Single-seat ultra-light aircraft cockpit layout method

Abstract

The invention discloses a single-seat ultra-light aircraft cockpit layout method, and belongs to the field of ultra-light aircraft cockpit design. The cabin layout comprises a comprehensive display and control console, a throttle lever, a three-axis control lever, a high-strength carbon fiber racing car grade lightweight seat, a five-point safety belt, a pedal and an emergency complete machine parachute. In functional design, the single-seat electric multi-rotor ultra-light aircraft has an automatic driving capability and has a manual stability augmentation mode, a fixed height mode, a fixed point mode and an airline flight mode. The single-seat ultra-light aircraft cockpit serves as an interaction and bearing entity of a single-seat electric multi-rotor ultra-light aircraft and a driver and is used for achieving the basic flight control function of the driver while ensuring reasonable man-machine interaction space accessibility and reasonable space perception and flight experience view. The aircraft has the functions of air flight and reliable, stable and comfortable riding, and provides basic flight communication, navigation, identification and positioning information functions, emergency landing safety function and noise suppression function.

Description

Technical Field

[0001] The invention belongs to the field of ultralight aircraft cockpit design, in particular to a single-seat ultralight aircraft cockpit layout method. Background Art

[0002] As a type of civil aircraft, ultralight aircraft mainly emphasizes safety, economy and comfort, and can be widely used in agriculture, forestry, animal husbandry, exploration, aerial photography, aviation sports and tourism. It is generally believed that the empty weight of a single-seat ultralight aircraft should not exceed 115 kilograms.

[0003] Currently, most ultralight aircraft are fixed-wing aircraft and helicopters. The cockpit layout of traditional general aviation fixed-wing aircraft is designed and optimized around long-distance flight and fixed-wing manned control logic, and helicopters are designed with variable pitch control as a feature. Since the single-seat electric multi-rotor ultralight aircraft has a four-axis eight-rotor layout, compact size, relatively simple system composition and low cost, and is mainly based on a single-person short-term and short-distance driving experience, its control logic is mainly controlled by controlling the lift distribution of the multi-rotor. The above-mentioned fixed-wing and helicopter cockpit layout methods are relatively complex and costly in terms of system functions, and the driving control logic is no longer applicable to multi-rotor ultralight aircraft. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a single-seat electric multi-rotor ultralight aircraft cockpit layout method to solve the above-mentioned problems. In order to solve the above-mentioned technical problems, the present invention proposes a single-seat electric multi-rotor ultralight aircraft cockpit layout method, which realizes functions including single-person convenient operation and control, comfortable riding, safe fixation, instrument information display and interaction through cockpit layout, ergonomic design and optimization.

[0005] The technical solution of the present invention:

[0006] A single-seat ultralight aircraft cockpit layout method. In terms of functional design, the single-seat electric multi-rotor ultralight aircraft has the ability of automatic driving, and has manual stabilization mode, altitude fixation mode, fixed point mode and route flight mode. The single-seat ultralight aircraft cockpit is an interaction and bearing entity between the single-seat electric multi-rotor ultralight aircraft and the driver. It is used to ensure reasonable human-machine interaction space accessibility, reasonable space perception and flight experience vision, while realizing the driver's basic flight control function, reliable, stable and comfortable riding functions in the air and the body, and providing basic flight communication, navigation, identification and positioning information functions, emergency landing safety functions, and noise suppression functions. In the design of the driver's basic flight control, combined with the characteristics of the aircraft and the spatial distribution, the "integrated display console, throttle lever, and three-axis joystick" method is adopted to realize the control of the aircraft.

[0007] The cockpit layout includes an integrated display and control console, throttle lever, three-axis joystick, high-strength carbon fiber racing-grade lightweight seat, five-point safety belt, foot pedals and emergency whole-aircraft parachute.

[0008] The integrated display and control console is arranged at the front of the cockpit, including an integrated display and control touch screen, an integrated display and control button assembly, and an integrated display and control support structure. The integrated display and control touch screen is divided into fixed information display, user-customized information display, and touch switch, which realize basic flight information, power monitoring and alarm, map navigation, route planning and other auxiliary information. The integrated display and control button assembly is used to realize flight function settings and auxiliary adjustment functions; the integrated display and control support structure is used to realize the connection and fixation between the integrated display and control console and the main structure of the fuselage;

[0009] The throttle lever adopts a lightweight design, and its size and weight are optimized on the basis of achieving basic functions. It is arranged on the inner side of the aluminum alloy tube beam on the upper left side of the cockpit through a throttle lever fixed support. The throttle lever handle rotates around the lower throttle lever shaft. It is in a neutral position when there is no operation. Pushing it forward reduces the throttle to make the aircraft descend, and pulling it backward increases the throttle to make the aircraft ascend.

[0010] The three-axis joystick includes a three-axis joystick handle, a three-axis joystick gimbal rocker, a three-axis joystick one-button takeoff / return landing button, a three-axis joystick motion mode selection button, a three-axis joystick whole-machine parachute ejection button, a three-axis joystick photo / video button, a three-axis joystick voice communication button, and a three-axis joystick fixed support; the three-axis joystick also adopts a lightweight design and is specifically designed to adapt to the control characteristics of single-seat electric multi-rotor ultralight aircraft. It is arranged on the upper right side of the cockpit and is in a neutral position when there is no control. Push the three-axis joystick handle forward to make the aircraft move forward, pull it backward to make the aircraft move backward, push it to the left to make the aircraft move left, and push it to the right to make the aircraft move right. Hold the three-axis joystick handle and turn it clockwise to make the aircraft nose turn to the right, and turn it counterclockwise to make the aircraft nose turn to the left. There are function buttons on the head of the three-axis joystick. In the normal control mode, one stick can realize attitude control, recording and communication functions. The three-axis joystick gimbal joystick can control the pitch and heading rotation of the gimbal camera. The three-axis joystick one-key takeoff / return landing button can realize the aircraft takeoff / return landing operation. The three-axis joystick motion mode selection button can realize a variety of customized motion modes of the aircraft. The three-axis joystick whole-machine parachute ejection button cooperates with the throttle lever to realize the ejection life-saving function in an emergency. The three-axis joystick photo / video button realizes the gimbal camera recording function. The three-axis joystick voice communication button realizes ground / air specific voice communication function.

[0011] In terms of riding function design, a high-strength carbon fiber racing-grade lightweight seat is set in the middle of the cockpit. The seat layout ensures that the center of gravity of the driver's sitting posture is close to the center of gravity of the entire aircraft, and the driver's hip point is as close as possible to the longitudinal axis of the center of gravity of the entire aircraft to balance the power output. Since the aircraft rotor plane tilts forward during forward flight, in order to ensure human comfort and vision during forward flight and cruising, the seat is tilted backward. The rearward tilt angle of the racing-grade lightweight seat formed at this time meets the requirements of comfort and vision. At the same time, this posture can reduce the impact on the human body during unpowered emergency landing. The driver's head movement circle is obtained through the size of the driver's helmet and the trajectory of the head movement. The maximum distance between the driver's hip point and the head movement circle provides design input for the seat design and the fuselage shell design. The driver is fixed with a five-point safety belt, which can ensure that the relative position of the driver and the aircraft is fixed during large maneuvers in the air to avoid the risk of falling. A foot pedal is set on the lower side of the front of the cockpit to provide support for the driver's legs.

[0012] In terms of accessibility and field of view design, in order to ensure the driver's operating experience, the human body accessible area and field of view design analysis are carried out. The control components are placed in the accessible area. At the same time, in order to ensure the front field of view, the height of the front part of the fuselage is lowered under the premise of ensuring the function and size of the integrated display console. In order to ensure the lateral field of view, the driver's head is higher than the load-bearing pipe beams on both sides of the fuselage. The downward angle formed by the line connecting the driver's eye point and the highest point of the front of the fuselage shell and the horizontal line meets the driver's environmental perception requirements during take-off and landing, and at the same time meets the driving and sightseeing experience requirements during flight. The inclination angle of the integrated display panel formed by the line connecting the driver's eye point and the center point of the integrated display touch screen and the horizontal line should not be too large to avoid causing discomfort to the driver when bowing his head for a long time. At the same time, the distance between the driver's eye point and the integrated display touch screen meets the requirements of clear visibility and reachability of the screen information. In the design of leg space, the distance design between the driver's hip point and the front baffle of the foot pedal meets the requirements of comfortable leg space extension. In the spatial design of the throttle lever and the three-axis joystick of the control components, the distance between the driver's shoulder point and the three-axis joystick meets the requirements of hand grip accessibility and comfort.

[0013] In terms of safety design, most of the human body is placed in a box-shaped fuselage composed of aluminum alloy frame beams, and a car-like roll cage support structure is set behind the head for protection. At the same time, the driver wears a driver's helmet to protect the head and reduce noise while providing voice communication functions. In addition, an optional emergency whole-machine parachute is set in the tail space of the fuselage behind the seat. The four parachute rope rings are set on the upper two side bearing beams in front, behind, left and right of the cockpit. The ropes are arranged according to the structure and shape of the aircraft. In the event of an emergency landing, the tail ejection port cover of the fuselage behind the seat pops out together with the main body of the whole-machine emergency parachute. Then the four parachute ropes are tensioned and the aircraft lands at a low speed with the assistance of the emergency whole-machine parachute. When touching down, the skid-type landing gear is buffered synchronously to reduce the risk of driver injury.

[0014] Beneficial effects of the present invention: The cockpit layout method of the single-seat electric multi-rotor ultralight aircraft of the present invention develops a cockpit layout parameter set suitable for the electric multi-rotor ultralight aircraft through cockpit parameterization design, selects and optimizes parameters from the perspective of ergonomics, and significantly improves the convenient control, comfortable riding, safe fixation, instrument information display and interaction of such aircraft. The throttle lever, three-axis joystick, and racing-level lightweight seat of the present invention are lightweight designed to minimize the empty weight and reduce the cost of the whole aircraft. The three-axis joystick of the present invention can realize attitude control, video recording and communication functions with one lever in the normal control mode, reduce the complexity of operation, and reduce the difficulty of operation for the driver. The fuselage of the present invention sets most of the driver in a box-type structure composed of aluminum alloy tube beams, and a car-like anti-roll cage support structure is set behind the head for protection. An optional whole-machine parachute is set in the tail space of the fuselage to reduce the grounding speed during emergency landing, and cooperates with the skid landing gear for synchronous buffering to reduce the risk of driver injury. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 It is a schematic diagram of the relevant arrangement of the cockpit of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0016] Figure 2 It is a schematic diagram of the cockpit layout of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0017] Figure 3 It is a side view schematic diagram of the cockpit layout of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0018] Figure 4 This is a schematic diagram of a three-axis joystick for a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0019] Figure 5 It is a schematic diagram of a three-axis throttle lever of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention;

[0020] Figure 6 The figure is a schematic diagram of a complete parachute system for a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention.

[0021] In the figure: fuselage 1, fuselage shell 111, whole machine parachute ejection hatch 113, fuselage main structure 12, throttle lever 14, three-axis joystick 15, racing-level lightweight seat 16, five-point safety belt 17, whole machine parachute 181, right front parachute rope ring 182, left front parachute rope ring 183, right rear parachute rope ring 184, left rear parachute rope ring 185, three-axis joystick fixing support 19, throttle lever fixing support 120, skid landing gear 3, integrated display console 13, integrated display console touch screen 131, integrated display console button assembly 132, integrated display console support structure 133, throttle lever 14, three-axis joystick 15, racing-level lightweight seat 16, foot pedal 121, foot pedal 121, driver 801, driver helmet 802, The center of gravity of the whole machine CG, the driver's hip point H, the driver's shoulder point S, the driver's eye point E, the downward viewing angle α, the inclination angle of the integrated display and control panel β, the rearward tilt angle of the racing-level lightweight seat γ, the driver's head movement circle Ф1, the distance D1 between the driver's eye point and the touch screen of the integrated display and control console, the distance D2 between the driver's hip point and the front baffle of the foot pedal, the distance D3 between the driver's shoulder point and the three-axis joystick, the maximum distance H1 between the driver's hip point and the head movement circle, the three-axis joystick handle 151, the three-axis joystick gimbal rocker 152, the three-axis joystick one-key takeoff / return landing button 153, the three-axis joystick motion mode selection button 154, the three-axis joystick whole machine parachute ejection button 155, the three-axis joystick photo / video button 156, and the three-axis joystick voice communication button 157. DETAILED DESCRIPTION

[0022] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0023] Figure 1 The figure shows a schematic diagram of the arrangement of a single-seat electric multi-rotor ultralight aircraft cockpit in an embodiment of the present invention, wherein the single-seat ultralight aircraft cockpit includes a fuselage 1, a fuselage shell 111, an entire aircraft parachute ejection hatch 113, a fuselage main structure 12, a throttle lever 14, a three-axis joystick 15, a racing-grade lightweight seat 16, a five-point safety belt 17, an entire aircraft parachute 181, a right front parachute rope ring 182, a left front parachute rope ring 183, a right rear parachute rope ring 184, a left rear parachute rope ring 185, a three-axis joystick fixing support 19, a throttle lever fixing support 120, and a skid-type landing gear 3. Figure 2The cockpit layout diagram of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention is shown, and the layout of the aircraft cockpit-related integrated display console 13, the integrated display console touch screen 131, the integrated display console button assembly 132, the integrated display console support structure 133, and the pedal 121 are supplemented. Specifically, for a single-seat electric multi-rotor ultralight aircraft cockpit layout method, through cockpit layout, ergonomic design and optimization, the functions including single-person convenient operation and control, comfortable riding, safe fixation, instrument information display and interaction are realized.

[0024] Specifically, in terms of functional design, the single-seat electric multi-rotor ultralight aircraft has the ability to autopilot, and has manual stabilization mode, altitude setting mode, fixed-point mode and route flight mode. As the interaction and carrier entity between the ultralight aircraft and the driver, the cockpit mainly realizes the driver's basic flight control functions, reliable, stable and comfortable riding functions of the air flight and the body, provides basic flight communication, navigation, identification and positioning and other effective information functions, emergency landing safety functions, noise suppression functions, reasonable human-computer interaction space accessibility, reasonable space perception and flight experience vision, etc. In the design of flight control, combined with the characteristics of the aircraft and the spatial distribution, the "integrated display console, throttle lever, and three-axis joystick" method is adopted to realize the control of the aircraft.

[0025] Specifically, in terms of cockpit layout, the cockpit is mainly composed of an integrated display and control console 13, a throttle lever 14, a three-axis joystick 15, a high-strength carbon fiber racing-level lightweight seat 16, a five-point safety belt 17, a foot pedal 121, and an emergency whole-machine parachute 181 system. Specifically, the integrated display and control console 13 is arranged at the front upper part of the cockpit, including an integrated display and control console touch screen 131, an integrated display and control console button assembly 132, and an integrated display and control console support structure 133. Specifically, the integrated display and control console touch screen 131 is divided into fixed information display, user-customized information display, touch switch, etc., to realize basic flight information, power monitoring alarm, map navigation, route planning and other auxiliary information. The integrated display and control console button assembly 132 mainly realizes flight function settings and auxiliary adjustment functions. The integrated display and control console support structure 133 realizes the connection and fixation of the integrated display and control console 13 with the main structure 12 of the fuselage.

[0026] Specifically, in terms of safety design, most of the human body is placed in the box-shaped fuselage main structure 12 composed of aluminum alloy tube beams, and a car-like roll cage support structure is set behind the head for protection. At the same time, the driver wears a driver's helmet 802 to protect the head while reducing noise and providing voice communication function.

[0027] Figure 3The side view schematic diagram of the cockpit layout of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the present invention is shown. Specifically, in terms of riding function design, a high-strength carbon fiber racing-grade lightweight seat 16 is arranged in the middle of the cockpit. The racing-grade lightweight seat 16 is arranged to ensure that the center of gravity of the driver's riding posture is close to the center of gravity CG of the entire aircraft, and the driver's hip point H is as close as possible to the longitudinal axis of the center of gravity CG of the entire aircraft to balance the power output. Since the aircraft rotor plane tilts forward during forward flight, in order to ensure human comfort and vision during forward flight and cruising, the seat is tilted backward and installed. The rearward tilt angle γ of the racing-grade lightweight seat formed at this time meets the comfort and vision requirements. At the same time, this posture can reduce the impact on the human body during unpowered emergency landing. The driver's head movement circle diameter Ф1 is obtained through the size of the driver's helmet 802 and the head movement trajectory. The maximum distance H1 between the driver's hip point and the head movement circle diameter provides design input for the seat design and the fuselage shell 111 design. The driver 801 is fixed with a five-point safety belt 17, which can ensure that the relative position of the driver 801 and the aircraft is fixed during large maneuvers in the air to avoid the risk of falling. A foot pedal 121 is provided at the lower front side of the cockpit to provide support for the driver's legs.

[0028] Specifically, in terms of accessibility and field of view design, in order to ensure the control experience of the driver 801, the human body accessible area and field of view design analysis are carried out. The control components are placed in the accessible area. At the same time, in order to ensure the front field of view, the height of the front part of the fuselage is lowered under the premise of ensuring the function and size of the integrated display and control console 13. In order to ensure the lateral field of view, the head of the driver 801 is higher than the load-bearing pipe beams on both sides of the fuselage. The lower angle of view α formed by the line connecting the driver's eye point E and the highest point of the front of the fuselage shell 111 and the horizontal line meets the environmental perception requirements of the driver 801 during take-off and landing, and at the same time meets the driving and sightseeing experience requirements during air flight. The inclination angle β of the integrated display and control panel formed by the line connecting the driver's eye point E and the center point of the panel of the integrated display and control console 13 and the horizontal line should not be too large to avoid causing discomfort to the driver when bowing his head for a long time. At the same time, the distance D1 between the driver's eye point and the integrated display and control touch screen meets the requirements of clear visibility and reachability of the screen information. In the design of leg space, the distance D2 between the driver's hip point and the front baffle of the foot pedal is designed to meet the requirements of comfortable leg space extension. In the spatial design of the throttle lever 15 and the three-axis joystick 14 of the operating components, the distance D3 between the driver's shoulder point S and the three-axis joystick meets the requirements of hand grip accessibility and comfort.

[0029] Figure 4The schematic diagram of the three-axis joystick of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is shown. Specifically, the three-axis joystick 15 is arranged inside the aluminum alloy tube beam of the fuselage main structure 12 at the right side of the middle front of the cockpit, and includes a three-axis joystick handle 151, a three-axis joystick gimbal rocker 152, a three-axis joystick one-key takeoff / return landing button 153, a three-axis joystick motion mode selection button 154, a three-axis joystick whole aircraft parachute ejection button 155, a three-axis joystick photo / video button 156, a three-axis joystick voice communication button 157, and a three-axis joystick fixing support 19. Specifically, the three-axis joystick 15 also adopts a lightweight design and is specially designed to adapt to the control characteristics of a single-seat electric multi-rotor ultralight aircraft. It is arranged on the upper right side of the cockpit and is in a neutral position when there is no control. Pushing the three-axis joystick handle 151 forward makes the aircraft move forward, pulling it backward makes the aircraft move backward, pushing it to the left makes the aircraft move to the left, and pushing it to the right makes the aircraft move to the right. Holding the three-axis joystick handle 151 and turning it clockwise makes the aircraft nose turn to the right, and turning it counterclockwise makes the aircraft nose turn to the left. The head of the three-axis joystick is provided with function buttons, which can realize attitude control, recording and communication functions with one stick in normal control mode. Among them, the three-axis joystick gimbal rocker 152 can control the time pitch and heading rotation of the gimbal camera, the three-axis joystick one-key takeoff / return landing button 153 can realize the aircraft takeoff / return landing operation, the three-axis joystick motion mode selection button 154 can realize a variety of customized motion modes of the aircraft, the three-axis joystick whole aircraft parachute ejection button 155 cooperates with the throttle lever to realize the ejection life-saving function in an emergency state, the three-axis joystick photo / video button 156 realizes the gimbal camera recording function, and the three-axis joystick voice communication button 157 realizes the ground / air specific voice communication function.

[0030] Figure 5 The schematic diagram of the three-axis throttle lever of the single-seat electric multi-rotor ultralight aircraft in the embodiment of the present invention is shown. Specifically, the throttle lever 14 is arranged on the inner side of the aluminum alloy tube beam of the main fuselage structure 12 on the left side in the front center of the cockpit, and includes a throttle lever handle 141, a throttle lever shaft 1142, a throttle lever shaft 2143, and a throttle lever fixed support 120. The throttle lever handle 141, the throttle lever shaft 1142, and the throttle lever shaft 2143 are connected and fixed by the throttle lever fixed support 120. Specifically, the throttle lever 14 adopts a lightweight design, and the size optimization and weight reduction are carried out on the basis of realizing the basic functions. The throttle lever handle rotates around the lower throttle lever shaft X, and is in a neutral position when there is no manipulation. Pushing forward reduces the throttle to realize the descent of the aircraft, and pulling backward increases the throttle to realize the ascent of the aircraft.

[0031] Figure 6The schematic diagram of the whole parachute system of a single-seat electric multi-rotor ultralight aircraft in an embodiment of the invention is shown, including a whole parachute 181, a right front parachute rope ring 182, a left front parachute rope ring 183, a right rear parachute rope ring 184, a left rear parachute rope ring 185, a right front parachute rope 182-1, a left front parachute rope 183-1, a right rear parachute rope 184-1, and a left rear parachute rope 185-1. Specifically, an optional emergency whole-machine parachute 181 is arranged in the tail space of the fuselage behind the racing-grade lightweight seat 16, and four sets of parachute rope rings, a right front parachute rope ring 182, a left front parachute rope ring 183, a right rear parachute rope ring 184, and a left rear parachute rope ring 185 are respectively arranged on the upper load-bearing beams on both sides of the front, rear, left and right sides of the cockpit. The right front parachute rope 182-1, the left front parachute rope 183-1, the right rear parachute rope 184-1, and the left rear parachute rope 185-1 are arranged in accordance with the structure and shape of the aircraft. During emergency landing, the whole-machine parachute ejection hatch 113 at the tail of the fuselage behind the seat is ejected together with the main body of the whole-machine parachute 181, and then the four parachute ropes are tensioned and the aircraft lands at a low speed with the assistance of the emergency whole-machine parachute 181. When touching down, the skid-type landing gear 3 is synchronously buffered to reduce the risk of injury to the pilot 801.

Claims

1. A method for cockpit layout of a single-seat ultralight aircraft, characterized in that: In terms of functional design, the single-seat electric multi-rotor ultralight aircraft has automatic driving capabilities, and has manual stabilization mode, altitude fixation mode, point fixation mode and route flight mode; the single-seat ultralight aircraft cockpit serves as an interaction and carrying entity between the single-seat electric multi-rotor ultralight aircraft and the driver. It is used to ensure reasonable human-machine interaction space accessibility, reasonable spatial perception and flight experience vision, while realizing the driver's basic flight control functions, reliable, stable and comfortable riding functions of the air flight and the body, providing basic flight communication, navigation, identification and positioning information functions, emergency landing safety functions, and noise suppression functions; in the design of the driver's basic flight control, combined with the characteristics of the aircraft and spatial distribution, the "integrated display and control console, throttle lever, three-axis joystick" method is adopted to realize the control of the aircraft; the cockpit layout includes an integrated display and control console, throttle lever, three-axis joystick, high-strength carbon fiber racing-grade lightweight seat, five-point safety belt, foot pedals and emergency whole-machine parachute.

2. The method for cockpit layout of a single-seat ultralight aircraft according to claim 1, characterized in that: The integrated display console is arranged at the front of the cockpit, including an integrated display touch screen, integrated display button components, and integrated display support structure; the integrated display touch screen is divided into fixed information display, user-customized information display, and touch switch to realize basic flight information, power monitoring and warning, map navigation, route planning and other auxiliary information; The integrated display and control button assembly is used to realize flight function settings and auxiliary adjustment functions; the integrated display and control support structure is used to realize the connection and fixation between the integrated display and control console and the main structure of the fuselage.

3. The method for cockpit layout of a single-seat ultralight aircraft according to claim 1, characterized in that: The throttle lever adopts a lightweight design, and its size and weight are optimized on the basis of achieving basic functions. It is arranged on the inner side of the aluminum alloy tube beam on the upper left side of the cockpit through a throttle lever fixed support. The throttle lever handle rotates around the lower throttle lever shaft. It is in a neutral position when there is no operation. Pushing it forward reduces the throttle to make the aircraft descend, and pulling it backward increases the throttle to make the aircraft ascend.

4. The method for cockpit layout of a single-seat ultralight aircraft according to claim 1, characterized in that: The three-axis joystick includes a three-axis joystick handle, a three-axis joystick gimbal rocker, a three-axis joystick one-button takeoff / return landing button, a three-axis joystick motion mode selection button, a three-axis joystick whole-machine parachute ejection button, a three-axis joystick photo / video button, a three-axis joystick voice communication button, and a three-axis joystick fixed support; the three-axis joystick also adopts a lightweight design and is specifically designed to adapt to the control characteristics of single-seat electric multi-rotor ultralight aircraft. It is arranged on the upper right side of the cockpit and is in a neutral position when there is no control. Push the three-axis joystick handle forward to make the aircraft move forward, pull it back to make the aircraft move backward, push it to the left to make the aircraft move left, push it to the right to make the aircraft move right, hold the three-axis joystick handle and turn it clockwise to make the aircraft move The nose of the aircraft rotates to the right, and counterclockwise rotation can make the nose of the aircraft rotate to the left; the head of the three-axis joystick is equipped with function buttons, which can realize attitude control, recording and communication functions with one stick in normal control mode. Among them, the three-axis joystick gimbal rocker can control the pitch and heading rotation of the gimbal camera, the three-axis joystick one-key takeoff / return landing button realizes the aircraft takeoff / return landing operation, the three-axis joystick motion mode selection button can realize a variety of customized motion modes of the aircraft, the three-axis joystick whole aircraft parachute ejection button cooperates with the throttle lever to realize the ejection life-saving function in an emergency, the three-axis joystick photo / video button realizes the gimbal camera recording function, and the three-axis joystick voice communication button realizes the ground / air specific voice communication function.

5. The method for cockpit layout of a single-seat ultralight aircraft according to claim 1, characterized in that: In terms of riding function design, a high-strength carbon fiber racing-grade lightweight seat is installed in the middle of the cockpit. The seat layout ensures that the center of gravity of the driver's sitting posture is close to the center of gravity of the entire aircraft, and the driver's hip point is as close as possible to the longitudinal axis of the center of gravity of the entire aircraft to balance the power output; because the aircraft's rotor plane tilts forward during forward flight, in order to ensure human comfort and vision during forward flight and cruising, the seat is installed with a tilt backward. The rearward tilt angle of the racing-grade lightweight seat formed at this time meets the comfort and vision requirements. At the same time, this posture can reduce the impact on the human body during unpowered emergency landing; the driver's head movement circle diameter is obtained through the driver's helmet size and head movement trajectory, and the maximum distance between the driver's hip point and the head movement circle diameter provides design input for the seat design and the fuselage shell design; the driver is fixed with a five-point safety belt, which can ensure that the relative position of the driver and the aircraft is fixed during large maneuvers in the air to avoid the risk of falling; a foot pedal is provided on the lower side of the front of the cockpit to provide support for the driver's legs.

6. The method for cockpit layout of a single-seat ultralight aircraft according to claim 1, characterized in that: In terms of accessibility and field of view design, in order to ensure the driver's operating experience, the human body accessible area and field of view design analysis are carried out; the operating components are placed in the accessible area. At the same time, in order to ensure the front field of view, the height of the front part of the fuselage is lowered under the premise of ensuring the function and size of the integrated display and control console; in order to ensure the lateral field of view, the driver's head is higher than the load-bearing pipe beams on both sides of the fuselage; the downward angle formed by the line connecting the driver's eye point and the highest point of the front of the fuselage shell and the horizontal line meets the driver's environmental perception requirements during take-off and landing, and at the same time meets the driving and sightseeing experience requirements during air flight; the inclination angle of the integrated display and control panel formed by the line connecting the driver's eye point and the center point of the integrated display and control touch screen and the horizontal line should not be too large to avoid causing discomfort to the driver when bowing his head for a long time. At the same time, the distance between the driver's eye point and the integrated display and control touch screen meets the requirements of clear visibility and reachability of the screen information; in the design of leg space, the distance design between the driver's hip point and the front baffle of the foot pedal meets the requirements of comfortable leg space extension; in the space design of the throttle lever and the three-axis joystick of the operating components, the distance between the driver's shoulder point and the three-axis joystick meets the requirements of hand grip accessibility and comfort.

7. The method for cockpit layout of a single-seat ultralight aircraft according to claim 1, characterized in that: In terms of safety design, most of the human body is placed in the box-type fuselage composed of aluminum alloy frame beams, and a car-like roll cage support structure is set behind the head for protection. At the same time, the driver wears a driver's helmet to protect the head while reducing noise and providing voice communication function. In addition, an optional emergency whole-aircraft parachute is provided in the tail space of the fuselage behind the seat. The four parachute rope rings are respectively set on the upper two side load-bearing beams in front, behind, left and right of the cockpit. The ropes are arranged according to the structure and shape of the aircraft. In case of emergency landing, the tail ejection port cover of the fuselage behind the seat is ejected together with the main body of the whole-aircraft emergency parachute. Then the four parachute ropes are tensioned and the aircraft lands at a low speed with the assistance of the emergency whole-aircraft parachute. When touching down, the skid-type landing gear is used for buffering simultaneously to reduce the risk of injury to the driver.

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