Aircraft head wing

Abstract

The invention provides an aircraft head wing which comprises a head wing body and an actuating device, the head wing body is arranged on the outer side of the head of an aircraft body, the head wing body is connected with the actuating device, and the actuating device can drive the head wing body to swing up and down. The aircraft head wing is placed at the front end of an aircraft, the aircraft head wing of a special structure and a new aircraft layout mode are formed, meanwhile, the control distance for a driver to control an airfoil actuating device is shortened, the control response is fast, and the manufacturing cost is low. The invention can be widely applied to aircrafts, is particularly suitable for small commercial aircrafts flying at low altitude, and is particularly suitable for being matched with fixed wings with multi-section joint structures for use.

Description

Technical Field

[0001] The invention relates to a fixed-wing aircraft, in particular to an aircraft head wing. Background Art

[0003] Traditional aircraft wings include fixed wings, rotary wings, rotors, tilt-rotor wings, multi-rotor wings, flapping wings, etc. The fixed wings of an aircraft generate lift for the aircraft, and the flapping wings achieve lift and control the flight posture by flapping up and down; fixed wings are mostly used on large aircraft for long-distance flights, and flapping wings are bionic models. The continuous improvement and application of these wings are all for the purpose of further improving the flexibility and maneuverability of aircraft flight on the basis of making the aircraft fly more smoothly.

[0004] The pitch function, stability and directional balance of traditional fixed-wing aircraft are achieved through the tail of the aircraft. The tail enables the aircraft to maintain pitch stability and directional balance, giving the aircraft a pitch function while ensuring the aircraft's directional stability and maneuverability. The fixed wings of traditional fixed-wing aircraft are mostly integrated structures, with ailerons and other operating surfaces on the fixed wings to achieve various control functions of the aircraft. This traditional aircraft uses ailerons and other control surfaces on the fixed wings to adjust the control surface, which has a small control area, small force, and poor maneuverability.

[0005] The tail of a traditional fixed-wing aircraft is installed at the rear of the aircraft for stability and control. The tail is generally divided into a vertical tail and a horizontal tail. There is a rudder at the rear of the vertical tail and an elevator at the rear of the horizontal tail. The tail of a traditional fixed-wing aircraft is installed at the rear of the aircraft. The pilot has a long control distance to control the wing surface actuator, the control mechanism is long and complex, the response is slow, and the manufacturing cost is high.

[0006] The fixed wing of the carrier-based aircraft can fold the outermost part of the fixed wing to reduce the volume and realize centralized storage. However, when taking off, the outermost fixed wing is opened to form a horizontal integrated wing and then locked to achieve takeoff and cruising. The purpose of the foldable and flippable storage of this wing is to reduce the volume and facilitate centralized storage. It becomes fixed again during flight, and there is no difference between it and the fixed wing of traditional fixed-wing aircraft during flight.

[0007] The application number is 202410653974.3, the application date is May 24, 2024, and the invention name is "A high-bionics bird-like flapping-wing aircraft and its use method". The disclosed bird-like flapping-wing aircraft optimizes aerodynamic performance and improves energy utilization through the bird-like appearance formed by the cooperation of a bionic body, a bionic tail, a bionic wing and a bionic head. The bionic wings can imitate the folding function of bird wings and the "8" trajectory movement of the wingtips, imitating the flying movements of birds, greatly improving the bionics. The climbing mechanism can enable the bird-like flapping-wing aircraft to flexibly climb on a rod-like object, thereby improving the environmental adaptability of the bird-like flapping-wing aircraft. However, the patent of this highly biomimetic bird-like flapping-wing aircraft and its use method discloses that the bionic wing provides lift, and at the same time, the bionic wing also provides the function of changing the flapping speed, flapping angle, and flapping posture, so as to adjust the aircraft's posture. While providing flight power, this flapping wing also controls the aircraft's posture. Its structure is complex. Compared with fixed-wing aircraft, it is difficult to achieve long-distance, long-endurance, and high-speed flight. Its load capacity is also limited, making it difficult to carry a large load and difficult to achieve manned flight. Summary of the invention

[0009] In view of the above technical problems, the present invention provides a fixed-wing aircraft with an articulated structure. A main propeller is arranged at the tail of the fuselage of the aircraft. The fixed wing of the fixed-wing aircraft with an articulated structure is a multi-section articulated structure. The flight power of the aircraft mainly comes from the thrust of the main propeller, and the lift of the flight mainly comes from the fixed wing. Because the fixed wing of the aircraft is an articulated structure fixed wing, the lift of the aircraft can be changed conveniently by adjusting the angles of different active wing sections of the wing in sections, thereby adjusting the aerodynamic changes of the wing, realizing the control of various flight postures of the aircraft, with a large control area, large acting force, and good maneuverability of the aircraft.

[0010] At the same time, the invention provides an aircraft nose wing. The fixed-wing aircraft with an articulated structure is provided with a nose wing at the front end of the aircraft. The nose wing is placed at the front end of the aircraft, forming an aircraft nose wing with a special structure and a new aircraft layout method. At the same time, the control distance of the pilot to control the wing surface actuator is shortened, the control response is fast, and the manufacturing cost is low.

[0011] The articulated fixed-wing aircraft is a brand-new layout structure, which is a more energy-saving, fast, stable and convenient means of transportation. It can use traditional take-off and landing methods to achieve take-off and landing of the aircraft, and can also be used in conjunction with the continuous rotation device disclosed in the application number 2024103467476, the application date is March 26, 2024, and the invention name is "Aircraft with tires and landing mechanisms removed and taking off and landing using a continuous rotation device". The aircraft landing gear is removed to achieve rapid take-off and landing on the continuous rotation device. The use of this articulated fixed-wing aircraft and the continuous rotation device is particularly suitable for low-altitude flying aircraft, achieving a more energy-saving, fast, stable and convenient flight travel purpose.

[0012] The head wing of the aircraft controls the pitching movement of the aircraft. The head wing and the joint structure fixed wing cooperate to achieve high maneuverability control of the aircraft. The joint structure fixed wing has a large control area and a large force. Its rapid change can quickly respond to the impact of the low-altitude troposphere, improve the stability of the aircraft flight, and improve the comfort of riding. During takeoff and landing, the angle of the joint structure fixed wing can be changed to achieve assist during takeoff and cushioning during landing. The aircraft can realize unmanned flight, manned flight, and cargo transportation, because it is still a fixed-wing aircraft with a special structure, which can realize long-distance cruising and long-duration flight, and large load capacity.

[0013] The invention provides a fixed-wing aircraft with an articulated structure, which solves the technical problem that traditional fixed-wing aircraft are difficult to realize high maneuverability control, and also solves the technical problem that flapping-wing aircraft are difficult to realize manned, high-load flight and long-distance flight.

[0014] To this end, the technical solution of the present invention is an aircraft head wing, including a head wing and an actuating device, wherein the head wing is arranged on the outside of the head of the aircraft fuselage, the head wing is connected to the actuating device, and the actuating device can drive the head wing to swing up and down.

[0015] Preferably, the head wing includes a right horizontal wingspan and a left horizontal wingspan, the right horizontal wingspan and the left horizontal wingspan are connected to form a horizontal wingspan of an integrated structure, the head wing also includes an upper vertical wingspan and a lower vertical wingspan, the upper vertical wingspan and the lower vertical wingspan are connected to form a vertical wingspan of an integrated structure, the horizontal wingspan and the vertical wingspan are vertically intersected, and the vertical wingspan is located in the middle of the horizontal wingspan; The outer surface of the head of the fuselage is a spherical arc surface; The outer edges of the right horizontal wing span and the left horizontal wing span are pointed rounded structures, and the outer surfaces of the right horizontal wing span and the left horizontal wing span extending to the other side are curved structures; the curved structures are smoothly transitioned and connected with the spherical curved surface of the outer surface of the head of the fuselage; The upper and lower peripheral edges of the upper vertical wing span and the lower vertical wing span are pointed rounded structures, and the outer surfaces of the upper vertical wing span and the lower vertical wing span extending to the other side are curved structures; the curved structures are smoothly connected with the spherical curved surface of the outer surface of the head of the fuselage.

[0016] Preferably, the inner side of the head wing is a spherical arc surface structure, and the spherical arc surface structure can rotate around the spherical arc surface of the head outer surface of the fuselage.

[0017] Preferably, a spherical base is provided on the inner side of the head wing, the outer surface of the spherical base is a spherical arc surface, and the horizontal wingspan and the vertical wingspan are smoothly transitionally connected to the spherical arc surface of the outer surface of the spherical base.

[0018] Preferably, the outer surface of the spherical base on the side close to the aircraft head is also a spherical arc surface, and the spherical arc surface can rotate around the spherical arc surface of the outer surface of the head of the fuselage.

[0019] Preferably, a through hole is provided at the front end of the fuselage, an actuating rod is fixedly provided on the inner side of the head wing, the actuating rod passes through the through hole and is connected to the actuating device, one end of the actuating device is fixed on the fuselage; the actuating device can drive the actuating rod to swing up and down, and the actuating rod drives the head wing to swing up and down.

[0020] Preferably, the end of the actuating rod is hinged to the fuselage, the actuating device is a hydraulic cylinder, and the hydraulic rod of the hydraulic cylinder is hinged to the middle position of the actuating rod.

[0021] Preferably, the actuating device is an electric cylinder, and the extension rod of the electric cylinder is hinged to the middle position of the actuating rod.

[0022] Preferably, the actuating device is a manual device.

[0023] Preferably, a gap is provided between the inner surface of the head wing and the spherical arc surface of the outer surface of the head of the fuselage.

[0024] The beneficial technical effect of the present invention is that, since the head wing is arranged on the outside of the head of the aircraft fuselage, a special aircraft head wing is formed. The aircraft with this aircraft head wing structure provides a new aircraft layout method, while shortening the control distance of the pilot to control the wing surface actuator, the control response is fast, and the manufacturing cost is low. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a structural schematic diagram of a fixed-wing aircraft with an articulated structure according to the present invention. The multi-section articulated wing of the aircraft in this embodiment has a wing swing section; Figure 2 It is another structural schematic diagram of the articulated fixed-wing aircraft of the present invention; Figure 3 yes Figure 2 Another angle view of Figure 4 Figure 2 The main view; Figure 5 yes Figure 2 A top view of Figure 6 It is the attitude diagram of the articulated fixed-wing aircraft during cruising; Figure 7 yes Figure 2 Another posture diagram; Figure 8 yes Figure 7 Another angle view of Fig. 9 yes Figure 7 The main view; Fig.10 yes Figure 7 A top view of Fig.11 It is a three-dimensional schematic diagram of the posture of a multi-section articulated wing of an articulated fixed-wing aircraft when the wing is folded; Fig.12 yes Fig.11 A three-dimensional diagram of the posture of the multi-section joint structure wing when it is fully retracted; Fig.13 It is the attitude diagram of the wing swing section of the joint structure fixed-wing aircraft when it changes downward; Fig.14 It is the attitude diagram of the wing swing section of the joint structure fixed-wing aircraft when it changes upward; Fig.15 It is the attitude diagram of the outer swing section of the wing of the joint structure fixed-wing aircraft when it changes downward; 16 is a schematic diagram of a multi-section articulated wing of an articulated fixed-wing aircraft when the wing is bent upward. At this time, the wing of the aircraft forms an upward reverse wing state, in which the aircraft flies more stably and is comfortable to ride; 17 is a schematic diagram of a multi-section articulated wing of an articulated fixed-wing aircraft when the wing is bent downward. At this time, the wing of the aircraft forms a downward reverse wing state. In this state, when there is an airflow impact, the flight attitude of the aircraft will respond quickly to the airflow, and this state can provide passengers with a flying experience. Fig.18 It is a three-dimensional schematic diagram of the posture of the multi-section articulated structure wing of the articulated structure fixed-wing aircraft of the present invention when it is located in the middle of the aircraft fuselage; Fig.19 yes Fig.18 Schematic diagram of the posture of the multi-section joint structure wing when it is folded; Fig. 20 yes Fig.18 Schematic diagram of the wing attitude; 21 Schematic diagram of the multi-section joint structure wing of a fixed-wing aircraft with a joint structure when it is bent upward, at which time the wing of the aircraft forms an upward reverse wing state; 22 is a schematic diagram of a multi-section articulated wing of an articulated fixed-wing aircraft when the wing is bent downward, at which time the wing of the aircraft forms a downward reverse wing state; Fig.23 is a three-dimensional schematic diagram of the head wing structure of the present invention; Fig.24 is a three-dimensional schematic diagram of the head wing structure of the present invention from another angle; Fig.25 It is an enlarged view of the head-wing structure; Fig.26 is the main view; Fig. 27 It is the right view; Fig.28 It is a top view; Fig.29 It is a cross-sectional view; Fig.30 This is a schematic diagram of the head and wings when they are tilted upwards; Fig.31 This is a schematic diagram of the head and wing when they are bent downward; Fig.32 It is a schematic diagram of a spherical base structure provided on the inner side of the head wing; Fig.33 yes Fig.32 A cross-sectional view of Fig.34 yes Fig.32 A magnified view of the head-wing structure; Fig.35 yes Fig.34 sectional view of .

[0027] Explanation of symbols in the figure: 1. Fuselage; 2. Multi-section joint structure wing; 201. Fixed section of wing; 202. Wing swing section; 203. Rotary joint; 204. Intermediate section joint rotary power device; 205. Fixed section joint rotary power device; 206. Outer swing section of wing; 207. Vertical winglet; 3. Head wing; 301. Lower vertical wingspan; 302. Upper vertical wingspan; 303. Right horizontal wingspan; 304. Left horizontal wingspan; 305. Spherical base; 4. Actuator; 5. Fixed hinge shaft; 6. Gap; 7. Actuator rod; 8. Through hole; 9. Main propeller; 10. Auxiliary propeller. DETAILED DESCRIPTION

[0029] The present invention will be further described below in conjunction with embodiments.

[0030] Figure 1-Figure 35 The invention discloses an embodiment of a fixed-wing aircraft with an articulated structure.

[0031] Figure 1 This is a structural schematic diagram of a fixed-wing aircraft with a joint structure according to the present invention. Figure 1 As can be seen, the articulated fixed-wing aircraft is provided with a fuselage 1, multi-section articulated wings 2 are provided on both sides of the fuselage 1, a head wing 3 is provided at the head of the fuselage, a main propeller 9 is provided at the tail of the fuselage 1, and the multi-section articulated wing 2 includes a wing fixed section 201, one side of the wing fixed section 201 is fixedly connected to the fuselage of the aircraft, a wing swing section 202 is provided on the outer side of the wing fixed section 201, the wing swing section 202 is rotatably connected to the wing fixed section 201, and the rotation angle between the wing swing section 202 and the wing fixed section 201 can be rotated to any angle as needed and maintain the angle.

[0032] A rotary joint 203 is provided between the wing swing section 202 and the wing fixed section 201, and the wing swing section 202 and the wing fixed section 201 are connected in an up and down rotation manner through the rotary joint 203; a fixed section joint rotary power device 205 is provided on the outer side of the wing fixed section 201, and the fixed section joint rotary power device 205 is arranged on the wing fixed section 201, and the rotary joint 203 is connected to the fixed section joint rotary power device 205, and the fixed section joint rotary power device 205 provides rotational power to the rotary joint 203 and makes the rotary joint 203 rotate to a required angle and maintain the angle, and the rotary joint 203 synchronously drives the wing swing section 202 to rotate to a required angle and maintain the angle.

[0033] The flight power of the aircraft mainly comes from the thrust of the main propeller 9, and its flight lift mainly comes from the fixed wing. The aircraft is still a type of fixed-wing aircraft. One side of the wing fixed section 201 is fixedly connected to the fuselage of the aircraft. This wing fixed section 201 provides a fixed lift for the aircraft to take off and fly. The multi-section joint structure wing 2 of the aircraft in this embodiment has a wing swing section 202. During flight, the wing swing section 202 can swing up and down to form a certain angle. When the wing swing section 202 on one side is bent downward at a certain angle, the aircraft will tilt to that side to change the flight attitude of the aircraft. Conversely, when the wing swing section 202 on the other side is bent downward at a certain angle, the aircraft will also tilt to that side to change the flight attitude of the aircraft.

[0034] When the aircraft starts, the wing swing sections 202 on both sides of the aircraft can be adjusted to tilt upward at a certain angle and keep the angle fixed, for example, tilt upward by about 10° and keep the angle fixed. When the aircraft starts, the wing swing sections 202 on both sides of the aircraft quickly tilt downward to a horizontal state, providing lift for the aircraft to take off again, which helps the aircraft to take off quickly.

[0035] When the aircraft is cruising, the wing swing sections 202 on both sides of the aircraft are generally kept in a horizontal posture. When encountering airflow impact, the wing swing section 202 can change the tilt angle to offset the impact of the airflow on the aircraft. For example, when the airflow impacts the aircraft from bottom to top, the wing swing section 202 can tilt upward at a certain angle to offset the upward impact of the airflow and keep the aircraft flying smoothly. The wing swing sections 202 on both sides of the aircraft can move at the same time, or they can move separately according to the size of the airflow impact, or the wing swing sections 202 on both sides can move differently to offset airflow impacts of different sizes; this change in the lift of the aircraft adjusted by the wing swing section 202 will not affect the overall flight mode and flight performance of the aircraft, because one side of the wing fixed section 201 of the aircraft is fixedly connected to the fuselage of the aircraft, and the wing fixed section 201 is a stable source of fixed lift for the aircraft to take off and cruise; all of the above actions are controlled by the aircraft flight control system.

[0036] The power of the fixed section joint rotation power device 205 of this embodiment is an electric cylinder, which can be built into the wing, and its output rotation shaft is connected to the rotation joint 203. The electric cylinder has a certain output torque and maintains a certain large torque, so as to ensure that the required angle between the wing swing section 202 and the wing fixed section 201 can be kept unchanged, and the fixed section joint rotation power device 205 can also quickly output torque at any time to change this angle and keep the changed angle in a stable state. In this way, when the aircraft takes off or cruises, a certain power can be provided, so that the angle between the wing swing section 202 and the wing fixed section 201 can be adjusted to a certain angle at any time as needed and maintained at this angle, providing a change in attitude for take-off and flight. The power of this embodiment adopts an electric cylinder, and other forms of power can also be selected, such as a hydraulic cylinder.

[0037] The wing fixing section 201 of this embodiment is located on the upper part of the aircraft fuselage 1, that is, the multi-section joint structure wing 2 is placed on the upper part of the aircraft fuselage 1. Such a layout is more convenient for setting doors and windows and other layouts in the lower part of the aircraft, and also provides more space for the lower half of the aircraft.

[0038] This embodiment Figure 1 It can also be seen that an auxiliary propeller 10 is provided on the wing swing section 202. The function of the auxiliary propeller 10 is to provide auxiliary flight power and aircraft attitude control power, thereby further improving the maneuverability of the multi-section joint structure fixed-wing aircraft.

[0039] The auxiliary propeller 10 of this embodiment is located at the upper part of the main propeller 9 in the vertical direction. This design allows the auxiliary propeller 10 and the main propeller 9 to be staggered in space. When the auxiliary propeller 10 needs to be started to provide thrust to control the attitude movement of the aircraft, the thrust in the space formed in the vertical direction responds faster to the flight attitude of the aircraft, which is more conducive to the large maneuverability control of the aircraft, that is, it can better form the control force in space, can quickly realize pitch control and rudder control, the control efficiency is higher, and the large maneuverability of the aircraft is stronger.

[0040] The provision of the auxiliary propeller 10 also provides the aircraft with multiple power sources, which not only makes the aircraft control more efficient, but also improves the safety margin of the aircraft. When the main propeller fails, the auxiliary propeller 10 can be used to complete the emergency flight of the aircraft; the power of the auxiliary propeller 10 can be electric power, and such an aircraft forms a hybrid power aircraft.

[0041] The auxiliary propeller 10 can also function to achieve natural deceleration of power when the aircraft lands, so that the original thrust becomes resistance to landing, decelerating rapidly and achieving rapid landing.

[0042] Figure 2 1 is another structural schematic diagram of a fixed-wing aircraft with a joint structure according to the present invention. The multi-section joint structure wing 2 of the aircraft has two sections of joint structures. Figure 2 It can be seen that the outer side of the wing swing section 202 is provided with an outer wing swing section 206, and the outer wing swing section 206 is rotationally connected with the wing swing section 202, and the rotation angle between the outer wing swing section 206 and the wing swing section 202 can be rotated to any angle as needed and maintained. A rotary joint 203 is provided between the outer wing swing section 206 and the wing swing section 202, and the outer wing swing section 206 and the wing swing section 202 are connected to each other through the rotary joint 203. The other side of the wing swing section 202 is provided with an intermediate section joint rotary power device 204, and the intermediate section joint rotary power device 204 is arranged on the wing swing section 202, and the rotary joint 203 is connected with the intermediate section joint rotary power device 204, and the intermediate section joint rotary power device 204 provides rotary power to the rotary joint 203 and makes the rotary joint 203 rotate to a required angle and maintain the angle, and the rotary joint 203 synchronously drives the outer wing swing section 206 to rotate to a required angle and maintain the angle.

[0043] Since the multi-section joint structure wing 2 is a multi-section joint structure, the wing swing section is rotationally connected to the wing fixed section, and the outer wing swing section is rotationally connected to the wing swing section. When the outer wing swing section rotates downward by a certain angle, it can provide a horizontal component of force to enable the aircraft to turn or roll; when the wing swing section rotates upward or downward by a certain angle, the lift of the aircraft can be changed, which is used to adjust the airflow impact that the aircraft often encounters in the troposphere, thereby maintaining the stability and comfort of the aircraft's flight, as well as the safety of the aircraft's flight.

[0044] The power of the middle section joint rotation power device 204 of this embodiment is also other power such as an electric cylinder or a hydraulic cylinder, and its function is the same as the above-mentioned function.

[0045] Figure 7 and Fig.11 It can be easily seen that the wing swing section 202 is tilted upward at a certain angle, and the outer side swing section 206 of the wing is tilted downward at a certain angle. The multi-section joint structure wing 2 can form a Z-shaped structure after tilting. Fig.12 It can be seen that the wing swing section 202 is tilted upward to a horizontal state, and the outer wing swing section 206 is tilted downward to a horizontal state. After the multi-section joint structure wing 2 is tilted, it can also form a completely horizontal structure that is folded mutually.

[0046] When the multi-section joint structure fixed-wing aircraft lands or moves with the ground landing platform or other water landing platform, the wing swing section 202 tilts upward at a certain angle, and the outer wing swing section 206 tilts downward at a certain angle. The multi-section joint structure wing can form a Z-shaped structure after tilting, forming a compact structure for folding, which is convenient for movement and transportation when the aircraft is not taking off.

[0047] Especially when the wing fixed section 201 is located at the upper part of the aircraft fuselage 1, at this time, the multi-section joint structure wing, the wing swing section 202 is tilted upward and is in a horizontal state, and the outer wing swing section 206 is tilted downward and is in a horizontal state. The multi-section joint structure wing can also form a mutually folded structure after tilting; at this time, the folded volume of the multi-section joint structure wing is particularly small, and it is located on the ground landing platform and other water landing platforms, occupying less space and having a smaller volume, and it is also easy to hide when special needs are needed.

[0048] The interior of the wing fixed section 201 of the present invention is provided with a fuel tank to meet the requirements of refueling; the outer side of the wing outer swing section 206 is provided with a vertical winglet 207, which can isolate the upper and lower airflows, making the aircraft more efficient during flight and control.

[0049] It can be seen in the figures of this embodiment that the aircraft equipped with the multi-section joint structure wing 2 is provided with a head wing 3 at the front of the aircraft to control the pitch movement of the aircraft and provide flight stability; an engine and a main propeller 9 are provided at the rear of the aircraft to provide power for the aircraft to fly; and multi-section joint structure wings are provided on both sides of the aircraft. The multi-section joint structure wing is a multi-section joint structure. When the aircraft is cruising, the multi-section joint structure wing is in a fully extended state. When the flight direction needs to be adjusted, the outer swing section 206 of the wing can be controlled to tilt downward at a certain angle to achieve the adjustment of the flight direction of the aircraft.

[0050] like Figure 13-Figure 15 As shown, when the outer wing swing section 206 on the right side of the aircraft is adjusted to tilt downward at a certain angle, the outer wing swing section 206 on the left side is kept horizontal, the aircraft can be controlled to turn to the right, otherwise it can turn to the left. Of course, the wing swing section 202 can also be adjusted to tilt downward at a certain angle, and the flight direction of the aircraft can also be changed.

[0051] When encountering unstable airflow during flight, the tilt angle of the wing swing section 202 can be changed to offset the impact caused by the airflow, such as Fig.14 As shown, the wing swing section 202 tilts upward to offset the upward airflow impact. Fig.13 As shown, the wing swing section 202 tilts downward to offset the impact of the downward airflow. This structure is particularly suitable for use on low-altitude commercial aircraft. When flying at low altitude, the flight altitude is at a relatively low altitude, and the airflow is mostly in the troposphere. The impact of the airflow on the aircraft is relatively large. This structure can offset the impact of the airflow well and improve driving controllability and riding comfort.

[0052] In this embodiment, when the aircraft changes its attitude, the upward or downward tilt angle of the wing swing section 202 is generally about 15°, and the upward or downward tilt angle of the outer wing swing section 206 is also generally about 15°, which can meet the high maneuverability of the aircraft. Of course, according to special flight conditions or special needs, a large angle of tilt can be achieved to meet the needs of flight control.

[0053] The tilt angle described above can sometimes be maintained at a tilt angle of about 5° according to flight and flight control requirements, so that the wing is not completely kept in a horizontal state, and a flight maneuverability can be maintained at any time, and airflow disturbances during flight can be flexibly responded to, or flight stability can be maintained.

[0054] For example, when the wing swing section 202 and the wing outer swing section 206 are simultaneously tilted upward at a certain small angle, the aircraft wing forms an upward reverse wing state, such as Fig.16As shown, in this state, the aircraft flies more stably and is comfortable to ride; when the wing swing section 202 and the outer wing swing section 206 are simultaneously tilted downward at a certain small angle, the aircraft wing forms a downward reverse wing state, such as Fig.17 As shown, in this state, when there is airflow impact, the aircraft's flight attitude will respond quickly to the airflow, and this state can provide passengers with a flying experience. Passengers will feel the rapid change of the aircraft's flight brought about by the airflow at this time. This small tilt angle is generally about 5° to achieve the above flight effect, and can also be tilted to any required angle according to the requirements of the flight control system.

[0055] Of course, when the wing swing section 202 and the outer wing swing section 206 are kept in a horizontal state, the flight at this time is a cruise flight, and the flight of the aircraft is also in a stable state, such as Figure 6 shown.

[0056] Compared with traditional fixed-wing aircraft, when the articulated wings swing up and down to adjust, the wing's changing area is larger, which can provide greater control force, directly change the lift, and the aircraft's attitude response is fast; while traditional aircraft change the aircraft's flight attitude and pitch angle through changes in the rudder surfaces before they can change the aircraft's lift and achieve the aircraft's displacement change. Such control efficiency is low and it is difficult to achieve high maneuverability of the aircraft.

[0057] A fuel tank may be provided inside the wing fixed section 201 to provide fuel for the aircraft to fly.

[0058] This embodiment of Figure 6 This is the attitude diagram of the multi-section joint structure wing during cruising. At this time, the multi-section joint structure wing is fully unfolded horizontally, providing a stable flight attitude for cruising and achieving maximum performance cruising.

[0059] Fig.13 It is a posture diagram of the wing swing section 202 of the multi-section joint structure wing when it changes downward. The posture at this time can be used as the posture of the aircraft when landing. When the aircraft lands, the wing swing section 202 can quickly return to horizontal at the moment of landing, further increasing the landing damping force, so that the landing of the aircraft can be well cushioned.

[0060] Fig.14 This is a posture diagram of the wing swing section 202 of the multi-section joint structure wing when it changes upward. The posture at this time can be used as the posture of the aircraft during catapult takeoff. When the aircraft takes off through the catapult mechanism, the wing swing section 202 can quickly return to horizontal at the moment of takeoff, further providing lift, making the aircraft takeoff faster and smoother.

[0061] In summary, since the wing of the present invention is a multi-section joint structure, the wing swing section 202 is rotationally connected to the wing fixed section 201, and the outer wing swing section 206 is rotationally connected to the wing swing section 202. When the outer wing swing section 206 rotates downward by a certain angle, it can provide a horizontal component of force to enable the aircraft to turn or roll; when the wing swing section 202 rotates upward or downward by a certain angle, it can change the lift of the aircraft, which is used to adjust the airflow impact often encountered by the aircraft in the troposphere, thereby maintaining the stability and comfort of the aircraft's flight, as well as the safety of the aircraft's flight.

[0062] Furthermore, the multi-section articulated wing has a simple structure, a simple control mechanism, and a low manufacturing cost, and is particularly suitable for business aircraft, such as business aircraft with about 5 seats or unmanned aircraft.

[0063] The invention realizes various flight attitude controls of the aircraft by adjusting the aerodynamic force changes of the wing in sections, has a large control area, a large acting force, and good maneuverability of the aircraft.

[0064] The aircraft of the present invention has multiple power sources and higher control efficiency. The hybrid power of oil and electricity improves the safety margin of the aircraft. The aircraft can quickly achieve maneuverability control through the multi-section joint structure wing from sliding, climbing, cruising, landing and other actions.

[0065] Fig.18 and Fig.19 As shown, it is a schematic diagram of a multi-section joint structure wing 2 fixedly connected to the aircraft at a position located in the middle of the aircraft fuselage. At this time, the aircraft layout can also achieve the above-mentioned various performances and functions.

[0066] The present invention can also provide an auxiliary propeller 10 on the wing fixed section 201, so that the force is more stable and the control is simpler.

[0067] Figure 23-Figure 35 It is a schematic diagram of the aircraft head wing structure of a joint structure fixed-wing aircraft of the present invention. As can be seen in the figure, it includes a head wing 3 and an actuating device 4. The head wing 3 is arranged on the outside of the head of the aircraft fuselage 1. The head wing 3 is connected to the actuating device 4, and the actuating device 4 can drive the head wing 3 to swing up and down.

[0068] In this embodiment, the head wing 3 includes a right horizontal wingspan 303 and a left horizontal wingspan 304, and the right horizontal wingspan 303 and the left horizontal wingspan 304 are connected to form a horizontal wingspan of an integrated structure. The head wing 3 also includes an upper vertical wingspan 302 and a lower vertical wingspan 301, and the upper vertical wingspan 302 and the lower vertical wingspan 301 are connected to form a vertical wingspan of an integrated structure. The horizontal wingspan and the vertical wingspan are vertically intersected, and the vertical wingspan is located in the middle of the horizontal wingspan; the outer surface of the head of the fuselage 1 is a spherical arc surface.

[0069] Fig.23 It can be seen that the outer edges of the right horizontal wing span 303 and the left horizontal wing span 304 are pointed rounded structures, and the outer surfaces of the right horizontal wing span 303 and the left horizontal wing span 304 extending to the other side are curved structures; the curved structures are smoothly connected with the spherical curved surface of the outer surface of the head of the fuselage 1; this smooth transition connection allows the curved surface structure of the outer surface extending to the other side of the right horizontal wing span 303 and the left horizontal wing span 304 to extend and transition to the spherical curved surface of the outer surface of the head of the aircraft, forming an integral and larger control surface, the stability of the aircraft after flight will be more stable, and the pitch attitude of the aircraft will be smoother when the head wing structure swings.

[0070] The upper and lower peripheral edges of the upper vertical wing span 302 and the lower vertical wing span 301 are pointed rounded structures, and the outer surfaces of the upper vertical wing span 302 and the lower vertical wing span 301 extending to the other side are curved structures; the curved structures are smoothly transitioned and connected with the spherical curved surface of the outer surface of the head of the fuselage 1. The same principle as described above, this structure also allows the curved surface structure of the outer surface of the upper vertical wing span 302 and the lower vertical wing span 301 extending to the other side to extend and transition to the spherical curved surface of the outer surface of the head of the aircraft, and also forms an integral and large-area control surface, so that the left and right stability of the aircraft after flight will be more stable.

[0071] When the aircraft is flying, the horizontal wingspan and the vertical wingspan of the aircraft head wing structure break through the airflow, causing the airflow to pass around the head wing 3. When the head wing 3 swings up and down, the up and down airflow of the horizontal wingspan changes, so that the aircraft can be controlled to produce a pitch movement. Because the aircraft head of this embodiment is provided with a head wing 3, the up and down swinging of the head wing 3 arranged at the head of the aircraft makes it easier to control the pitch movement of the aircraft with higher accuracy, and the pitch control of the aircraft is more flexible and precise, which can meet the application needs of more precise aircraft maneuverability; at the same time, the control distance of the pilot to control the wing surface actuator is shortened, and the control response is fast.

[0072] Because compared with the existing tail-wing aircraft, the head wing of the aircraft of this embodiment can control the up and down airflow passing through the horizontal wingspan of the aircraft earlier, that is, it can respond to the pitching action caused by the airflow more quickly, and the airflow at the head of the aircraft is mostly in laminar mode, and when it controls the pitching action of the aircraft, there is little disturbance of the interfering airflow, and the control is smooth. The tail structure at the rear of the aircraft will disturb the interfering airflow such as turbulence generated by the up and down airflow passing through the aircraft, and the control distance is far, and the control action transmission is far. At the same time, the vertical wingspan acting airflow will control the aircraft to maintain a stable posture.

[0073] It can also be seen in the figure that the inner side of the head wing 3 is a spherical arc structure, which corresponds to the spherical arc surface of the outer surface of the head of the fuselage 1. When the head wing 3 swings up and down, it will be more flexible, the pressure generated by the flow of air will be smoother, and the control will be more stable.

[0074] In the embodiment of the present invention, a spherical base 305 may be provided on the inner side of the head wing 3, the outer surface of the spherical base 305 is a spherical arc surface, and the horizontal wingspan and the vertical wingspan are smoothly transitioned and connected with the spherical arc surface of the outer surface of the spherical base 305. With such a structure, the aircraft head wing is a complete structure with a spherical base 305, the impact force of the airflow on the head wing will be more stable and smooth, the manipulation of the head wing will be more smooth, and the control experience and aircraft driving control will be easier.

[0075] At the same time, the outer surface of the spherical base 305 near the aircraft head is also a spherical arc surface, which corresponds to the spherical arc surface of the outer surface of the head of the fuselage 1. Such a structure is also for easier control of the up and down swing of the head wing and the smooth change of the airflow.

[0076] Fig.29 As can be seen in the figure, the front end of the fuselage 1 is provided with a through hole 8, and the inner side of the head wing 3 is fixed with an actuating rod 7, which passes through the through hole 8 and is connected to the actuating device 4, one end of which is fixed on the fuselage 1; the actuating device 4 can drive the actuating rod 7 to swing up and down, and the actuating rod 7 drives the head wing 3 to swing up and down. The end of the actuating rod 7 is hinged to the fuselage 1 through a fixed hinge shaft 5, and the actuating device 4 is a hydraulic cylinder, and the hydraulic rod of the hydraulic cylinder is hinged to the middle position of the actuating rod 7. The pilot can operate the aircraft joystick to drive the hydraulic cylinder to move, so as to realize the pitch flight of the aircraft.

[0077] In the present invention, the actuating device 4 can also be an electric cylinder, and the extension rod of the electric cylinder is hinged at the middle position of the actuating rod 7. For the same reason, the actuating device 4 is a manual device, because the head wing is located at the head of the aircraft, the control distance is short, and a manual joystick can be used to achieve manual operation, and the aircraft manufacturing cost is low.

[0078] There is a gap between the inner surface of the head wing 3 and the spherical arc surface of the head outer surface of the fuselage 1. The air in the gap can stabilize the airflow that is diverted up and down and left and right. When the head wing swings, it will generate a certain damping force, which provides good control comfort and stability, and a good experience.

[0079] In summary, in the embodiment of the present invention, since the head wing 3 is arranged outside the head of the aircraft fuselage 1, a special aircraft head wing is formed. The aircraft with the head wing structure provides a new aircraft layout mode, and at the same time shortens the control distance of the pilot to control the wing surface actuator, has a fast control response, and has a low manufacturing cost. At the same time, the engine of the aircraft can be placed in the rear half of the aircraft, and the aircraft noise is lower when driving and riding the aircraft. Fig.16 It can be seen that the propeller 9 of the aircraft is placed at the tail of the aircraft.

[0080] The aircraft with the head-wing structure is particularly suitable for being installed on an aircraft with a multi-segment joint structure wing. The multi-segment joint structure fixed-wing aircraft with a multi-segment joint structure has a wing composed of multiple segments, several segments of which can be bent to change the lift of the aircraft, thereby changing the flight direction of the aircraft. The bending of several segments of the wing can also offset the fluctuation of airflow during the flight of the aircraft, and adaptively adjust the swinging posture of the aircraft to make passengers feel comfortable.

[0081] The head wing structure and the multi-section joint structure wing of the multi-section joint structure are used in combination, which can not only improve the maneuverability of the joint structure fixed-wing aircraft, but also maintain the stability of the flight cruise, and can cope with the air flow impact in the troposphere. The present invention is particularly suitable for low-altitude commercial aircraft, such as 5-seat commercial aircraft or drones, because most low-altitude commercial aircraft fly in the troposphere. When flying at such a high altitude, there are many unstable airflows such as turbulence in the troposphere, and the requirements for controllability, ride comfort and manufacturing cost are higher. Only low-cost manufacturing can be more competitive in the market. The aircraft of the present invention can also fly in the high-altitude stratosphere.

[0082] The articulated fixed-wing aircraft is a brand-new layout structure, which is a more energy-saving, fast, stable and convenient means of transportation. It can use traditional take-off and landing methods to achieve take-off and landing of the aircraft, and can also cooperate with the continuous rotation device disclosed in the application number 2024103467476, the application date is March 26, 2024, and the invention name is "Aircraft with tires and landing mechanisms removed and taking off and landing using a continuous rotation device". Remove the aircraft landing device to achieve rapid take-off and landing on the continuous rotation device. This articulated fixed-wing aircraft and the continuous rotation device are particularly suitable for low-altitude flying aircraft, and can achieve more energy-saving, fast, stable and convenient flight travel purposes. Of course, as described in the patent document with application number 2024103467476, the continuous rotation device can be placed on the ground, on a moving car, on a moving ship, and other application scenarios to achieve flexible take-off and landing of articulated fixed-wing aircraft.

[0083] However, what is described above is only a specific embodiment of the present invention and should not be used to limit the scope of implementation of the present invention. Therefore, the replacement of equivalent components, or equivalent changes and modifications made according to the scope of protection of the present invention should still fall within the scope covered by the claims of the present invention.

Claims

1. An aircraft head wing, characterized by: It comprises a head wing and an actuating device. The head wing is arranged on the outside of the head of the aircraft fuselage. The head wing is connected to the actuating device. The actuating device drives the head wing to swing up and down.

2. The aircraft head wing according to claim 1, characterized in that: The head wing includes a right horizontal wingspan and a left horizontal wingspan, the right horizontal wingspan and the left horizontal wingspan are connected to form a horizontal wingspan of an integrated structure, the head wing also includes an upper vertical wingspan and a lower vertical wingspan, the upper vertical wingspan and the lower vertical wingspan are connected to form a vertical wingspan of an integrated structure, the horizontal wingspan and the vertical wingspan are vertically intersected, and the vertical wingspan is located in the middle of the horizontal wingspan; The outer surface of the head of the fuselage is a spherical arc surface; The outer edges of the right horizontal wing span and the left horizontal wing span are pointed rounded structures, and the outer surfaces of the right horizontal wing span and the left horizontal wing span extending to the other side are curved structures; the curved structures are smoothly transitionally connected with the spherical curved surface of the outer surface of the head of the fuselage; The upper and lower peripheral edges of the upper vertical wing span and the lower vertical wing span are pointed rounded structures, and the outer surfaces of the upper vertical wing span and the lower vertical wing span extending to the other side are curved structures; the curved structures are smoothly transitioned to the spherical curved surface of the outer surface of the head of the fuselage.

3. The aircraft head wing according to claim 2, characterized in that: A spherical base is provided on the inner side of the head wing, the outer surface of the spherical base is a spherical arc surface, and the horizontal wingspan and the vertical wingspan are smoothly transitionally connected with the spherical arc surface of the outer surface of the spherical base.

4. The aircraft head wing according to claim 3, characterized in that: The outer surface of the spherical base on the side close to the aircraft head is also a spherical arc surface, and the spherical arc surface can rotate around the spherical arc surface of the outer surface of the head of the fuselage.

5. The aircraft head wing according to claim 2, characterized in that: A gap is arranged between the inner surface of the head wing and the spherical arc surface of the outer surface of the head of the fuselage.

6. The aircraft head wing according to claim 1, characterized in that: The inner side of the head wing is a spherical arc surface structure, and the spherical arc surface structure can rotate around the spherical arc surface of the outer surface of the head of the fuselage.

7. The aircraft head wing according to claim 1, characterized in that: A through hole is provided at the front end of the fuselage, an actuating rod is fixedly provided on the inner side of the head wing, the actuating rod passes through the through hole and is connected with an actuating device, one end of the actuating device is fixed on the fuselage; the actuating device drives the actuating rod to swing up and down, and the actuating rod drives the head wing to swing up and down.

8. The aircraft head wing according to claim 7, characterized in that: The end of the actuating rod is hinged to the fuselage, the actuating device is a hydraulic cylinder, and the hydraulic rod of the hydraulic cylinder is hinged to the middle position of the actuating rod.

9. The aircraft head wing according to claim 7, characterized in that: The actuating device is an electric cylinder, and the extension rod of the electric cylinder is hinged to the middle position of the actuating rod.

10. The aircraft head wing according to claim 1, characterized in that: The actuating device is a manual device.

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