Manned fixed wing multi-mode control device

Abstract

The utility model belongs to the technical field of fixed wings, and provides a manned fixed wing multi-mode control device which comprises an operation table. The mechanical control assembly is installed in the operation table, the mechanical control assembly is used for manually driving the fixed wings, the mechanical control assembly comprises a support installed in the operation table, a first linkage rod is rotationally installed at the upper end of the support, a first transmission connecting rod is rotationally installed at the front end of the first linkage rod, and a first rocker is installed at the upper end of the first linkage rod; and the intelligent control assembly is installed in the operation table, the intelligent control assembly is used for intelligently controlling the fixed wings, and the intelligent control assembly comprises a supporting frame installed in the operation table. According to the utility model, the mechanical control assembly, the intelligent control assembly, the separation assembly and the limiting assembly are integrated, and through cooperative operation of the components, diversified control modes of the fixed-wing aircraft are realized, including mechanical control, semi-automatic control and full-automatic control.

Description

Technical Field

[0001] This utility model belongs to the field of fixed-wing technology, specifically a multi-mode control device for manned fixed-wing aircraft. Background Technology

[0002] The background technology of fixed-wing aircraft has a long history, and its development has witnessed the gradual realization of humankind's dream of flight and continuous technological innovation. Fixed-wing aircraft, with their unique wing structure—that is, the wings are fixed to both sides of the fuselage and do not change shape or position with changes in flight attitude—have become the most fundamental and important component of modern aviation. With their high speed, long range, and high payload capacity, fixed-wing aircraft play an irreplaceable role in many fields, including civil aviation, military reconnaissance, cargo transportation, air rescue, scientific research, and leisure and entertainment.

[0003] While existing fixed-wing aircraft play a crucial role in the aviation field, their control modes are relatively simple, mainly relying on traditional mechanical control systems or rudimentary autopilot assistance systems. This limited control mode restricts the aircraft's flexibility and adaptability, especially in the face of complex and ever-changing flight environments and emergencies. Pilots may find it difficult to quickly adjust flight strategies, affecting flight safety and efficiency.

[0004] In terms of power, the power configurations of existing fixed-wing aircraft are usually relatively fixed, lacking the ability to dynamically adjust according to the flight phase. While strong power support is required during takeoff and climb, continuing full-power operation during cruise not only wastes energy but also increases flight costs and environmental burden. Furthermore, in the event of a power system failure, current technologies often lack effective emergency takeover mechanisms, potentially leading to flight interruptions or even accidents, seriously threatening flight safety. Utility Model Content

[0005] To address the aforementioned technical problems, this utility model provides a multi-mode control device for manned fixed-wing aircraft.

[0006] A manned fixed-wing multi-mode control device includes:

[0007] Control panel;

[0008] A mechanical control assembly, installed inside the control panel, is used for manual operation of the fixed-wing aircraft. The mechanical control assembly includes a bracket installed inside the control panel, a linkage rod rotatably mounted on the upper end of the bracket, a transmission link rotatably mounted on the front end of the linkage rod, and a rocker arm mounted on the upper end of the linkage rod.

[0009] An intelligent control component, installed inside the control panel, is used for intelligent control of the fixed wing. The intelligent control component includes a support frame installed inside the control panel. A second linkage rod is rotatably mounted on the upper end of the support frame. The front end of the second linkage rod is rotatably mounted on a second transmission link. A second rocker arm is mounted on the upper end of the second transmission link. A second support ring is mounted opposite each other at the lower end inside the control panel. A second rotating shaft passes through the second rocker arm. Both ends of the second rotating shaft are rotatably connected to two second support rings. A driven helical gear is installed at the front end of the second rotating shaft and inside the second support ring. A driving helical gear meshes with the driven helical gear. A driving component is installed at the lower end of the driving helical gear.

[0010] A separation component, installed inside the control panel, is used to divide the intelligent control component into automatic and semi-automatic driving modes. The separation component includes two guide grooves installed opposite to each other on the outside of the support ring. A moving plate and a sliding plate are slidably installed inside each of the two guide grooves. The driving component and the driving helical gear are respectively installed on the moving plate and the sliding plate. The moving plate and the sliding plate are connected by a connecting plate. A telescopic component is installed on one side inside the control panel. The output end of the telescopic component is connected to the connecting plate.

[0011] Preferably, the mechanical control assembly further includes two support rings installed opposite each other at the lower end of the inside of the operating table, and a rotating shaft passes through the inside of the rocker arm, with both ends of the rotating shaft being rotatably connected to the two support rings respectively.

[0012] Preferably, it also includes a limiting component, the limiting component including a support plate installed at the lower end of the inside of the operating table, a bidirectional component installed at the upper end of the support plate, a pressure plate installed at each of the two output ends of the bidirectional component, and a friction plate installed at one end of each of the two pressure plates.

[0013] Preferably, the two pressure plates are slidably engaged with support ring one and support ring two, and when the bidirectional component drives the pressure plates to move toward each other, the friction plate applies a radial locking force to the rotating shaft one or rotating shaft two.

[0014] A manned fixed-wing multi-mode propulsion system includes:

[0015] Fixed wing body;

[0016] The wings, which are mounted on both sides of the fixed wing body, are used to provide the lift and control required for flight;

[0017] The front-end power unit consists of two units, each located inside one of the two wings, and is used to provide thrust in the forward direction of the fuselage.

[0018] The rear-end power unit is provided in one unit and is located at the rear of the fixed wing fuselage to provide thrust to the fuselage in the forward direction.

[0019] Preferably, the front-end power component and the rear-end power component are one or more combinations of an electric motor, an internal combustion engine, or a turbine engine.

[0020] Compared with the prior art, the present invention has the following beneficial effects:

[0021] This invention integrates mechanical control components, intelligent control components, separation components, and limit components. Through their coordinated operation, it achieves diverse control modes for fixed-wing aircraft, encompassing mechanical control, semi-automatic control, and fully automatic control. The introduction of the separation component allows the aircraft to quickly switch between autopilot and semi-automatic modes, flexibly responding to various flight requirements. The ingenious design of the mechanical and intelligent control components ensures a smooth transition between manual operation and intelligent control, allowing operators to easily switch between different control modes. Simultaneously, the deep integration of mechanical transmission and intelligent control further guarantees the stability and flight safety of the aircraft in various modes.

[0022] The power unit of this invention can be flexibly adjusted according to different needs during flight phases. During takeoff and climb, all power units can operate simultaneously, providing powerful support to ensure the aircraft quickly reaches the required altitude and speed. During cruise, to save fuel and improve flight efficiency, some front-end power units can be shut down, relying solely on the rear-end power units to maintain flight. This flexible power configuration helps optimize flight performance and reduce operating costs. Furthermore, in the event of power system failure, other surviving power units can quickly take over and continue powering the fixed-wing aircraft, effectively preventing flight accidents and enhancing the aircraft's safety margin. This design is particularly suitable for long-distance flights or missions in complex weather conditions, providing pilots with greater safety assurance. Attached Figure Description

[0023] Figure 1 This is a schematic diagram of the control device of this utility model;

[0024] Figure 2 This is a schematic diagram of the first internal structure of the control device of this utility model;

[0025] Figure 3 This is a schematic diagram of the second internal structure of the control device of this utility model;

[0026] Figure 4 This is a schematic diagram of the third internal structure of the control device of this utility model;

[0027] Figure 5For the present utility model Figure 3 Enlarged view of a portion of point A in the middle;

[0028] Figure 6 For the present utility model Figure 4 Enlarged view of a section at point B in the middle;

[0029] Figure 7 This is a schematic diagram of the power device structure of this utility model.

[0030] In the picture:

[0031] 1. Control panel; 2. Mechanical control components; 21. Bracket; 22. Linkage rod one; 23. Transmission link one; 24. Rocker arm one; 25. Support ring one; 26. Rotating shaft one; 3. Intelligent control components; 31. Support frame; 32. Linkage rod two; 33. Transmission link two; 34. Rocker arm two; 35. Support ring two; 36. Rotating shaft two; 37. Driven helical gear; 38. Drive helical gear; 39. Drive component; 4. Separation component; 41. Guide groove; 42. Moving plate; 43. Sliding plate; 44. Connecting plate; 45. Telescopic component; 5. Limiting component; 51. Support plate; 52. Bidirectional component; 53. Pressure plate; 54. Friction plate; 6. Fixed wing body; 7. Wing; 8. Front power component; 9. Rear power component. Detailed Implementation

[0032] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. It should be noted that the drawings are schematic and not illustrated to scale. For clarity and convenience, the relative sizes and proportions of the parts shown in the drawings have been exaggerated or reduced in size. Any size is only illustrative and not limiting.

[0033] Example 1:

[0034] refer to Figures 1-4 This utility model provides a multi-mode control device for a manned fixed-wing aircraft, comprising:

[0035] Control panel 1;

[0036] Mechanical control component 2 is installed inside the control panel 1. Mechanical control component 2 is used for manual operation of the fixed wing. Mechanical control component 2 includes a bracket 21 installed inside the control panel 1. A linkage rod 22 is rotatably mounted on the upper end of the bracket 21. The front end of the linkage rod 22 is rotatably mounted on a transmission link 23. A rocker arm 24 is mounted on the upper end of the linkage rod 22.

[0037] The mechanical control assembly 2 also includes two support rings 25 installed at the lower end of the inside of the control panel 1, and a rotating shaft 26 is inserted inside the rocker arm 24. The two ends of the rotating shaft 26 are rotatably connected to the two support rings 25 respectively.

[0038] The intelligent control component 3 is installed inside the operating console 1. The intelligent control component 3 is used to intelligently control the fixed wing. The intelligent control component 3 includes a support frame 31 installed inside the operating console 1. A linkage rod 32 is rotatably installed on the upper end of the support frame 31. The front end of the linkage rod 32 is rotatably installed on a transmission link 33. A rocker arm 34 is installed on the upper end of the transmission link 33. A support ring 35 is installed opposite to the lower end inside the operating console 1. A rotating shaft 36 passes through the rocker arm 34. The two ends of the rotating shaft 36 are rotatably connected to the two support rings 35 respectively. A driven helical gear 37 is installed at the front end of the rotating shaft 36 and inside the support rings 35. A driving helical gear 38 meshes with the driven helical gear 37. A driving component 39 is installed at the lower end of the driving helical gear 38. The driving component 39 includes, but is not limited to, a motor.

[0039] Separation component 4 is installed inside the control panel 1. Separation component 4 is used to divide the intelligent control component 3 into automatic driving and semi-automatic driving. Separation component 4 includes two guide grooves 41 installed opposite to each other outside the support ring 35. A moving plate 42 and a sliding plate 43 are slidably installed inside the two guide grooves 41. A drive component 39 and a drive helical gear 38 are respectively installed on the moving plate 42 and the sliding plate 43. The moving plate 42 and the sliding plate 43 are connected by a connecting plate 44. A telescopic component 45 is installed on one side inside the control panel 1. The output end of the telescopic component 45 is connected to the connecting plate 44. The telescopic component 45 includes, but is not limited to, an electric telescopic rod.

[0040] Detailed implementation: The mechanical control component 2 is used to realize the manual piloting mode of the fixed-wing aircraft. The operator manually controls the aircraft using a joystick 24 on the control panel 1. The joystick 24 is connected to the support ring 25 via a rotating shaft 26. The two ends of the rotating shaft 26 are rotatably connected to the two support rings 25 respectively, allowing the joystick 24 to rotate inside the control panel 1.

[0041] When the operator pushes or pulls the joystick 24, the linkage 22 rotates accordingly, transmitting the operation signal to the control surfaces of the fixed-wing aircraft, such as the ailerons and elevators, via the transmission link 23, thereby achieving attitude control of the aircraft. The mechanical connection between the linkage 22 and the transmission link 23 ensures the accuracy and real-time nature of manual operation. When it is necessary to switch to the intelligent control mode, the mechanical control component 2 is limited by the limit component 5, and the intelligent control component 3 takes over control.

[0042] The intelligent control component 3 is used to realize the intelligent control mode of the fixed-wing aircraft, including autopilot and semi-autopilot. When the drive component 39 is activated, the drive helical gear 38 drives the driven helical gear 37 to rotate, which in turn drives the rotating shaft 36 to rotate, thereby causing the rocker arm 34 to rotate automatically, which in turn drives the linkage rod 32 to move. The linkage rod 32 transmits the control signal to the control surface of the fixed-wing aircraft through the transmission link 33, realizing the automatic control of the aircraft. The rocker arm 34, as the operating component of the intelligent control component 3, can be assisted by the operator in the semi-autopilot mode.

[0043] When a mode switch is required, the telescopic component 45 is activated, pushing or pulling the connecting plate 44, causing the moving plate 42 and the sliding plate 43 to slide within the guide groove 41. The moving plate 42 and the sliding plate 43 are respectively connected to the driving component 39 and the driving helical gear 38. The telescopic component 45 drives the connecting plate 44 to move, thereby synchronously driving the driving component 39 and the driving helical gear 38 to move, thus realizing the separation or engagement of the driving helical gear 38 and the driven helical gear 37. When the driving helical gear 38 and the driven helical gear 37 are separated, the operator participates in the semi-autonomous driving of the fixed wing through the joystick 2 34.

[0044] This device integrates mechanical control component 2, intelligent control component 3, separation component 4, and limit component 5. Through their coordinated operation, it enables diverse control modes for fixed-wing aircraft, covering mechanical control, semi-automatic control, and fully automatic control. The introduction of separation component 4 allows the aircraft to quickly switch between autopilot and semi-automatic modes, flexibly responding to various flight requirements. The ingenious design of mechanical control component 2 and intelligent control component 3 ensures a smooth transition between manual operation and intelligent control, allowing operators to easily switch between different control modes. Simultaneously, the deep integration of mechanical transmission and intelligent control further guarantees the stability and flight safety of the aircraft in various modes.

[0045] refer to Figure 5 It also includes a limiting component 5, which includes a support plate 51 installed at the lower end of the inside of the operating table 1. A bidirectional component 52 is installed on the upper end of the support plate 51. A pressure plate 53 is installed on both output ends of the bidirectional component 52, and a friction plate 54 is installed on one end of each pressure plate 53.

[0046] The two pressure plates 53 are slidably engaged with the support ring 25 and the support ring 35. When the bidirectional component 52 drives the pressure plates 53 to move towards each other, the friction plate 54 applies a radial locking force to the rotating shaft 26 or the rotating shaft 36. The bidirectional component 52 includes, but is not limited to, a non-synchronous bidirectional telescopic cylinder.

[0047] Detailed implementation: When switching to manual driving mode, the bidirectional component 52 drives the pressure plate 53 near the rotating shaft 36 to move inside the support ring 35, thereby causing the friction plate 54 at that end to slide inward and abut against the rotating shaft 36 of the intelligent control component 3. At this time, the rotating shaft 36 is fixed, and the intelligent control component 3 cannot drive the transmission link 33, thus avoiding interference between the automatic driving signal and manual operation.

[0048] When switching to automatic or semi-automatic driving mode, the bidirectional component 52 drives the pressure plate 53 near the section of the rotating shaft 26 to move inside the support ring 25, so that the friction plate 54 at this end abuts against the rotating shaft 26 of the mechanical control component 2, locking the mechanical transmission of the rocker arm 24 and preventing manual operation from interfering with intelligent control.

[0049] Example 2:

[0050] refer to Figure 6 This utility model provides a multi-mode power device for manned fixed-wing aircraft, comprising:

[0051] Fixed wing body 6;

[0052] Wings 7 are mounted on both sides of the fixed wing body 6 and are used to provide the lift and control required for flight;

[0053] The front-end power unit 8 consists of two units, each located inside one of the two wings 7, and is used to provide thrust in the forward direction of the fuselage.

[0054] The rear-end power unit 9 is provided in one unit and is located at the rear of the fixed wing body 6. It is used to provide thrust to the airframe in the forward direction.

[0055] The front-end power unit 8 and the rear-end power unit 9 are one or more combinations of electric motors, internal combustion engines or turbine engines.

[0056] Detailed implementation: This power unit integrates a front-end power component 8 and a rear-end power component 9, which together provide stable and flexible flight power for the fixed wing body 6. The wings 7 are mounted on both sides of the fixed wing body 6.

[0057] In terms of power configuration, this power unit employs three power units, including two forward power units 8 and one rear power unit 9. The two forward power units 8 are respectively located inside the two wings 7, and their main function is to provide forward thrust to the fixed wing, enabling it to overcome air resistance and maintain a stable flight speed. The rear power unit 9 is located at the rear of the fixed wing body 6, and it also provides forward thrust to the fixed wing. Working in conjunction with the forward power units 8, they propel the fixed wing forward.

[0058] These three power units can be flexibly adjusted according to flight requirements. During takeoff and climb, the front power unit 8 and the rear power unit 9 may operate simultaneously to provide sufficient power for the aircraft to quickly reach the required altitude and speed. During cruise, to save fuel and improve flight efficiency, one or two of the front power units 8 may be shut down, relying solely on the rear power unit 9 to maintain flight. Furthermore, in the event of a power system failure, the other surviving power units can serve as backups, continuing to power the fixed-wing aircraft and thus enhancing its safety margin.

[0059] This power plant can be flexibly adjusted according to the different needs of each flight phase. During takeoff and climb, all power units can operate simultaneously, providing powerful support to ensure the aircraft quickly reaches the required altitude and speed. During cruise, to save fuel and improve flight efficiency, some front-end power units can be shut down, relying solely on the rear-end power units to maintain flight. This flexible power configuration helps optimize flight performance and reduce operating costs. Furthermore, in the event of power system failure, other surviving power units can quickly take over and continue to power the fixed-wing aircraft, effectively preventing flight accidents and enhancing the aircraft's safety margin. This design is particularly suitable for long-distance flights or missions in complex weather conditions, providing pilots with greater safety assurance.

[0060] All standard parts used in this invention can be purchased from the market, and irregularly shaped parts can be customized according to the description and drawings. The specific connection methods for each part all employ conventional methods such as bolts, rivets, and welding, which are mature technologies in the prior art. The machinery, parts, and equipment all use conventional models in the prior art, and the circuit connections also use conventional connection methods in the prior art, which will not be detailed here. Any content not described in detail in this specification belongs to the prior art known to those skilled in the art.

[0061] In the description of this utility model, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. "A plurality of" means two or more, unless otherwise explicitly specified.

[0062] In this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0063] In this utility model, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "on top of," and "over" the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0064] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0065] The accompanying drawings of the embodiments disclosed in this utility model only involve the structures involved in the embodiments disclosed in this utility model. Other structures can refer to the general design. In the absence of conflict, the same embodiment and different embodiments of the present invention can be combined with each other.

[0066] Although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art can still modify the technical solutions described in the foregoing embodiments or make equivalent substitutions for some of the technical features. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A manned fixed-wing multi-mode control device, characterized by: The utility model relates to a kind of unmanned aerial vehicle control device, including: Operation platform (1); Mechanical control component (2) is installed in operation platform (1) inside, the mechanical control component (2) is used to drive fixed wing manually, the mechanical control component (2) includes support (21) installed in operation platform (1) inside, linkage rod one (22) is rotatably installed on the upper end of support (21), linkage rod one (22) front end is rotatably installed in transmission connecting rod one (23), linkage rod one (22) upper end is installed with rocker one (24); Intelligent control component (3) is installed in operation platform (1) inside, the intelligent control component (3) is used to control fixed wing intelligently, the intelligent control component (3) includes support frame (31) installed in operation platform (1) inside, linkage rod two (32) is rotatably installed on the upper end of support frame (31), linkage rod two (32) front end is rotatably installed in transmission connecting rod two (33), transmission connecting rod two (33) upper end is installed with rocker two (34), operation platform (1) inside lower end is oppositely installed with support ring two (35), rotating shaft two (36) is arranged in the inside of rocker two (34), rotating shaft two (36) both ends are rotatably connected with two support ring two (35), driving bevel gear (37) is installed in the front end of rotating shaft two (36) and the inside of support ring two (35), driving bevel gear (37) is engaged with driving bevel gear (38) outside, driving member (39) is installed in the lower end of driving bevel gear (38); Separation component (4) is installed in operation platform (1) inside, the separation component (4) is used to separate intelligent control component (3) into automatic driving and semi-automatic driving, the separation component (4) includes two guide grooves (41) oppositely installed in the outside of support ring two (35), two guide grooves (41) are slidably installed with moving plate (42) and sliding plate (43) inside, driving member (39) and driving bevel gear (38) are installed in moving plate (42) and sliding plate (43) respectively, moving plate (42) and sliding plate (43) are connected by connecting plate (44), telescopic piece (45) is installed in one side of operation platform (1) inside, and the output end of telescopic piece (45) is connected with connecting plate (44).

2. The manned fixed-wing multi-mode control system of claim 1, wherein: The mechanical control component (2) further includes two support rings one (25) oppositely installed in the lower end of operation platform (1), rotating shaft one (26) is arranged in the inside of rocker one (24), and rotating shaft one (26) both ends are rotatably connected with two support rings one (25).

3. The manned fixed-wing multi-mode control system of claim 1, wherein: Further including limiting component (5), the limiting component (5) includes support plate (51) installed in the lower end of operation platform (1), two-way piece (52) is installed on the upper end of support plate (51), pressure plate (53) is installed on the two output ends of two-way piece (52), and one end of two pressure plates (53) is installed with friction plate (54).

4. The manned fixed-wing multi-mode control system of claim 3, wherein: Two said pressing plates (53) and support ring one (25), support ring two (35) sliding fit, and when the bidirectional piece (52) drive pressing plate (53) move towards, the friction plate (54) to rotating shaft one (26) or rotating shaft two (36) exert radial locking force.

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