Long-endurance aircraft provided with multifunctional power generation air inlet channel

Abstract

The invention relates to the technical field of aircrafts, in particular to a long-endurance aircraft provided with a multifunctional power generation air inlet duct, which comprises an aircraft body, wing modules are arranged on the left side and the right side of the aircraft body respectively, a wind energy collecting device comprises a power generation pipeline and a pipeline cover for mounting the power generation pipeline, and a transverse connecting arm is arranged between the pipeline cover and the aircraft body. The inner end of the transverse connecting arm is integrally connected with the machine body; the generated electric energy is orderly and efficiently accessed to an aircraft power system; wind power formed by rotation of all the wind driven generators in the power generation pipeline is uniformly blown from the front end of the air inlet to the rear end, the air flow superposition effect is achieved and sprayed out from the air outlet in the rear end of the power generation pipeline, and the air resistance generated when the aircraft advances can be effectively reduced. The same aircraft can be provided with a plurality of groups of power generation pipelines for power generation and a photovoltaic collection plate with the maximum area, so that the flight air resistance kinetic energy recovery power generation efficiency and the solar power generation efficiency of the aircraft are maximized, the air resistance reduced by air flow sucked into an air inlet is maximized, and the function of the long-endurance aircraft is realized.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, and in particular to a long-endurance aircraft provided with a multifunctional power generation air inlet. Background Art

[0002] The air intake can effectively reduce the air resistance of fast-moving objects. This has been verified on aircraft. When a fast-moving object, such as a supersonic aircraft, exceeds the speed of sound and breaks through the sound barrier, the air resistance no longer increases linearly in proportion to the speed, but instead does not increase or increases in a small proportion. At this time, the air intake can play a strong role in promoting the aircraft. If there is no air intake, the energy consumption caused by the air resistance of the aircraft flying at high speed will be much greater.

[0003] Aircraft power systems are becoming increasingly advanced, with advanced batteries, motors, energy recovery, power monitoring, safety, and intelligence technologies advancing with each passing day. However, issues such as endurance and energy consumption exceeding 90 kilometers per hour have not been adequately addressed. Furthermore, the lack of wind kinetic energy generated by air resistance during travel has not been addressed accordingly. Summary of the Invention

[0004] The purpose of the present invention is to provide a long-endurance aircraft with a multifunctional power generation air intake to address the deficiencies of the prior art.

[0005] To achieve the above object, the technical solution of the present invention is as follows:

[0006] A long-endurance aircraft equipped with a multifunctional power generation air intake comprises an airframe, wing modules are respectively provided on the left and right sides of the airframe, a vertical tail is mounted on the tail of the airframe, the vertical tail is mounted on a rudder capable of laterally swinging, and power units are respectively mounted on the left and right sides of the tail of the airframe. The invention is characterized in that: wind energy collection devices are also provided on both sides of the airframe, the wind energy collection devices comprising a power generation pipeline and a pipeline cover for mounting the power generation pipeline, a transverse connecting arm is provided between the pipeline cover and the airframe, and the inner end of the transverse connecting arm is integrally connected to the airframe;

[0007] The outer end of the transverse connecting arm is provided with an angle adjustment mechanism for adjusting the inclination angle of the pipe cover;

[0008] One end of the power generation pipe is connected to an air inlet and the other end is connected to an air outlet. Multiple wind power generation modules are arranged at intervals along the length direction of the power generation pipe, and two adjacent wind power generation modules are coaxially aligned. The wind power generation module includes an internal power generation bracket and a wind turbine and a transmission circuit installed on the internal power generation bracket. The internal power generation bracket is installed in the power generation pipe to fix the wind turbine.

[0009] The beneficial effects of the present invention are as follows: when the aircraft is traveling at a high speed, the air inlet of the power generation duct absorbs strong and stable wind energy; when the aircraft takes off, air is sucked in from the front end of the air inlet, accelerated, and then discharged from the air outlet at the rear end, which can effectively reduce air resistance; when the aircraft speeds up, a stronger airflow enters the air inlet to drive the wind turbine at the front end to rotate at a high speed to generate electricity; the high-speed rotation of the wind turbine at the front end generates a backward airflow, which drives the wind turbine at the rear end to generate electricity in sequence, until all the wind turbine generator sets in the power generation duct rotate at a high speed to generate electricity, thereby achieving the superposition of wind power generation efficiency, and the generated electricity is orderly and efficiently connected to the aircraft power system; the wind force generated by the rotation of all wind turbines in the power generation duct is uniformly blown from the front end of the air inlet to the rear end, achieving the airflow superposition effect and being ejected from the air outlet at the rear end of the power generation duct, which can effectively reduce the air resistance of the aircraft; the same aircraft can be provided with multiple groups of power generation ducts for power generation, thereby maximizing the power generation efficiency of the aircraft's flight air resistance kinetic energy recovery and maximizing the reduction of air resistance by the airflow inhaled at the air inlet, thereby achieving the function of a long-endurance aircraft. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 This is a schematic diagram of the structure of a long-endurance aircraft.

[0011] Figure 2 This is a schematic diagram of the long-endurance aircraft's top-down structure.

[0012] Figure 3 It is a structural diagram of the connection between the pipe cover and the body.

[0013] Figure 4 Schematic diagram of the cross-sectional structure of the transverse connecting arm.

[0014] Figure 5 This is a schematic diagram of the cross-sectional structure of the power generation pipeline.

[0015] Figure 6 Schematic diagram of the wind power module structure.

[0016] Reference numerals include:

[0017] 1-Body,

[0018] 11-wing module, 12-vertical tail, 13-rudder, 14-power unit, 15-pipe cover, 2-power generation pipeline,

[0019] 21-air inlet, 22-air outlet, 23-circuit connection arm, 24-circuit slot, 25-charging wire

[0020] 26-wire conduit, 27-arc groove, 28-power transmission hole,

[0021] 3- Wind power generation module,

[0022] 31-internal power generation bracket, 32-wind turbine, 33-bracket seat, 34-support rod, 35-circuit cavity,

[0023] 36-rotating power generation shaft, 37-power generation blades, 38-conversion device, 39-transmission wires,

[0024] 4- Angle adjustment mechanism,

[0025] 41- transverse connecting arm, 42- driving hole, 43- driving shaft, 44- driving sleeve, 45- first fan-shaped groove,

[0026] 46-second sector slot, 47-top hydraulic cylinder, 48-bottom hydraulic cylinder,

[0027] 5-The first limiting structure,

[0028] 51-arc plate, 52-first arc track, 53-first limit connecting block, 54-fixed plate,

[0029] 55 - second limiting structure, 56 - second arc track, 57 - inner swing arm, 58 - swing cavity. DETAILED DESCRIPTION

[0030] The present invention is described in detail below with reference to the accompanying drawings.

[0031] like Figure 1-6 As shown, a long-endurance aircraft with a multifunctional power generation air inlet includes an airframe 1, wing modules 11 are respectively provided on the left and right sides of the airframe 1, a vertical tail 12 is installed at the tail of the airframe 1, and the vertical tail 12 is installed with a rudder 13 that can swing laterally, power units 14 are respectively installed on the left and right sides of the tail of the airframe 1, and wind energy collection devices are also provided on both sides of the airframe 1, and the wind energy collection devices include a power generation pipeline 2 and a pipeline cover 15 for installing the power generation pipeline 2, a transverse connecting arm 41 is provided between the pipeline cover 15 and the airframe 1, and the inner end of the transverse connecting arm 41 is integrally connected to the airframe 1.

[0032] The openings of the air inlet 21 and the air outlet 22 of the power generation pipeline 2 are both enlarged trumpet structures, which facilitates the inflow of larger airflow into the air inlet 21 and the outflow of larger airflow from the air outlet 22, thereby beneficially increasing the wind kinetic energy of the power generation pipeline 2.

[0033] Multiple wind power generation modules 3 are arranged at intervals along the length direction in the power generation pipeline 2, and two adjacent wind power generation modules 3 are coaxially aligned. The wind power generation module 3 includes an internal power generation bracket 31 and a wind turbine 32 and a transmission circuit installed on the internal power generation bracket 31. The internal power generation bracket 31 is installed in the power generation pipeline 2 to fix the wind turbine 32.

[0034] When the aircraft is traveling at high speed, the air inlet 21 of the power generation duct 2 absorbs strong and stable wind energy. When the aircraft takes off, air is sucked in from the front end of the air inlet 21, accelerated, and then discharged from the rear end air outlet 22, effectively reducing air resistance. When the aircraft speeds up, a stronger airflow enters the air inlet 21, driving the wind turbines 32 at the front end to rotate at high speed to generate electricity. The high-speed rotation of the wind turbines 32 at the front end generates a backward airflow, which drives the wind turbines 32 at the rear end in a sequential arrangement to generate electricity, until all the wind turbines 32 in the power generation duct 2 are rotating at high speed to generate electricity, achieving superposition of wind power generation efficiency, and the generated electricity is connected to the aircraft power system in an orderly and efficient manner. The wind force generated by the rotation of all the wind turbines 32 in the power generation duct 2 is uniformly blown from the front end of the air inlet 21 to the rear end, achieving the superposition effect of airflow and being ejected from the air outlet 22 at the rear end of the power generation duct 2, effectively reducing the air resistance of the aircraft. The same aircraft can be equipped with multiple power generation ducts 2 to maximize the efficiency of power generation by recovering the kinetic energy of the aircraft's flight air resistance and maximizing the reduction of air resistance by the airflow inhaled by the air inlet 21, thereby realizing the function of a long-endurance aircraft.

[0035] The transverse connecting arm 41 is also formed with a circuit connecting arm 23 made of the same material. This circuit connecting arm 23 is integrally connected to the transverse connecting arm 41. A circuit slot 24 for the power supply line is formed within this circuit connecting arm 23. The inner end of this circuit connecting arm 23 is integrally connected to the aircraft body 1. The aircraft's electrical system includes a power supply battery housed within the aircraft body 1. The power supply battery is signal-connected to a charge controller and rectifier. A charging cable 25 is routed within the circuit slot 24 and is signal-connected to the charge controller, which monitors the battery voltage in real time.

[0036] The wind turbine 32 includes a rotating generator shaft 36 rotatably mounted on a support base 33. Generator blades 37 are mounted on the rotating generator shaft 36. When rotating, the generator blades 37 generate wind that flows along the length of the generator pipe 2. All wind turbines 32 generate a uniform airflow from the inlet to the outlet of the generator pipe 2. Multiple support rods 34 are mounted inside the generator pipe 2 in conjunction with the support base 33. The support rods 34 are arranged in a circular pattern and equidistantly around the periphery of the support base 33. The outer ends of the support rods 34 connect to the interior of the generator pipe 2, thereby securing the support base 33. Furthermore, the rotating generator shaft 36 mounted on the support base 33 can rotate stably to generate electricity, and the generator blades 37 can actively rotate under the force of the wind to generate electricity. A conversion device 38 is located within the support base 33 to convert mechanical energy into electrical energy. Specifically, the conversion device 38 consists of a stator and a rotor. The stator, which generates the induced electromotive force and is composed of an iron core and windings, generates the induced electromotive force. The rotor, which generates the magnetic field, generates an alternating electromotive force and an alternating current in the coil by rotating a closed coil in the magnetic field, continuously cutting the magnetic flux lines based on the laws of electromagnetic induction and electromagnetic force. The aforementioned AC generator is a common generator technology available today, and its specific principles and structure are not detailed here.

[0037] The internal power generation bracket 31 is provided with a transmission wire 39, and the power generation pipeline 2 is formed with a power transmission hole 28 for the transmission wire 39 to pass through. The internal power generation bracket 31 includes a bracket seat 33 for installing a wind turbine 32 and a plurality of support rods 34 in contact with the inner walls of the plurality of power generation pipelines 2. The plurality of support rods 34 are connected to the periphery of the bracket seat 33, and one of the support rods 34 is formed with a circuit cavity 35 with a hollow structure. The power transmission hole 28 is coaxially aligned with the circuit cavity 35; the inner wall of the pipeline cover 15 is formed with a side groove, which is connected to the power transmission hole 28. The side groove is arranged with a main transmission line, which can be connected to the plurality of transmission wires 39. The outer wall of the pipeline cover 15 is installed with a wire pipeline 26, and the circuit connection arm 23 An arc-shaped groove 27 connected to the circuit groove 24 is formed, and the arc-shaped groove 27 is used to insert the power line conduit 26. The outer and inner ends of the wire conduit 26 are connected to multiple main transmission lines. A joint is provided in the wire conduit 26 for circuit transmission to prevent power outages. The outer end of the wire conduit 26 is connected to the charging wire 25. The charging wire 25 has a longer length, which can reserve a certain length for the wire conduit 26 when it swings to prevent breakage. Two sections of accordion protective covers are installed along the length direction of the arc-shaped groove 27. One end of the accordion protective cover is installed at the outer end of the arc-shaped groove 27, and the other end is connected to the wire conduit 26. When the wire conduit 26 moves along the arc-shaped groove 27, the accordion protective cover can always block the arc-shaped groove 27, thereby increasing the protection of the circuit groove 24.

[0038] It is connected to the circuit slot 24. After the conversion device 38 within the bracket seat 33 converts mechanical energy into electrical energy, a transmission line 39 travels along the circuit cavity 35 and the power transmission hole 28 into the wire transmission tube, where it is transmitted to the battery energy storage for storage. Multiple wind power generation modules 3 enable the orderly accumulation of electrical energy, which is then connected to the aircraft power system of the aircraft body 1 and other power supply applications, thereby achieving the power generation function of the present invention.

[0039] Furthermore, the AC power generated by the conversion device 38 is converted to DC power via a rectifier circuit. This rectifier circuit, typically composed of components such as diodes, converts sinusoidal AC power into unidirectional DC power. Depending on the voltage requirements of the energy storage device, a transformer may be required to step up or down the voltage. This power is then connected to the aircraft's electrical system via charging cables 25 in the circuit slot 24.

[0040] An angle adjustment mechanism 4 is provided at the outer end of the transverse connecting arm 41 for adjusting the tilt angle of the duct cover 15. This mechanism includes a drive hole 42 formed along the transverse connecting arm 41. A drive shaft 43 is mounted on the outer wall of the duct cover 15, which is inserted into the drive hole 42. The drive shaft 43 is rotatable within the drive hole 42, and a drive sleeve 44 is mounted in the drive hole 42 for rotating the drive shaft 43. The tilt angle of the duct cover 15 is adjustable from front to back. When adjusted to a high front-low rear tilt angle, the high-speed airflow through the power generation duct 2 creates an upward thrust, assisting the aircraft in takeoff and upward flight. When the tilt angle is adjusted to a low front-high rear, the downward thrust generated accelerates the aircraft's descent. If the air inlet remains horizontal, no upward or downward thrust is generated, which is the optimal power generation operating state for the aforementioned function.

[0041] Specifically, the transverse connecting arm 41 is provided with a first limiting structure 5 for limiting the tilting of the duct cover 15. The first limiting structure 5 includes an arc-shaped plate 51 mounted on the outer end of the transverse connecting arm 41. The arc-shaped plate 51 is formed with a first arc-shaped track 52. The outer wall of the duct cover 15 is formed with a first limiting connection block 53. The first limiting connection block 53 moves along the length direction of the first arc-shaped track 52. The transverse connecting arm 41 is provided with a fixing plate 54 connected to the arc-shaped plate 51. When the duct cover 15 swings to the corresponding tilt angle, the first limiting connection block 53 located on the outer wall of the duct cover 15 slides along the length direction of the first arc-shaped track 52, that is, the duct cover 15 swings and tilts within the predetermined track, ensuring that the tilting angle of the swing does not exceed the stroke, and the problem of excessive tilt angle does not occur. This prevents the duct cover from breaking when the aircraft is flying at high speed, and ensures stable angle adjustment. The accuracy of the tilt angle adjustment can also be guaranteed.

[0042] Furthermore, the transverse connecting arm 41 is provided with a second limiting structure 55 for limiting the tilting of the pipe cover 15. The second limiting structure 55 includes a first fan-shaped groove 45 formed on the wall of the drive hole 42 and a second fan-shaped groove 46 formed on the wall of the drive sleeve 44. The first fan-shaped groove 45 and the second fan-shaped groove 46 are radially aligned. A radially arranged inner swing arm 57 is installed on the outer wall of the drive shaft 43. The inner swing arm 57 passes through the second fan-shaped groove 46 and the first fan-shaped groove 45 and extends toward the transverse connecting arm 41. The transverse connecting arm 41 is formed with a swing cavity 58 for the longitudinal swinging of the inner swing arm 57. When the drive shaft 43 rotates, the inner swing arm 57 radially installed on the drive shaft 43 will swing longitudinally, pass through the first fan-shaped groove 45 and the second fan-shaped groove 46, and swing in the swing cavity 58 of the transverse connecting arm 41, thereby controlling the tilt angle of the pipe cover 15 and preventing the tilt angle from being too large.

[0043] Furthermore, a longitudinally arranged second arc track 56 is provided in the swing chamber 58, and a second limit connecting block is installed at the end of the inner swing arm 57, and the second limit connecting block slides with the second arc track 56; a top hydraulic cylinder 47 located above the inner swing arm 57 and a bottom hydraulic cylinder 48 located below the inner swing arm are provided in the swing chamber 58, the top hydraulic cylinder 47 is installed on the top wall of the swing chamber 58, and the bottom hydraulic cylinder 48 is installed on the bottom wall of the swing chamber 58, the top hydraulic cylinder 47 and the bottom hydraulic cylinder 48 are longitudinally aligned and the driving ends of the top hydraulic cylinder 47 and the bottom hydraulic cylinder 48 are both facing the inner swing arm 57.

[0044] In this embodiment, the top hydraulic cylinder 47 and the bottom hydraulic cylinder 48 are signal-connected, and the driving end of the top hydraulic cylinder 47 and the driving end of the bottom hydraulic cylinder 48 respectively resist the inner swing arm 57. When the inclination angle of the pipe cover 15 needs to be adjusted, when the driving rod of the top hydraulic cylinder 47 is extended, the driving end of the bottom hydraulic cylinder 48 is retracted; the hydraulic cylinder has a large torque. When flying at high speed, the torque of the hydraulic system can ensure the inclination angle of the pipe cover 15 and maintain the angle unchanged. The hydraulic system can accurately adjust the flow and pressure through the servo valve, and cooperate with the position sensor to achieve millimeter-level precision control to meet the angle requirements of the pipe cover 15 under different flight conditions.

[0045] It should be noted that the hydraulic system pipeline passes through the transverse connecting arm 41 from the body 1, enters the swing chamber 58, and is connected to the top hydraulic cylinder 47 and the bottom hydraulic cylinder 48. The top hydraulic cylinder 47 and the bottom hydraulic cylinder 48 are connected by signal through a control panel and a signal sensor. When the driving end of the top hydraulic cylinder 47 extends, presses against the inner swing arm 57 and drives the inner swing arm 57 to swing downward, the driving end of the bottom hydraulic cylinder 48 retracts and maintains support for the inner swing arm 57 to prevent the inner swing arm 57 from being in a vacant position.

[0046] The duct cover 15, transverse connecting arm 41, and first retaining structure 5 are all formed from a high-strength magnesium alloy. Using magnesium alloy reduces fuselage weight, thereby reducing engine thrust requirements and lowering fuel consumption. This lightweighting also improves the aircraft's acceleration, climb rate, and range.

[0047] Preferably, the wind turbine 32 is a high-speed permanent magnet synchronous generator to be suitable for high-speed flight of an aircraft. The high-speed generator converts kinetic energy into electrical energy, which can be used as a UPS emergency power supply.

[0048] In one embodiment, one or more pipe covers 15 may be provided at other appropriate positions of the fuselage, and the power generation pipes 2 may be arranged inside the pipe covers 15 .

[0049] In one embodiment, wind energy and solar energy collection devices are also provided on both sides and around the wing module 11. The solar energy collection device includes a photovoltaic panel and a circuit system. The photovoltaic panel is organically integrated with the fuselage wing and the outer wall of the power generation air inlet. The same aircraft can be provided with multiple sets of power generation pipelines and photovoltaic collection panels with the largest area to maximize the efficiency of power generation by recovering kinetic energy of aircraft flight air resistance and solar power generation, and to maximize the reduction of air resistance by the air intake airflow, thereby realizing the function of long-endurance aircraft.

[0050] In summary, it can be seen that the present invention has the above-mentioned excellent characteristics, which can enhance its performance unprecedented in the past and become a product with great practical value.

[0051] The above contents are only preferred embodiments of the present invention. For ordinary technicians in this field, according to the concept of the present invention, there may be changes in the specific implementation methods and application scopes. The contents of this specification should not be understood as limiting the present invention.

Claims

1. A long-endurance aircraft equipped with a multifunctional power generation air intake, comprising an airframe, wing modules disposed on both left and right sides of the airframe, a vertical tail mounted at the rear of the airframe, the vertical tail mounted with a rudder capable of laterally swinging, and power units mounted on both left and right sides of the rear of the airframe, characterized in that: Wind energy collection devices are also provided on both sides of the machine body. The wind energy collection devices include a power generation pipe and a pipe cover for installing the power generation pipe. A transverse connecting arm is provided between the pipe cover and the machine body. The inner end of the transverse connecting arm is integrally connected to the machine body. The outer end of the transverse connecting arm is provided with an angle adjustment mechanism for adjusting the inclination angle of the pipe cover; One end of the power generation pipe is connected to an air inlet and the other end is connected to an air outlet. Multiple wind power generation modules are arranged at intervals along the length direction of the power generation pipe, and two adjacent wind power generation modules are coaxially aligned. The wind power generation module includes an internal power generation bracket and a wind turbine and a transmission circuit installed on the internal power generation bracket. The internal power generation bracket is installed in the power generation pipe to fix the wind turbine.

2. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 1, characterized in that: The angle adjustment mechanism includes a driving hole formed along the transverse connecting arm. A driving shaft inserted into the driving hole is installed on the outer wall of the pipe cover. The driving shaft can rotate in the driving hole. The driving hole is installed with a driving sleeve for the driving shaft to rotate.

3. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 2, characterized in that: The transverse connecting arm is provided with a first limiting structure for limiting the tilting of the pipe cover. The first limiting structure includes an arc-shaped plate installed on the outer end of the transverse connecting arm. The arc-shaped plate is formed with a first arc track. The outer wall of the pipe cover is formed with a first limiting connecting block. The first limiting connecting block moves along the length direction of the first arc track. The transverse connecting arm is installed with a fixed plate connected to the arc plate.

4. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 3, characterized in that: The transverse connecting arm is provided with a second limiting structure for limiting the tilting of the pipe cover. The second limiting structure includes a first fan-shaped groove formed on the wall of the driving hole and a second fan-shaped groove formed on the wall of the driving sleeve. The first fan-shaped groove and the second fan-shaped groove are radially aligned. A radially arranged inner swing arm is installed on the outer wall of the driving shaft. The inner swing arm passes through the second fan-shaped groove, the first fan-shaped groove and extends to the transverse connecting arm. The transverse connecting arm is formed with a swing cavity for the inner swing arm to swing longitudinally.

5. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 4, characterized in that: The swing chamber is provided with a longitudinally arranged second arc track, and a second limit connecting block is installed at the end of the inner swing arm, and the second limit connecting block slides with the second arc track; the swing chamber is provided with a top hydraulic cylinder located above the inner swing arm and a bottom hydraulic cylinder located below the inner swing arm, the top hydraulic cylinder is installed on the top wall of the swing chamber, and the bottom hydraulic cylinder is installed on the bottom wall of the swing chamber, the top hydraulic cylinder and the bottom hydraulic cylinder are longitudinally aligned and the driving ends of the top hydraulic cylinder and the bottom hydraulic cylinder are both facing the inner swing arm.

6. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 5, characterized in that: The pipe cover, the transverse connecting arm and the first limiting structure are all formed by processing from a high-strength magnesium alloy material.

7. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 1 or 6, characterized in that: The horizontal connecting arm is also formed with a circuit connecting arm made of the same material. The circuit connecting arm is integrally connected to the horizontal connecting arm. A circuit groove for the power supply line to pass through is formed in the circuit connecting arm. The inner end of the circuit connecting arm is integrally connected to the body.

8. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 7, characterized in that: The internal power generation bracket is provided with a transmission wire, and the power generation pipeline is formed with a power transmission hole for the transmission wire to pass through. The internal power generation bracket includes a bracket seat for installing a wind turbine and multiple support rods in contact with the inner walls of multiple power generation pipelines. The multiple support rods are connected to the periphery of the bracket seat, one of the support rods is formed with a circuit cavity with a hollow structure, and the power transmission hole is coaxially aligned with the circuit cavity; the power transmission hole is connected to the circuit groove.

9. The long-endurance aircraft equipped with a multifunctional power generation air inlet according to claim 8, characterized in that: The wind turbine includes a rotating power generation shaft rotatably mounted on a support seat, and the rotating power generation shaft is equipped with power generation blades. When the power generation blades rotate, they can generate wind flowing along the length direction of the power generation pipeline. All wind turbines generate the same-direction airflow from the inlet to the outlet of the power generation pipeline.

Images