Compound-wing aircraft and control system therefor

Abstract

A compound-wing aircraft (10) and a control system therefor. Flight modes of the compound-wing aircraft (10) comprise a vertical take-off and landing mode, a cruise mode, and a transition mode. The control system comprises a control module (1) and a flight control module (2). The control module (1) comprises at least a first control device (11) and a second control device (12) which can be operated by a user. The first control device (11) is movable along a range, and sends different instructions to the flight control module (2) at different positions in the range, so as to respectively complete flight actions of the compound-wing aircraft (10) in the various flight modes. The second control device (12) is movable along each of a plurality of different directions, and sends different instructions to the flight control module (2) in different directions, the instructions being respectively used for controlling flight parameters of the compound-wing aircraft (10) in the various modes. The second control device (12) controls the speed or attitude of the compound-wing aircraft (10) while the first control device (11) is operated. The control system enables effective control of the compound-wing aircraft (10) in a plurality of flight modes, with simple operation.

Description

Composite wing aircraft and its control system TECHNICAL FIELD

[0001] The present application relates to the field of aircraft technology, in particular to a composite wing aircraft and its control system. BACKGROUND

[0002] The composite wing aircraft includes multiple flight modes, and different control buttons need to be used when controlling different flight modes, thus increasing the degree of operation complexity, and there is an urgent need to design a control system that can control the flight process of different modes, so as to have the characteristics of high safety and simple operation. SUMMARY

[0003] The purpose of the present application is to provide a composite wing aircraft and its control system, and the operation system of the present application realizes effective control of the composite wing aircraft in multiple flight modes, and the operation is simple.

[0004] To solve the above technical problems, the present application provides a flight control system for controlling the flight height and flight mode of an aircraft, the flight mode of the aircraft including vertical take-off and landing mode, cruising mode and conversion mode, the control system including a control module and a flight control module, the control module including at least one first control device and one second control device, the first control device being movable along a range, different positions in the range sending different instructions to the flight control module to complete the flight action of the aircraft in each flight mode; the second control device being movable along multiple different directions, the different directions sending different instructions to the flight control module to control the flight parameters of the aircraft in the vertical take-off and landing mode, the flight parameters of the aircraft in the conversion mode, and the flight parameters of the aircraft in the cruising mode, and the speed or attitude of the aircraft being controlled at the same time as the first control device is controlled.

[0005] Optionally, the second control device has different control mappings in each flight mode when moving along multiple different directions.

[0006] Optionally, in the vertical take-off and landing mode, when the second control device moves along the front-back direction, the aircraft moves forward and backward; and when the second control device moves along the left-right direction, the aircraft moves left and right.

[0007] Optionally, in the cruising mode and the conversion mode, when the second control device moves along the front-back direction, the aircraft changes the flight height; and when the second control device moves along the left-right direction, the aircraft changes the yaw angular velocity to realize coordinated turning.

[0008] Optionally, the second control device is further provided with a cap-shaped button, the cap-shaped button can be pressed in multiple directions to send different instructions to the flight control module for controlling the flight parameters of the aircraft in different modes, and the cap-shaped button has different control mappings in different flight modes when pressed in multiple directions.

[0009] Optionally, in the VTOL mode, when the cap-shaped button is pressed in the front-back direction, the aircraft changes the flight height; when the cap-shaped button is pressed in the left-right direction, the aircraft changes the yaw angular velocity to realize coordinated turning.

[0010] Optionally, in the cruise mode, when the cap-shaped button is pressed in the front-back direction, the aircraft changes the cruise speed.

[0011] Optionally, the range includes at least a first position, a second position, and a third position; the first position represents the airport elevation of the aircraft; the second position represents the transition height of the aircraft; the third position represents the cruise height of the aircraft; when the first control device is in the first position, the first instruction is sent to the flight control module to make the aircraft land to the airport elevation; when the first control device is in the third position, the third instruction is sent to the flight control module to make the aircraft rise to the cruise height.

[0012] Optionally, in the range, a plurality of points are distributed between the first position and the second position, representing different heights of the aircraft relative to the ground in the VTOL mode, and a plurality of points are distributed between the second position and the third position, representing different heights of the aircraft relative to the ground in the cruise mode.

[0013] Optionally, when the first instruction is sent to the flight control module, the flight control module controls the aircraft to land from the cruise mode to the airport elevation, and the flight control module automatically and gradually controls the aircraft to enter the transition mode first and then enter the VTOL mode.

[0014] Optionally, when the third instruction is sent to the flight control module, the flight control module controls the aircraft to rise from the VTOL mode or stay on the ground to the cruise height, and the flight control module automatically and gradually controls the aircraft to enter the transition mode first and then enter the cruise mode.

[0015] Optionally, the second control device is further provided with a backup key, which can be used as a backup of the second control device. The backup key can be moved in different directions to send different instructions to the flight control module, respectively for controlling the flight parameters of the aircraft in the VTOL mode, the transition mode, and the cruising mode, while the first control device is being controlled.

[0016] Optionally, the second control device is further provided with a backup mode switching key, which is used to switch the aircraft to a backup control mode: when the aircraft is in the VTOL mode, the second control device is moved in the front-back direction to control the pitch angle of the aircraft, and is moved in the left-right direction to control the roll angle of the aircraft; when the aircraft is in the cruising mode and the transition mode, the second control device is moved in the front-back direction to control the pitch angle of the aircraft, and is moved in the left-right direction to control the yaw angular velocity of the aircraft.

[0017] The operating system of the present application realizes effective control of the compound wing aircraft in multiple flight modes, and the operation is simple. BRIEF DESCRIPTION OF DRAWINGS

[0018] FIG. 1 shows a schematic diagram of the modules of the compound wing aircraft according to an embodiment of the present application;

[0019] FIG. 2 shows a schematic diagram of the structure of the first control device according to an embodiment of the present application;

[0020] FIG. 3 shows a top view of the second control device according to an embodiment of the present application;

[0021] FIG. 4 shows a schematic diagram of the flight routes of the aircraft in different modes according to an embodiment of the present application;

[0022] FIG. 5 shows a schematic diagram of the structure of the second control device according to an embodiment of the present application;

[0023] FIG. 6 shows a schematic diagram of the cap-shaped key of the second control device according to an embodiment of the present application;

[0024] FIG. 7 shows a schematic diagram of the structure of the second control device according to an embodiment of the present application. DETAILED DESCRIPTION

[0025] The following embodiments further illustrate the technical solutions of the present application. It can be understood that the specific embodiments described herein are only used to explain the present application. In addition, it should be noted that, for the purpose of description, only parts related to the present application are shown in the drawings, not all.

[0026] In the description of the present application, it is necessary to point out that unless specifically defined and limited otherwise, the terms "mounting", "connected", "connection" should be understood broadly, for example, it can be fixed connection, or detachable connection; it can be mechanical connection, or electrical connection; it can be direct connection, or indirect connection through intermediate medium, or internal connection of two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0027] In the present application, unless specifically defined and limited otherwise, the first feature "on" or "under" the second feature can include that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact through another feature between them. Moreover, the first feature "on", "above" and "over" the second feature includes that the first feature is directly above and obliquely above the second feature, or only indicates that the horizontal height of the first feature is higher than that of the second feature. The first feature "under", "below" and "under" the second feature includes that the first feature is directly below and obliquely below the second feature, or only indicates that the horizontal height of the first feature is less than that of the second feature.

[0028] In the present application, the vertical take-off and landing mode can be realized by any known machine type and driving method, for example, multi-rotor, single screw (such as helicopter), jet, etc. The present application particularly includes all such machine types and driving methods, or their combinations. The cruise mode can be realized by any known machine type and driving method, for example, fixed wing, multi-rotor, single screw (such as helicopter), jet, etc. Similarly, the present application particularly includes all such machine types and driving methods, or their combinations.

[0029] In the present application, the vertical take-off and landing mode can be described as a multi-rotor mode in some embodiments. It is particularly noted that when described as a multi-rotor mode, it is not limited to only multi-rotor, but can also be described as other machine types and driving methods.

[0030] In the present application, the cruise mode can be described as a fixed wing mode. It is particularly noted that when described as a fixed wing mode, it is not limited to only fixed wing, but can also be described as other machine types and driving methods.

[0031] The flight mode of the compound wing aircraft includes vertical take-off and landing mode, cruise mode and conversion mode. In the vertical take-off and landing mode, after the compound wing aircraft generates airspeed, the rotor motor rotates slowly to generate lift, and after reaching a certain airspeed, the lift is generated by the fixed wing, and the aircraft is switched to the cruise mode; in the cruise mode, the tail propeller serves as the forward thrust of the aircraft, and the fixed wing provides lift, and the rotor motor is no longer needed to provide lift.

[0032] The embodiments of the present application provide a kind of aircraft control system, as shown in Figures 1-3, the control system of composite wing aircraft 10 includes: control module 1 and flight control module 2.Control module 1 includes a first control device 11 and a second control device 12, first control device 11 and second control device 12 can be controlled by user. First control device 11 can be moved along a range, different positions in the range to send different instructions to flight control module 2, respectively complete the flight action of composite wing aircraft 10 in each flight mode, that is, from vertical take-off mode, through conversion mode, into cruise mode, or from cruise mode, through conversion mode, into vertical take-off mode.

[0033] Different positions in the movable range of first control device 11 include at least first position A, second position B and third position C. First control device 11 includes a base 110 and a handle 111 rotatably attached to the base 110, the handle 111 can be rotated back and forth around the base 110 from A point to C point range. First position A represents the airport elevation of the aircraft. Second position B represents the conversion height of the aircraft; third position C represents the cruise height of the aircraft. When first control device 11 is at first position A, first instruction is sent to flight control module 2, so that the aircraft lands to the airport elevation. When first control device 11 is at third position C, third instruction is sent to flight control module 2, so that the aircraft rises to the cruise height.

[0034] In the above range, many points are distributed between first position A and second position B, representing different heights of the aircraft to the ground in the vertical take-off mode. Many points are distributed between second position B and third position C, representing different heights of the aircraft to the ground in the cruise mode. It should be noted that the area between the two second positions B in the figure represents the conversion mode between the vertical take-off mode and the cruise mode, and the handle 111 of the first control device 11 cannot stay in the conversion area.

[0035] Now refer to Figure 4, which shows the flight path of the aircraft in each state mode. When the handle 111 of the first control device 11 is directly pushed from 0 degrees to 180 degrees (for example, the first control device is directly pushed from 0 degrees to 180 degrees within a few seconds), the aircraft enters the vertical take-off mode from the position P0, slowly rises, experiences the routes F1 and F2, until it rises to the P2 point, and then enters the positive conversion mode. It should be noted that during the conversion process, the height of the aircraft to the ground does not change, but the aircraft converts along the route F3 in the figure until the position P3 completes the conversion mode, and then enters the climb phase. When climbing to the position P4, the aircraft enters the fixed-wing cruise mode, and the aircraft starts cruising.

[0036] While the first control 11 is operated, the second control 12 can also be operated to control the speed or attitude of the aircraft. As shown in Fig. 3, the second control 12 is a dual-channel rocker, which can be moved in different directions to send different instructions to the flight control module 2 for controlling the flight parameters of the aircraft in the VTOL mode, the transition mode and the cruising mode, respectively, while the first control 11 is operated.

[0037] The second control 12 has different control mappings in different flight modes when it is moved in different directions. Specifically, when the first control 11 is operated to make the aircraft enter the VTOL mode, the second control 12 is moved in the front-back direction to control the corresponding front-back movement of the aircraft, and the second control 12 is moved in the left-right direction to control the corresponding left-right movement of the aircraft.

[0038] When the first control 11 is operated to make the aircraft enter the transition mode or ascend to the cruising height, the second control 12 can also be moved in the front-back direction to control the aircraft to change the flight height in the cruising mode and the transition mode. For example, the second control 12 is moved forward to control the aircraft to ascend to break through the previous maximum cruising height. Correspondingly, the second control 12 is moved backward to control the aircraft to descend.

[0039] In addition, when the first control 11 is operated to make the aircraft ascend to the cruising height in the cruising mode and the transition mode, the second control 12 can also be moved in the left-right direction to control the aircraft to change the yaw rate to realize coordinated turning, and the greater the turning amplitude, the greater the yaw rate. For example, the second control 12 is moved leftward to control the aircraft to yaw leftward. The second control 12 is moved rightward to control the aircraft to yaw rightward.

[0040] Further, as shown in Figs. 5 and 6, the second control 12 is also provided with a cap-shaped button 121, which can be pressed in different directions to send different instructions to the flight control module 2 for controlling the flight parameters of the aircraft in different modes. The cap-shaped button 121 has different control mappings in different flight modes when it is pressed in different directions. In the VTOL mode, the cap-shaped button 121 is pressed in the front-back direction to control the aircraft to change the flight height. The second control 12 adds the cap-shaped button 121 to control the height of the aircraft, which can be used as a backup control channel to increase the safety factor.

[0041] When the cap-shaped button 121 is pressed in the left-right direction, the control aircraft changes the yaw angle velocity to realize coordinated turning. In the cruising mode, when the cap-shaped button 121 is pressed in the front-back direction, the control aircraft changes the cruising speed. In this case, the second control device 12 adds the yaw control of the cap-shaped button 121 to the aircraft, which can be used as a backup control channel to increase the safety factor.

[0042] The second control device 12 is also provided with a backup button 122, which can be used as a backup of the different control mappings of the second control device 12 in different flight modes to cope with the failure of the front-back and left-right control of the second control device 12. The backup button 122 can be moved in multiple front-back and left-right directions to send different instructions to the flight control module 2, which are respectively used to control the flight parameters of the aircraft in the vertical take-off and landing mode, the flight parameters in the transition mode, and the flight parameters in the cruising mode, and control the speed or attitude of the aircraft.

[0043] The second control device 12 is also provided with a backup mode switching button 123 for switching the aircraft to a backup control mode: when the aircraft is in the vertical take-off and landing mode, the second control device 12 is moved in the front-back direction to control the pitch angle of the aircraft, and is moved in the left-right direction to control the roll angle of the aircraft. When the aircraft is in the cruising mode and the transition mode, the second control device 12 is moved in the front-back direction to control the pitch angle of the aircraft, and is moved in the left-right direction to control the yaw angle velocity of the aircraft. When the navigation data (such as speed information) is insufficient, the control mode can be switched to the backup control mode through the backup mode switching button to cope with the control failure caused by the lack of information.

[0044] The operation system of the present application realizes effective control of the compound wing aircraft in multiple flight modes, and the operation is simple.

[0045] As shown in FIG. 7, in one embodiment, the second control device 12 is also provided with an alarm clearing button 124 for turning off part of the alarm sound prompts. In one embodiment, the second control device 12 is also provided with a response trigger 125 for turning on the microphone when the pilot communicates with the ground crew or the tower.

[0046] The second embodiment of the present application provides a compound wing aircraft, as shown in FIG. 1, which comprises the above-mentioned control system. The control system comprises a control module 1 and a flight control module 2. The operation system of the compound wing aircraft of the second embodiment of the present application realizes effective control of the compound wing aircraft in multiple flight modes, and the operation is simple.

[0047] The above examples are merely illustrative of the principles of the application and its best mode. Numerous modifications and changes will be readily apparent to those skilled in the art, and it is intended to embrace all such modifications and changes that fall within the scope of the application as set forth in the claims.

Claims

1. An aircraft handling system for controlling a flight altitude and a flight mode of an aircraft, the flight mode of the aircraft including a vertical take-off and landing mode, a cruising mode and a transition mode, characterized in that, The control system comprises a control module and a flight control module, the control module comprises at least a first control device and a second control device, which can be controlled by a user; The first control device can be moved along a range, and different positions in the range send different instructions to the flight control module, respectively completing the flight action of the aircraft in each flight mode; The second control device can be moved along multiple different directions, and different directions send different instructions to the flight control module, respectively used for controlling the flight parameters of the aircraft in the vertical take-off and landing mode, the transition mode, and the cruising mode, and controlling the speed or attitude of the aircraft while the first control device is controlled.

2. The aircraft control system according to claim 1, wherein, The second control device moves along multiple different directions in each flight mode and has different control mappings.

3. The aircraft control system according to claim 1, wherein, In the vertical take-off and landing mode, when the second control device moves along the front-back direction, the aircraft moves forward and backward; when the second control device moves along the left-right direction, the aircraft moves left and right.

4. The aircraft control system according to claim 1, wherein, In the cruising mode and the transition mode, when the second control device moves along the front-back direction, the aircraft changes the flight height; when the second control device moves along the left-right direction, the aircraft changes the yaw angular velocity to realize coordinated turning.

5. The aircraft control system according to claim 1, wherein, The second control device is also provided with a cap-shaped button, which can be pressed along multiple directions to send different instructions to the flight control module, used for controlling the flight parameters of the aircraft in each mode, and the cap-shaped button has different control mappings when pressed along multiple directions in each flight mode.

6. The aircraft control system according to claim 5, wherein, In the vertical take-off and landing mode, when the cap-shaped button is pressed along the front-back direction, the aircraft changes the flight height; when the cap-shaped button is pressed along the left-right direction, the aircraft changes the yaw angular velocity to realize coordinated turning.

7. The aircraft control system according to claim 5, wherein, In the cruising mode, when the cap-shaped button is pressed along the front-back direction, the aircraft changes the cruising speed.

8. The aircraft control system according to claim 1, wherein, Different positions in the range at least include a first position, a second position, and a third position; The first position represents the airport elevation of the aircraft; the second position represents the transition height of the aircraft; The third position represents the cruising height of the aircraft; When the first control device is at the first position, a first instruction is sent to the flight control module, so that the aircraft lands to the airport elevation; when the first control device is at the third position, a third instruction is sent to the flight control module, so that the aircraft rises to the cruising height.

9. The aircraft control system according to claim 8, wherein, In the range, many points are distributed between the first position and the second position, representing different heights of the aircraft relative to the ground in the vertical take-off and landing mode, and many points are distributed between the second position and the third position, representing different heights of the aircraft relative to the ground in the cruising mode.

10. The aircraft control system according to claim 8, wherein, When the first instruction is sent to the flight control module, the flight control module controls the aircraft to descend from the cruising mode to the airport level, and the flight control module automatically and gradually controls the aircraft to enter the transition mode first and then enter the vertical take-off and landing mode.

11. The aircraft control system according to claim 8, wherein, When the third instruction is sent to the flight control module, the flight control module controls the aircraft to ascend to the cruising height from the vertical take-off and landing mode or when staying on the ground, and the flight control module automatically and gradually controls the aircraft to enter the transition mode first and then enter the cruising mode.

12. The aircraft control system according to claim 1, wherein, The second control device is further provided with a backup button, which can be used as a backup of the second control device, and the backup button can be moved in different directions to send different instructions to the flight control module, respectively used to control the flight parameters of the aircraft in the vertical take-off and landing mode, the transition mode and the cruising mode, and control the speed or attitude of the aircraft while the first control device is controlled.

13. The aircraft control system according to claim 1, wherein, The second control device is further provided with a backup mode switching button, which is used to switch the aircraft to a backup control mode: when the aircraft is in the vertical take-off and landing mode, the second control device is moved in the front-back direction to control the pitch angle of the aircraft, and is moved in the left-right direction to control the roll angle of the aircraft; when the aircraft is in the cruising mode and the transition mode, the second control device is moved in the front-back direction to control the pitch angle of the aircraft, and is moved in the left-right direction to control the yaw angular velocity of the aircraft.

14. A compound wing aircraft characterized by, The control system as claimed in any one of claims 1-13.

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