Strong-wind-resistant four-rotor and variable fixed-wing aircraft system

Abstract

The invention discloses a strong-wind-resistant four-rotor and variable fixed-wing aircraft system, relates to the technical field of unmanned aerial vehicles, and solves the problem that an existing four-rotor unmanned aerial vehicle is insufficient in wind resistance in emergency rescue and disaster relief. The two variable fixed wings located on the left side or the right side are arranged on the upper side and the lower side respectively, each push rod is used for pushing one variable fixed wing to rotate around the axis of a rotating shaft in the push rod, and one fixed rotor wing is installed on the front side of each variable fixed wing. A unique fixed wing adjusting structure is adopted, a connecting structure of the variable fixed wing and the unmanned aerial vehicle body is protected, data are monitored and collected in real time through a sensor, the control system is adopted to control the aircraft to be in different flight stages, the variable fixed wing can actively change the direction in the flight process, and the unmanned aerial vehicle is more stable. And the method is a core mechanical foundation for improving the wind resistance.

Description

Technical Field

[0001] The present invention relates to the technical field of unmanned aerial vehicles, and particularly to a strong-wind-resistant quadrotor and variable fixed-wing aircraft system. Background Art

[0002] In the field of aviation technology, especially when it comes to the application of unmanned aerial vehicles in complex environments, existing quadrotor unmanned aerial vehicles face significant limitations. Unmanned aerial vehicles play an important role in disaster relief and rescue operations, such as rapid response and monitoring. They can quickly reach the disaster site, provide real-time disaster situation data, and assist in rescue decision-making. Personnel search and rescue, they can penetrate into complex terrains, efficiently locate trapped people, and improve the search and rescue efficiency. Material delivery, when transportation is blocked, they can timely deliver urgently needed materials to the disaster area to ensure the basic needs of the affected people.

[0003] In the scenario of high-rise building fire fighting, strong hot air waves and turbulence pose serious challenges to the stability of unmanned aerial vehicles. Traditional quadrotor unmanned aerial vehicles often cannot safely approach the fire point due to their difficulty in resisting these airflows, which limits their application in fire fighting and rescue tasks. Similarly, when taking off and landing in open but windy environments such as large wind valleys, unmanned aerial vehicles also have difficulty maintaining stable flight, resulting in an increased risk of mission execution.

[0004] By retrieving similar technical solutions: CN214824061U, CN220281721U, although existing crosswind vertical takeoff and landing unmanned aerial vehicles can adjust the wing direction to resist crosswinds, they rely on the precise cooperation of an anemometer and a flight control computer, with high costs and certain requirements for the experience of the pilot. Another anti-wind wing of an unmanned aerial vehicle mainly relies on passive structures such as a wind-resistant cover to reduce wind resistance and lacks the ability to actively adjust lift, resulting in limited anti-wind performance in complex wind fields. These deficiencies highlight the limitations of existing technologies in complex environments.

[0005] Limitations of the existing technology: Poor anti-wind ability, insufficient flight stability in strong wind environments, difficult to approach the fire point during high-rise building fire fighting, and difficult to take off and land in large wind valleys. Limited endurance and payload, the endurance and payload capabilities limit their application in long-term and large-scale rescue tasks. Weak adaptability to complex environments, vulnerable to building blockages and terrain influences, resulting in signal loss and difficult flight. Summary of the Invention

[0006] Aiming at the problem of insufficient anti-wind ability of existing quadrotor unmanned aerial vehicles in disaster relief and rescue operations, the purpose of the present invention is to provide a strong-wind-resistant aircraft system combining a quadrotor and a variable fixed wing. By adjusting the direction of the fixed wing, the lift and anti-wind performance are increased, enabling the unmanned aerial vehicle to fly stably in complex environments such as high-rise building fire fighting and large wind valleys, and improving its application efficiency in emergency rescue.

[0007] In order to achieve the above purpose, the technical solution adopted by the present invention is as follows:

[0008] An anti-strong wind quadrotor and variable fixed-wing aircraft system, which includes: an aircraft main body, variable fixed wings 4, push rods 5 and fixed rotors 6. On the left and right sides of the aircraft main body, two variable fixed wings 4 are respectively arranged. The two variable fixed wings 4 on the left side or the right side are respectively arranged on the upper and lower sides. A fixed wing beam 46 is provided on the front side of each variable fixed wing 4. A structural support beam parallel to the fixed wing beam 46 is inserted into each variable fixed wing 4. A rotating shaft is installed on both the upper and lower sides of the aircraft main body. The two variable fixed wings 4 on the upper side are rotatably installed on the rotating shaft on the upper side, and the two variable fixed wings 4 on the lower side are rotatably installed on the rotating shaft on the lower side;

[0009] On the left and right sides of the aircraft main body, two push rods 5 are respectively arranged. The two push rods 5 on the left side or the right side are respectively arranged on the upper and lower sides. One end of each push rod 5 is hinged to the aircraft main body, and the other end of each push rod 5 is hinged to the structural support beam of the variable fixed wing 4 on the same side. Each push rod 5 is used to push a variable fixed wing 4 to rotate around the axis of its inner rotating shaft; The four push rods 5 are all controlled by the control system to operate independently; A fixed rotor 6 is installed on the front side of each variable fixed wing 4;

[0010] It further includes: a sensor, which is installed on the aircraft main body and is used to monitor the wind speed and direction and give real-time feedback.

[0011] In the above anti-strong wind quadrotor and variable fixed-wing aircraft system, the aircraft main body includes: a front connecting rod 1, a rear connecting rod 2 and two lateral connecting rods 3. The two lateral connecting rods 3 are symmetrically arranged up and down. A front connecting rod 1, a rear connecting rod 2 and two lateral connecting rods 3 are hinged to form a parallelogram linkage mechanism.

[0012] In the above anti-strong wind quadrotor and variable fixed-wing aircraft system, two first hinge through holes 11 that are symmetrically arranged up and down are opened on the front connecting rod 1. A fourth hinge through hole 31 is opened at the front end of each lateral connecting rod 3. Each first hinge through hole 11 of the front connecting rod 1 and the fourth hinge through hole 31 of a lateral connecting rod 3 are hinged by a hinge shaft; Two third hinge through holes 21 that are symmetrically arranged up and down are opened on the rear connecting rod 2. A sixth hinge through hole 33 is opened at the rear end of each lateral connecting rod 3. Each third hinge through hole 21 of the rear connecting rod 2 and the sixth hinge through hole 33 of a lateral connecting rod 3 are hinged by a hinge shaft.

[0013] The above-mentioned strong-wind-resistant quadrotor and variable fixed-wing aircraft system, wherein two second hinge through-holes 12 that are symmetrically arranged up and down are formed on the rear connecting rod 2, a connecting shaft is inserted into each second hinge through-hole 12, and one end of each push rod 5 is hinged to the end of a connecting shaft; a connecting groove 43 for exposing the structural support beam is formed on each variable fixed wing 4, and the other end of each push rod 5 is located in a connecting groove 43 and is hinged to the structural support beam.

[0014] The above-mentioned strong-wind-resistant quadrotor and variable fixed-wing aircraft system, wherein a fifth hinge through-hole 32 that penetrates left and right is provided on each lateral connecting rod 3, and the fifth hinge through-hole 32 is used for inserting a rotating shaft.

[0015] The above-mentioned strong-wind-resistant quadrotor and variable fixed-wing aircraft system, wherein each fixed rotor includes: a rotor motor and a six-blade propeller. A rotor motor is installed on the front side of each variable fixed wing 4, and each six-blade propeller is installed at the output end of a rotor motor.

[0016] The above-mentioned strong-wind-resistant quadrotor and variable fixed-wing aircraft system, wherein for the two variable fixed wings 4 located on the upper side, their upper wing surfaces are arc-shaped wing surfaces 47 and their lower wing surfaces are streamlined wing surfaces 48; for the two variable fixed wings 4 located on the lower side, their lower wing surfaces are arc-shaped wing surfaces 47 and their upper wing surfaces are streamlined wing surfaces 48.

[0017] The above-mentioned strong-wind-resistant quadrotor and variable fixed-wing aircraft system, wherein the two variable fixed wings 4 located on the left or right are respectively a first fixed wing 41 and a second fixed wing 42, and the first fixed wing 41 and the second fixed wing 42 are mirror-symmetrically arranged in structure.

[0018] The above-mentioned strong-wind-resistant quadrotor and variable fixed-wing aircraft system, wherein the variable fixed wings 4 located above the left side and below the right side of the aircraft body are first fixed wings 41; the variable fixed wings 4 located above the right side and below the left side of the aircraft body are second fixed wings 42.

[0019] The above-mentioned strong-wind-resistant quadrotor and variable fixed-wing aircraft system, wherein a first opening groove 44 and a second opening groove 45 are formed on the variable fixed wing 4, both the first opening groove 44 and the second opening groove 45 communicate with the streamlined wing surface 48, the variable fixed wing 4 is rotatably installed on the rotating shaft through the first opening groove 44, and the second opening groove 45 is used for inserting the structural support beam.

[0020] Due to the adoption of the above technology, the positive effects of the present invention compared with the prior art are:

[0021] (1) The present invention adopts a unique fixed-wing adjustment structure to protect the connection structure between the variable fixed wing and the UAV fuselage, especially the installation method of the control device and the push rod and its connection mechanism with the variable fixed wing. This structure enables the variable fixed wing to actively change its direction during flight, which is the core mechanical basis for improving the wind resistance performance.

[0022] (2) In the present invention, sensors are used to monitor and collect data in real time, and a control system is adopted to control the aircraft in different flight stages (quadcopter mode, fixed-wing mode and their conversion processes). The direction of the variable fixed wing is adjusted in real time according to the wind speed and flight state to ensure the stability and wind resistance of the aircraft.

[0023] (3) In the present invention, the aerodynamic performance is optimized, and the aerodynamic shape design and its parameters (such as aspect ratio, camber, etc.) of the fixed wing are protected. These designs can enable the aircraft to obtain better lift characteristics and lower drag after adjusting the direction of the fixed wing, thus improving the overall aerodynamic performance. Description of the Drawings

[0024] Figure 1 It is a schematic structural diagram of a strong wind-resistant quadcopter and variable fixed-wing aircraft system of the present invention.

[0025] Figure 2 It is a front view of a strong wind-resistant quadcopter and variable fixed-wing aircraft system of the present invention.

[0026] Figure 3 It is Figure 2 a left view of

[0027] Figure 4 It is Figure 2 a top view of

[0028] Figure 5 It is a schematic structural diagram of the front link of a strong wind-resistant quadcopter and variable fixed-wing aircraft system of the present invention.

[0029] Figure 6 It is a schematic structural diagram of the rear link of a strong wind-resistant quadcopter and variable fixed-wing aircraft system of the present invention.

[0030] Figure 7 It is a schematic structural diagram of the lateral link of a strong wind-resistant quadcopter and variable fixed-wing aircraft system of the present invention.

[0031] Figure 8 It is a schematic structural diagram of the first fixed wing of a strong wind-resistant quadcopter and variable fixed-wing aircraft system of the present invention.

[0032] Figure 9 It is Figure 8 a top view of

[0033] Figure 10 It is a schematic structural view of the second fixed wing of a strong wind-resistant quadrotor and variable fixed-wing aircraft system of the present invention.

[0034] Figure 11 is Figure 10 the top view of.

[0035] In the attached drawings: 1, front connecting rod; 2, rear connecting rod; 3, lateral connecting rod; 4, variable fixed wing; 5, push rod; 6, fixed rotor; 11, first hinge through hole; 12, second hinge through hole; 21, third hinge through hole; 31, fourth hinge through hole; 32, fifth hinge through hole; 33, sixth hinge through hole; 41, first fixed wing; 42, second fixed wing; 43, connecting groove; 44, first opening groove; 45, second opening groove; 46, fixed wing beam; 47, arc-shaped wing surface; 48, streamlined wing surface. Specific embodiments

[0036] The present invention will be further described below in conjunction with the attached drawings and specific embodiments, but it is not limited to the present invention.

[0037] Please refer to Figures 1 to 11 as shown, which shows a strong wind-resistant quadrotor and variable fixed-wing aircraft system, wherein, it includes: an aircraft body, a variable fixed wing 4, a push rod 5 and a fixed rotor 6. Two variable fixed wings 4 are respectively arranged on the left and right sides of the aircraft body, as Figure 2 shown, located at position 1, position 2, position 3 and position 4 respectively. Among them, the variable fixed wings 4 at position 1 and position 4 are the first fixed wings 41, and the specific structure can be referred to Figure 8 and Figure 9 ; the variable fixed wings 4 at position 2 and position 3 are the second fixed wings 42, and the specific structure can be referred to Figure 10 and Figure 11 ; a fixed wing beam 46 is arranged on the front side of each variable fixed wing 4, and a structural support beam parallel to the fixed wing beam 46 is inserted into each variable fixed wing 4. A rotating shaft is installed on both the upper and lower sides of the aircraft body. The two variable fixed wings 4 on the upper side are rotatably installed on the upper rotating shaft, and the two variable fixed wings 4 on the lower side are rotatably installed on the lower rotating shaft;

[0038] Further, in a preferred embodiment, two push rods 5 are provided on each of the left and right sides of the aircraft body. The two push rods 5 on the left or right side are respectively arranged on the upper and lower sides. One end of each push rod 5 is hinged to the aircraft body, and the other end of each push rod 5 is hinged to the structural support beam of the variable fixed wing 4 on the same side. Each push rod 5 is used to push a variable fixed wing 4 to rotate around the axis of its inner rotating shaft; when all four push rods 5 are in the fully extended or fully retracted state, the two variable fixed wings 4 on the left or right side are symmetrically arranged up and down, the two variable fixed wings 4 on the upper or lower side are located in the same plane, and for the two variable fixed wings 4 on the left or right side, each wing surface facing away from the other variable fixed wing 4 is an arc-shaped wing surface 47, and each wing surface facing the other variable fixed wing 4 is a streamlined wing surface 48. By designing the wing surfaces of the four variable fixed wings 4, the flight resistance of the aircraft is reduced and the lift of the aircraft during flight is increased.

[0039] Further, in a preferred embodiment, all four push rods 5 are controlled by the control system to operate independently, and the operating angles of the four variable fixed wings 4 are respectively controlled.

[0040] Further, in a preferred embodiment, a fixed rotor 6 is installed on the front side of each variable fixed wing 4;

[0041] Further, in a preferred embodiment, it further includes: a sensor. The sensor is installed on the aircraft body and is used to monitor the wind speed and direction and provide real-time feedback. The control system controls the operating angles of the four variable fixed wings 4 respectively according to the data obtained by the sensor.

[0042] Further, in a preferred embodiment, all four push rods 5 are electro-hydraulic push rods, and other push rod structures capable of extending and retracting can also be used.

[0043] Further, in a preferred embodiment, all four push rods 5 are controlled by the servo motor to operate independently, and they can also be replaced by other driving devices that can cooperate with the push rods 5 and achieve independent driving.

[0044] Further, in a preferred embodiment, as Figures 1 to 4 shown, the aircraft body is simplified into a parallelogram linkage mechanism formed by hinging a front link 1, a rear link 2 and two lateral links 3 to each other.

[0045] Further, in a preferred embodiment, as Figure 7 shown, the lateral link 3 is respectively provided with a fourth hinge through hole 31 and a sixth hinge through hole 33 for installing the hinge shaft at its front and rear ends, which are used for hinging with the front link 1 and the rear link 2; a fifth hinge through hole 32 is provided in the middle thereof, which can be used for installing two non-interfering rotating shafts located on the same axis, or can also be used for installing a longer rotating shaft that can extend out from the front and rear sides.

[0046] Further, in a preferred embodiment, each fixed rotor includes a rotor motor and a six-blade propeller. A rotor motor is installed on the front side of each variable fixed wing 4, and each six-blade propeller is installed at the output end of a rotor motor. The rotor motor drives the six-blade propeller to rotate.

[0047] Further, in a preferred embodiment, a first opening groove 44 is formed in the variable fixed wing 4. The first opening groove 44 communicates with the streamlined wing surface 48. The first opening groove 44 is located at one-third of the variable fixed wing 4 from the front side to the rear side. The variable fixed wing 4 is rotatably installed on the rotating shaft through the first opening groove 44.

[0048] Further, in a preferred embodiment, a second opening groove 45 is formed in the variable fixed wing 4. The second opening groove 45 is used for inserting a structural support beam. The structural support beam cooperates with the fixed wing beam 46 to improve the strength and wind resistance of the variable fixed wing 4.

[0049] The above is only a preferred embodiment of the present invention, and does not limit the implementation manners and protection scope of the present invention.

[0050] The present invention also has the following implementation manners on the above basis:

[0051] In a further embodiment of the present invention, when the unmanned aerial vehicle flies against the wind, the wind acts on the variable fixed wing 4 to generate lift and drag. The control system monitors the wind speed and flight state in real time and calculates the required wing angle adjustment amount. The control system sends instructions to drive the steering gear and hydraulic rod to adjust the direction of the variable fixed wing 4. The adjusted variable fixed wing 4 increases the lift and is more resistant to strong wind interference.

[0052] In a further embodiment of the present invention, the specific process is as follows:

[0053] Wind speed monitoring: The wind speed and wind direction are monitored in real time through sensors, and the data is transmitted to the control system.

[0054] Data processing: The control system calculates the optimal wing angle adjustment amount according to the wind speed and flight state.

[0055] Instruction sending: The control system sends adjustment instructions to the steering gear and hydraulic rod.

[0056] Wing adjustment: The driving device and the push rod 5 drive the variable fixed wing 4 to rotate around the rotating shaft, changing the windward angle of the variable fixed wing 4.

[0057] Effect feedback: The adjusted variable fixed wing 4 increases the lift and reduces the drag, enabling the unmanned aerial vehicle to maintain stable flight in strong winds.

[0058] In a further embodiment of the present invention, the position of the rotating shaft is at about 1 / 3 of the cross-section of the variable fixed wing 4, that is, within the first opening groove 44, which can significantly reduce the torque brought to the rotating shaft when the variable fixed wing 4 rotates and improve the service life of the rotating shaft.

[0059] In a further embodiment of the present invention, a unique fixed wing adjustment structure is adopted to protect the connection structure between the variable fixed wing 4 and the drone fuselage, especially the installation method of the control device and the push rod 5 and its connection mechanism with the variable fixed wing 4. This structure can enable the variable fixed wing 4 to actively change its direction during flight and is the core mechanical basis for improving the wind resistance performance.

[0060] In a further embodiment of the present invention, sensors are used to monitor and collect data in real time, and a control system is adopted to control the aircraft at different flight stages (quadcopter mode, fixed wing mode and their conversion processes). The direction of the variable fixed wing 4 is adjusted in real time according to the wind speed and flight state to ensure the stability and wind resistance of the aircraft.

[0061] In a further embodiment of the present invention, the aerodynamic performance is optimized, and the aerodynamic shape design and its parameters (such as aspect ratio, camber, etc.) of the fixed wing are protected. These designs can enable the aircraft to obtain better lift characteristics and lower drag after adjusting the direction of the fixed wing, and improve the overall aerodynamic performance.

[0062] In a further embodiment of the present invention, the deformation process and control method of the aircraft are realized, and the specific steps, action sequences and corresponding control methods of the whole deformation process from the quadcopter mode to the fixed wing mode are protected to ensure the smooth switching between different modes of the aircraft and maintain stable flight.

[0063] In a further embodiment of the present invention, it further includes: a fairing, an inflation valve and a support structure. A fairing connected by an airbag network is arranged above the drone, and the angle of the fairing is adjusted through the inflation valve and the support structure to optimize the flow field and improve the propulsion speed and stability.

[0064] In a further embodiment of the present invention, the inflation valve and the support structure are used to adjust the angle of the fairing. The structure is simple, can be quickly opened and closed, and can adapt to most weather hovering conditions.

[0065] In a further embodiment of the present invention, the variable fixed wing 4 can adopt a compliant structure design, and the wing adjustment is realized by using the flexible deformation of the structure. For example, a lattice compliant structure is adopted, and the variable trailing edge of the wing is realized through its elastic deformation to replace the traditional hinge mechanism.

[0066] In a further embodiment of the present invention, the variable fixed wing 4 with a compliant structure design is easy to be miniaturized and lightweight, and is suitable for integrated design and processing, making it suitable for occasions with limited space; it has no friction and requires no maintenance, making it suitable for special environments such as dust-free and vacuum; it has no clearance and no hysteresis, and can achieve high precision and high reliability.

[0067] In a further embodiment of the present invention, the four variable fixed wings 4 can also adopt a fixed wing structure with the same arc on the upper and lower wing surfaces.

[0068] The above are only the preferred embodiments of the present invention, and do not limit the implementation manners and protection scope of the present invention. For those skilled in the art, it should be realized that all the equivalent replacements and obvious changes made by using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. An anti-strong-wind quadrotor and variable fixed-wing aircraft system, characterized in that Comprising: An aircraft body, variable fixed wings (4), push rods (5) and fixed rotors (6). Two variable fixed wings (4) are arranged on each of the left and right sides of the aircraft body. The two variable fixed wings (4) on the left side or the right side are respectively arranged on the upper and lower sides. A fixed wing spar (46) is provided on the front side of each variable fixed wing (4). A structural support beam parallel to the fixed wing spar (46) is inserted into each variable fixed wing (4). A rotating shaft is installed on each of the upper and lower sides of the aircraft body. The two variable fixed wings (4) on the upper side are rotatably installed on the rotating shaft on the upper side, and the two variable fixed wings (4) on the lower side are rotatably installed on the rotating shaft on the lower side; Two push rods (5) are arranged on each of the left and right sides of the aircraft body. The two push rods (5) on the left side or the right side are respectively arranged on the upper and lower sides. One end of each push rod (5) is hinged to the aircraft body, and the other end of each push rod (5) is hinged to the fixed wing spar (46) of the variable fixed wing (4) on the same side. Each push rod (5) is used to push a variable fixed wing (4) to rotate around the axis of its inner rotating shaft; The four push rods (5) are all controlled by a control system to operate independently; A fixed rotor (6) is installed on the front side of each variable fixed wing (4); Also comprising: a sensor, the sensor is installed on the aircraft body, and the sensor is used to monitor the wind speed and direction and give real-time feedback.

2. The anti-strong-wind quadrotor and variable fixed-wing aircraft system according to claim 1, wherein The aircraft body includes: a front connecting rod (1), a rear connecting rod (2) and two lateral connecting rods (3). The two lateral connecting rods (3) are symmetrically arranged up and down. A front connecting rod (1), a rear connecting rod (2) and two lateral connecting rods (3) are hinged to form a parallelogram linkage mechanism.

3. The anti-strong-wind quadrotor and variable fixed-wing aircraft system according to claim 2, characterized in that, Two first hinge through holes (11) symmetrically arranged up and down are formed on the front connecting rod (1). A fourth hinge through hole (31) is formed at the front end of each lateral connecting rod (3). Each first hinge through hole (11) of the front connecting rod (1) and the fourth hinge through hole (31) of a lateral connecting rod (3) are hinged by a hinge shaft; Two third hinge through holes (21) symmetrically arranged up and down are formed on the rear connecting rod (2). A sixth hinge through hole (33) is formed at the rear end of each lateral connecting rod (3). Each third hinge through hole (21) of the rear connecting rod (2) and the sixth hinge through hole (33) of a lateral connecting rod (3) are hinged by a hinge shaft.

4. The anti-strong wind quadrotor and variable fixed-wing aircraft system according to claim 2, characterized in that, Two second hinge through holes (12) symmetrically arranged up and down are formed on the rear connecting rod (2). A connecting shaft is inserted into each second hinge through hole (12). One end of each push rod (5) is hinged to the end of a connecting shaft; A connecting groove (43) for exposing the structural support beam is formed on each variable fixed wing (4). The other end of each push rod (5) is located in a connecting groove (43) and is hinged to the structural support beam.

5. The anti-strong wind quadrotor and variable fixed-wing aircraft system according to claim 2, characterized in that, A fifth hinge through hole (32) penetrating left and right is provided on each lateral connecting rod (3), and the fifth hinge through hole (32) is used to insert a rotating shaft.

6. The anti-strong-wind quadrotor and variable fixed-wing aircraft system according to claim 5, characterized in that, Each fixed rotor includes: a rotor motor and a six-blade propeller. A rotor motor is installed on the front side of each variable fixed wing (4), and each six-blade propeller is installed at the output end of a rotor motor.

7. The anti-strong-wind quadrotor and variable fixed-wing aircraft system according to claim 1, characterized in that Among the two variable fixed wings (4) located on the upper side, their upper wing surfaces are arc-shaped wing surfaces (47), and their lower wing surfaces are streamlined wing surfaces (48); among the two variable fixed wings (4) located on the lower side, their lower wing surfaces are arc-shaped wing surfaces (47), and their upper wing surfaces are streamlined wing surfaces (48).

8. The anti-strong-wind quadrotor and variable fixed-wing aircraft system according to claim 2, wherein, The two variable fixed wings (4) located on the left or right side are respectively the first fixed wing (41) and the second fixed wing (42), and the first fixed wing (41) and the second fixed wing (42) are mirror-image arranged in structure.

9. The anti-strong wind quadrotor and variable fixed-wing aircraft system according to claim 8, characterized in that, The variable fixed wing (4) located above the left side and below the right side of the aircraft body is the first fixed wing (41); the variable fixed wing (4) located above the right side and below the left side of the aircraft body is the second fixed wing (42).

10. The anti-strong wind quadrotor and variable fixed-wing aircraft system according to claim 7, characterized in that, The variable fixed wing (4) is provided with a first opening groove (44) and a second opening groove (45). Both the first opening groove (44) and the second opening groove (45) communicate with the streamlined wing surface (48). The variable fixed wing (4) is rotatably installed on the rotating shaft through the first opening groove (44), and the second opening groove (45) is used for passing through the structural support beam.

Images