDI igniter is used for igniting the oil engine, the accelerator control servo steering engine controls the accelerator of the oil engine to regulate the rotating speed of the oil engine, and in order to guarantee the long-term use of the oil engine, the speed regulation switch component of the power device can also be arranged into an auxiliary oil tank for providing fuel for the oil engine, so that the sufficient fuel of the oil engine is guaranteed.
In order to better implement the invention, the number of the ducts 7 is eight, and the two rows of ducts 7 are symmetrically provided with four ducts respectively; in the four ducts 7 in any row, the reactive torque grid rudders 6 in the two ducts 7 in the middle are transversely arranged, and the reactive torque grid rudders 6 in the two ducts 7 at the two ends are longitudinally arranged. The ducts 7 are eight in total, four ducts in the middle of two rows are arranged transversely, the remaining four ducts are arranged longitudinally, so that the aircraft is controlled to move transversely through the anti-torque grid rudders 6 in the four ducts in the middle, the aircraft is controlled to move longitudinally through the anti-torque grid rudders 6 in the remaining four ducts, the aircraft is controlled to move in a plane in a combined manner, and the flight of the aircraft is controlled, and meanwhile, the anti-torque grid rudders 6 in the four ducts 7 arranged longitudinally cross and offset the anti-torque generated by the power device.
In order to better implement the present invention, as shown in fig. 6, this embodiment further discloses a flight control system of a rectangular combined ducted aircraft, which includes a ground control system and a flight control system inside the aircraft connected by a data chain,
wherein,
the ground control system comprises an air route planning system, a task planning system and a real-time monitoring system, wherein the air route planning system, the task planning system and the real-time monitoring system are all connected with a ground wireless data link terminal;
the flight control system comprises an anti-torque grid rudder servo system, a power device servo system and a main control system arranged in a flight control equipment box, wherein the main control system comprises an air pressure height sensor, an attitude sensor, a GPS positioning device, a wireless data chain terminal, a flight controller and a driving power supply, and the air pressure height sensor, the attitude sensor, the GPS positioning device, the wireless data chain terminal and the driving power supply are all connected with the flight controller.
Through above flight control system, the aircraft can accurate survey and control flying height, speed, longitude and latitude and flight gesture etc. real time monitoring aircraft flight state that can be fine to can accurate control and adjust aircraft flight parameter, realize the accurate location of aircraft, the operation response is quick.
Meanwhile, the embodiment also discloses a flight control method of the rectangular combined ducted aircraft, which comprises a ground control method and a flight control method which are carried out simultaneously,
wherein,
the flight control method comprises the following steps: the GPS positioning device positions longitude and latitude coordinates and altitude of the aircraft and measures the flying speed of the aircraft during flying; the attitude sensor is used for measuring the flying attitude of the aircraft so as to meet the balance requirement during flying; the barometric altitude sensor can measure the flying barometric pressure and flying height of the aircraft, and the measured flying height and altitude height can be calibrated mutually through the flying controller;
the GPS positioning device, the attitude sensor and the air pressure height sensor transmit monitored data to the flight controller, the flight controller outputs corresponding signals to the anti-torque grid rudder servo system and the power device servo system after receiving the data, and the anti-torque grid rudder servo system and the power device servo system control the actions of the anti-torque grid rudder and the power device so as to realize the stable flight of the aircraft;
the ground control method comprises the following steps: the flight controller transmits the received data to a ground wireless data link terminal through a wireless data link terminal and a data link, and the ground wireless data link terminal transmits the data to a real-time monitoring system to realize data monitoring of the attitude, the speed, the altitude, the air pressure and the longitude and latitude of the aircraft;
meanwhile, the air route planning system is used for planning an air route, transmitting air route data to the flight controller through a data chain, changing the flight air route through the aircraft control reaction torque grid rudder servo system and the power device servo system, and adjusting the speed, the height and the flight attitude of the aircraft; the task planning system is used for pre-formulating the aircraft task, formulating a specific flight task and realizing flexible flight of the aircraft.
By the method, the aircraft can move in any direction, stably runs during movement, is accurately controlled, can monitor flight data at any time and change flight paths, and can not incline or jolt during flight or change flight states due to continuous control, so that the aircraft is balanced more quickly and accurately, and the safety, stability and use of the aircraft are guaranteed.
The specific embodiment is as follows:
as shown in fig. 1-7, a rectangular combined ducted aircraft comprises a rectangular ducted body 1, wherein the rectangular ducted body 1 is symmetrically provided with two rows of ducts 7 with the same number, a reactive torque grid rudder 6, a power device and a power device support 2 are sequentially arranged in the ducts 7 from bottom to top, and a flight control equipment box 8 is further arranged between the two rows of ducts 7 in the rectangular ducted body 1; the anti-torque grid rudder 6 comprises odd grid slipstream rudders 11 which are sequentially arranged, the odd grid slipstream rudders 11 are connected into a whole through a grid slipstream rudder connecting rod 13 to realize synchronous linkage, and one end of the middle grid slipstream rudder 11 is also connected with a driving servo steering engine 14; control surface rotating shafts 12 are arranged at two ends of the grid slipstream rudders 11; the power device comprises a propeller thruster 5 and a motor connected with the propeller thruster 5; the supporting piece 2 comprises a cylinder seat 9 and four supporting legs 10, a speed regulating switch assembly of a power device is arranged in the cylinder seat 9, the power device is arranged at the lower end of the cylinder seat 9, and the four supporting legs 10 are uniformly distributed and clamped on the side surface of an opening at the upper end of the duct 7; the number of the ducts 7 is eight, and the two rows of ducts 7 are symmetrically provided with four ducts respectively; in the four ducts 7 in any row, the anti-torque grid rudders 6 in the two ducts 7 in the middle are transversely arranged, and the anti-torque grid rudders 6 in the two ducts 7 at the two ends are longitudinally arranged.
As shown in fig. 7, eight reactive torque lattice rudders 6 are arranged in the rectangular combined ducted aircraft, which are respectively denoted as 1#, 2#, 1#, 8#, and the length direction of the aircraft is set as an X axis, and the width direction is set as a Y axis; the 1#/2#/3#/4# reactive torque grid rudder is arranged along the X axial direction, the 5#/6#/7#/8# reactive torque grid rudder is arranged along the Y axial direction, wherein the 1# -4 # reactive torque grid rudder controls the rectangular combined ducted aircraft to move along the Y axial direction, the 5# -8 # reactive torque grid rudder controls the rectangular combined ducted aircraft to move along the X axial direction, and controls the opening and closing of the propeller thruster 5 and the motor and the speed regulation of the speed regulation switch component of the power device, so that the lifting of the rectangular combined ducted aircraft can be controlled, and the motion of the aircraft in a three-dimensional plane is realized by combining the three components; and the 1# reaction torque grid rudder and the 4# reaction torque grid rudder mutually offset the reaction torque generated by the propeller 5 with each other, and the 2# reaction torque grid rudder and the 3# reaction torque grid rudder mutually offset the reaction torque generated by the propeller 5 with each other.
The above description is an embodiment of the present invention. The specific parameters in the above embodiments and examples are only for the purpose of clearly illustrating the invention verification process of the inventor and are not intended to limit the scope of the invention, which is defined by the claims, and all equivalent structural changes made by using the contents of the specification and the drawings of the present invention should be covered by the scope of the present invention.
Claims (7)
1. The utility model provides a rectangle combination duct aircraft, its characterized in that includes the rectangle duct body (1), and the rectangle duct body (1) symmetry is provided with two rows duct (7) of the same number, has set gradually anti-torque grid rudder (6), power device and power device support piece (2) from up down in duct (7), the rectangle duct body (1) is located still to be provided with between two rows duct (7) and flies accuse equipment case (8).
2. The rectangular combined ducted aircraft according to claim 1, wherein the anti-torque grid rudder (6) comprises a plurality of grid slipstream rudders (11) arranged in sequence, the plurality of grid slipstream rudders (11) are connected into a whole through a grid slipstream rudder connecting rod (13) to realize synchronous linkage, and any one grid slipstream rudder (11) is further connected with a driving servo steering engine (14).
3. The rectangular combined ducted aircraft according to claim 2, wherein a control surface rotating shaft (12) is arranged at each of two ends of the plurality of grid slipstream rudders (11), and the driving servo steering engine (14) is connected to the control surface rotating shaft (12) at one end of any one of the grid slipstream rudders (11).
4. The rectangular combined ducted aircraft according to claim 2, wherein the number of the grid slipstream rudders (11) is odd, and the driving servo steering engine (14) is connected to one end of the grid slipstream rudders (11) in the middle.
5. The rectangular combination ducted aircraft according to claim 1, wherein said power means comprise propeller propellers (5) and electric or oil motors (4) connected to the propeller propellers (5).
6. The rectangular combined ducted aircraft according to claim 1, wherein the supporting member (2) comprises a cylindrical seat (9) and a plurality of supporting legs (10), a speed-regulating switch assembly of a power device is arranged inside the cylindrical seat (9), the power device is arranged at the lower end of the cylindrical seat (9), and the plurality of supporting legs (10) are uniformly distributed and clamped on the side of the opening at the upper end of the duct (7).
7. The rectangular combined ducted aircraft according to claim 1, wherein the number of the ducts (7) is eight, and each of the two rows of ducts (7) is symmetrically provided with four ducts; in the four ducts (7) in any row, the anti-torque grid rudders (6) in the two ducts (7) in the middle are transversely arranged, and the anti-torque grid rudders (6) in the two ducts (7) at the two ends are longitudinally arranged.
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| CN201621287885.9U CN206187336U (en) | 2016-11-29 | 2016-11-29 | Rectangle combination duct aircraft |
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| CN201621287885.9U CN206187336U (en) | 2016-11-29 | 2016-11-29 | Rectangle combination duct aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477036A (en) * | 2016-11-29 | 2017-03-08 | 四川特飞科技股份有限公司 | A kind of rectangle combination duct aircraft and its flight control system and method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106477036A (en) * | 2016-11-29 | 2017-03-08 | 四川特飞科技股份有限公司 | A kind of rectangle combination duct aircraft and its flight control system and method |
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