Rotorcraft

Abstract

The invention relates to the technical field of rotorcrafts, and provides a rotorcraft which comprises a rotorcraft body, a pre-rotating device, a plurality of rotors, a propeller and a main power device. The pre-rotation device comprises a mounting cabin, a driving gas cylinder, a control unit and a power supply unit. By arranging the mounting cabin, the rotor wings are arranged in the mounting cabin, and the rotor wings are provided with the airflow nozzles capable of driving the rotor wings to rotate; a driving gas cylinder is arranged in the mounting cabin and is communicated with the gas flow nozzle through a gas supply channel; the control unit is arranged to control the driving gas cylinder to supply gas to the gas flow nozzle, and the power supply unit supplies power to the control unit. According to the prewhirling device, the rotorcraft can generate prewhirling power through the gas of the driving gas cylinder, an additional transmission mechanism or a transmission connecting rod is not needed, the purpose that the rotor is prewhirled to the target take-off rotating speed is achieved, the weight of the rotorcraft is effectively reduced, the structural complexity of the prewhirling device is reduced, cost is reduced, and reliability is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of rotorcraft, in particular to a rotorcraft. BACKGROUND

[0002] In order to reduce the hardware condition requirements of rotorcraft to the landing site and expand the practicability of rotorcraft, the rotorcraft is generally pre-rotated, so that the take-off distance of the rotorcraft can be significantly reduced.

[0003] At present, the pre-rotation of the rotorcraft is generally realized by an engine or an electric motor, a transmission connecting rod, and a pre-rotation mechanism combined with a clutch. This pre-rotation structure is mainly suitable for self-rotating rotor mechanisms with the engine or the electric motor being rear-mounted and the rotor head being relatively close.

[0004] However, in the related rotorcraft pre-rotation technology, the transmission connecting rod needs to be arranged for a long distance, resulting in a complex structure, excessive weight, high cost, and low reliability of the entire pre-rotation mechanism. SUMMARY

[0005] In view of the above-mentioned defects of the prior art, the present application provides a rotorcraft to solve at least one of the above-mentioned technical defects in the prior art, so that the pre-rotation of the rotorcraft does not require a transmission connecting rod, the structure of the entire pre-rotation mechanism can be simplified, the weight and cost of the rotorcraft can be effectively reduced, and the reliability is high.

[0006] In order to achieve the purpose of the present application, the present application provides a rotorcraft, which comprises a rotorcraft body, a pre-rotation device, a plurality of rotors, a propeller, and a main power device. The main power device is installed in the rotorcraft body and is drivingly connected with the propeller. The pre-rotation device is installed above the rotorcraft body. The plurality of rotors are rotatably installed above the rotorcraft body and are connected with the pre-rotation device. When the rotorcraft takes off, the pre-rotation device first drives the plurality of rotors to pre-rotate, and then the propeller drives the rotorcraft to take off. The pre-rotation device comprises:

[0007] A mounting cabin is installed above the rotorcraft body. The plurality of rotors are connected with the mounting cabin and are distributed radially around the mounting cabin.

[0008] A driving gas cylinder is arranged in the mounting cabin and is in communication with the airflow nozzle through a gas supply channel.

[0009] A control unit is connected with the driving gas cylinder and / or the gas supply channel and is adapted to control the driving gas cylinder to supply gas to the airflow nozzle.

[0010] A power supply unit is electrically connected with the control unit and is adapted to provide power supply for the control unit.

[0011] Preferably, the rotorcraft body is provided with a support seat protruding therefrom, the support seat is provided with a rotating shaft, the plurality of rotors and the installation cabin are synchronously rotatably connected to the rotating shaft, and the control unit controls the driving gas cylinder to stop supplying gas to the gas flow nozzle in the flight state.

[0012] Preferably, the installation cabin is a decompression cabin, and the rotors are hollow structures provided with the gas supply channels.

[0013] Preferably, the rotors are sealed to the installation cabin, the rotors include first and second rotors, the gas supply channels include first and second channels, and the gas flow nozzles include first and second nozzles.

[0014] The first channel is provided in the first rotor and is in communication with the installation cabin.

[0015] The second channel is provided in the second rotor and is in communication with the installation cabin.

[0016] The first nozzle is provided in the first rotor, is in communication with the first channel, and has a jet direction opposite to a pre-rotation direction of the first rotor.

[0017] The second nozzle is provided in the second rotor, is in communication with the second channel, and has a jet direction opposite to a pre-rotation direction of the second rotor.

[0018] The driving gas cylinder is provided with a solenoid valve.

[0019] The control unit is electrically connected to the solenoid valve and is adapted to control an on-off state of the solenoid valve.

[0020] The power supply unit is a battery and is also installed in the installation cabin.

[0021] Preferably, first ends of the first and second rotors are sealed to the installation cabin.

[0022] The first channel extends from the first end of the first rotor to a second end of the first rotor.

[0023] The second channel extends from the first end of the second rotor to a second end of the second rotor.

[0024] The first nozzle is provided at the second end of the first rotor, and the second nozzle is provided at the second end of the second rotor.

[0025] Preferably, the first nozzle and the second nozzle are centrally symmetrically arranged.

[0026] The jet direction of the first nozzle is perpendicular to the first rotor, and the jet direction of the second nozzle is perpendicular to the second rotor.

[0027] Preferably, the installation cabin further comprises a pressure sensor, an angular velocity sensor and a wireless communication unit, wherein the pressure sensor, the angular velocity sensor and the wireless communication unit are arranged in the installation cabin,

[0028] The pressure sensor is electrically connected to the control unit, and is adapted to feed pressure data in the installation cabin to the control unit,

[0029] The control unit controls the on-off state of the electromagnetic valve according to the pressure data fed back by the pressure sensor;

[0030] The angular velocity sensor is electrically connected to the control unit, and the angular velocity sensor is adapted to monitor the angular velocity value of the rotor and feed angular velocity data to the control unit,

[0031] The control unit controls the on-off state of the electromagnetic valve according to the angular velocity data fed back by the angular velocity sensor;

[0032] The wireless communication unit is electrically connected to the control unit, and is adapted to receive external instructions to control the control unit.

[0033] Preferably, the driving gas cylinder comprises a first driving gas cylinder and a second driving gas cylinder, and the electromagnetic valve comprises a first electromagnetic valve and a second electromagnetic valve,

[0034] The first electromagnetic valve is arranged in the first driving gas cylinder, and the second electromagnetic valve is arranged in the second driving gas cylinder,

[0035] The first electromagnetic valve and the second electromagnetic valve are electrically connected to the control unit.

[0036] Preferably, the installation cabin comprises a first cabin shell and a second cabin shell and a sealing ring, the first cabin shell and the second cabin shell are detachably connected by the sealing ring to form a containing cavity,

[0037] The rotorcraft body is provided with a support seat protruding therefrom, the support seat is provided with a rotating shaft, and the second cabin shell is connected to the rotating shaft,

[0038] The rotor is arranged in the second cabin shell and connected to the rotating shaft, and the rotor and the second cabin shell rotate synchronously,

[0039] The driving gas cylinder, the control unit and the power supply unit are all arranged in the containing cavity.

[0040] Preferably, the airflow nozzle is a subsonic nozzle, and the jet speed is 0.8-0.9Ma,

[0041] The air pressure of the installation cabin is stabilized at 2.8-3 times of the standard atmospheric pressure.

[0042] The rotorcraft provided by the application sets the rotor in the installation cabin, and the rotor is provided with an airflow nozzle capable of driving the rotor to rotate; a driving gas cylinder is arranged in the installation cabin, the driving gas cylinder is communicated with the airflow nozzle through a gas supply channel; a control unit is arranged to control the driving gas cylinder to supply gas to the airflow nozzle, and a power supply unit provides power supply for the control unit. The rotorcraft can generate pre-rotation power through the gas in the driving gas cylinder, and does not need additional transmission mechanism or transmission connecting rod to realize pre-rotation of the rotor to the target take-off rotation speed, effectively reduce the weight of the rotorcraft, reduce the structural complexity of the pre-rotation device, reduce the cost, and improve the reliability. BRIEF DESCRIPTION OF DRAWINGS

[0043] The above and other objects, features and advantages of the present application will become more apparent from the following detailed description when taken in conjunction with the accompanying drawings in which similar reference characters refer to similar elements throughout and in which: the drawings are not necessarily to scale, emphasis instead being placed upon illustrating the principles of the application.

[0044] Figure 1 The pre-rotation device of the rotorcraft and the overall structure of the rotorcraft provided by the embodiment of the application are shown in the schematic view;

[0045] Figure 2 The pre-rotation device of the rotorcraft and the structure of the rotorcraft provided by the embodiment of the application are shown in the schematic view;

[0046] Figure 3 The pre-rotation device of the rotorcraft and the structure of the rotorcraft provided by the embodiment of the application are shown in the schematic view; Figure 2 The enlarged schematic view of A in the middle;

[0047] Figure 4 The relationship between the components in the pre-rotation device of the rotorcraft and the components of the rotorcraft provided by the embodiment of the application is shown in the schematic view.

[0048] 1, rotor; 11, first rotor; 12, second rotor; 13, first channel; 14, second channel; 15, gas supply channel; 2, rotorcraft body; 3, support seat; 31, rotating shaft; 4, propeller;

[0049] 100, installation cabin; 101, sealing ring; 102, containing cavity; 110, first cabin shell; 120, second cabin shell;

[0050] 200, airflow nozzle; 210, first nozzle; 220, second nozzle;

[0051] 300, driving gas cylinder; 310, first driving gas cylinder; 320, second driving gas cylinder;

[0052] 400 solenoid valve; 410 first solenoid valve; 420 second solenoid valve;

[0053] 500 control unit; 510 pressure sensor; 530 wireless communication unit;

[0054] 600 power supply unit. DETAILED DESCRIPTION

[0055] For the purpose of facilitating the understanding of the present application, the present application will be described in more detail below with reference to the relevant drawings.

[0056] It should be noted that when an element is referred to as being "connected" to another element, it can be directly connected to the other element or can be connected to the other element with intervening elements. The terms "mounted", "one end", "the other end", and the like as used herein are only for illustrative purposes.

[0057] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this application belongs. The terminology used in the description herein is for describing specific embodiments only and is not intended to be limiting of the application. As used herein, the term "and / or" includes any and all combinations of one or more of the associated listed items.

[0058] The present application will be described below with reference to the drawings. Figures 1 to 4 Embodiments of the present application will be described below. It should be understood that the following description is merely illustrative of the present application and does not pose any limitation on the present application.

[0059] In conjunction with Figures 1 to 4 Embodiments of the present application also provide a rotorcraft, which comprises a rotorcraft body 2, a pre-rotation device, a plurality of rotors 1, a propeller 4, and a main power device. The main power device is installed in the rotorcraft body 2 and is drivingly connected to the propeller 4. The pre-rotation device is installed above the rotorcraft body 2, the plurality of rotors 1 are rotatably installed above the rotorcraft body 2 and are connected to the pre-rotation device, and the propeller 4 is arranged in front of the rotorcraft body 2. When the rotorcraft takes off, the pre-rotation device first drives the plurality of rotors 1 to pre-rotate, and then the propeller 4 drives the rotorcraft to take off. At least two rotors 1 are provided with airflow nozzles 200 suitable for driving the rotors 1 to rotate.

[0060] The pre-rotation device comprises a mounting cabin 100, a driving gas cylinder 300, a control unit 500, and a power supply unit 600.

[0061] The mounting cabin 100 is installed above the rotorcraft body 2, and the plurality of rotors 1 are connected to the mounting cabin 100 and are distributed radially around the mounting cabin 100. The plurality of rotors 1 can be provided as two rotors, or three or more rotors.

[0062] The driving gas cylinder 300 is arranged in the mounting cabin 100, and the driving gas cylinder 300 is communicated with the airflow nozzle 200 through the gas supply channel 15. The gas in the driving gas cylinder 300 can be transmitted to the airflow nozzle 200 through the gas supply channel 15.

[0063] The control unit 500 is connected with the driving gas cylinder 300 and / or the gas supply channel 15, and can control the driving gas cylinder 300 to supply gas to the airflow nozzle 200.

[0064] The power supply unit 600 is electrically connected with the control unit 500, and is adapted to supply power for the control unit 500.

[0065] It can be understood that the rotorcraft provided by the embodiments of the present application is arranged with the mounting cabin 100, the rotor 1 is arranged in the mounting cabin 100, the rotor 1 is arranged with the airflow nozzle 200 which can drive the rotor 1 to rotate, the driving gas cylinder 300 is arranged in the mounting cabin 100, the driving gas cylinder 300 is communicated with the airflow nozzle 200 through the gas supply channel 15, the control unit 500 is arranged to control the driving gas cylinder 300 to supply gas to the airflow nozzle 200, and the power supply unit 600 supplies power for the control unit 500. The rotorcraft can generate pre-rotation power by the gas in the driving gas cylinder 300, and does not need additional transmission mechanism or transmission connecting rod to realize pre-rotation of the rotor 1 to the target take-off rotation speed, so that the weight of the rotorcraft is effectively reduced, the structural complexity of the pre-rotation device is reduced, the cost is reduced, and the reliability is improved.

[0066] Specifically, in combination with Figure 2 and Figure 3 In some embodiments of the present application, the rotorcraft body 2 is arranged with the support seat 3 in a protruding manner, the support seat 3 is arranged with the rotating shaft 31, and the plurality of rotors 1 and the mounting cabin 100 are synchronously rotatably connected to the rotating shaft 31. In the flight state, the control unit 500 controls the driving gas cylinder 300 not to supply gas to the airflow nozzle 200. The rotation of the rotor 1 of the rotorcraft is more stable, and the flight is more stable.

[0067] In addition, the mounting cabin 100 can be a decompression cabin, the rotor 1 is a hollow structure, and the rotor 1 is arranged with the gas supply channel 15. The structure of the rotorcraft is simpler, and the manufacturing cost can be reduced.

[0068] In combination with Figures 1 to 4 In some embodiments of the present application, the rotor 1 includes the first rotor 11 and the second rotor 12, the gas supply channel 15 includes the first channel 13 and the second channel 14, the first rotor 11 is arranged with the first channel 13, the second rotor 12 is arranged with the second channel 14, the pre-rotation device of the rotorcraft includes the mounting cabin 100, the airflow nozzle 200, the driving gas cylinder 300, the electromagnetic valve 400, the control unit 500 and the power supply unit 600, and the airflow nozzle 200 includes the first nozzle 210 and the second nozzle 220.

[0069] The rotor 1 is sealed to the mounting cabin 100.

[0070] The first channel 13 connects the mounting cabin 100 and the first rotor 11.

[0071] The second channel 14 connects the mounting cabin 100 and the second rotor 12.

[0072] The first nozzle 210 is arranged on the first rotor 11, and the first nozzle 210 is connected to the first channel 13. The spraying direction of the first nozzle 210 is opposite to the pre-rotation direction of the first rotor 11.

[0073] The second nozzle 220 is arranged on the second rotor 12, and the second nozzle 220 is connected to the second channel 14. The spraying direction of the second nozzle 220 is opposite to the pre-rotation direction of the second rotor 12.

[0074] The electromagnetic valve 400 is arranged on the drive gas cylinder 300, and the drive gas cylinder 300 is arranged in the mounting cabin 100.

[0075] The control unit 500 is electrically connected to the electromagnetic valve 400, and can control the on-off state of the electromagnetic valve 400.

[0076] The power supply unit 600 is electrically connected to the electromagnetic valve 400 and the control unit 500, and provides power. The power supply unit 600 is a battery, and is also arranged in the mounting cabin 100.

[0077] When the electromagnetic valve 400 is in the open state, the gas sprayed from the drive gas cylinder 300 enters the first channel 13 through the connection between the first rotor 11 and the mounting cabin 100, and is sprayed from the first nozzle 210. The gas enters the second channel 14 through the connection between the second rotor 12 and the mounting cabin 100, and is sprayed from the second nozzle 220; thereby driving the first rotor 11 and the second rotor 12 to rotate in the pre-rotation direction, and realizing the pre-rotation of the rotorcraft.

[0078] When the electromagnetic valve 400 is in the closed state, the drive gas cylinder 300 stops spraying gas. After the high-pressure gas in the mounting cabin 100 continues for a period of time, the gas stops being sprayed from the first nozzle 210 and the second nozzle 220, and the rotorcraft stops pre-rotation.

[0079] It can be understood that the rotorcraft provided by the embodiments of the present application is provided by setting the mounting cabin 100, and sealingly penetrating the first rotor 11 and the second rotor 12 in the mounting cabin 100, setting the first channel 13 on the first rotor 11 to communicate with the mounting cabin 100, and setting the second channel 14 on the second rotor 12 to communicate with the mounting cabin 100; then, setting the first nozzle 210 with a jet direction opposite to the first rotor 11 on the first rotor 11, and setting the second nozzle 220 with a jet direction opposite to the second rotor 12 on the second rotor 12; setting the driving gas cylinder 300 with the electromagnetic valve 400 in the mounting cabin 100, and setting the control unit 500 to control the opening of the electromagnetic valve 400 and the power supply unit 600 to provide power supply; so that the control unit 500 can control the driving gas cylinder 300 to spray high-pressure gas, to control the first nozzle 210 and the second nozzle 220 to spray gas, to drive the first rotor 11 and the second rotor 12 to pre-rotate, so that the pre-rotation device can generate pre-rotation power by high-pressure gas, and an additional transmission mechanism or transmission connecting rod is not needed to realize pre-rotation of the rotor to a target take-off rotation speed, effectively reducing the weight of the rotorcraft, reducing the structural complexity of the pre-rotation device, reducing the cost, and improving the reliability.

[0080] Specifically, in combination with Figure 2 and Figure 3 In some embodiments of the present application, the first end of the first rotor 11 is sealingly arranged in the mounting cabin 100, and the first end of the second rotor 12 is sealingly arranged in the mounting cabin 100.

[0081] The first channel 13 extends from the first end of the first rotor 11 to the second end of the first rotor 11.

[0082] The second channel 14 extends from the first end of the second rotor 12 to the second end of the second rotor 12.

[0083] The first nozzle 210 is arranged at the second end of the first rotor, and the second nozzle 220 is arranged at the second end of the second rotor 12; the lever principle is used to make the force on the first nozzle 210 and the second nozzle 220 when pushing the rotor 1 to rotate in the pre-rotation direction minimum, so that the rotor 1 can be better pushed to rotate, and the structure is simple.

[0084] Further, in combination with Figures 1 to 3 In some embodiments of the present application, the first nozzle 210 and the second nozzle 220 are arranged in a central symmetry.

[0085] The jet direction of the first nozzle 210 is perpendicular to the first rotor 11, and the jet direction of the second nozzle 220 is perpendicular to the second rotor 12; so that the first nozzle 210 and the second nozzle 220 can be more concentrated and uniform in force when pushing the rotor 1 to rotate in the pre-rotation direction, so that the rotation of the rotor 1 is more stable, and the energy consumed is minimum.

[0086] Combining Figures 2 to 4 In some embodiments of the application, the pre-rotation device of the rotorcraft further comprises a pressure sensor 510, an angular velocity sensor and a wireless communication unit 530, which are all arranged in the installation cabin 100.

[0087] The pressure sensor 510 is electrically connected to the control unit 500 and can feed back the pressure data in the installation cabin 100 to the control unit 500.

[0088] The control unit 500 controls the on-off state of the electromagnetic valve 400 according to the pressure data fed back by the pressure sensor 510.

[0089] The pressure sensor 510 in the installation cabin 100 is responsible for monitoring the cabin air pressure.

[0090] When the air pressure in the installation cabin 100 reaches three times the standard atmospheric pressure, the pressure sensor 510 feeds back a signal to the control unit 500, which closes the electromagnetic valve 400 driving the gas cylinder 300 and stops charging the installation cabin 100.

[0091] When the air pressure in the installation cabin 100 is lower than 2.8 times the standard atmospheric pressure, the control unit 500 controls the electromagnetic valve 400 to open and charge the installation cabin 100.

[0092] A feedback loop is formed by the pressure sensor 510 to stabilize the air pressure in the installation cabin 100 at 2.8-3 times the standard atmospheric pressure; so that the pre-rotation device can stably push the rotor 1 to pre-rotate.

[0093] The angular velocity sensor is electrically connected to the control unit 500, and the angular velocity sensor can monitor the angular velocity value of the rotor 1 and feed back the angular velocity data to the control unit 500.

[0094] The control unit 500 controls the on-off state of the electromagnetic valve 400 according to the angular velocity data fed back by the angular velocity sensor.

[0095] When the pre-rotation of the rotor 1 accelerates to the target rotational speed, the control unit 500 controls the electromagnetic valve 400 driving the gas cylinder 300 to be closed, which can stop the further pre-rotation acceleration of the rotor 1.

[0096] After the rotor 1 reaches the target pre-rotation speed, the rotorcraft can take off by sliding, and the pre-rotation process is completed. The pre-rotation control is simpler, easier to operate, and more accurate.

[0097] In addition, combining Figures 2 to 4In some embodiments of the present application, the driving gas cylinder 300 comprises a first driving gas cylinder 310 and a second driving gas cylinder 320, and the electromagnetic valve 400 comprises a first electromagnetic valve 410 and a second electromagnetic valve 420. The first driving gas cylinder 310 and the second driving gas cylinder 320 can be filled with 4L of 13Mpa high-pressure gas.

[0098] 4L of 13Mpa high-pressure gas can complete three 150kg-level rotorcraft take-off pre-rotation operations, enough to complete a single-day flight mission, and can also replace the new driving gas cylinder 300 during post-flight maintenance to meet the next day's flight mission requirements.

[0099] The first electromagnetic valve 410 is arranged in the first driving gas cylinder 310, and the second electromagnetic valve 420 is arranged in the second driving gas cylinder 320.

[0100] The first electromagnetic valve 410 and the second electromagnetic valve 420 are electrically connected with the control unit 500. The control unit 500 can simultaneously control the on-off state of the first electromagnetic valve 410 and the second electromagnetic valve 420, so that the pre-rotation device can provide more high-pressure gas to ensure the normal operation of pre-rotation.

[0101] In combination Figure 2 In some embodiments of the present application, the pre-rotation device of the rotorcraft further comprises a sealing ring 101, and the installation cabin 100 comprises a first cabin shell 110 and a second cabin shell 120. The installation cabin 100 formed by the first cabin shell 110 and the second cabin shell 120 is completely sealed with the rotor 1 and can withstand five standard atmospheres, about 500kpa.

[0102] The first cabin shell 110 and the second cabin shell 120 are detachably sealed and connected by the sealing ring 101 to form a containing cavity 102.

[0103] The rotorcraft body 2 is provided with a support seat 3 protruding therefrom, the support seat 3 is provided with a rotating shaft 31, and the second cabin shell 120 is connected to the rotating shaft 31.

[0104] The rotor 1 is sealingly arranged in the second cabin shell 120 and connected with the rotating shaft 31, and the rotor 1 and the second cabin shell 120 rotate synchronously.

[0105] The driving gas cylinder 300, the control unit 500, and the power supply unit 600 are arranged in the containing cavity 102. This facilitates the installation and removal of the related components of the pre-rotation device, and also saves the installation space required by the pre-rotation device.

[0106] In combination Figure 4 In some embodiments of the present application, the pre-rotation device of the rotorcraft further comprises a wireless communication unit 530.

[0107] The wireless communication unit 530 is electrically connected with the control unit 500, can receive external instructions to control the control unit 500, thereby controlling the on-off state of the electromagnetic valve 400, facilitating the state control operation of driving the high-pressure gas in the gas cylinder 300, and enabling the pre-rotation device to operate more intelligently, and the use can be remotely operated, convenient and fast.

[0108] In combination Figure 1 In some embodiments of the present application, the airflow nozzle 200 is a subsonic nozzle, and the jet speed is 0.8-0.9Ma. That is, the first nozzle 210 and the second nozzle 220 can also be subsonic nozzles, and the subsonic nozzles can adopt 0.8-0.9Ma, which can convert high-pressure gas into high-speed jet flow, thereby increasing the output of power, and the manufacturing cost is relatively low, and easy to maintain and replace.

[0109] In combination Figures 1 to 4 The embodiment of the present application provides a pre-rotation method of a rotorcraft, which comprises the following steps:

[0110] First step: a first nozzle 210 and a second nozzle 220 with opposite jet directions and pre-rotation directions are respectively arranged at two ends of a rotor 1 of a rotorcraft.

[0111] Second step: a sealed mounting cabin 100 is arranged on the rotor 1, the mounting cabin 100 is communicated with the first nozzle 210 through a first channel 13, and the mounting cabin 100 is communicated with the second nozzle 220 through a second channel 14.

[0112] Third step: a driving gas cylinder 300 with an electromagnetic valve 400 is placed in the mounting cabin 100, and the state of jetting gas of the first nozzle 210 and the second nozzle 220 is controlled through the on-off state of the electromagnetic valve 400.

[0113] Fourth step: a control unit 500 is electrically connected with the electromagnetic valve 400, and the on-off state of the electromagnetic valve 400 is controlled through the control unit 500.

[0114] Fifth step: a wireless communication unit 530 is electrically connected with the control unit 500, and instructions are transmitted to the control unit 500 through the wireless communication unit 530.

[0115] Sixth step: a pressure sensor 510 is electrically connected with the control unit 500, and pressure data in the mounting cabin 100 is fed back to the control unit 500 to control the on-off state of the electromagnetic valve 400.

[0116] Seventh step: an angular velocity sensor is electrically connected with the control unit 500, and is suitable for monitoring the angular velocity value of the rotor 1 and feeding back angular velocity data to the control unit 500 to control the on-off state of the electromagnetic valve 400.

[0117] The eighth step: the power supply unit 600 is electrically connected with the electromagnetic valve 400, the control unit 500, the wireless communication unit 530, the pressure sensor 510 and the angular velocity sensor, so as to provide power supply.

[0118] It should be noted that according to the pre-rotation method of the rotorcraft provided above, the rotorcraft can slide on the runway and wait for the take-off instruction; after receiving the take-off instruction, the pilot of the rotorcraft issues a start pre-rotation instruction.

[0119] The wireless communication unit 530 receives the start instruction and transmits the instruction to the control unit 500, the control unit 500 controls the electromagnetic valve 400 to open, and drives the gas in the gas cylinder 300 to enter the installation cabin 100, the gas pressure in the installation cabin 100 rises, the gas is sprayed from the first nozzle 210 through the first channel 13 and from the second nozzle 220 through the second channel 14, and the rotor 1 rotates to realize pre-rotation.

[0120] The pressure sensor 510 in the installation cabin 100 starts to work, monitors the gas pressure value in the installation cabin 100, and feeds back to the control unit 500, the control unit 500 controls the opening or closing of the electromagnetic valve 400 according to the data fed back by the pressure sensor 510, so that the gas pressure in the installation cabin 100 can be stabilized at 2.8-3 times the standard atmospheric pressure; the stable gas pressure ensures the high-speed gas flow spraying speed at the first nozzle 210 and the second nozzle 220 of the rotor 1, so that the rotating speed of the rotor 1 is stably improved.

[0121] When the angular velocity sensor monitors that the rotating speed of the rotor 1 reaches the target pre-rotation speed, a signal can be sent to the pilot through the wireless communication unit 530 to prompt that the take-off pre-rotation angular velocity value is reached, and feedback to the control unit 500 to control the electromagnetic valve 400 to close the high-pressure gas cylinder to drive the gas cylinder 300, so as to stop driving the gas cylinder 300 to release gas.

[0122] Finally, 11. The pilot operates the rotorcraft to take off according to the rotorcraft rotating speed instrument data fed back by the control unit 500, and the pre-rotation device drives the plurality of rotors 1 to pre-rotate before the propeller 4 drives the rotorcraft to take off. At least two rotors 1 are provided with airflow nozzles 200 suitable for rotating the rotors 1. The take-off process is completed.

[0123] It can be understood that the pre-rotation method of the rotorcraft provided by the embodiment of the present application is characterized in that: a first nozzle 210 and a second nozzle 220 with opposite jet directions and pre-rotation directions are arranged at two ends of a rotor 1 of the rotorcraft respectively; a sealed installation cabin 100 is arranged on the rotor 1, the installation cabin 100 is connected with the first nozzle 210 through a first channel 13, and the installation cabin 100 is connected with the second nozzle 220 through a second channel 14; a driving gas cylinder 300 with an electromagnetic valve 400 is placed in the installation cabin 100, the state of jetting gas of the first nozzle 210 and the second nozzle 220 is controlled through the on-off state of the electromagnetic valve 400; a control unit 500 is electrically connected with the electromagnetic valve 400, and the on-off state of the electromagnetic valve 400 is controlled through the control unit 500; a wireless communication unit 530 is electrically connected with the control unit 500, and instructions are transmitted to the control unit 500 through the wireless communication unit 530; a pressure sensor 510 is electrically connected with the control unit 500, and pressure data in the installation cabin 100 is fed back to the control unit 500 to control the on-off state of the electromagnetic valve 400; an angular velocity sensor is electrically connected with the control unit 500, and the angular velocity value of the rotor 1 is monitored and angular velocity data is fed back to the control unit 500 to control the on-off state of the electromagnetic valve 400; and a power supply unit 600 is electrically connected with the electromagnetic valve 400, the control unit 500, the wireless communication unit 530, the pressure sensor 510 and the angular velocity sensor, so as to provide power supply. Thus, the pre-rotation of the rotorcraft can be driven by high-pressure gas, and no additional transmission mechanism or transmission connecting rod is needed to realize pre-rotation of the rotor to a target take-off rotation speed, so that the weight of the rotorcraft is effectively reduced, the structural complexity of the pre-rotation device is reduced, the cost is reduced, and the reliability is improved.

[0124] In this specification, unless otherwise expressly specified and limited, a first feature is "on", "above", or "under" a second feature can mean that the first and second features are directly in contact, or the first and second features are indirectly in contact through an intermediate medium. Moreover, the first feature "above", "over", and "on" the second feature can mean that the first feature is directly above or obliquely above the second feature, or only means that the first feature is horizontally higher than the second feature. The first feature "below", "under", and "under" the second feature can mean that the first feature is directly below or obliquely below the second feature, or only means that the first feature is horizontally lower than the second feature.

[0125] In the description of the specification, the description using the terms "preferred embodiment", "still another embodiment", "some embodiments", "other embodiments" or "specific examples" etc. means that the specific features, structures, materials or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present application. In the specification, the illustrative expressions of the above terms are not necessarily directed to the same embodiment or example. Also, the specific features, structures, materials or characteristics described can be combined in any appropriate manner in any one or more embodiments or examples. Furthermore, the person skilled in the art can combine and combine the different embodiments or examples described in the specification and the features of the different embodiments or examples, without contradiction.

[0126] Although the embodiments of the present application have been shown and described above, it is understood that the above-described embodiments are exemplary, and should not be construed as limiting the present application, and those skilled in the art can make changes, modifications, replacements and variations to the above-described embodiments within the scope of the present application.

Claims

1. A rotorcraft, comprising a rotorcraft body, a pre-rotation device, a plurality of rotors, a propeller and a main power device, the main power device is installed in the rotorcraft body and drivingly connected with the propeller, the pre-rotation device is installed above the rotorcraft body, the plurality of rotors are rotatably installed above the rotorcraft body and connected with the pre-rotation device, when the rotorcraft takes off, the pre-rotation device first drives the plurality of rotors to pre-rotate, and then the propeller drives the rotorcraft to take off, characterized in that, At least two rotors are provided with airflow nozzles suitable for driving the rotation of the rotors, The pre-rotation device comprises: A mounting cabin mounted above the rotorcraft body, the plurality of rotors being connected to the mounting cabin and radially distributed around the mounting cabin; A drive gas cylinder provided in the mounting cabin and communicated with the airflow nozzles through a gas supply channel; A control unit connected with the drive gas cylinder and / or the gas supply channel, suitable for controlling the drive gas cylinder to supply gas to the airflow nozzles; A power supply unit electrically connected with the control unit, suitable for providing power supply for the control unit.

2. The gyroplane according to claim 1, characterized in that The rotorcraft body is provided with a support seat protruding therefrom, the support seat is provided with a rotating shaft, the plurality of rotors and the mounting cabin are synchronously rotatably connected to the rotating shaft, in the flight state, the control unit controls the drive gas cylinder not to supply gas to the airflow nozzles.

3. The gyroplane of claim 1, wherein, The mounting cabin is a decompression cabin, the rotors are hollow structures, and the gas supply channel is provided in the rotors.

4. The rotorcraft of claim 3, wherein The rotors are sealed in the mounting cabin, the rotors include a first rotor and a second rotor, the gas supply channel includes a first channel and a second channel, and the airflow nozzles include a first nozzle and a second nozzle, The first channel is provided in the first rotor and communicated with the mounting cabin, The second channel is provided in the second rotor and communicated with the mounting cabin, The first nozzle is provided in the first rotor and communicated with the first channel, and the jet direction of the first nozzle is opposite to the pre-rotation direction of the first rotor; The second nozzle is provided in the second rotor and communicated with the second channel, and the jet direction of the second nozzle is opposite to the pre-rotation direction of the second rotor; The drive gas cylinder is provided with a solenoid valve; The control unit is electrically connected with the solenoid valve and suitable for controlling the on-off state of the solenoid valve; The power supply unit is a battery also mounted in the mounting cabin.

5. The gyroplane according to claim 4, characterized in that The first end of the first rotor is sealed in the mounting cabin, and the first end of the second rotor is sealed in the mounting cabin, The first channel extends from the first end of the first rotor to the second end of the first rotor, The second channel extends from the first end of the second rotor to the second end of the second rotor, The first nozzle is provided at the second end of the first rotor, and the second nozzle is provided at the second end of the second rotor.

6. The gyroplane according to claim 5, characterized in that The first nozzle and the second nozzle are centrally symmetrically arranged, The jet direction of the first nozzle is perpendicular to the first rotor, and the jet direction of the second nozzle is perpendicular to the second rotor.

7. The gyroplane of claim 4, wherein, Further comprising a pressure sensor, an angular velocity sensor, and a wireless communication unit, all of which are provided in the mounting cabin, The pressure sensor is electrically connected with the control unit and suitable for feeding back the pressure data in the mounting cabin to the control unit, The control unit controls the on-off state of the solenoid valve according to the pressure data fed back by the pressure sensor. The angular velocity sensor is electrically connected with the control unit, and is adapted to monitor the angular velocity value of the rotor and feed back angular velocity data to the control unit, The control unit controls the on-off state of the electromagnetic valve according to the angular velocity data fed back by the angular velocity sensor; The wireless communication unit is electrically connected with the control unit, and is adapted to receive external instructions to control the control unit.

8. The gyroplane of claim 4, wherein, The driving gas cylinder comprises a first driving gas cylinder and a second driving gas cylinder, and the electromagnetic valve comprises a first electromagnetic valve and a second electromagnetic valve, The first electromagnetic valve is arranged in the first driving gas cylinder, and the second electromagnetic valve is arranged in the second driving gas cylinder, The first electromagnetic valve and the second electromagnetic valve are electrically connected with the control unit.

9. The gyroplane of claim 4, wherein, The mounting cabin comprises a first cabin shell and a second cabin shell and a sealing ring, the first cabin shell and the second cabin shell are detachably and sealingly connected through the sealing ring to form a containing cavity, The rotorcraft body is provided with a support seat protruding therefrom, the support seat is provided with a rotating shaft, and the second cabin shell is connected to the rotating shaft, The rotor is arranged in the second cabin shell and is connected with the rotating shaft, and the rotor and the second cabin shell rotate synchronously, The driving gas cylinder, the control unit and the power supply unit are all mounted in the containing cavity.

10. The gyroplane of claim 4, wherein, The airflow nozzle is a subsonic nozzle, and the jet speed is 0.8-0.9Ma, The air pressure of the mounting cabin is stabilized at 2.8-3 times of the standard atmospheric pressure.

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