CN116533696A - Cross-medium aircraft power device and working method thereof - Google Patents

Cross-medium aircraft power device and working method thereof Download PDF

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Publication number
CN116533696A
CN116533696A CN202310520445.1A CN202310520445A CN116533696A CN 116533696 A CN116533696 A CN 116533696A CN 202310520445 A CN202310520445 A CN 202310520445A CN 116533696 A CN116533696 A CN 116533696A
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China
Prior art keywords
propeller
motor
aircraft
medium
cross
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CN202310520445.1A
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Chinese (zh)
Inventor
刘娜
朱清华
刘辉
范伟强
张舒翼
章文龙
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Nanjing University of Aeronautics and Astronautics
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Nanjing University of Aeronautics and Astronautics
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Application filed by Nanjing University of Aeronautics and Astronautics filed Critical Nanjing University of Aeronautics and Astronautics
Priority to CN202310520445.1A priority Critical patent/CN116533696A/en
Publication of CN116533696A publication Critical patent/CN116533696A/en
Pending legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60F—VEHICLES FOR USE BOTH ON RAIL AND ON ROAD; AMPHIBIOUS OR LIKE VEHICLES; CONVERTIBLE VEHICLES
    • B60F5/00—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media
    • B60F5/02—Other convertible vehicles, i.e. vehicles capable of travelling in or on different media convertible into aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H21/00—Use of propulsion power plant or units on vessels
    • B63H21/12—Use of propulsion power plant or units on vessels the vessels being motor-driven
    • B63H21/17—Use of propulsion power plant or units on vessels the vessels being motor-driven by electric motor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
    • B63H—MARINE PROPULSION OR STEERING
    • B63H5/00—Arrangements on vessels of propulsion elements directly acting on water
    • B63H5/07—Arrangements on vessels of propulsion elements directly acting on water of propellers
    • B63H5/14—Arrangements on vessels of propulsion elements directly acting on water of propellers characterised by being mounted in non-rotating ducts or rings, e.g. adjustable for steering purpose
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Ocean & Marine Engineering (AREA)
  • Transportation (AREA)
  • Other Liquid Machine Or Engine Such As Wave Power Use (AREA)

Abstract

The invention discloses a cross-medium aircraft power device and a working method thereof, and the technical scheme is that the cross-medium aircraft power device comprises a duct lip; a medium-crossing motor is arranged in the duct lip, and comprises a front motor and a rear motor; the front motor is internally provided with a water-driven propeller, and the water-driven propeller is used for providing underwater thrust when the aircraft is underwater; the rear motor is arranged on one side of the front motor, one side, deviating from the front motor, of the rear motor is connected with a pneumatic propeller, and the pneumatic propeller is used for providing air thrust when the aircraft flies in the air. The invention relates to a cross-medium aircraft power device and a working method thereof, which have the effects of realizing that an aircraft can navigate across medium and reducing resistance in the navigation process by taking a double-rotor motor, a pneumatic propeller and a water-driven propeller as power devices.

Description

Cross-medium aircraft power device and working method thereof
Technical Field
The invention relates to the technical field of aircrafts, in particular to a cross-medium aircraft power device and a working method thereof.
Background
The medium-crossing aircraft is an aircraft which passes through a gas/water two-phase interface, enters water from air or enters air from water to fly or voyage, integrates the characteristics of good maneuverability, long endurance time of a submarine, strong concealment and the like of the aircraft, can perform the tasks of warning investigation, burst prevention fight, communication relay or resource exploration, water quality monitoring, maritime search and rescue and the like, and belongs to typical medium-crossing aircraft. Cross-medium aircrafts have wide prospects for both army and civil use and are increasingly valued.
As a new concept aircraft, a power system is one of the core problems of research and development of the cross-medium aircraft, and in order to realize air flight and underwater navigation, the power system must have the capability of continuously switching two mediums. However, as the physical characteristics of water and air are too far apart, the dynamic characteristics of the air-water hybrid aircraft are obviously different from those of the traditional aircraft, the power system of the traditional cross-medium aircraft is a combination of an air power system and a water power system, and for a large-sized cross-medium aircraft, two power system schemes are feasible, but for a small-sized cross-medium aircraft, the volume and the weight of the air-water hybrid aircraft cannot bear two independent power systems. An integrated cross-medium power system is provided, which combines volume and weight and can be used on a small cross-medium aircraft.
According to the resistance formulaThe resistance is related to the coefficient of resistance, density, advancing speed, etc., and the value of the resistance is related to the properties of the medium, the properties of the object, the temperature, etc. in a seriesThe requirement is that the density of water is 772 times of the density of air, and by comparison, the resistance of the same object in water is much larger than that in air, if the same propeller is used in water and in air, the rotating speed of the propeller is required to be increased to overcome the resistance in water, but the rotating speed of the propeller is increased, and the resistance in water is also increased. For the appearance of the propeller, the rotating speed of the marine propeller cannot be very high due to the large water resistance, larger thrust can be obtained only by making the blades of the propeller large, however, the density of air is much smaller than that of water, and the aeroengine can only obtain larger thrust by increasing the rotating speed, but the large blades cannot raise the pressure brought by the large rotating speed, so that the same type of blade cannot be used by the hydrodynamic propeller and the pneumatic propeller, and the problem of the aircraft power device capable of being used across media is to be solved.
Disclosure of Invention
Aiming at the defects existing in the prior art, the invention aims to provide a cross-medium aircraft power device and a working method thereof, which have the effects of taking a double-rotor motor, a pneumatic propeller and a water-driven propeller as power devices, realizing that the aircraft can navigate across medium and reducing resistance in the navigation process.
In order to achieve the above purpose, the present invention provides the following technical solutions:
a cross-medium aircraft power plant comprising:
a bypass lip;
a medium-crossing motor is arranged in the duct lip, and comprises a front motor and a rear motor;
the front motor is internally provided with a water-driven propeller, and the water-driven propeller is used for providing underwater thrust when the aircraft is underwater;
the rear motor is arranged on one side of the front motor, one side, deviating from the front motor, of the rear motor is connected with a pneumatic propeller, and the pneumatic propeller is used for providing air thrust when the aircraft flies in the air.
As a further improvement of the invention, the front motor comprises a front motor stator and a front motor rotor, the rear motor comprises a rear motor stator and a rear motor rotor, the front motor stator is fixedly connected with the rear motor stator, the front motor comprises a front outer end block and a front inner end block, the rear motor comprises a rear inner end block, a front motor bearing is arranged between the front outer end block and the front motor rotor, a front motor bearing is also arranged between the front motor rotor and the front motor stator, a rear motor bearing is arranged between the rear inner end block and the rear motor rotor, and a rear motor bearing is also arranged between the rear motor rotor and the rear motor stator.
As a further improvement of the invention, a stator connecting block is also arranged between the front motor rotor and the rear motor rotor.
As a further improvement of the invention, the water-driven propeller is arranged between the front motor rotor and the front lower end block, and the water-driven propeller and the front motor rotor are positioned through keys, so that when the aircraft is under water, the front motor rotor rotates to drive the water-driven propeller to generate underwater thrust.
As a further improvement of the invention, the rear motor rotor is provided with a paddle clamp, and the pneumatic screw propeller is arranged in the paddle clamp, so that when the aircraft is in the air, the rear motor rotor rotates to drive the pneumatic screw propeller to rotate to generate air thrust.
As a further improvement of the invention, the paddle clamp is also provided with a limiter, and the limiter is used for limiting the pneumatic propeller.
As a further improvement of the invention, the pneumatic propeller is rotationally connected with the propeller clamp through a plugging bolt.
As a further improvement of the invention, it further comprises a controller, in which a design strategy for the blade-shaped design of the aerodynamic propeller is arranged, comprising the following steps:
s1: determining design parameters of blades in an aerodynamic propeller, the design parameters comprising: the number of the blades, the radius of the propeller, the radius of the hub, the micro-ends of the blades, the required pulling force of the propeller, the flying speed, the rotating speed of the propeller, the air density of the flying height and the loss coefficient;
s2: the lagrangian multiplier k is calculated and the specific integral equation is shown below.
Wherein: kp is a correction factor;
s3: in order to calculate the chord length bi and the pitch angle of the ith section, the incoming flow angle and the induced speed attack angle of the phyllin are calculated, and the specific calculation formula is as follows:
s4: calculating aerodynamic attack angle alpha at specified airfoil maximum lift-drag ratio by utilizing profile or xflr software max And the lift coefficient C at that time lmax Coefficient of resistance C dmax ；
S5: the chord length bi and pitch angle of the ith section are calculated as follows:
θ＝β * +α max
s6: the fourth step is repeated to calculate the chord length and pitch angle of all the blade micro-segments;
s7: and calculating the tension, resistance, torque and power of each leaf element micro-segment, adding the calculated tension, resistance, torque and power, and finally obtaining the efficiency of the propeller.
As a further improvement of the present invention, the step S7 specifically includes:
the lift and drag forces acting on individual phyllins are:
wherein C is l 、C d The wing profile lift coefficient and the drag coefficient are represented by w, the sum speed of the wing profile flowing to the blade, b, the chord length of the phyllostachys, and dr, the phyllostachys micro-segment;
the leaf extract tension, rotation resistance, effective power and required power are as follows:
dT＝dLcosβ * -dDsinβ *
dQ＝dDcosβ * +dLsinβ *
dP yx ＝(dLcosβ * -dDsinβ * )*V
dP＝(dDcosβ * +dLsinβ * )*Ωr
wherein beta is * For the incoming flow angle of the phyllanthin, V is the inflow speed of the propeller, Ω is the rotational linear speed of the phyllanthin position, and because the inflow speed is often far greater than the induction speed at the speed point of the aerodynamic propeller design, the induction speed in the incoming flow of the phyllanthin is ignored, namely:
the above formula is arranged to obtain the leaf extract with the following efficiency:
wherein C is l /C d Is the lift-drag ratio of the wing profile.
A method of operating a cross-medium aircraft power plant, providing a cross-medium aircraft power plant as described above:
when the aircraft is in an air medium, the controller controls the pneumatic propeller to be opened, and the motor works after switching to drive the pneumatic propeller to rotate so as to provide air thrust for the aircraft;
when the aircraft crosses the medium to the water, the controller switches the front motor to work so as to drive the water-driven propeller to provide the water thrust for the aircraft;
the ducted front lip rectifies the aircraft.
The invention has the beneficial effects that:
1. the cross-medium power system is adopted, the cross-medium motor is designed into a double-rotor motor integrated design, the motor is formed by combining front and rear motors, the motor structure is compact, and the defects that the weight of a power system is large, the structure is complex, the efficiency is low and the like caused by taking one power system underwater are overcome;
2. the whole cross-medium power device is in a coaxial double-propeller mode, power underwater and air can be freely switched, a ducted shaftless water-driven propeller is adopted, so that the kinetic energy loss at a propeller shaft can be reduced, the air-driven propeller can be folded underwater, the underwater navigation resistance can be reduced, and the propulsion efficiency of the water-driven propeller can be improved;
3. the design of the front lip of the duct and the design of the pneumatic propeller improve the effect of the pneumatic propeller in providing air thrust in the air.
Drawings
FIG. 1 is a schematic diagram of the overall structure of the present invention;
FIG. 2 is a side view of the motor of the present invention;
FIG. 3 is a cross-sectional view of the motor of the present invention;
FIG. 4 is an enlarged cross-sectional view of the motor of the present invention;
FIG. 5 is a schematic view of the folded state of the aerodynamic propeller of the present invention;
FIG. 6 is a force analysis diagram embodying phyllin;
FIG. 7 is a modeled rendering diagram embodying a rotor structure;
FIG. 8 is a flow chart of a computational design embodying a pneumatic propeller;
FIG. 9 is a pressure cloud chart of the symmetric cross section of the working state of the water-driven propeller of the present invention;
fig. 10 is a pressure coefficient cloud chart of a symmetrical section of the working state of the pneumatic propeller of the present invention.
Reference numerals: 1. a front motor; 2. a rear motor; 3. a bypass lip; 4. a front motor rotor; 5. a front motor stator; 6. a rear motor rotor; 7. a rear motor stator; 8. a front outer end block; 9. a front inner end block; 10. a rear inner end block; 11. plugging and bolting; 12. a paddle clamp; 13. a stator connecting block; 14. pneumatic propellers; 15. a limiter; 16. a water-driven propeller; 17. a key; 18. a front motor bearing; 19. and a rear motor bearing.
Detailed Description
The invention will now be described in further detail with reference to the drawings and examples. Wherein like parts are designated by like reference numerals. It should be noted that the words "front", "back", "left", "right", "upper" and "lower" used in the following description refer to directions in the drawings, and the words "bottom" and "top", "inner" and "outer" refer to directions toward or away from, respectively, the geometric center of a particular component.
Referring to fig. 1 to 10, a specific embodiment of a power device of a medium-crossing aircraft and a working method thereof according to the present invention includes a duct lip 3 and a medium-crossing motor, the medium-crossing motor is disposed in the duct lip 3, the medium-crossing motor includes a front motor 1 and a rear motor 2, a water-driven propeller 16 is disposed in the front motor 1, the water-driven propeller 16 is used for providing underwater thrust for the aircraft under water, the rear motor 2 is disposed on one side of the front motor 1, a pneumatic propeller 14 is connected to one side of the rear motor 2 facing away from the front motor 1, and the pneumatic propeller 14 is used for providing air thrust for the aircraft during air flight.
The front motor 1 comprises a front motor stator 5 and a front motor stator 4, the rear motor 2 comprises a rear motor stator 7 and a rear motor rotor 6, the front motor stator 5 is fixedly connected with the rear motor stator 7, the front motor 1 comprises a front outer end block 8 and a front inner end block 9, the rear motor 2 comprises a rear inner end block 10, a front motor bearing 18 is arranged between the front outer end block 8 and the front motor stator 4, a front motor bearing 18 is also arranged between the front motor stator 4 and the front motor stator 5, a rear motor bearing 19 is arranged between the rear inner end block 10 and the rear motor rotor 6, a rear motor bearing 19 is also arranged between the rear motor rotor 6 and the rear motor stator 7, a stator connecting block 13 is also arranged between the front motor stator 4 and the rear motor rotor 6, a rotor structure is also arranged between the air propeller 14 and the bypass lip 3, the rotor structure comprises an inner rotor and an outer rotor, the arrangement of the inner rotor and the outer rotor reduces the resistance of the air propeller 14 during operation, and provides efficient driving for the air propeller 14.
The water-driven screw propeller 16 is arranged between the front motor stator 4 and the front lower end block, and the water-driven screw propeller 16 and the front motor stator 4 are positioned through a key 17, so that when the aircraft is under water, the front motor stator 4 rotates to drive the water-driven screw propeller 16 to generate underwater thrust.
The rear motor rotor 6 is provided with a paddle clamp 12, the pneumatic screw propeller 14 is arranged in the paddle clamp 12, so that when the aircraft is in the air, the rear motor rotor 6 rotates to drive the pneumatic screw propeller 14 to rotate to generate air thrust, the paddle clamp 12 is also provided with a limiter 15, the limiter 15 is used for limiting the pneumatic screw propeller 14, the pneumatic screw propeller 14 is rotationally connected with the paddle clamp 12 through a plugging bolt 11, and when the aircraft enters water, the pneumatic screw propeller 14 is contracted to be in a state that the axes of the duct lips 3 are parallel.
The cross-medium aircraft power plant further comprises a controller, wherein a design strategy for blade-shaped design of the aerodynamic propeller is configured in the controller, and comprises the following steps of:
s1: determining design parameters of blades in an aerodynamic propeller, the design parameters comprising: the number of the blades, the radius of the propeller, the radius of the hub, the micro-ends of the blades, the required pulling force of the propeller, the flying speed, the rotating speed of the propeller, the air density of the flying height and the loss coefficient;
s2: the lagrangian multiplier k is calculated and the specific integral equation is shown below.
Wherein: kp is a correction factor;
s3: in order to calculate the chord length bi and the pitch angle of the ith section, the incoming flow angle and the induced speed attack angle of the phyllin are calculated, and the specific calculation formula is as follows:
s4: calculating aerodynamic attack angle alpha at specified airfoil maximum lift-drag ratio by utilizing profile or xflr software max And the lift coefficient C at that time lmax Coefficient of resistance C dmax ；
S5: the chord length bi and pitch angle of the ith section are calculated as follows:
θ＝β * +α max
s6: the fourth step is repeated to calculate the chord length and pitch angle of all the blade micro-segments;
s7: and calculating the tension, resistance, torque and power of each leaf element micro-segment, adding the calculated tension, resistance, torque and power, and finally obtaining the efficiency of the propeller.
As a further improvement of the present invention, the step S7 specifically includes:
the lift and drag forces acting on individual phyllins are:
wherein C is l 、C d The wing profile lift coefficient and the drag coefficient are represented by w, the sum speed of the wing profile flowing to the blade, b, the chord length of the phyllostachys, and dr, the phyllostachys micro-segment;
the leaf extract tension, rotation resistance, effective power and required power are as follows:
dT＝dLcosβ * -dDsinβ *
dQ＝dDcosβ * +dLsinβ *
dP yx ＝(dLcosβ * -dDsinβ * )*V
dP＝(dDcosβ * +dLsinβ * )*Ωr
wherein beta is * For the incoming flow angle of the phyllanthin, V is the inflow speed of the propeller, Ω is the rotational linear speed of the phyllanthin position, and because the inflow speed is often far greater than the induction speed at the speed point of the aerodynamic propeller design, the induction speed in the incoming flow of the phyllanthin is ignored, namely:
the above formula is arranged to obtain the leaf extract with the following efficiency:
wherein C is l /C d Is the lift-drag ratio of the wing profile.
After the design of the pneumatic propeller 14 is completed, the controller forms a control information table, and the control information table is used for controlling the operation of the pre-switching motor 1 or the post-switching motor 2 under different mediums so as to switch the flight mode of the aircraft.
The working method of the cross-medium aircraft power plant comprises the steps of providing the cross-medium aircraft power plant:
when the aircraft is in an air medium, the controller controls the pneumatic propeller 14 to be opened and the switched motor 2 works to drive the pneumatic propeller 14 to rotate so as to provide air thrust for the aircraft;
when the aircraft crosses the medium into the water, the controller switches the front motor 1 to work to drive the water-driven propeller 16 to provide the water thrust for the aircraft;
the ducted front lip rectifies the aircraft.
Working principle and effect:
the front motor 1 is composed of a front motor stator 5 and a front motor rotor 4, the rear motor 2 is composed of a rear motor rotor 6 and a rear motor stator 7, the front motor stator 5, a front outer end block 8 and a stator connecting block 13 are fixedly connected through bolts, a front motor bearing 18 is arranged between the front outer end block 8 and the front motor rotor 4, a front motor bearing 18 is also arranged between the stator connecting block 13 and the front motor rotor 5, a hydrodynamic propeller 16 is fixed with the front motor rotor 4 through a key 17, a front inner end block 9 is arranged at the front part of the front motor bearing 18 and the front motor rotor 4, the front inner end block 9 is used for preventing the front motor bearing 18 from being thrown out in the working process, a rear motor bearing 19 is arranged between the stator connecting block 13 and the rear motor rotor 6, a rear inner end block 10 is arranged between the rear inner end block 10 and the rear motor rotor 6, and the rear inner end block 10 is used for preventing the rear motor bearing 19 from being thrown out in the working process of the rear motor 2.
The duct lip 3 is arranged at the front part of the front outer end block 8 and fixed through gluing, the propeller clamp 12 is fixed on the rear motor rotor 6 through bolts, the pneumatic propeller 14 is arranged on the propeller clamp 12 through the plugging bolts 13, the limiter 15 is further arranged on the propeller clamp 12, and after the pneumatic propeller 14 is folded backwards, the limiter 15 plays a limiting role, so that the pneumatic propeller 14 is folded at a specified position.
The cross-medium aircraft power device in the application is divided into two working states, namely an underwater working state and an air working state, when in the underwater working state, the pneumatic propeller 14 is folded backwards, the front motor 1 works by being limited by the limiter 15, and the front motor rotor 4 rotates to drive the water-driven propeller 16 to rotate to provide underwater thrust; in an air working state, the pneumatic propeller 14 is opened, the rear motor 2 works, and the rear motor rotor 6 rotates to drive the pneumatic propeller to rotate to provide air thrust.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above examples, and all technical solutions belonging to the concept of the present invention belong to the protection scope of the present invention. It should be noted that modifications and adaptations to the present invention may occur to one skilled in the art without departing from the principles of the present invention and are intended to be within the scope of the present invention.

Claims (10)

1. A cross-medium aircraft power plant, comprising:
a bypass lip (3);
a medium-crossing motor is arranged in the duct lip (3), and comprises a front motor (1) and a rear motor (2);
a water-driven propeller (16) is arranged in the front motor (1), and the water-driven propeller (16) is used for providing underwater thrust when the aircraft is underwater;
the rear motor (2) is arranged on one side of the front motor (1), one side, deviating from the front motor (1), of the rear motor (2) is connected with a pneumatic propeller (14), and the pneumatic propeller (14) is used for providing air thrust when the aircraft flies in the air.
2. A cross-medium aircraft power plant according to claim 1, characterized in that: front motor (1) includes front motor stator (5) and front motor rotor (4), back motor (2) include back motor stator (7) and back motor rotor (6), front motor stator (5) and back motor stator (7) rigid coupling, front motor (1) include outer end block (8) and interior end block (9) in front, back motor (2) include interior end block (10) in the back, front motor bearing (18) are equipped with between outer end block (8) in the front and front motor rotor (4), front motor bearing (18) are also equipped with between front motor rotor (4) and front motor stator (5), back motor bearing (19) are equipped with between back interior end block (10) and back motor rotor (6), back motor bearing (19) are also equipped with between back motor rotor (6) and back motor stator (7).
3. A cross-medium aircraft power plant according to claim 2, characterized in that: a stator connecting block (13) is further arranged between the front motor rotor (4) and the rear motor rotor (6).
4. A cross-medium aircraft power plant according to claim 2, characterized in that: the water-driven propeller (16) is arranged between the front motor rotor (4) and the front lower end block, and the water-driven propeller (16) and the front motor rotor (4) are positioned through a key (17), so that when the aircraft is underwater, the front motor rotor (4) rotates to drive the water-driven propeller (16) to generate underwater thrust.
5. A cross-medium aircraft power plant according to claim 4, characterized in that: the rear motor rotor (6) is provided with a paddle clamp (12), and the air-driven propeller (14) is arranged in the paddle clamp (12) so that when the aircraft is in the air, the rear motor rotor (6) rotates to drive the air-driven propeller (14) to rotate to generate air thrust.
6. A cross-medium aircraft power plant according to claim 5, characterized in that: the propeller clamp (12) is also provided with a limiter (15), and the limiter (15) is used for limiting the pneumatic propeller (14).
7. A cross-medium aircraft power plant according to claim 5, characterized in that: the pneumatic propeller (14) is rotationally connected with the propeller clamp (12) through a plugging bolt (11).
8. A cross-medium aircraft power plant according to claim 7, characterized in that: the method further comprises a controller, wherein a design strategy for blade-shaped design of the aerodynamic propeller is configured in the controller, and comprises the following steps of:
s1: determining design parameters of blades in an aerodynamic propeller, the design parameters comprising: the number of the blades, the radius of the propeller, the radius of the hub, the micro-ends of the blades, the required pulling force of the propeller, the flying speed, the rotating speed of the propeller, the air density of the flying height and the loss coefficient;
s2: the lagrangian multiplier k is calculated and the specific integral equation is shown below.
Wherein: kp is a correction factor;
s3: in order to calculate the chord length bi and the pitch angle of the ith section, the incoming flow angle and the induced speed attack angle of the phyllin are calculated, and the specific calculation formula is as follows:
s4: calculation of specified airfoil maximum lift-drag ratio using profile or xflr softwarePneumatic angle of attack alpha max And the lift coefficient C at that time lmax Coefficient of resistance C dmax ；
S5: the chord length bi and pitch angle of the ith section are calculated as follows:
θ＝β * +α max
s6: the fourth step is repeated to calculate the chord length and pitch angle of all the blade micro-segments;
s7: and calculating the tension, resistance, torque and power of each leaf element micro-segment, adding the calculated tension, resistance, torque and power, and finally obtaining the efficiency of the propeller.
9. A cross-medium aircraft power plant according to claim 8, characterized in that: the step S7 specifically includes:
the lift and drag forces acting on individual phyllins are:
wherein C is l 、C d The wing profile lift coefficient and the drag coefficient are represented by w, the sum speed of the wing profile flowing to the blade, b, the chord length of the phyllostachys, and dr, the phyllostachys micro-segment;
the leaf extract tension, rotation resistance, effective power and required power are as follows:
dT＝dLcosβ * -dDsinβ *
dQ＝dDcosβ * +dLsinβ *
dP yx ＝(dLcosβ * -dDsinβ * )*V
dP＝(dDcosβ * +dLsinβ * )*Ωr
wherein beta is * For the incoming flow angle of the phyllanthin, V is the inflow speed of the propeller, Ω is the rotational linear speed of the phyllanthin position, and because the inflow speed is often far greater than the induction speed at the speed point of the aerodynamic propeller design, the induction speed in the incoming flow of the phyllanthin is ignored, namely:
the above formula is arranged to obtain the leaf extract with the following efficiency:
wherein C is l /C d Is the lift-drag ratio of the wing profile.
10. A method of operating a cross-medium aircraft power plant, providing a cross-medium aircraft power plant as claimed in any one of claims 1 to 9, characterized in that:
when the aircraft is in an air medium, the controller controls the pneumatic propeller (14) to be opened, and the motor (2) is switched to work to drive the pneumatic propeller (14) to rotate so as to provide air thrust for the aircraft;
when the aircraft crosses the medium into the water, the controller switches the front motor (1) to work so as to drive the water-driven propeller (16) to provide the water thrust for the aircraft;
the ducted front lip rectifies the aircraft.
CN202310520445.1A 2023-05-10 2023-05-10 Cross-medium aircraft power device and working method thereof Pending CN116533696A (en)

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Application Number Priority Date Filing Date Title
CN202310520445.1A CN116533696A (en) 2023-05-10 2023-05-10 Cross-medium aircraft power device and working method thereof

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Application Number Priority Date Filing Date Title
CN202310520445.1A CN116533696A (en) 2023-05-10 2023-05-10 Cross-medium aircraft power device and working method thereof

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