A tilt-fold-variable pitch self-locking rotor and method oriented to the shaft fan power

Abstract

The application relates to a tilt-folding-variable-pitch self-locking rotor and method facing shaft fan power, and belongs to the field of aircraft power. The rotor structure disclosed by the application comprises a first driving shaft (31), a tilting mechanism (5), a tilting driving motor (4), a rotor folding electromagnetic switch (6), a hydraulic variable-pitch system (7), a worm gear self-locking mechanism (8) and a rotor (9). The first driving shaft (31) drives the rotor (9) through bevel gears, the tilting driving motor (4) controls the tilting of the rotor, the rotor folding electromagnetic switch (6) uses a conductive copper core (63) to transmit power, the worm gear self-locking mechanism (8) is powered by a wire (81) to a folding motor (82), the worm gear (83) drives the worm wheel (84) to rotate, and then the rotor folding part (92) fixedly connected with the worm wheel (84) is folded, and the lead angle of the worm gear (83) is smaller than the equivalent friction angle between meshing gear teeth. The application uses the electromagnetic switch to realize low-speed locking of the folding safe position of the rotor, power transmission of the worm gear self-locking mechanism (8), and locking of the rotor position by using the self-locking capacity of the worm gear mechanism.

Description

TECHNICAL FIELD

[0001] The application relates to a tilt-folding-pitch self-locking rotor and a method thereof, and belongs to the field of aircraft power. BACKGROUND

[0002] The vertical take-off and landing high-speed aircraft based on the integrated shaft fan variable cycle engine fully meets the requirements of 'quick support and agile attack', and can well meet the future combat needs of the army. The rotor is required to be folded when the rotor is in the high-speed economic propulsion of the turbofan, so as to seek the best propulsion efficiency, and the rotor is required to be tiltable and variable-pitch, so as to adapt to the rapid thrust or lift demand.

[0003] In order to meet the requirements of tilting, folding and variable pitch of the rotor, the Safran Helicopter Engines Company (invention patent application publication No. CN116157324A) proposes a propelling unit with foldable propeller blades and a method for folding the blades. The folding of the propeller is controlled by a movable control member and a connecting rod to form a crank slider mechanism, the variable pitch control is realized by a pitch actuator to control the displacement of a control rod, and the linear motion of the control rod is converted into the variable pitch rotary motion of the propeller through the crank slider mechanism. The disadvantage of the scheme is that the position self-locking of the propeller is realized by a motor to enable locking, which is not conducive to reducing the energy consumption of the equipment.

[0004] The patent with the invention patent application publication No. CN102348889A proposes a folding blade turbine. A driving shaft is used to transmit linear displacement to a rotating linear motion sliding shaft, so as to fold the rotor. The variable geometry allows the wing plate to be sized for relatively weak wind, and to maintain operation without damage under relatively strong wind. In extreme conditions, the wing plate can be completely folded to ensure safety. The technical scheme has the problems of wear and tear between the driving shaft and the sliding shaft, is not suitable for high-speed rotation, and the folding equipment is not suitable for cumulative installation of the variable pitch mechanism, and the rotor folding does not have self-locking capability.

[0005] It is necessary to design a corresponding tiltable, foldable and variable pitch self-locking rotor to adapt to the design requirements of the rotor of the vertical take-off and landing high-speed aircraft. SUMMARY

[0006] The application aims to provide a tilt-folding-pitch self-locking rotor and a method thereof, and aims to develop a tiltable, foldable and variable pitch self-locking rotor with low energy consumption. The electromagnetic switch is used for low-speed locking of the rotor and power transmission of the worm and gear self-locking mechanism (8). The lead angle of the designed worm is smaller than the equivalent friction angle between the meshing teeth, the rotor folding self-locking capability is achieved, the folding position of the rotor is prevented from being changed by external aerodynamic force, the equipment is powered off after the rotor is unfolded or folded, and the low energy consumption characteristic is strong.

[0007] To achieve the above object, the present application provides the following technical solutions:

[0008] A tilt-folding-pitching self-locking rotor, comprising a first driving shaft, a tilting mechanism, a tilting driving motor, a rotor folding electromagnetic switch, a hydraulic pitch changing system, a worm gear self-locking mechanism and a rotor, wherein the first driving shaft is indirectly connected to a power output shaft through a bevel gear steering shaft, the rotor is driven by the first driving shaft, the tilting driving motor is installed on a stationary wing and drives a tilting gear on the tilting mechanism to control the tilting of the rotor, the rotor folding electromagnetic switch comprises a conductive copper core, an armature, a spring, an iron core, a coil and an on-off controller, and is configured to lock the rotor and supply power to the worm gear self-locking mechanism, the hydraulic pitch changing system comprises a rotary joint, a pitch changing piston and a pitch changing operating pin, oil is supplied from an oil source system to the left and right cavities of the pitch changing piston through the rotary joint, and an electro-hydraulic servo valve controls the pressure difference between the left and right cavities to cause the pitch changing piston to change position, thereby controlling the rotary motion of the pitch changing operating pin, the pitch changing operating pin is an eccentric pin, and the principle of a crank slider mechanism is used to convert linear motion into rotary motion, the worm gear self-locking mechanism is installed in a rotor blade root, a worm wheel is fixedly connected to a rotor folding part, the worm gear self-locking mechanism supplies power to the folding motor through a wire to drive the worm to rotate the worm wheel, and then the folding motor and the rotor folding part fixedly connected to the worm wheel are folded, when the wire is connected to the rotor blade root from the rotor head cover, the wire needs to be connected to the rotating pitch changing operating pin, and the connection is achieved through a brush or a wire with a certain length, the lead angle of the worm is smaller than the equivalent friction angle between the meshing gear teeth, and the worm gear self-locking mechanism is configured to realize the self-locking of the rotor folding part, and only the worm can drive the worm wheel, not vice versa, so that the rotor folding part is prevented from randomly unfolding or folding when subjected to external interference force;

[0009] The power output shaft passes through a double-sided S-shaped air inlet channel, rotates 90 degrees upward through a bevel gear steering shaft to drive a counter-rotating bevel gear, thereby driving the first driving shaft and the second driving shaft in a counter-rotating manner, and the first driving shaft and the second driving shaft drive the rotors on both sides in a tiltable, foldable and pitch-changeable manner;

[0010] The rotor front edge of the rotor blade is provided with a first limit switch, and the rotor rear edge is provided with a second limit switch, when the rotor folding part moves to the fully unfolded position, the first limit switch is triggered due to the pressing of the rotor folding part to the rotor front edge, thus generating a first signal, when the rotor folding part moves to the fully folded position, the second limit switch is triggered due to the pressing of the rotor folding part to the rotor rear edge, thus generating a second signal, the first signal and the second signal are connected to the on-off controller of the rotor folding electromagnetic switch through wires, the rotor rotating shaft is provided with a rotor rotating speed sensor, and the measurement signal is transmitted to the on-off controller of the rotor folding electromagnetic switch, the tilt-folding-variable-pitch self-locking rotor facing the shaft fan power is installed on the aircraft, the aircraft is provided with a flight control system and is connected to the on-off controller of the rotor folding electromagnetic switch.

[0011] The tilt-folding-variable-pitch self-locking rotor facing the shaft fan power is characterized by a folding self-locking control method, which comprises the following steps:

[0012] S1: unfolding→folding process;

[0013] S11: the on-off controller of the rotor folding electromagnetic switch receives the signals from the flight control system of the aircraft and the rotor rotating speed sensor in an interrupt triggered manner, when the aircraft breaks through the medium-speed barrier of 400-500 km / h, the flight control system sends a first state signal to the on-off controller, and the flight control system of the aircraft controls the shaft fan engine to switch from the turbo-shaft mode to the turbo-fan mode, when the rotor rotating speed is lower than 5-50 rpm, the rotor rotating speed sensor sends a signal to the on-off controller;

[0014] S12: after receiving the signals from the flight control system and the rotor rotating speed sensor at the same time, the rotor folding electromagnetic switch pops out the conductive copper core, and aligns the hole of the wire with the rotor residual rotation, so as to lock the folding safe position of the rotor at low speed, and avoid the rotor folding to hit the wing, after the rotor folding electromagnetic switch is turned on, power is transmitted to the rotor folding motor to drive the worm gear to rotate and fold the rotor, until the rotor is completely folded to trigger the second limit switch;

[0015] S13: the on-off controller receives the second signal from the second limit switch in an interrupt triggered manner, when the on-off controller receives the second signal and the first state signal at the same time, the rotor is completely folded, the rotor folding electromagnetic switch is turned off, and the self-locking ability of the worm gear self-locking mechanism is used to self-lock the folding state of the rotor;

[0016] S2: folding→unfolding process:

[0017] S22: the rotor folding electromagnetic switch receives signals from the flight control system and the rotor speed sensor in the form of an interrupt, when the aircraft is landing vertically, the flight control system sends a second state signal to the on-off controller, and the shaft fan engine is switched from the turbofan mode to the turboshaft mode;

[0018] S23: the rotor folding electromagnetic switch pops out the conductive copper core after receiving the second state signal from the flight control system, aligns the hole of the wire, and thus locks the folding safety position of the rotor at low speed, avoiding the rotor folding hitting the wing. After the rotor folding electromagnetic switch is turned on, power is transmitted to the rotor folding motor, which drives the worm gear to rotate and unfold the rotor until the first limit switch is triggered;

[0019] S24: the on-off controller receives the first signal from the first limit switch in the form of an interrupt, when the on-off controller receives the first signal and the second state signal at the same time, the rotor is fully unfolded, the rotor folding electromagnetic switch is turned off, and the self-locking ability of the worm gear self-locking mechanism is used to self-lock the rotor in the unfolded state.

[0020] The tilt-folding-variable-pitch self-locking rotor for shaft fan power is characterized in that the tilt-folding-variable-pitch self-locking rotor is applied to the shaft fan engine, and the working process is as follows:

[0021] SS1: take-off stage: the shaft fan engine works in the turboshaft mode, the fan is stopped, the power output shaft drives the first drive shaft to rotate, the tilt drive motor drives the tilt teeth on the tilt mechanism to control the rotor to tilt to the vertical position, thereby generating large vertical lift, at this time the rotor folding electromagnetic switch is in the off state by the elastic force of the spring, the hydraulic variable pitch system slowly increases the pitch angle of the rotor, and the self-locking ability of the worm gear self-locking mechanism is used to lock the rotor in the unfolded state;

[0022] SS2: medium-low speed cruise stage: the shaft fan engine works in the turboshaft mode, the fan is stopped, when flying at a low speed of 200-300 km / h, the tilt drive motor drives the tilt teeth on the tilt mechanism to control the rotor to tilt forward, when flying at a medium speed of 400-500 km / h, the tilt drive motor drives the tilt teeth on the tilt mechanism to control the rotor to tilt to the horizontal position, throughout the process the rotor folding electromagnetic switch is still in the off state, the pitch angle of the rotor is slowly increased, and the rotor is locked in the unfolded state;

[0023] SS3: high-speed cruising stage: the shaft fan engine is converted from turbo-shaft mode to turbo-fan mode, when the rotor speed is lower than 5-50 rpm, the rotor folding electromagnetic switch is popped out into the hole of the rotor upper wire by electromagnetic force, thereby the low-speed locking of the folding safe position of the rotor is realized, the rotor folding is avoided to hit the wing, then power is supplied to the folding motor to drive the worm to rotate the worm wheel, and then the rotor is folded, after folding to the position, the rotor folding electromagnetic switch is disconnected, and the self-locking ability is used to realize the self-locking of the rotor folding, and high-speed flight of 700-1000 km / h is realized;

[0024] SS4: vertical landing: the shaft fan engine is converted from turbo-fan mode to turbo-shaft mode, when the rotor speed is lower than 5-50 rpm, the rotor folding electromagnetic switch is powered to pop out, thereby the low-speed locking of the folding safe position of the rotor is realized, the rotor folding is avoided to hit the wing, then power is supplied to unfold the rotor, after unfolding to the position, the rotor folding electromagnetic switch is disconnected, and finally the rotor rotates and the fan stops.

[0025] Compared with the prior art, the advantages of the present application are: a tilting-folding-pitch self-locking rotor and method for shaft fan power are proposed, the rotor is unfolded to the folding state and the folding to the unfolding state by power driving based on the electromagnetic switch, the low-speed locking of the folding safe position of the rotor is realized to avoid the rotor folding to hit the wing, the first limit switch and the second limit switch are used for precise rotor position closed-loop control, and the self-locking ability of the worm gear self-locking mechanism is used for self-locking of the rotor folding-unfolding state, after the rotor folding or unfolding is completed, the electromagnetic switch is disconnected, thereby the low-energy consumption rotor folding self-locking is realized. BRIEF DESCRIPTION OF DRAWINGS

[0026] Figure 1 It is a three-dimensional structure schematic diagram of the tiltable foldable pitch self-locking rotor in the folding state of the present application.

[0027] Figure 2 It is a schematic diagram of the worm gear self-locking mechanism in the folding and unfolding positions of the present application.

[0028] Figure 3 It is a schematic diagram of the rotor in the positive pitch and negative pitch positions of the present application.

[0029] Figure 4 It is a shaft fan engine loaded with the tiltable foldable pitch self-locking rotor of the present application.

[0030] Figure 5 It is an aircraft applied with the tiltable foldable pitch self-locking rotor of the present application.

[0031] In the figure: 1-power output shaft, 2-steering bevel gear, 3-driving shaft, 31-first driving shaft, 32-second driving shaft, 4-inclination driving motor, 5-inclination mechanism, 51-inclination tooth, 6-electromagnetic switch, 61-spring, 62-armature, 63-conductive copper core, 7-hydraulic variable-pitch system, 71-rotary joint, 72-variable-pitch operating pin, 73-variable-pitch piston, 81-wire, 82-rotor folding motor, 83-worm, 84-worm gear, 91-rotor blade root, 92-rotor folding part, 911-first limit switch, 912-second limit switch, 10-double-sided S-bend air inlet, 11-aircraft. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the accompanying drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0033] Please refer to Figure 1The embodiment of the application is a tilt-folding-pitching self-locking rotor, which comprises a first driving shaft 31, a tilting mechanism 5, a tilting driving motor 4, a rotor folding electromagnetic switch 6, a hydraulic pitch system 7, a worm gear self-locking mechanism 8 and a rotor 9. The first driving shaft 31 is indirectly driven by a power output shaft 1 through a bevel gear steering shaft. The rotor 9 is driven by the first driving shaft 31. The tilting driving motor 4 is installed on a stationary wing and drives a tilting gear 51 on the tilting mechanism 5 to control the tilting of the rotor. The rotor folding electromagnetic switch 6 comprises a conductive copper core 63, an armature 62, a spring 61, an iron core, a coil and an on-off controller, which are configured to lock the rotor and supply power to the worm gear self-locking mechanism 8. The hydraulic pitch system 7 comprises a rotary joint 71, a pitch piston 73 and a pitch operation pin 72. Oil is supplied from an oil source system to the left and right cavities of the pitch piston 73 through the rotary joint 71. An electro-hydraulic servo valve controls the pressure difference between the left and right cavities to cause the pitch piston 73 to change position, thereby controlling the rotary motion of the pitch operation pin 72. The pitch operation pin 72 is an eccentric pin, which converts linear motion into rotary motion by using the principle of a crank slider mechanism. The worm gear self-locking mechanism 8 is installed in a rotor blade root 91. A worm wheel 84 and a rotor folding part 92 are fixedly connected. The worm gear self-locking mechanism 8 drives the worm wheel 84 to rotate by supplying power to a folding motor 82 through a wire 81, so as to fold the rotor folding part 92 fixedly connected with the worm wheel 84. When the wire 81 is connected to the rotor blade root 91 from the rotor head cover, the wire 81 needs to be connected to the rotating pitch operation pin 72. The connection is achieved by using an electric brush or a wire with a certain length. The lead angle of the worm wheel 83 is smaller than the equivalent friction angle between the meshing gear teeth, which is configured to realize the self-locking of the rotor folding part 92. The worm wheel 84 can only drive the worm wheel 83, but not vice versa, so as to avoid the random unfolding or folding of the rotor folding part 92 under external interference force.

[0034] Please refer to Figure 4 and Figure 5 In the embodiment of the application, the power output shaft 1 passes through a double-sided S-shaped air inlet channel 10 and drives a counter rotating bevel gear upward by rotating 90 degrees through a bevel gear steering shaft 2, so as to drive a first driving shaft 31 and a second driving shaft 32 in a counter rotating manner. The first driving shaft 31 and the second driving shaft 32 respectively drive two rotors which can be tilted, folded and have variable pitch.

[0035] Please refer to Figure 1 and Figure 3In the embodiment of the present application, the first limit switch 911 is installed on the front edge of the rotor blade root 91, and the second limit switch 912 is installed on the rear edge of the rotor blade root 91. When the rotor folding part 92 moves to the fully unfolded position, the first limit switch 911 is triggered because the rotor folding part 92 presses the front edge of the rotor blade root 91, thereby generating a first signal. When the rotor folding part 92 moves to the fully folded position, the second limit switch 912 is triggered because the rotor folding part 92 presses the rear edge of the rotor blade root 91, thereby generating a second signal. The first signal and the second signal are connected to the on-off controller of the rotor folding electromagnetic switch 6 through the wire 81. The rotor rotating shaft is provided with a rotor rotating speed sensor, and the measurement signal is transmitted to the on-off controller of the rotor folding electromagnetic switch 6. The tilt-folding-variable-pitch self-locking rotor facing the shaft fan power is installed on the aircraft, the aircraft is provided with a flight control system, and is connected to the on-off controller of the rotor folding electromagnetic switch 6.

[0036] Please refer to Figure 2 In the embodiment of the present application, the tilt-folding-variable-pitch self-locking rotor facing the shaft fan power is characterized by a folding self-locking control method of the rotor, which comprises the following steps.

[0037] S1: unfolding→folding process:

[0038] S11: the on-off controller of the rotor folding electromagnetic switch 6 receives the signals from the flight control system of the aircraft 11 and the rotor rotating speed sensor in the form of interrupt triggering. When the aircraft 11 breaks through the medium-speed barrier of 400-500 km / h, the flight control system sends a first state signal to the on-off controller. The flight control system of the aircraft 11 controls the shaft fan engine to switch from the turbo-shaft mode to the turbo-fan mode. When the rotor rotating speed is lower than 5-50 rpm, the rotor rotating speed sensor sends a signal to the on-off controller.

[0039] S12: after receiving the signals from the flight control system and the rotor rotating speed sensor at the same time, the rotor folding electromagnetic switch 6 pops out the conductive copper core 63, and aligns the hole of the wire 81 by using the rotor residual rotation, thereby locking the folding safe position of the rotor at low speed and avoiding the rotor folding part 92 from hitting the wing. After the rotor folding electromagnetic switch 6 is turned on, power is transmitted to the rotor folding motor 82 to drive the worm gear to rotate and fold the rotor 9 until the second limit switch 912 is triggered when the rotor is completely folded.

[0040] S13: the on-off controller receives the second signal from the second limit switch 912 in the form of interrupt triggering. When the on-off controller receives the second signal and the first state signal at the same time, the rotor 9 is completely folded, the rotor folding electromagnetic switch 6 is turned off, and the self-locking ability of the worm gear self-locking mechanism 8 is used to perform self-locking on the folding state of the rotor.

[0041] S2: folding→unfolding process:

[0042] S21: the on-off controller of the rotor folding electromagnetic switch 6 receives signals from the flight control system of the aircraft and the rotor speed sensor in an interruptive manner, when the aircraft is landing vertically, the flight control system sends a second state signal to the on-off controller, and the shaft fan engine is switched from the turbofan mode to the turboshaft mode;

[0043] S22: after receiving the second state signal from the flight control system, the rotor folding electromagnetic switch 6 pops out the conductive copper core 63 and aligns the hole of the wire 81, thereby locking the folding safety position of the rotor at a low speed and avoiding the rotor folding hitting the wing, after the rotor folding electromagnetic switch 6 is turned on, power is supplied to the rotor folding motor 82, the rotor folding motor 82 drives the worm gear to rotate and unfold the rotor 9 until the first limit switch 911 is triggered;

[0044] S23: the on-off controller receives the first signal from the first limit switch 911 in an interruptive manner, when the on-off controller receives the first signal and the second state signal at the same time, the rotor 9 is fully unfolded, the rotor folding electromagnetic switch 6 is turned off, and the self-locking ability of the worm gear self-locking mechanism 8 is used to self-lock the rotor in the unfolded state;

[0045] Please refer to Figure 2 Figure 3 In the embodiment of the application, the tilting-folding-variable-pitch self-locking rotor for the shaft fan power is applied to the shaft fan engine, and the working process is as follows:

[0046] ① Take-off stage: the shaft fan engine works in the turboshaft mode, the fan is stopped, the power output shaft 1 drives the first drive shaft 31 to rotate, the tilting drive motor 4 drives the tilting teeth 51 on the tilting mechanism 5 to control the rotor to tilt to the vertical position, thereby generating large vertical lift, at this time, the rotor folding electromagnetic switch 6 is in the off state by the elastic force of the spring 61, the hydraulic variable pitch system 7 slowly increases the pitch angle of the rotor, and the worm gear self-locking mechanism 8 locks the rotor 9 in the unfolded state;

[0047] ② Medium-low speed cruising stage: the shaft fan engine works in the turboshaft mode, the fan is stopped, when flying at a low speed of 200-300 km / h, the tilting drive motor 4 drives the tilting teeth 51 on the tilting mechanism 5 to control the rotor to tilt forward, when flying at a medium speed of 400-500 km / h, the tilting drive motor 4 drives the tilting teeth 51 on the tilting mechanism 5 to control the rotor to tilt to the horizontal position, throughout the process, the rotor folding electromagnetic switch 6 is still in the off state, the pitch angle of the rotor is slowly increased, and the rotor 9 is locked in the unfolded state;

[0048] 3. High-speed cruise stage: the shaft-fan engine is converted from turbo-shaft mode to turbo-fan mode, when the rotor speed is lower than 5-50 rpm, the rotor folding electromagnetic switch 6 pops out the conductive copper core 63 into the hole of the rotor wire 81 by electromagnetic force, thereby locking the rotor at the folding safe position at low speed, avoiding the rotor folding hitting the wing, then power is supplied to the folding motor 82 to drive the worm 83 to rotate the worm wheel 84, thereby folding the rotor, after folding to the position, the rotor folding electromagnetic switch 6 is disconnected, and the self-locking ability is used to realize the rotor folding self-locking, and high-speed flight of 700-1000 km / h is realized;

[0049] 4. Vertical landing: the shaft-fan engine is converted from turbo-fan mode to turbo-shaft mode, when the rotor speed is lower than 5-50 rpm, the rotor folding electromagnetic switch 6 is powered on to pop out, thereby locking the rotor at the folding safe position at low speed, avoiding the rotor folding hitting the wing, then power is supplied to unfold the rotor, after unfolding to the position, the rotor folding electromagnetic switch 6 is disconnected, and finally the rotor rotates and the fan stops.

[0050] The present application is not limited to the above-mentioned embodiments, and based on the technical solutions disclosed in the present application, those skilled in the art can make some simple modifications, equivalent changes and modifications to some technical features without creative labor, which are all within the scope of the technical solutions of the present application.

Claims

1. A tilt-fold-vari self-locking rotor oriented to axial fan power, comprising: The first drive shaft (31) is driven by the steering bevel gear (2), the rotor (9) is driven by the first drive shaft (31), the tilt drive motor (4) is installed on the static wing and drives the tilt gear (51) on the tilt mechanism (5) to control the rotor tilt, the rotor folding electromagnetic switch (6) includes a conductive copper core (63), a armature (62), a spring (61), an iron core, a coil and an on-off controller, which is configured to lock the rotor and supply power to the worm and gear self-locking mechanism (8), the hydraulic pitch control system (7) includes a rotary joint (71), a pitch control piston (73) and a pitch control operating pin (72), the oil is supplied from the oil source system to the left and right cavities of the pitch control piston (73) through the rotary joint (71), and the pressure difference between the left and right cavities is controlled by an electro-hydraulic servo valve to cause the pitch control piston (73) to change position, thereby controlling the rotational movement of the pitch control operating pin (72), the pitch control operating pin (72) is an eccentric pin that converts linear motion into rotational motion using the principle of the crank slider mechanism, the worm and gear self-locking mechanism (8) is installed in the rotor blade root (91), the worm (84) and the rotor folding part (92) are fixedly connected, the worm and gear self-locking mechanism (8) supplies electric energy to the folding motor (82) through the wire (81) to drive the worm (83) to rotate the worm (84), and then fold the rotor folding part (92) fixedly connected with the worm (84), the lead angle of the worm (83) is smaller than the equivalent friction angle between the meshing teeth, which is configured to realize self-locking of the rotor folding part (92), and only the worm (83) can drive the worm (84), not the worm (84) can drive the worm (83), so as to avoid random unfolding or folding of the rotor folding part (92) when it is disturbed by external forces. The rotor leading edge of the rotor blade root (91) is provided with a first limit switch (911), and the rotor trailing edge is provided with a second limit switch (912), when the rotor folding part (92) moves to the fully unfolded position, the rotor folding part (92) presses the rotor leading edge of the rotor blade root (91) to trigger the first limit switch (911), thereby generating a first signal, when the rotor folding part (92) moves to the fully folded position, the rotor folding part (92) presses the rotor trailing edge of the rotor blade root (91) to trigger the second limit switch (912), thereby generating a second signal, the first signal and the second signal are connected to the on-off controller of the rotor folding electromagnetic switch (6) through the wire (81), the rotor (9) is provided with a rotor speed sensor on the rotating shaft, and the measurement signal is transmitted to the on-off controller of the rotor folding electromagnetic switch (6), the tilt-folding-pitch self-locking rotor facing the shaft fan disturbance force is installed on the aircraft, the aircraft is provided with a flight control system and is connected to the on-off controller of the rotor folding electromagnetic switch (6).

2. A tilt-fold-vari self-locking rotor system for a fan driven shaft, as claimed in claim 1, wherein, The folding self-locking control method of the rotor includes the following steps: S1: Unfolding → Folding process; S11: The on / off controller of the rotor folding electromagnetic switch (6) receives signals from the flight control system and rotor speed sensor of the aircraft (11) in the manner of triggering interruption. When the aircraft breaks through the medium speed barrier of 400-500 km / h, the flight control system sends the first state signal to the on / off controller. The flight control system of the aircraft controls the shaft fan engine to switch from turboshaft mode to turbofan mode. When the rotor speed is lower than 5-50 rpm, the rotor speed sensor sends a signal to the on / off controller. S12: After receiving signals from the flight control system and the rotor speed sensor at the same time, the rotor folding electromagnetic switch (6) pops out the conductive copper core (63) and uses the rotor's residual rotation to align with the hole in the wire (81). After the rotor folding electromagnetic switch (6) is turned on, it supplies power to the rotor folding motor (82), which drives the worm gear to rotate and fold the rotor (9) until the rotor is completely folded and triggers the second limit switch (912). S13: The on / off controller receives the second signal from the second limit switch (912) in the manner of triggering an interrupt. When the on / off controller receives the second signal and the first state signal at the same time, the rotor (9) is fully folded, the rotor folding electromagnetic switch (6) is disconnected, and the self-locking capability of the worm gear self-locking mechanism (8) is used to self-lock the rotor in the folding state. S2: Folding → Unfolding process; S21: The on / off controller of the rotor folding electromagnetic switch (6) receives signals from the flight control system and rotor speed sensor of the aircraft in the manner of triggering interruption. When the aircraft lands vertically, the flight control system sends a second status signal to the on / off controller, and the shaft fan engine switches from turbofan mode to turboshaft mode. S22: After receiving the second state signal from the flight control system, the rotor folding electromagnetic switch (6) pops out the conductive copper core (63), aligns it with the hole in the wire (81), and after the rotor folding electromagnetic switch (6) is turned on, it supplies power to the rotor folding motor (82). The rotor folding motor (82) drives the worm gear to rotate and unfold the rotor (9) until the rotor is fully unfolded and triggers the first limit switch (911). S23: The on / off controller receives the first signal from the first limit switch (911) in the manner of triggering an interrupt. When the on / off controller receives the first signal and the second state signal at the same time, the rotor (9) is fully deployed, the rotor folding electromagnetic switch (6) is disconnected, and the self-locking capability of the worm gear self-locking mechanism (8) is used to self-lock the rotor deployment state.

3. A tilt-fold-feather self-locking rotor oriented to axial fan power as claimed in claim 1, characterized by, The tiltable, foldable, variable-pitch self-locking rotor is used in a shaft fan engine, and the working process is as follows: ① Takeoff phase: The shaft fan engine operates in turboshaft mode, the fan stops, the power output shaft (1) drives the first drive shaft (31) to rotate, the tilt drive motor (4) drives the tilt gear (51) on the tilt mechanism (5) to control the rotor to tilt to the vertical position, thereby generating vertical lift. At this time, the rotor folding electromagnetic switch (6) is in the open state with the help of the spring force (61), the hydraulic pitch system (7) slowly increases the rotor pitch angle, and uses the worm gear self-locking mechanism (8) to lock the rotor (9) in the unfolded state; ②Middle and low speed cruise stage: the shaft fan engine works in the mode of turbo-shaft, the fan is stopped, when the aircraft flies at the speed of 200-300km / h, the tilt drive motor (4) drives the tilt teeth (51) on the tilt mechanism (5) to control the rotor to tilt forward, when the aircraft flies at the speed of 400-500km / h, the tilt drive motor (4) drives the tilt teeth (51) on the tilt mechanism (5) to control the rotor to tilt to the horizontal position, during the whole process, the rotor folding electromagnetic switch (6) is still in the off state, the pitch angle of the rotor is slowly increased, and the rotor (9) is locked in the unfolded state; ③High speed cruise stage: the shaft fan engine is converted from the mode of turbo-shaft to the mode of turbo-fan, when the rotor speed is lower than 5-50rpm, the rotor folding electromagnetic switch (6) pops out the conductive copper core (63) into the hole of the rotor wire (81) by electromagnetic force, and supplies power to the folding motor (82) to drive the worm (83) to rotate the worm wheel (84), and then fold the rotor, after folding to the position, the rotor folding electromagnetic switch (6) is disconnected, and the self-locking ability is used to realize the self-locking of the rotor folding, and the aircraft flies at the speed of 700-1000km / h; ④Vertical landing: the shaft fan engine is converted from the mode of turbo-fan to the mode of turbo-shaft, when the rotor speed is lower than 5-50rpm, the rotor folding electromagnetic switch (6) is energized to pop out, and power is supplied to unfold the rotor, after unfolding to the position, the rotor folding electromagnetic switch (6) is disconnected, and finally the rotor rotates, and the fan is stopped.

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