New-configuration cross-medium aircraft based on blade tip jet rotors and working method of new-configuration cross-medium aircraft

Abstract

The invention discloses a new-configuration cross-medium aircraft based on blade tip jet rotors and a working method thereof, the aircraft has an air flight mode, an underwater navigation mode and a cross-medium mode, and comprises a fuselage; the main rotor system comprises an electric centrifugal compressor which is arranged on the fuselage in a jacking manner and a blade tip air injection main rotor blade which is connected with an air path of the electric centrifugal compressor; the auxiliary lift system comprises lift units arranged on the fuselage in a distributed mode, and the lift units can be independently controlled; in the air flight mode, the propeller tip jets air, the main rotor rotates, and the auxiliary lift system works to realize air flight; and in the underwater navigation mode, the blade tip jets air, the main rotor stops rotating, the blades on the single side are overturned around the fixed axis till the blade nozzles face the advancing rear portion, and the underwater water jet propulsion device is formed. The novel-configuration cross-medium aircraft disclosed by the invention adopts a distributed lift force layout, has relatively large take-off weight and good maneuverability, can realize continuous medium crossing, and is small in water entering and exiting impact.

Description

Technical Field

[0001] The present invention belongs to the field of cross-medium aircraft, and in particular relates to a cross-medium aircraft based on a blade tip jet rotor and a working method thereof. Background Art

[0002] With the progress of society and the development of science and technology, mission scenarios involving water and air media, such as hydrological surveys, underwater pipeline exploration and covert reconnaissance, are increasing. Compared with platforms such as submersibles that can only work underwater, seaplanes that cannot dive underwater, and submarine-launched drones that can only cross the medium once and work in the air, cross-media aircraft are widely valued by scientific researchers in various countries because they can cross the water and air media multiple times and have the characteristics of high speed of aircraft and concealment of submarines.

[0003] At present, the cross-medium aircraft studied at home and abroad are mainly divided into fixed wings, multi-rotor wings, hybrid wings, bionic flapping wings, bionic swept wings and other types. These cross-medium aircraft generally have problems such as small load, inability to continuously cross the medium or large impact of entering the water. In addition, most cross-medium aircraft use the same set of propulsion devices to drive the movement of the aircraft in the two media in the same propulsion mode. Due to the great difference in the physical properties of the water and air media, it is difficult for the aircraft to achieve better efficiency in both media at the same time. If independent propulsion devices are used in different media, the weight of the aircraft will inevitably increase. The additional propulsion device will also increase the drag of the aircraft in a single medium and reduce the efficiency of the aircraft. Therefore, designing a cross-medium aircraft with a large load, continuous crossing of the medium and small impact of entering and exiting the water has become an urgent problem to be solved. The tip jet rotor has application prospects in the field of cross-medium aircraft because it does not generate anti-torque when working and its unique working mode can provide power to the aircraft in different ways in the two media.

[0004] For example, the patent (application number: CN202410686386.X, publication date: 2024.08.23, publication number: CN118529247A) proposes a water-air amphibious cross-medium aircraft with a water storage tank, which uses water inlet and outlet of the water storage tank to achieve medium crossing, and uses an independent ducted propeller for underwater propulsion. The water storage in the water tank makes the cross-medium process of the aircraft take a long time, and the additional propulsion device increases the resistance of the aircraft in a single medium.

[0005] The patent (patent application number: CN202410644966.2, publication date: 2024.06.25, publication number: CN118238560A) proposes a fuselage tilt thrust vector cross-medium aircraft, which is equipped with multiple airbags at the bottom of the fuselage, and a high-pressure gas tank for inflating the airbags inside the fuselage. The aircraft's entry and exit posture is adjusted by inflating and deflating the airbags at different positions, so that the aircraft can enter and exit the water in a manner similar to a quadcopter. The aircraft is equipped with a dedicated underwater vector propulsion device underwater. The inflation and deflation of the airbags make the cross-medium process of the aircraft take a long time, and the additional propulsion device also increases the drag of the aircraft in a single medium.

[0006] The patent (patent application number: CN202311217560.8, publication date: 2023.11.17, publication number: CN117067835A) discloses a highly maneuverable cross-medium aircraft. Before entering the water, the aircraft retracts its wings to become a swept-wing structure, the propeller in the air stops and folds, and the aircraft dives into the water. The underwater ducted thruster provides power for the aircraft to navigate underwater. When leaving the water, the aircraft relies on power to rush out of the water, and then the propeller in the air works and the wings unfold. The cross-medium mode of the aircraft will bring a greater impact on the onboard equipment and the body itself, and the underwater thruster will bring unnecessary drag to the aircraft's aerial flight.

[0007] The patent (patent application number: CN202311412695.X, publication date: 2023.12.12, publication number: CN117207723A) discloses a coaxial water-air power device and a variable configuration cross-medium aircraft, which has four coaxial water-air power devices consisting of an air propeller and an underwater propeller. Different propellers are used in different media, and the control method is the same as that of a quadcopter. When crossing the medium, the two medium propellers work together to complete the cross-medium maneuver. In addition, the aircraft can also retract the arm equipped with the power device and sail at high speed underwater. The underwater propulsion device of the aircraft will bring unnecessary waste resistance to aerial flight.

[0008] The patent (patent application number: CN202210816555.8, publication date: 2022.11.04, publication number: CN115285350A) discloses a variant cross-medium aircraft and a control method that can repeatedly enter and exit water. The aircraft is a fixed-wing aircraft driven by four propellers when cruising in the air. When crossing the medium, the wings are folded so that the propellers are all facing upwards to approach the water surface in a four-rotor working mode, and the medium is crossed by using a water tank to absorb and discharge water. The underwater propeller provides power during underwater cruising. The water tank absorption and drainage takes a long time, making the cross-medium process discontinuous, and the additional propulsion device also increases the waste resistance of the aircraft in a single medium.

[0009] The above-mentioned cross-medium aircraft all have the disadvantages of long cross-medium process time, discontinuous cross-medium process, large impact of entering and exiting water that can easily cause equipment damage, independent propulsion device that increases drag, and limited take-off weight, which restricts the application of cross-medium aircraft. Summary of the invention

[0010] In view of the above-mentioned defects, the present invention provides a new configuration of cross-medium aircraft based on blade tip jet rotors, which realizes the design of a cross-medium aircraft with a large load, continuous crossing of the medium, small impact of entering and exiting the water, and low running resistance.

[0011] A new configuration cross-medium aircraft based on a blade tip jet rotor, which has an air flight mode, an underwater navigation mode and a cross-medium mode, and the aircraft comprises: a fuselage; a main rotor system, comprising an electric centrifugal compressor placed on top of the fuselage and a blade tip jet main rotor blade connected to the compressor air path, wherein the compressor has a compressed air ejection mode and a compressed water ejection mode; an auxiliary lift system, comprising lift units distributedly arranged on the fuselage, and the lift units can be independently controlled respectively;

[0012] In the air flight mode, the air flight is achieved based on the rotation of the main rotor with the jet at the blade tip and the operation of the propulsion device;

[0013] In underwater navigation mode, the tip jet main rotor stops rotating, and the single-side blade flips around a fixed axis so that the blade nozzle faces the rear of the vehicle, serving as an underwater water jet propulsion device;

[0014] In the cross-medium mode, when the aircraft is about to enter the water, the auxiliary lift system rotor and the main rotor stop, and the aircraft enters the water by its own gravity; at the same time, the blades on one side of the main rotor flip and switch to an underwater water jet propulsion device; when the aircraft is about to emerge from the water, the auxiliary lift system drives the aircraft partially out of the water, and at the same time, the main rotor blades flip and switch back to the air state to drive the aircraft out of the water. At this time, the auxiliary lift system stops at the water-air interface, and starts working immediately after it is completely out of the water, and the aircraft enters the air flight mode.

[0015] Preferably, the compressor is an electric single-stage centrifugal compressor having a plurality of centrally symmetrical air outlet passages corresponding to a plurality of blades of the tip jet main rotor.

[0016] Preferably, the main rotor system has at least two main rotor blades.

[0017] Preferably, the main rotor system installation axis passes through the fuselage center of mass, and the main rotor blades are installed on a multi-outlet electric centrifugal compressor through a rotating mechanism and a gas flow channel to provide the main lift for the aircraft.

[0018] Preferably, when sailing underwater, the main rotor blades rotate until the chord line is always parallel to the direction of the incoming flow.

[0019] Preferably, the lift unit is an electric rotor, which is directly driven by a brushless motor and installed in the same plane below the main rotor plane.

[0020] Preferably, the number of the electric rotors is four, which are distributed and installed at four diagonal corners of the fuselage.

[0021] The present invention also discloses a working method of a new configuration cross-medium aircraft with a blade tip jet rotor, which has air flight, underwater navigation and cross-medium modes.

[0022] Aerial flight mode: vertical takeoff based on the tip-jet main rotor and auxiliary lift system, and each auxiliary lift unit is controlled separately to achieve aircraft attitude control;

[0023] Cross-medium mode: When preparing to enter the water, the main rotor and the auxiliary lift system rotor stop rotating, and the aircraft enters the water by its own gravity; when preparing to exit the water, the main rotor and the auxiliary lift system rotor work to generate lift to drive the aircraft out of the water;

[0024] In underwater navigation mode, the main rotor blades flip and switch to underwater propulsion mode, and the chord of the main rotor blades is always parallel to the incoming flow direction; the underwater attitude control of the aircraft is achieved based on each auxiliary lift unit.

[0025] Preferably, attitude control includes pitch maneuver, heading change and roll maneuver, and the auxiliary lift system is divided into a front lift unit and a rear lift unit according to the forward direction, and the lift units are divided into a left lift unit and a right lift unit according to the left and right sides of the forward direction. Among them, pitch maneuver: control the change of the rotation speed of the rear or front lift unit to generate a torque to change the pitch attitude of the aircraft; heading change: control the increase of the rotation speed of one diagonal lift unit, and the decrease of the rotation speed of the other diagonal lift unit to generate an unbalanced torque to change the heading of the aircraft; roll maneuver: control the change of the rotation speed of the left or right lift unit to generate a torque to change the roll attitude of the aircraft.

[0026] The beneficial effects of the present invention are:

[0027] (1) The cross-medium aircraft of the present invention adopts a distributed lift layout design based on the tip jet main rotor.

[0028] The tip-jet main rotor provides 60% lift, and the auxiliary lift system composed of four electric auxiliary rotors provides 40% lift. While increasing the load capacity of the cross-medium aircraft, it also has the advantages of being able to continuously cross the medium, with little impact on entering and exiting the water, and being maneuverable and flexible. This solves the problems of existing cross-medium aircraft with limited load capacity, discontinuous cross-medium process, or large impact on entering and exiting the water.

[0029] (2) The cross-medium aircraft of the present invention has innovative power device layout and underwater driving mode, using a top-mounted electric centrifugal compressor to provide power for the tip jet rotor, and the rotor blades can be flipped underwater so that the nozzles are all facing backwards, and water jet propulsion is performed underwater. The rotor provides power to the aircraft in the water and air media in different ways, which solves the problem that the existing cross-medium aircraft is equipped with two independent power devices, which causes unnecessary weight increase, or uses the same propulsion device to work in two media in the same driving mode, which makes it difficult to achieve better efficiency at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below.

[0031] Figure 1 It is an overall view of the aerial flight status of the cross-media aircraft of the present invention;

[0032] Figure 2 It is an overall view of the underwater navigation state of the cross-media aircraft of the present invention;

[0033] Figure 3 This is a main force analysis diagram of the cross-medium aircraft in the air flight state of the present invention;

[0034] Figure 4 This is a main force analysis diagram of the cross-medium aircraft in underwater navigation state of the present invention;

[0035] Figure 5 It is a schematic diagram of the working mode of the cross-media aircraft of the present invention.

[0036] Reference numerals: 1 main rotor, 2 auxiliary lift system, 3 electric centrifugal compressor, 4 fuselage. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] Example 1

[0039] The invention discloses a new configuration cross-medium aircraft based on a blade tip jet rotor, which adopts a distributed lift layout design. The blade tip jet main rotor is powered by an overhead electric centrifugal compressor, and the rotor blades can be flipped so that the nozzles are all facing backwards, and water spraying provides power for the aircraft to navigate underwater. The aircraft has a large take-off weight and good maneuverability, and can realize an aerial flight mode, an underwater navigation mode, and a continuous medium crossing with a small impact on entering and exiting the water.

[0040] like Figure 1 As shown, the overall layout of the aircraft in flight includes a fuselage 4, a main rotor using a tip jet main rotor 1 with a top-mounted power device, and its installation axis passes through the center of mass of the fuselage 4. The rotor blades are installed on an improved double-outlet electric centrifugal compressor 3 through a rotating mechanism and a gas flow channel, forming a power, lift, and control integrated pressure jet rotor system to provide the main lift for the aircraft. In this embodiment, the main rotor 1 uses two rotor blades located on the same straight line in the same plane. The blades of the tip jet main rotor 1 have a nozzle, which is as shown in the figure below. Figure 1 As shown, the nozzles of the two main rotor blades face in opposite directions, and can drive the main rotor blades to rotate when jetting, providing power for the aircraft. In this embodiment, the electric centrifugal compressor 3 is improved to a double outlet to correspond to the air path of the two main rotor blades. The compressor housing is connected to the main rotor blades and rotates together with the main rotor blades, simplifying the structure. At the same time, corresponding to the structure of placing the air source inside the fuselage and connecting it to the blades through the air path pipeline in the prior art, the electric centrifugal compressor 3 is placed on top in this embodiment and directly connected to the main rotor blades, which is less likely to cause leakage, reduces flow loss, and improves system integration.

[0041] The auxiliary lift system 2 includes lift units distributed on the fuselage, and the lift units can be independently controlled. In this embodiment, four common air motor direct-drive rotors are used, which are directly driven by brushless motors and installed in the same plane below the main rotor plane. The auxiliary lift system 2 is also an aircraft attitude control system. When flying in the air and diving underwater, attitude control is achieved by separately controlling each direct-drive rotor. In addition, it also plays an important role in the cross-medium process. A sensor is also provided below the auxiliary lift system to detect whether it is in contact with the water surface.

[0042] In the entire power system, the tip-jet main rotor 1 provides 60% of lift, and the auxiliary lift system 2 composed of four electric auxiliary rotors provides 40% of lift.

[0043] like Figure 2The figure shows the overall layout of the aircraft in underwater navigation. After entering the water, the main rotor stops rotating and is locked at a position perpendicular to the fuselage axis. The single-side blade flips, and the blade nozzles on both sides face backwards. The rotor becomes an underwater water jet propulsion device, which generates thrust by spraying water. Regardless of the aircraft's underwater posture, the rotor blade chord is always parallel to the incoming flow direction.

[0044] The aircraft also has a cross-medium mode. When the aircraft is about to enter the water, a sensor is installed under the auxiliary lift system to detect whether it is in contact with the water surface. When it detects that the bottom of the auxiliary lift system is in contact with the water surface, the auxiliary lift system rotor and the main rotor stop rotating, and the aircraft relies on its own gravity to enter the water. At the same time, the blades on one side of the main rotor flip and switch to the underwater working state; when the aircraft is about to emerge from the water, the auxiliary lift system drives the aircraft partially out of the water. At the same time, the main rotor blades flip and switch back to the air state, and start rotating to generate lift, further driving the aircraft out of the water. At this time, the auxiliary lift system stops at the water-air interface, and works immediately after it is completely out of the water, and the aircraft enters the air flight mode.

[0045] The aircraft fuselage adopts a sealed structure, which can provide greater buoyancy underwater and at the same time ensure watertightness to ensure the normal operation of the electronic equipment placed inside it.

[0046] Example 2

[0047] The present invention also discloses a working method of a new configuration cross-medium aircraft based on a blade tip jet rotor, such as Figure 5 As shown, the new configuration cross-medium aircraft based on the blade tip jet rotor has air flight, underwater navigation and cross-medium modes, among which the cross-medium process can be further divided into water entry process and water exit process.

[0048] The aircraft takes off vertically with the help of the main rotor and the auxiliary lift system, and flies in an aerial flight mode similar to that of a multi-rotor aircraft. When preparing to enter the water, the aircraft continuously adjusts its attitude to approach the water surface. When the bottom of the auxiliary lift system touches the water surface, the auxiliary lift system rotor and the main rotor stop, and the aircraft enters the water under its own gravity. At the same time, the main rotor blades flip and switch to the underwater working state, providing power for the aircraft to cruise underwater, and the auxiliary lift system controls the aircraft's attitude. When it needs to get out of the water, the aircraft cruises close to the water surface, and the auxiliary lift system drives the aircraft partially out of the water. At the same time, the main rotor blades flip and switch back to the aerial state, and begin to rotate to generate lift, further driving the aircraft out of the water. The auxiliary lift system stops at the water-air interface, and works immediately after it is completely out of the water, and the aircraft enters the aerial flight mode.

[0049] Specifically,

[0050] Air flight mode

[0051] The aircraft's flight mode is similar to that of a traditional quadcopter, and it can perform vertical takeoff and landing, fixed-point hovering, pitch maneuvers, heading change maneuvers, and roll maneuvers. Figure 3 As shown, where M a is the anti-torque of the auxiliary lift unit, and M is the pitch moment of the fuselage.

[0052] Vertical take-off and landing and hovering: The main rotor rotates and increases the speed to generate lift F Lj , the auxiliary lift system speed increases to generate lift F La , if the total lift and the aircraft weight satisfy

[0053] F Lj +4F La >G

[0054] The aircraft generates a vertical upward acceleration a z , if the total lift and the aircraft weight satisfy

[0055] F Lj +4F La =G

[0056] The aircraft can hover if the total lift and the aircraft gravity are

[0057] F Lj +4F La <G

[0058] The aircraft will generate a vertical downward acceleration a from the hovering state z .

[0059] Pitch maneuver: The rotation speed of the auxiliary propulsion devices C and D increases, generating a torque to rotate the aircraft around the y-axis. The thrust of the main rotor and the auxiliary lift system in the vertical direction is balanced with gravity.

[0060] F Ljz +4F Laz =G

[0061] The horizontal component of force causes the aircraft to generate forward acceleration

[0062] F Ljx +4F Lax -f=ma x

[0063] Similarly, when the rotation speed of the auxiliary propulsion devices A and B increases, the aircraft moves backward.

[0064] Heading change: When the speed of one diagonal auxiliary lift system increases and the speed of the other diagonal auxiliary lift system decreases, an unbalanced torque is generated to rotate the aircraft around the z-axis, thereby changing the heading. For example, when the speed of auxiliary lift systems A and D increases and the speed of B and C decreases, there is

[0065] M A +M D >M C +M B

[0066] The aircraft rotates clockwise.

[0067] Roll maneuver: Similar to pitch maneuver control, the speed of the auxiliary propulsion devices A and C increases, generating torque to rotate the aircraft around the x-axis, and the thrust of the main rotor and the auxiliary lift system in the vertical direction is balanced with gravity

[0068] F Ljz +4F Laz =G

[0069] The horizontal force causes the aircraft to accelerate sideways.

[0070] F Ljy +4F Lay -f=ma y

[0071] Similarly, when the rotation speed of the auxiliary propulsion devices B and D increases, the aircraft moves to the other side.

[0072] Underwater cruise mode

[0073] When the aircraft enters the water, the main rotor stops, and the single-side rotor blade rotates, with both blade nozzles facing backwards. At the same time, the compressor changes to underwater working mode to pressurize water and spray out, and the rotor system becomes an underwater propulsion device. The rotor blades always keep the chord parallel to the incoming flow direction, and the thrust direction of the propulsion device is always opposite to the incoming flow direction. The aircraft can complete cruising, fixed-point hovering, buoyancy, pitching maneuvers, heading change maneuvers, and rolling maneuvers underwater. The main force analysis is as follows: Figure 4 As shown. The buoyancy F generated by the aircraft B Slightly less than the total weight of the aircraft.

[0074] Underwater cruising: The thrust generated by the rotor propulsion device overcomes the resistance of the aircraft to provide power for underwater cruising, and the auxiliary lift system keeps the aircraft stable. The buoyancy generated by the aircraft and the thrust of the auxiliary lift system are balanced in the vertical direction, then

[0075] F B +4F La =G

[0076] Keep the aircraft's diving depth stable.

[0077] Ascending, diving and hovering: The rotor propulsion device stops generating thrust, and

[0078] F B +4F La =G

[0079] At this time, the aircraft hovers in the water. Increase the rotational speed of the auxiliary lift system, the thrust increases, and then there is

[0080] F B +4F La >G

[0081] The aircraft generates an upward acceleration a z . Reduce the rotational speed of the auxiliary lift system or reverse the auxiliary lift system, the thrust decreases or a downward thrust is generated, then there is

[0082] F B +4F La <G or F B <4F La +G

[0083] The aircraft generates a diving acceleration a z .

[0084] Pitch maneuver: Increase the rotational speeds of the auxiliary lift systems C and D, generate a moment to make the aircraft rotate around the y-axis, and the resultant force of the thrust in the vertical direction and the buoyancy balances the gravity

[0085] F B +4F Laz =G

[0086] The resultant force of the horizontal component force and the thrust of the propulsion device makes the aircraft sail forward, which can be expressed as

[0087] F T +4F Lax -f=ma x

[0088] When the rotational speeds of the auxiliary propulsion devices A and B increase and the propulsion device stops generating thrust, the aircraft moves backward.

[0089] Course change: The underwater course change is similar to that in the air. When the rotational speed of one diagonal auxiliary lift system increases and the rotational speed of the other diagonal auxiliary lift system decreases, an unbalanced moment is generated to make the aircraft rotate around the z-axis, and then the course changes. For example, when the rotational speeds of the auxiliary lift systems A and D increase and the rotational speeds of B and C decrease, then there is

[0090] M A +M D >M C +M B

[0091] The aircraft rotates clockwise.

[0092] Roll maneuver: Increase the rotational speeds of the auxiliary propulsion devices A and C, generate a moment to make the aircraft rotate around the x-axis, and the buoyancy and the thrust of the auxiliary lift system in the vertical direction balance the gravity

[0093] F B +4F Laz =G

[0094] The horizontal force causes the aircraft to accelerate sideways.

[0095] 4F Lay -f=ma y

[0096] Similarly, when the rotation speed of the auxiliary propulsion devices B and D increases, the aircraft moves to the other side.

[0097] Cross-media model

[0098] The cross-medium mode is mainly divided into water entry mode and water exit mode. In order to avoid the influence of the medium interface on the propulsion device, all rotors stop when entering the water. During the water exit process, the main rotor and the auxiliary lift system work alternately.

[0099] Water entry mode: The aircraft gradually approaches the water surface from the air flight state. When the bottom of the auxiliary lift system touches the water surface, the main rotor and the auxiliary lift system stop rotating, and the aircraft enters the water by its own gravity. At this time, the blades on one side of the main rotor begin to flip synchronously. When the auxiliary lift system is completely in the water, it will start working immediately to keep the aircraft stable. When the main rotor is switched to the underwater propulsion device and the aircraft is completely in the water, it will enter the underwater navigation mode.

[0100] Out of water mode: The aircraft gradually approaches the water surface from the underwater navigation state, the auxiliary lift system speed increases, the thrust is increased, the aircraft is partially out of water, and the main rotor is exposed to the water surface. At this time, the thrust of the auxiliary lift system is balanced with the buoyancy and gravity generated by the submerged part of the aircraft

[0101] F′ B +4F La =G

[0102] The main rotor switches back to the airborne flight state and begins to generate lift, bringing the aircraft further out of the water. When the auxiliary lift system reaches the water surface, it stops rotating. The lift generated by the main rotor and the buoyancy generated by the submerged part of the aircraft cause the aircraft to rise further.

[0103] F″ B +F Lj >G

[0104] Then, when the auxiliary lift system is completely out of the water, it starts working immediately, and the aircraft completes its exit from the water and enters the aerial flight mode.

[0105] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A new configuration cross-medium aircraft based on a blade tip jet rotor, characterized in that: The aircraft has an aerial flight mode, an underwater navigation mode and a cross-medium mode, and the aircraft includes: body; The main rotor system comprises an electric centrifugal compressor mounted on the top of the fuselage and a tip jet main rotor blade connected to the compressor air path, wherein the compressor has a compressed air ejection mode and a compressed water ejection mode; the auxiliary lift system comprises lift units distributedly arranged on the fuselage, and the lift units can be independently controlled respectively; In the aerial flight mode, the tip jet main rotor rotates and the auxiliary lift system works to achieve aerial flight; In the underwater navigation mode, the main rotor with jets from the blade tip stops rotating, and the blades on one side flip around a fixed axis so that the blade nozzle faces the rear of the vehicle, thus serving as an underwater water jet propulsion device; In the cross-medium mode, when the aircraft is about to enter the water, the auxiliary lift system rotor and the main rotor stop, and the aircraft enters the water by its own gravity; at the same time, the blades on one side of the main rotor flip and switch to an underwater water jet propulsion device; when the aircraft is about to emerge from the water, the auxiliary lift system drives the aircraft partially out of the water, and at the same time, the main rotor blades flip and switch back to the air state to drive the aircraft out of the water. At this time, the auxiliary lift system stops at the water-air interface, and starts working immediately after it is completely out of the water, and the aircraft enters the air flight mode.

2. The novel cross-medium aircraft based on the blade tip jet rotor according to claim 1 is characterized in that: The compressor is an electric single-stage centrifugal compressor having a plurality of centrally symmetrical air outlet passages, which respectively correspond to a plurality of blades of the tip jet main rotor.

3. The novel cross-medium aircraft based on the blade tip jet rotor according to claim 1 is characterized in that: The main rotor system installation axis passes through the fuselage mass center, and the tip jet main rotor blades are installed on the multi-outlet electric centrifugal compressor through a rotating mechanism and a gas flow channel to provide the main lift for the aircraft.

4. The novel cross-medium aircraft based on the blade tip jet rotor according to claim 3 is characterized in that: The main rotor system has at least two main rotor blades.

5. The novel cross-medium aircraft based on the blade tip jet rotor according to claim 4 is characterized in that: When working underwater, the tip jet main rotor blades can be flipped around a fixed axis until the nozzles are all facing backwards, and the blade chord line can always be parallel to the incoming flow direction.

6. The novel cross-medium aircraft based on the blade tip jet rotor according to claim 1 is characterized in that: The lift unit of the auxiliary lift system is an electric rotor, which is directly driven by a motor and installed on the same plane below the main rotor plane.

7. The novel cross-medium aircraft based on the blade tip jet rotor according to claim 6 is characterized in that: The number of the electric rotors is four, which are distributed and installed at four diagonal corners of the fuselage.

8. The novel cross-medium aircraft based on the blade tip jet rotor according to claim 1 is characterized in that: A sensor is provided at the bottom of the auxiliary lift system.

9. A method for operating a new configuration trans-medium aircraft with a blade tip jet rotor, characterized in that: Based on the aircraft as described in any one of claims 1 to 8, it has air flight, underwater navigation and cross-medium modes, The aerial flight mode: vertical take-off based on the tip jet main rotor and the auxiliary lift system, and controlling each auxiliary lift unit separately to achieve aircraft attitude control; The cross-medium mode: when preparing to enter the water, the main rotor and the auxiliary lift system rotor stop rotating, and the aircraft enters the water by its own gravity; when preparing to exit the water, the main rotor and the auxiliary lift system rotor work to generate lift to drive the aircraft out of the water; In the underwater navigation mode, the main rotor blades flip and switch to the underwater propulsion mode, and the chord line of the main rotor blades is always parallel to the incoming flow direction; the underwater attitude control of the aircraft is achieved based on each lift unit.

10. The operating method of the novel configuration trans-medium aircraft with blade tip jet rotor according to claim 9, characterized in that: The attitude control includes pitch maneuver, heading change and roll maneuver. The lift unit is divided into a front lift unit and a rear lift unit according to the forward direction, and the lift unit is divided into a left lift unit and a right lift unit according to the left and right sides of the forward direction. Among them, the pitch maneuver: control the change of the rotation speed of the rear or front lift unit to generate a torque to change the pitch attitude of the aircraft; the heading change: control the increase of the rotation speed of a diagonal lift unit and the decrease of the rotation speed of the other diagonal lift unit to generate an unbalanced torque to change the heading of the aircraft; the roll maneuver: control the change of the rotation speed of the left or right lift unit to generate a torque to change the roll attitude of the aircraft.

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