CN113911335A - Two-curtain driving energy-adjustable rotary wing aircraft with fixed wings - Google Patents
Two-curtain driving energy-adjustable rotary wing aircraft with fixed wings Download PDFInfo
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- CN113911335A CN113911335A CN202111364315.0A CN202111364315A CN113911335A CN 113911335 A CN113911335 A CN 113911335A CN 202111364315 A CN202111364315 A CN 202111364315A CN 113911335 A CN113911335 A CN 113911335A
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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
- B64C27/26—Compound rotorcraft, i.e. aircraft using in flight the features of both aeroplane and rotorcraft characterised by provision of fixed wings
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/08—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like adjustable
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention discloses a two-pull-curtain driving energy-adjustable rotary wing aircraft with fixed wings, which is characterized by comprising rotary curtain wings, rotating shafts, speed reducers, motors, an aircraft body frame and the fixed wings, wherein the two rotating shafts are symmetrically arranged at two sides of the aircraft body frame, the axial directions of the two rotating shafts are vertical to the longitudinal symmetrical plane of the aircraft, the two motors arranged on the aircraft body frame respectively drive the two rotating shafts to continuously rotate after being decelerated by the two speed reducers arranged on the aircraft body frame, the two rotary curtain wings are respectively and fixedly connected to the two rotating shafts, the rotary curtain wings comprise rotary frames, and curtain wings arranged in the rotating frame, wherein the curtain wings comprise a curtain wing frame and a soft curtain arranged on the curtain wing frame, a coil spring and a driving motor are also arranged in the curtain wing frame, used for controlling the expansion and contraction of the soft curtain, and a fixed wing is arranged on the frame of the machine body and used for generating lift force.
Description
Technical Field
The invention relates to the field of movable wing aircrafts and flying robots, in particular to a two-curtain driving energy-adjustable rotary wing aircraft with fixed wings.
Background
The flying mode of the aircraft comprises three flying types of a fixed wing, a rotor wing and a flapping wing, wherein the rotor wing and the flapping wing all belong to movable wings.
Flapping wing flight is a flight mode adopted by natural flying organisms, mainly utilizes the up-and-down flapping of double wings to simultaneously generate lift force and thrust, and is mainly characterized in that the functions of lifting, hovering and propelling are integrated, and meanwhile, the flapping wing flight has strong maneuverability and flexibility and is more suitable for executing flight bypassing obstacles and the like. For an aircraft in a small-size and low-speed flight state, the aircraft flies at a low Reynolds number, and the unsteady lift force generated by the flapping wings is much larger than the unsteady lift force of the fixed wings; from the thrust aspect, the flapping wing propulsion efficiency is higher than the propeller propulsion efficiency. At present, the research of the flapping wing air vehicle mainly focuses on simulating the flight attitude of flying organisms in the nature and designing various flapping wing mechanisms. However, the common problem of these flapping wing mechanisms is that the overall aerodynamic efficiency is low, even lower than that of the fixed wing micro-aircraft of the same scale. The main reason for the low overall efficiency of the flapping wing aircraft is that most of the existing researches simply imitate the appearance and flapping motion of wings of birds or insects, but the problems that the air resistance is reduced and unsteady aerodynamic force is generated by utilizing the change of the self posture and the structure of the wings in the process of flapping the flapping wings of flying organisms up and down are difficult to realize, and the generated problem of low aerodynamic efficiency seriously restricts the popularization and the application of the flapping wing aircraft.
Rotorcraft provides lift to an aircraft with the tension of a rotor (including a propeller), and the forward tension of the aircraft is derived from the horizontal component resulting from small angular deflections of the rotor vector. The attitude control and horizontal movement of the multi-rotor small aircraft which is developed rapidly at present are realized by differential tension of the multiple rotors. Rotorcraft are characterized by having vertical take-off and landing and hovering functions, and the ability to fly in relatively small areas. However, because the rotor of the rotorcraft is immobile relative to the central axis of the rotor, the rotorcraft has large advancing resistance, so that the rotorcraft has high energy consumption, low aerodynamic efficiency and difficult high-power long-endurance flight.
Disclosure of Invention
The invention aims to provide a double-pull-curtain driving energy-adjustable rotary wing aircraft with fixed wings, which remarkably reduces the flight resistance of flapping wing type and rotor wing type aircrafts, improves the aerodynamic efficiency and has larger thrust, so as to solve the problems in the prior art.
The invention discloses a two-pull-curtain driving energy-adjustable rotary wing aircraft with fixed wings, which is characterized by comprising rotary curtain wings, second speed reducers, motors, rotating shafts, a fuselage frame and the fixed wings, wherein the two rotating shafts are symmetrically arranged on two sides of the fuselage frame, the axial directions of the two rotating shafts are perpendicular to the longitudinal symmetrical plane of the aircraft, the two motors arranged on the fuselage frame respectively drive the two rotating shafts to continuously rotate after being decelerated by the two second speed reducers arranged on the fuselage frame, and the two rotary curtain wings are respectively and fixedly connected to the two rotating shafts; the rotary curtain wing comprises a rotary frame and a curtain wing arranged in the rotary frame, the curtain wing comprises a curtain wing frame and a soft curtain sleeved on the curtain wing frame, and a coil spring and a driving motor are also arranged in the curtain wing frame and used for controlling the expansion and contraction of the soft curtain; the fixed wing is arranged on the fuselage frame and used for generating lift force.
Furthermore, the rotating frame is provided with a central hole, a straight beam and a curtain wing mounting plate, the direction of the straight beam is parallel to the axis of the central hole, the straight beam is provided with a curtain wing mounting hole, the axis of the curtain wing mounting hole is orthogonal to the axis of the central hole, the curtain wing mounting plate is provided with a curtain wing fixing hole, and the axis of the curtain wing fixing hole is orthogonal to the axis of the central hole; the curtain wings are inserted into the curtain wing mounting holes; the rotating shaft is connected with the central hole and a second speed reducer arranged on the aircraft.
Further, the curtain wing frame is provided with a first coil spring mounting hole, a second coil spring mounting hole, a guide rail, a curtain wing mounting beam, a motor mounting hole, a rotating wheel shaft, a curtain wing fixing shaft, a first mounting plate, a second mounting plate and a connecting cross beam, the soft curtain is provided with a windward side and a leeward side, the guide rail is mounted on the first mounting plate and the second mounting plate, the rotating wheel shaft is inserted into the first mounting plate and the second mounting plate, the connecting cross beam is inserted into the first mounting plate and the second mounting plate, the curtain wing mounting beam is inserted into the guide rail and can slide, the driving motor is mounted on the motor mounting hole, and the coil springs are mounted on the first coil spring mounting hole and the second coil spring mounting hole.
Further, the aircraft further comprises an electric motor arranged on the aircraft, and an output shaft of the electric motor is installed in the second speed reducer input hole.
Further, the curtain wing is further provided with a first speed reducer, the rotating wheel shaft is installed on an output shaft of the first speed reducer, and an output shaft of the driving motor is installed in an input hole of the first speed reducer.
Further, the rotating frame further comprises at least one of an outer reinforcing curved beam and an inner reinforcing curved beam for reinforcing the strength of the rotating frame.
Further, the straight beam, the outer reinforcing curved beam and the inner reinforcing curved beam are all hollow structures;
and/or the presence of a gas in the gas,
the straight beam, the outer reinforcing curved beam and the inner reinforcing curved beam are made of engineering plastics;
and/or the presence of a gas in the gas,
the straight beam, the outer reinforcing curved beam and the inner reinforcing curved beam are made of carbon fiber materials.
Further, the straight beams are uniformly distributed in the circumferential direction of the central hole, and the number of the straight beams is more than 1; the curtain wing mounting holes are uniformly distributed on the straight beams in a straight line, and the number of the curtain wing mounting holes on each straight beam is more than 1; the number of coil springs in each wing frame is 2.
The technical scheme for realizing the aim of the invention is to provide a two-pull-curtain driving energy-adjustable rotary wing aircraft with fixed wings, which comprises rotary curtain wings, second speed reducers, motors, rotating shafts, an aircraft body frame and the fixed wings, wherein the two rotating shafts are symmetrically arranged at two sides of the aircraft body frame, the axial directions of the two rotating shafts are vertical to the longitudinal symmetrical plane of the aircraft, the two motors arranged on the aircraft body frame respectively drive the two rotating shafts to continuously rotate after being decelerated by the two second speed reducers arranged on the aircraft body frame, and the two rotary curtain wings are respectively and fixedly connected to the two rotating shafts; the rotary curtain wing comprises a rotary frame and a curtain wing arranged in the rotary frame, the curtain wing comprises a curtain wing frame and a soft curtain sleeved on the curtain wing frame, and a coil spring and a driving motor are also arranged in the curtain wing frame and used for controlling the expansion and contraction of the soft curtain; the fixed wing is arranged on the frame of the machine body and used for generating lift force, the rotating frame is provided with a center hole, a straight beam and a curtain wing mounting plate, the direction of the straight beam is parallel to the axis of the center hole, the straight beam is provided with a curtain wing mounting hole, the axis of the curtain wing mounting hole is orthogonal to the axis of the center hole, the curtain wing mounting plate is provided with a curtain wing fixing hole, and the axis of the curtain wing fixing hole is orthogonal to the axis of the center hole; the curtain wings are inserted in the curtain wing mounting holes; the curtain wing frame is provided with a first coil spring mounting hole, a second coil spring mounting hole, a guide rail, a curtain wing mounting beam, a motor mounting hole, a wheel shaft, a curtain wing fixing shaft, a first mounting plate, a second mounting plate and a connecting beam, the soft curtain is provided with a windward side and a leeward side, the guide rail is mounted on the first mounting plate and the second mounting plate, the wheel shaft is inserted in the first mounting plate and the second mounting plate, the connecting beam is inserted in the first mounting plate and the second mounting plate, the curtain wing mounting beam is inserted in the guide rail and can slide, the driving motor is mounted on the motor mounting hole, the coil springs are mounted on the first coil spring mounting hole and the second coil spring mounting hole, the motor output shaft is mounted in the second reducer input hole, and the curtain wing is also provided with the first reducer, the rotating wheel shaft is arranged on an output shaft of the first speed reducer, an output shaft of the driving motor is arranged in an input hole of the first speed reducer, the rotating frame further comprises at least one of an outer reinforcing curved beam and an inner reinforcing curved beam which are used for reinforcing the strength of the rotating frame, and the straight beam, the outer reinforcing curved beam and the inner reinforcing curved beam are all of hollow structures and made of light materials such as engineering plastics, carbon fibers and the like.
The working principle of the invention is as follows: when the motor starts to rotate in the forward direction, the rotating shaft is driven to rotate continuously after being decelerated by the reducer, the driving motor controls the working and resetting states of the curtain wings, when a pair of curtain wings rotate to the working position from the non-working position, the driving motor stops working, the coil spring stretches the soft curtain to the maximum area, the curtain wings are perpendicular to the airflow direction, the airflow directly acts on the front surfaces of the curtain wings to enable the soft curtain to obtain the maximum air driving force, the positive pressure of the airflow acting on the windward surface of the soft curtain can be decomposed into lifting force and pushing force, the working state is realized at the moment, and when the curtain wings rotate to the vertical direction from the horizontal direction, the driving motor starts to work, the rotating wheel shaft is driven to rotate, the soft curtain is contracted, and the airflow directly flows out of the curtain wing frame and returns to the resetting state; when the motor rotates reversely, the gas reverse thrust power generated by the rotary curtain wing device is opposite to that generated when the motor rotates forwardly. When the rotating speeds of the two motors are the same, the thrust generated by the rotating curtain wings on the left side and the right side are the same, so that the aircraft flies forward, and when the rotating speeds of the motors on the two sides are different, the thrust generated by the rotating curtain wings on the left side and the right side are different, so that the aircraft can realize the turning function.
Compared with the prior art, the invention has the following remarkable advantages:
1. according to the two-pull-curtain energy-adjustable rotary wing aircraft with the fixed wings, the curtain wings in the rotary curtain wings are set to rotate continuously, so that the advantage of continuous rotation of the rotor wing is kept, and the defect that flapping wings need to move back and forth is overcome.
2. According to the two-pull-curtain driving energy-adjustable rotary wing aircraft with the fixed wings, the soft curtain is switched between the working state and the reset state under the control of the driving motor and driven by the coil spring, and the two-pull-curtain driving energy-adjustable rotary wing aircraft with the fixed wings is simple in structure, high in control precision and good in reliability.
3. According to the two-pull-curtain energy-adjustable rotary wing aircraft with the fixed wings, the continuously rotating curtain wings are controlled by the motor to rotate relative to the central rotating shaft, so that the curtain wings move upwind in the largest area to obtain the largest aerodynamic force in the working state, and the upwind area of the curtain wings is variable in the working state, so that the driving energy is adjustable; and when the wing-shaped air flow type flapping wing aircraft is in a reset state, the air flow directly flows out of the curtain wing frame, so that the resistance is greatly reduced, the aim of improving the pneumatic efficiency is fulfilled, and the pneumatic efficiency is far higher than that of the existing rotor wing and flapping wing aircraft.
4. The two-pull-curtain driving energy-adjustable rotary wing aircraft with the fixed wings is provided with two symmetrical rotary curtain wings to generate thrust, the thrust is higher, and the driving energy of the rotary curtain wings at two sides is adjustable, so that the aircraft is convenient to steer and does not need a steering engine to steer; the fixed wing generates lift force, so that the energy is saved when the aircraft is in a flat flight state, the energy utilization efficiency is further improved, and the purpose of long endurance is achieved.
5. The two-curtain-pulling driving energy-adjustable rotary wing aircraft with the fixed wings is simple in structure, good in processing manufacturability and low in production cost.
Drawings
Fig. 1 is a schematic diagram of the overall structure of the two-curtain driving energy-adjustable rotary wing aircraft with fixed wings.
Fig. 2 is a detailed structural schematic diagram of the two-curtain driving energy-adjustable rotary wing aircraft with fixed wings.
Fig. 3 is a detailed structure diagram of the reset state of the rotary curtain wing of the two-pull-curtain driving energy-adjustable rotary wing aircraft with fixed wings.
Fig. 4 is a detailed structural diagram of the working state of the rotary curtain wing of the two-pull-curtain driving energy-adjustable rotary wing aircraft with fixed wings.
Fig. 5 is a schematic structural diagram of a rotating frame of the two-curtain driving energy-adjustable rotary wing aircraft with fixed wings according to the present invention.
Fig. 6 is a schematic structural view of a curtain wing frame of a two-curtain driving energy-adjustable rotary wing aircraft with fixed wings according to the present invention.
Fig. 7 is a schematic structural diagram of the soft curtain of the two-pull curtain driving energy adjustable rotary wing aircraft with fixed wings.
Detailed Description
The invention is further described below with reference to the accompanying drawings, but the invention is not limited in any way.
Example 1: with reference to fig. 1, 2, 3, 4, 5, 6 and 7, the high-voltage wire inspection unmanned aerial vehicle adopting the two-curtain-pull energy-adjustable rotary wing aircraft with fixed wings. The aircraft wing curtain comprises rotary curtain wings, second speed reducers 6, motors 7, rotating shafts 8, an aircraft body frame 10 and fixed wings 11, wherein the two rotating shafts 8 are symmetrically arranged on two sides of the aircraft body frame 10, the axial directions of the two rotating shafts 8 are perpendicular to the longitudinal symmetrical plane of an aircraft, the two motors 7 arranged on the aircraft body frame 10 respectively drive the two rotating shafts 8 to continuously rotate after being decelerated through the two second speed reducers 6 arranged on the aircraft body frame 10, and the two rotary curtain wings are respectively and fixedly connected to the two rotating shafts 8; the rotary curtain wing comprises a rotary frame 1 and a curtain wing arranged in the rotary frame 1, the curtain wing comprises a curtain wing frame 1 and a soft curtain 2 sleeved on the curtain wing frame 1, and a coil spring 3 and a driving motor 5 are also arranged in the curtain wing frame 1 and used for controlling the expansion and contraction of the soft curtain 2; the fixed wing 11 is arranged on the fuselage frame 10 and used for generating lift force; the rotating frame 9 is provided with a center hole 901, a straight beam 902 and a curtain wing mounting plate 904, the direction of the straight beam 902 is parallel to the axis of the center hole 901, the straight beam 902 is provided with a curtain wing mounting hole 903, the axis of the curtain wing mounting hole 903 is orthogonal to the axis of the center hole 901, the curtain wing mounting plate 904 is provided with a curtain wing fixing hole 905, and the axis of the curtain wing fixing hole 905 is orthogonal to the axis of the center hole 901; the curtain wings are inserted into the curtain wing mounting holes 903; the rotary shaft 8 is connected with a central hole 901 and a second speed reducer 6 arranged on an aircraft, a curtain wing frame 1 is provided with a first coil spring mounting hole 101, a second coil spring mounting hole 102, a guide rail 103, a curtain wing mounting beam 104, a motor mounting hole 105, a rotary shaft 106, a curtain wing fixing shaft 107, a first mounting plate 108, a second mounting plate 109 and a connecting cross beam 110, a soft curtain 2 is provided with a soft curtain windward side 201 and a soft curtain leeward side 202, the guide rail 103 is mounted on the first mounting plate 108 and the second mounting plate 109, the rotary shaft 106 is inserted in the first mounting plate 108 and the second mounting plate 109, the connecting cross beam 110 is inserted in the first mounting plate 108 and the second mounting plate 109, the curtain wing mounting beam 104 is inserted in the guide rail 103 and can slide, a driving motor 5 is mounted on the motor mounting hole 105, a coil spring 3 is mounted on the first coil spring mounting hole 101 and the second coil spring mounting hole 102, and further comprises a motor 7 arranged on the aircraft, an output shaft of the motor 7 is arranged in an input hole of the second speed reducer 6, the curtain wing is further provided with a first speed reducer 4, the rotating wheel shaft 106 is arranged on the output shaft of the first speed reducer 4, an output shaft of the driving motor 5 is arranged in the input hole of the first speed reducer 4, the rotating frame 9 further comprises at least one of an outer reinforcing curved beam 906 and an inner reinforcing curved beam 907 for reinforcing the strength of the rotating frame 9, and the straight beam 902, the outer reinforcing curved beam 906 and the inner reinforcing curved beam 907 are all of a hollow structure and are made of engineering plastics, carbon fibers and the like. After the high-voltage wire inspection unmanned aerial vehicle adopts the two-pull-curtain driving energy-adjustable rotary wing aircraft with the fixed wings, the rotary wing aircraft can complete various detection and photographing works due to small resistance and high pneumatic efficiency of the rotary curtain wings, and compared with the rotary wing unmanned aerial vehicle, after carrying the same working load of photographic equipment and the like, the flight time is increased by 20 percent, so that longer flight time work is realized.
Example 2: with reference to fig. 1, 2, 3, 4, 5, 6 and 7, the unmanned aerial vehicle special for fire extinguishing in high-rise buildings adopts a two-curtain-pull driving energy-adjustable rotary wing aircraft with fixed wings. The aircraft wing curtain comprises rotary curtain wings, second speed reducers 6, motors 7, rotating shafts 8, an aircraft body frame 10 and fixed wings 11, wherein the two rotating shafts 8 are symmetrically arranged on two sides of the aircraft body frame 10, the axial directions of the two rotating shafts 8 are perpendicular to the longitudinal symmetrical plane of an aircraft, the two motors 7 arranged on the aircraft body frame 10 respectively drive the two rotating shafts 8 to continuously rotate after being decelerated through the two second speed reducers 6 arranged on the aircraft body frame 10, and the two rotary curtain wings are respectively and fixedly connected to the two rotating shafts 8; the rotary curtain wing comprises a rotary frame 1 and a curtain wing arranged in the rotary frame 1, the curtain wing comprises a curtain wing frame 1 and a soft curtain 2 sleeved on the curtain wing frame 1, and a coil spring 3 and a driving motor 5 are also arranged in the curtain wing frame 1 and used for controlling the expansion and contraction of the soft curtain 2; the fixed wing 11 is arranged on the fuselage frame 10 and used for generating lift force; the rotating frame 9 is provided with a center hole 901, a straight beam 902 and a curtain wing mounting plate 904, the direction of the straight beam 902 is parallel to the axis of the center hole 901, the straight beam 902 is provided with a curtain wing mounting hole 903, the axis of the curtain wing mounting hole 903 is orthogonal to the axis of the center hole 901, the curtain wing mounting plate 904 is provided with a curtain wing fixing hole 905, and the axis of the curtain wing fixing hole 905 is orthogonal to the axis of the center hole 901; the curtain wings are inserted into the curtain wing mounting holes 903; the rotary shaft 8 is connected with a central hole 901 and a second speed reducer 6 arranged on an aircraft, a curtain wing frame 1 is provided with a first coil spring mounting hole 101, a second coil spring mounting hole 102, a guide rail 103, a curtain wing mounting beam 104, a motor mounting hole 105, a rotary shaft 106, a curtain wing fixing shaft 107, a first mounting plate 108, a second mounting plate 109 and a connecting cross beam 110, a soft curtain 2 is provided with a soft curtain windward side 201 and a soft curtain leeward side 202, the guide rail 103 is mounted on the first mounting plate 108 and the second mounting plate 109, the rotary shaft 106 is inserted in the first mounting plate 108 and the second mounting plate 109, the connecting cross beam 110 is inserted in the first mounting plate 108 and the second mounting plate 109, the curtain wing mounting beam 104 is inserted in the guide rail 103 and can slide, a driving motor 5 is mounted on the motor mounting hole 105, a coil spring 3 is mounted on the first coil spring mounting hole 101 and the second coil spring mounting hole 102, and further comprises a motor 7 arranged on the aircraft, an output shaft of the motor 7 is arranged in an input hole of the second speed reducer 6, the curtain wing is further provided with a first speed reducer 4, the rotating wheel shaft 106 is arranged on the output shaft of the first speed reducer 4, an output shaft of the driving motor 5 is arranged in the input hole of the first speed reducer 4, the rotating frame 9 further comprises at least one of an outer reinforcing curved beam 906 and an inner reinforcing curved beam 907 for reinforcing the strength of the rotating frame 9, and the straight beam 902, the outer reinforcing curved beam 906 and the inner reinforcing curved beam 907 are all of a hollow structure and are made of engineering plastics, carbon fibers and the like. After the two-pull-curtain driving energy-adjustable rotary wing aircraft with the fixed wings is adopted by the unmanned aerial vehicle special for fire extinguishment of the high-rise building, the rotary wing aircraft has stronger maneuverability due to large thrust of the working stroke of the rotary curtain wings, small resistance of the rotor wings and high pneumatic efficiency, can quickly respond to the emergency situation of the high-rise building and quickly fly to a fire catching point of the high-rise building for fire extinguishment.
Claims (7)
1. The two-curtain-pulling driving energy-adjustable rotary wing aircraft with the fixed wings is characterized by comprising rotary curtain wings, second speed reducers (6), motors (7), rotating shafts (8), a fuselage frame (10) and the fixed wings (11), wherein the two rotating shafts (8) are symmetrically arranged on two sides of the fuselage frame (10), the axis directions of the two rotating shafts (8) are perpendicular to the longitudinal symmetrical plane of the aircraft, the two motors (7) arranged on the fuselage frame (10) respectively drive the two rotating shafts (8) to continuously rotate after being decelerated through the two second speed reducers (6) arranged on the fuselage frame (10), and the two rotary curtain wings are respectively and fixedly connected to the two rotating shafts (8); the rotary curtain wing comprises a rotary frame (1) and a curtain wing arranged in the rotary frame (1), the curtain wing comprises a curtain wing frame (1) and a soft curtain (2) sleeved on the curtain wing frame (1), and a coil spring (3) and a driving motor (5) are further arranged in the curtain wing frame (1) and used for controlling the expansion and contraction of the soft curtain (2); the fixed wing (11) is arranged on the fuselage frame (10) and is used for generating lift force;
the rotating frame (9) is provided with a center hole (901), a straight beam (902) and a curtain wing mounting plate (904), the direction of the straight beam (902) is parallel to the axis of the center hole (901), the straight beam (902) is provided with a curtain wing mounting hole (903), the axis of the curtain wing mounting hole (903) is orthogonal to the axis of the center hole (901), the curtain wing mounting plate (904) is provided with a curtain wing fixing hole (905), and the axis of the curtain wing fixing hole (905) is orthogonal to the axis of the center hole (901); the curtain wings are inserted into the curtain wing mounting holes (903); the rotating shaft (8) is connected with the central hole (901) and the second speed reducer (6) arranged on the aircraft.
2. The two-curtain drive energy adjustable rotary wing aircraft with fixed wings of claim 1, wherein: the curtain wing frame (1) is provided with a first coil spring mounting hole (101), a second coil spring mounting hole (102), a guide rail (103), a curtain wing mounting beam (104), a motor mounting hole (105), a rotating wheel shaft (106), a curtain wing fixing shaft (107), a first mounting plate (108), a second mounting plate (109) and a connecting beam (110), the soft curtain (2) is provided with a soft curtain windward side (201) and a soft curtain leeward side (202), the guide rail (103) is mounted on the first mounting plate (108) and the second mounting plate (109), the rotating wheel shaft (106) is inserted in the first mounting plate (108) and the second mounting plate (109), the connecting beam (110) is inserted in the first mounting plate (108) and the second mounting plate (109), the curtain wing mounting beam (104) is inserted in the guide rail (103) and can slide, the driving motor (5) is installed on the motor installation hole (105), and the coil spring (3) is installed on the first coil spring installation hole (101) and the second coil spring installation hole (102).
3. The two-curtain drive energy adjustable rotary wing aircraft with fixed wings of claim 1, wherein: and an output shaft of the motor (7) is arranged in an input hole of the second speed reducer (6).
4. The two-curtain drive energy adjustable rotary wing aircraft with fixed wings of claim 1, wherein: the curtain wing is further provided with a first speed reducer (4), the rotating wheel shaft (106) is installed on an output shaft of the first speed reducer (4), and an output shaft of the driving motor (5) is installed in an input hole of the first speed reducer (4).
5. The two-curtain drive energy adjustable rotary wing aircraft with fixed wings of claim 1, wherein: the rotating frame (9) further comprises at least one of an outer reinforcing curved beam (906) and an inner reinforcing curved beam (907) for reinforcing the strength of the rotating frame (9).
6. The two-curtain drive energy adjustable rotary wing aircraft with fixed wings of claim 1, wherein: the straight beam (902), the outer reinforcing curved beam (906) and the inner reinforcing curved beam (907) are all hollow structures;
or the straight beam (902), the outer reinforced curved beam (906) and the inner reinforced curved beam (907) are made of engineering plastics;
or the straight beam (902), the outer reinforcing curved beam (906) and the inner reinforcing curved beam (907) are made of carbon fiber materials.
7. The two-curtain drive energy adjustable rotary wing aircraft with fixed wings of claim 1, wherein: the straight beams (902) are uniformly distributed in the circumferential direction of the central hole (101), and the number of the straight beams (902) is more than 1; the curtain wing mounting holes (903) are linearly and uniformly distributed on the straight beams (902), and the number of the curtain wing mounting holes (903) on each straight beam (902) is more than 1; the number of the coil springs (3) in each curtain wing frame (1) is 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111364315.0A CN113911335A (en) | 2021-11-17 | 2021-11-17 | Two-curtain driving energy-adjustable rotary wing aircraft with fixed wings |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111364315.0A CN113911335A (en) | 2021-11-17 | 2021-11-17 | Two-curtain driving energy-adjustable rotary wing aircraft with fixed wings |
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|---|---|
| CN113911335A true CN113911335A (en) | 2022-01-11 |
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| CN202111364315.0A Pending CN113911335A (en) | 2021-11-17 | 2021-11-17 | Two-curtain driving energy-adjustable rotary wing aircraft with fixed wings |
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| CN110254705A (en) * | 2019-07-19 | 2019-09-20 | 苏州高博软件技术职业学院 | Blade with fixed-wing can turn Horizontal single-wheel formula and move rotor aircraft |
| CN110282125A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn vertical dicycly based on blade and move the aircraft that the wing pushes |
| CN110282124A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn horizontal four wheeled dynamic rotor aircraft in conjunction with the blade of fixed-wing |
-
2021
- 2021-11-17 CN CN202111364315.0A patent/CN113911335A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR402421A (en) * | 1909-04-26 | 1909-10-07 | Eugene Sunguroff | Air thruster |
| CN108275269A (en) * | 2018-01-24 | 2018-07-13 | 浙江工业职业技术学院 | A kind of imitative bird flapping flight device of line wheel amplitude modulation wound membrane formula |
| CN110254705A (en) * | 2019-07-19 | 2019-09-20 | 苏州高博软件技术职业学院 | Blade with fixed-wing can turn Horizontal single-wheel formula and move rotor aircraft |
| CN110282125A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn vertical dicycly based on blade and move the aircraft that the wing pushes |
| CN110282124A (en) * | 2019-07-19 | 2019-09-27 | 苏州高博软件技术职业学院 | It can turn horizontal four wheeled dynamic rotor aircraft in conjunction with the blade of fixed-wing |
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