CN117818870A - Aircraft without external rotating power part - Google Patents

Abstract

The invention discloses an aircraft without external rotating power components, which belongs to the technical field of aircrafts and comprises an aircraft body, and an air source, a high-pressure manifold and an annular propeller which are arranged on the aircraft body, wherein the air source is connected with the annular propeller through the high-pressure manifold, the annular propeller comprises an annular body and a connecting structure, the annular body comprises an inner side wall and an outer side wall which are mutually connected, a propulsion channel is formed on the inner side of the inner side wall, an annular airflow distribution cavity is formed between the inner side wall and the outer side wall, an annular slit is formed on the inner side wall, the annular slit is communicated with the propulsion channel and the airflow distribution cavity, the connecting structure is connected with the outer side wall, the airflow distribution cavity is communicated with the high-pressure manifold through the connecting structure, and the annular slit can guide airflow to the air outlet direction of the propulsion channel. The invention utilizes the annular propeller to generate the propulsion airflow far larger than the input airflow, can realize the flight of the aircraft without an external rotating power part, can change the form of taking a battery as a main energy source, and can improve the cruising ability and the loading ability.

Description

Aircraft without external rotating power part

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft without an external rotating power part.

Background

Unmanned aerial vehicles and other aircrafts are generally driven by a propeller or a rotor wing, can take off and land vertically, do not need a long runway or a specific take-off and landing area, and can take off and land more flexibly in urban environments. The flexible unmanned aerial vehicle has stronger adaptability than the unmanned aerial vehicle with fixed configuration, allows the appearance structure to change and pass through narrow space, carries out more kinds of tasks.

Whether a common unmanned aerial vehicle or a flexible unmanned aerial vehicle is adopted, the external rotating power components such as a screw or a rotor wing are adopted for driving, so that surrounding air is inevitably driven to generate larger noise. Moreover, the existing unmanned aerial vehicle generally uses a battery as a main energy source, the energy density of the battery is smaller, and the cruising ability and the loading ability of the aircraft are limited. Therefore, how to improve the above-mentioned drawbacks is a technical problem to be solved.

Disclosure of Invention

The invention aims to provide an aircraft without an external rotating power part, so as to solve the problems in the prior art, an annular propeller is arranged on a machine body, a propulsion airflow is formed by utilizing a propulsion channel, and the propulsion airflow far larger than the flow of input gas is generated by utilizing the annular propeller, so that the flight of the aircraft can be realized without the external rotating power part, the form of taking a battery as a main energy source can be changed, and the cruising ability and the loading ability can be improved.

In order to achieve the above object, the present invention provides the following solutions:

the invention provides an aircraft without an external rotating power component, which comprises an aircraft body, and an air source, a high-pressure manifold and an annular propeller which are arranged on the aircraft body, wherein the air source is connected with the annular propeller through the high-pressure manifold, the annular propeller comprises an annular body and a connecting structure, the annular body comprises an inner side wall and an outer side wall which are mutually connected, a propulsion channel is formed on the inner side of the inner side wall, an annular air flow distribution cavity is formed between the inner side wall and the outer side wall, an annular slit is formed on the inner side wall, the annular slit is communicated with the propulsion channel and the air flow distribution cavity, the connecting structure is connected with the outer side wall, the air flow distribution cavity is communicated with the high-pressure manifold through the connecting structure, and the annular slit can guide air flow to the air outlet direction of the propulsion channel.

Preferably, the annular thrusters are symmetrically distributed on two sides of the machine body, the cross section of the propulsion channel is in a waist shape, the length directions of the waist shapes of the annular thrusters on the same side are in the same direction, and the length directions of the waist shapes of the annular thrusters on different sides are parallel.

Preferably, the high-pressure manifold is of an M-shaped structure, the air source is connected with a middle folding point of the M-shaped structure, the annular propellers are connected with two folding points at the top end and two end points at the bottom end of the M-shaped structure, and the annular propellers are distributed at four corners of the machine body.

Preferably, the connection structure adopts a allosteric mechanism, and the allosteric mechanism is used for adjusting the inclination angle of the annular propeller, and the flying mode is changed by changing the air outlet direction of the propulsion channel.

Preferably, a flow control mechanism is arranged inside the high-pressure manifold at a position close to the annular propeller, and the flow control mechanism controls the airflow rate by changing the aperture size of the high-pressure manifold.

Preferably, the air source is a turbojet engine, the turbojet engine is longitudinally arranged along the axis of the machine body, and the air inlet end of the turbojet engine is positioned at the front end of the machine body.

Preferably, the engine comprises a storage battery and an oil tank, wherein the storage battery is electrically connected with an electricity utilization component, the oil tank is connected with the turbojet engine, and the storage battery and the oil tank are both positioned at the bottom of the engine body.

Preferably, the machine body comprises a framework, a flexible skin and a deformation supporting mechanism, wherein the flexible skin is surrounded outside the framework, one end of the deformation supporting mechanism is connected with the framework, the other end of the deformation supporting mechanism is connected with the flexible skin, and the flexible skins in different shapes are obtained by changing the telescopic length of the deformation supporting mechanism.

Preferably, a small diameter hole is formed in the flexible skin along the extending direction of the breadth of the flexible skin, a flexible rope is arranged in the small diameter hole in a penetrating mode, one end of the flexible rope is connected to the framework, the other end of the flexible rope is connected with a winding structure, and the winding structure is fixed to the framework.

Preferably, the deformation supporting mechanism is located on the top surface of the framework, the winding structure is fixed at the rear end of the framework, and one end of the flexible cable is fixedly connected to the front end of the framework.

Compared with the prior art, the invention has the following technical effects:

according to the invention, the annular propeller is arranged on the machine body, the air source is utilized to provide air flow for the annular propeller, the provided air flow forms propulsion air flow in the propulsion channel through the annular propeller, and the propulsion air flow which is far larger than the flow of input air can be generated through the annular propeller based on the coanda effect and the injection effect, so that the flight of the aircraft can be realized without an external rotating power part, the noise caused by the operation of the traditional rotating power part is reduced, and the air source can adopt other energy sources except a battery, such as fossil energy, thereby changing the form of taking the battery as a main energy source, and improving the cruising ability and the loading ability of the aircraft.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a schematic view showing a curved surface state of a machine body according to the present invention;

FIG. 2 is a longitudinal cross-sectional view of FIG. 1;

FIG. 3 is an enlarged view of the construction of FIG. 2 at A;

FIG. 4 is a top view of FIG. 1;

FIG. 5 is an enlarged view of the structure of FIG. 4 at B;

FIG. 6 is a cross-sectional view of C-C of FIG. 4;

FIG. 7 is a sectional view D-D of FIG. 4;

FIG. 8 is a schematic view showing a plane state of the body of the present invention;

FIG. 9 is a longitudinal cross-sectional view of FIG. 8;

FIG. 10 is an enlarged view of the structure of FIG. 9 at E;

FIG. 11 is a schematic diagram of a framework structure of the present invention;

FIG. 12 is a schematic view of the high pressure manifold of the present invention;

wherein, 1, the organism; 2. an annular propeller; 21. an annular body; 211. an inner sidewall; 212. an outer sidewall; 22. advancing the channel; 23. an annular slit; 24. an airflow distribution chamber; 3. a winding structure; 4. a rope fixed end; 5. a flexible skin; 6. a flexible cord; 7. a skeleton; 8. a deformation supporting mechanism; 9. a controller; 10. a storage battery; 11. an oil tank; 12. a small diameter hole; 13. a turbojet engine; 14. a high pressure manifold; 15. a flow control mechanism; 16. an allosteric mechanism.

Detailed Description

The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.

The invention aims to provide an aircraft without an external rotating power part, which solves the problems in the prior art, and the aircraft can realize the flight of the aircraft without the external rotating power part by arranging an annular propeller on a machine body, forming a propulsion airflow by utilizing a propulsion channel and generating the propulsion airflow far larger than the flow of input gas by utilizing the annular propeller, changing the form of taking a battery as a main energy source and improving the cruising ability and the loading ability.

In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of the invention will be rendered by reference to the appended drawings and appended detailed description.

The coanda effect is the effect that describes the flow of a fluid due to viscous attachment to a solid phase interface. The ejection effect is an effect for describing that the low-speed high-pressure fluid is driven by the high-speed low-pressure fluid to flow together under the action of viscosity. Based on the coanda effect and the injection effect, the total flow finally generated by the aerodynamic component can be improved. Based on the coanda effect and the injection effect, the fuel power component is combined, so that the endurance capacity and the load capacity can be improved, the rotating component is designed in the machine body, and the noise generated by the rotating component is reduced.

As shown in fig. 1 to 12, the present invention provides an aircraft without external rotating power components, comprising an aircraft body 1, and a gas source, a high-pressure manifold 14 and an annular propeller 2 which are mounted on the aircraft body 1, wherein the aircraft body 1 is used as a main body of the aircraft and is used for bearing and mounting all components, and the position of the annular propeller 2 is determined so as to be capable of providing lifting force of the aircraft body 1 by using the annular propeller 2. The air source can adopt a jet engine or a high-pressure air bottle and other devices capable of providing high-pressure air flow. The air source is connected to the annular thrusters 2 via a high pressure manifold 14, and the air flow of the air source is delivered to each annular thruster 2 by means of the high pressure manifold 14. The annular propeller 2 includes an annular body 21 and a connecting structure, the annular body 21 includes an inner sidewall 211 and an outer sidewall 212 connected to each other, an inner diameter side of the inner sidewall 211 forms a propulsion passage 22, and the propulsion passage 22 axially penetrates the annular body 21 for forming a propulsion air flow. An annular airflow distribution cavity 24 is formed between the inner side wall 211 and the outer side wall 212, the inner side wall 211 is provided with an annular slit 23, the annular slit 23 is communicated with the propulsion channel 22 and the airflow distribution cavity 24, and the airflow entering the airflow distribution cavity 24 is dispersed to the annular slit 23 and enters the propulsion channel 22 from the annular slit 23. The connecting structure is connected with the outer side wall 212, the air flow distribution cavity 24 is communicated with the high-pressure manifold 14 through the connecting structure, and the high-pressure manifold 14 guides air flow of an air source into the connecting structure and then enters the air flow distribution cavity 24 through the connecting structure. The annular slit 23 may be an inclined channel formed on the inner sidewall 211, so that when the air flow enters the propulsion channel 22 through the annular slit 23, the air flow can be sprayed obliquely towards the air outlet direction of the propulsion channel 22, and the air flow is guided to the air outlet direction of the propulsion channel 22 to generate thrust in the opposite direction, so as to further realize the ascent and flight of the aircraft. The annular slit 23 can convert the high-pressure gas entering the gas flow distribution cavity 24 into high-speed gas, and flow along the wall surface of the inner side wall 211, so that the gas pressure in the propulsion channel 22 is reduced, and the atmospheric air at the top of the annular body 21 is driven to flow together with the high-speed gas, so that the gas flow rate far greater than that input by the gas source exhaust end is generated at the bottom of each annular propeller 2.

According to the invention, the annular propeller 2 is arranged on the machine body 1, the air source is utilized to provide air flow for the annular propeller 2, the provided air flow is formed into propulsion air flow in the propulsion channel 22 through the annular propeller 2, and the propulsion air flow which is far larger than the flow of input air can be generated through the annular propeller 2 based on the coanda effect and the injection effect, so that the flight of an aircraft can be realized without an external rotating power part, the noise caused by the operation of the traditional rotating power part is reduced, and the air source can adopt other energy sources except a battery, such as fossil energy sources, so that the form of taking the battery as a main energy source can be changed, and the cruising ability and the loading ability of the aircraft can be improved.

As shown in fig. 4, the annular thrusters 2 may be symmetrically distributed on two sides of the machine body 1, the cross section of the thrust channel 22 is in a waist shape, the length directions of the waist shapes of the annular thrusters 2 on the same side are in the same direction, and the length directions of the waist shapes of the annular thrusters 2 on different sides are parallel. The symmetrically distributed annular propellers 2 can generate balanced propelling force to the machine body 1, so that the stable flight of the aircraft is ensured.

As shown in fig. 11 and 12, the high-pressure manifold 14 may be in an M-shaped structure, the air source is connected to a middle folding point of the M-shaped structure, the annular impellers 2 are connected to two top folding points and two bottom folding points of the M-shaped structure, and the air flow can be delivered to each annular impeller 2 by using the high-pressure manifold 14, so that the air source arranged in the middle can provide the air flow for the annular impellers 2 distributed at four corners of the machine body 1. The arrangement of the four ring-shaped propellers 2 corresponds to that of a quadrotor.

As shown in fig. 4, the connection structure may employ an allosteric mechanism 16, where the allosteric mechanism 16 is used to adjust the inclination angle of the annular propeller 2, so that the angle between the annular propeller 2 and the horizontal plane can be changed in a fixed direction, and further, the direction of the propulsion channel 22 is changed, and the flight mode of the aircraft can be changed by changing the air outlet direction of the propulsion channel 22. The allosteric mechanism 16 may adopt a hinge rotating mechanism based on a servo motor, and the hinge rotating mechanism is installed between the annular propeller 2 and the high-pressure manifold 14, so that the annular propeller 2 is stably connected with the machine body 1, and the angle of the annular propeller 2 can be driven to change in the hinging direction. During the period when the aircraft has been hovered or is flying in a plane, the direction of the annular propeller 2 can be changed by the allosteric mechanism 16, so that the state of vertical upward from the axis is changed into the state of tilting from the top to the front end of the aircraft, and the higher plane flying speed is realized.

As shown in fig. 12, a flow control mechanism 15 is provided inside the high-pressure manifold 14 at a position close to the annular propeller 2, and the flow control mechanism 15 controls the flow rate of the air flow by changing the aperture size of the high-pressure manifold 14 to change the lift force of the corresponding annular propeller 2. The flow control mechanism 15 may take the form of a gate valve which, for stable, accurate, linear control of the air flow, may take the form of an iris valve which is capable of gradually decreasing the aperture from the outside to the inside or gradually increasing the aperture from the inside to the outside, for example a multiple vane configuration driven by a servo motor. It will be appreciated by those skilled in the art that by adjustment of the flow control mechanism 15, the aircraft possesses the same motion control characteristics as a conventional four-rotor aircraft employing a symmetrical layout, enabling 6 degrees of freedom motions of vertical take off and landing, fly-flat, yaw, pitch, yaw, etc.

As shown in fig. 2, 9, 11 and 12, the air source may be a turbojet engine 13, and the turbojet engine 13 may use fuel oil as an energy source, so as to change the existing driving mode that mainly relies on a battery as an energy source. The turbojet engine 13 has a thrust-weight ratio of not less than 8, and uses aviation kerosene or diesel oil as an energy source, and is capable of self-sucking and compressing air, and high-pressure air generated by combustion is delivered to the high-pressure manifold 14. Although the turbojet engine 13 also has rotating power components, all of its rotating power components are located within the turbojet engine 13, and the fuel-powered aircraft can solve the problems of the aircraft in terms of endurance and load, and also can reduce noise. The turbojet engine 13 is longitudinally arranged along the axis of the machine body 1, the air inlet end of the turbojet engine 13 is positioned at the front end of the machine body 1, the air outlet end of the turbojet engine 13 is directly connected with the high-pressure manifold 14, and the air inlet of the turbojet engine 13 can be facilitated when the aircraft flies forwards. When the invention is in operation, the turbojet engine 13 acquires fuel oil from the fuel tank 11, meanwhile, low-pressure air is sucked into the air inlet end, high-pressure air is generated by the combustion of the turbojet engine 13, the high-pressure air is distributed to each annular propeller 2 through the high-pressure manifold 14, high-speed air is sprayed out, and the air outside the annular propellers 2 is driven to flow under the coanda effect and the injection effect to generate lifting force.

As shown in fig. 2 and 9, the electric motor comprises a storage battery 10 and an oil tank 11, wherein the storage battery 10 is electrically connected with electric components for supplying electric energy to the electric components, and the electric components comprise a controller 9, a steering engine for driving a flow control mechanism 15, a allosteric mechanism 16, a winding structure 3 for controlling a flexible cable 6 and the like. The controller 9 is equipped with various flight sensors and wireless communication modules, and is capable of receiving remote control commands, sensing the flight status and desired environmental parameters, and controlling the turbojet 13, the flow control mechanism 15, and the allosteric mechanism 16 to complete given commands. The tank 11 is connected to the turbojet engine 13 for supplying fuel thereto, the tank 11 being of such a capacity that the turbojet engine 13 operates at a maximum design rotational speed for at least 30 minutes. The storage battery 10 and the oil tank 11 are both positioned at the bottom of the machine body 1, so that the machine body 1 is convenient to carry out weight balancing, and the gravity center stability of the machine body is ensured. The controller 9 may be mounted at the rear end of the machine body 1 directly behind the turbojet engine 13. The framework 7, the deformation supporting mechanism 8, the oil tank 11, the high-pressure manifold 14, the annular propeller 2 and other structures are made of high-strength lightweight materials, so that the weight of the whole aircraft is reduced, the loading capacity of the aircraft is improved as much as possible, for example, the structure is made of carbon fiber materials, and the sufficient strength, high-temperature resistance and light weight can be realized.

As shown in fig. 1 to 5 and 8 to 11, the machine body 1 comprises a framework 7, a flexible skin 5 and a deformation supporting mechanism 8, the flexible skin 5 surrounds the outside of the framework 7, the appearance is a curved hexahedron with vertical sides, the shape and the size of the upper curved surface and the lower curved surface are the same, the projection of the upper curved surface and the lower curved surface in the vertical direction is rectangular, and the shape is a structure which enables the machine body 1 to have larger lifting force. The skeleton 7, which is the main body of the aircraft, can carry the assembly load of other components, is realized in a three-dimensional truss structure, the overall appearance can be designed as a cuboid frame, and additional reinforcing rods can be arranged at the positions for carrying all important components. One end of the deformation supporting mechanism 8 is connected with the framework 7, and the other end of the deformation supporting mechanism 8 is connected with the flexible skin 5. The deformation supporting mechanism 8 can adopt a telescopic structure, is a supporting rod or a rod group, and can realize reciprocating motion in an active driving structure or a structure based on elastic potential energy, so that the flexible skin 5 can be connected to the rigid framework 7 without influencing flexible deformation driving. When the active driving type structure is adopted, an air pressure energy storage telescopic rod structure can be adopted, and stable deformation and support are realized by controlling the switch valve of the telescopic rod structure. By changing the telescopic length of the deformation support mechanism 8, it is possible to obtain flexible skins 5 of different shapes, as shown in fig. 1 and 2 in a curved state and in fig. 8 and 9 in a planar state.

Further, a small diameter hole 12 is formed in the flexible skin 5 along the extending direction of the breadth, a flexible rope 6 is arranged in the small diameter hole 12 in a penetrating mode, one end of the flexible rope 6 is connected to the framework 7 through the rope fixing end 4, the other end of the flexible rope 6 is connected with the winding structure 3, and the winding structure 3 is fixed to the framework 7. The bending strength and winding stiffness of the flexible cord 6 enable a full turn of winding around the winding structure 3 without breaking and fatigue effects. The length of the flexible cable 6 in the flexible skin 5 can be controlled by driving or not of the winding structure 3, so that efficient active driving is realized, and the flexibility degree of the flexible skin 5 can be controlled. When the winding structure 3 is not driven in rotation, the flexible skin 5 is not affected by external stress, and the original appearance structure is maintained. When the winding structure 3 is driven in rotation, the flexible cord 6 decreases in length within the flexible skin 5, creating a stress on the main structure opposite to the convex direction, deforming the flexible skin 5 assembly into a nearly planar structure. By transforming the structure of the flexible skin 5, different aerodynamic properties can be obtained for different flight mission requirements.

The flexible skin 5 may be a shape memory polymer composite material having the following properties: the material can be formed by pressure thermoplastic at high temperature, and can be used at normal temperature after forming, external stress can be applied to the material to deform the material, and the material can be converted into the original shape by internal stress after removing the external stress, for example, silica gel and other materials with the performance can be adopted. The high-strength lightweight flexible cables 6 are arranged side by side inside the flexible skin 5, and improve the strength of the flexible skin 5 while providing an active allosteric manipulation actuation force transmission structure.

The deformation supporting mechanism 8 may be located on the top surface of the skeleton 7, and at this time, the flexible skin 5 on the top surface may be bent and deformed under the action of the deformation supporting mechanism 8. The winding structure 3 may be fixed at the rear end of the frame 7, and one end (rope fixing end 4) of the flexible rope 6 is fixedly connected at the front end of the frame 7.

The flexible skin 5 shown in figures 1 and 2 is only mounted on the upper surface of the aircraft for modifying the appearance of the aircraft to obtain different aerodynamic properties. It will be appreciated by those skilled in the art that each side panel portion of the skeleton 7 may be replaced by a flexible skin 5 of reasonable design and arrangement to provide more complex structural changes in the exterior configuration of the aircraft, while ensuring reasonable structural strength and rigidity of the aircraft.

The aircraft without the external rotating power component provided by the invention takes the turbojet engine 13 as a power source, sucks low-pressure air to burn to generate high-pressure air, shunts the high-pressure air through the high-pressure manifold 14, and ejects the high-pressure air at high speed through the annular propeller 2, so that high-flow gas lift force is generated under the coanda effect and the injection effect, and the aircraft is propelled to move. When the flexible skin 5 is not deformed, the magnitude and direction of lift force generated by the annular propeller 2 can be adjusted by operating the deformation mechanism 16 of the annular propeller 2 and the flow control mechanism 15 of the high-pressure manifold 14, so that the control of the degree of freedom of movement of the aircraft is realized. The flexible skin 5 can be designed with the desired aerodynamic profile to give the aircraft better aerodynamic properties during certain flight phases. It should be noted that: in any particular embodiment of the aircraft without external rotating power components according to the invention, the components of the flexible skin 5, the air inlet and outlet pipes, the high-pressure manifold 14, the annular propeller 2 and the like, which relate to aerodynamic characteristics and high-pressure gas delivery, all need to be designed and calibrated experimentally to ensure that they reach a sufficient lift-to-weight ratio.

The principles and embodiments of the present invention have been described in detail with reference to specific examples, which are provided to facilitate understanding of the method and core ideas of the present invention; also, it is within the scope of the present invention to be modified by those of ordinary skill in the art in light of the present teachings. In view of the foregoing, this description should not be construed as limiting the invention.

Claims (10)

1. An aircraft without external rotating power components, which is characterized in that: including organism and install air supply, high-pressure manifold and the annular propeller on the organism, the air supply passes through high-pressure manifold connects annular propeller includes annular body and connection structure, annular body includes interconnect's inside wall and lateral wall, the internal diameter side of inside wall forms propulsion passageway, the inside wall with form annular air current distribution chamber between the lateral wall, the inside wall is provided with annular slit, annular slit intercommunication propulsion passageway with air current distribution chamber, connection structure connects the lateral wall, air current distribution chamber passes through connection structure intercommunication high-pressure manifold, annular slit can be with the air current direction of giving vent to anger of propulsion passageway.

2. The aircraft without external rotating power components of claim 1, wherein: the annular thrusters are symmetrically distributed on two sides of the machine body, the cross section of the propulsion channel is waist-shaped, the length directions of the waist-shaped annular thrusters on the same side are the same, and the length directions of the waist-shaped annular thrusters on different sides are parallel.

3. The aircraft without external rotating power components of claim 2, wherein: the high-pressure manifold is of an M-shaped structure, the air source is connected with a middle folding point of the M-shaped structure, the annular propellers are connected with two folding points at the top end and two end points at the bottom end of the M-shaped structure, and the annular propellers are distributed at four corners of the machine body.

4. The aircraft without external rotating power components of claim 1, wherein: the connection structure adopts a allosteric mechanism, and the allosteric mechanism is used for adjusting the inclination angle of the annular propeller, and changes the flight mode by changing the air outlet direction of the propulsion channel.

5. The aircraft without external rotating power components of claim 1, wherein: and a flow control mechanism is arranged in the high-pressure manifold and close to the annular propeller, and the flow control mechanism controls the airflow flow by changing the aperture size of the high-pressure manifold.

6. The aircraft without external rotating power components of claim 1, wherein: the air source adopts a turbojet engine, the turbojet engine is longitudinally arranged along the axis of the machine body, and the air inlet end of the turbojet engine is positioned at the front end of the machine body.

7. The aircraft without external rotating power components of claim 6, wherein: the turbojet engine comprises a storage battery and an oil tank, wherein the storage battery is electrically connected with an electricity utilization component, the oil tank is connected with the turbojet engine, and the storage battery and the oil tank are both positioned at the bottom of the engine body.

8. The aircraft without external rotating power component according to any one of claims 1-7, wherein: the machine body comprises a framework, a flexible skin and a deformation supporting mechanism, wherein the flexible skin is surrounded outside the framework, one end of the deformation supporting mechanism is connected with the framework, the other end of the deformation supporting mechanism is connected with the flexible skin, and the flexible skin in different shapes is obtained by changing the telescopic length of the deformation supporting mechanism.

9. The aircraft without external rotating power components of claim 8, wherein: the flexible skin is characterized in that a small diameter hole is formed in the flexible skin along the extending direction of the breadth of the flexible skin, a flexible rope is arranged in the small diameter hole in a penetrating mode, one end of the flexible rope is connected to the framework, the other end of the flexible rope is connected with a winding structure, and the winding structure is fixed to the framework.

10. The aircraft without external rotating power components of claim 9, wherein: the deformation supporting mechanism is positioned on the top surface of the framework, the winding structure is fixed at the rear end of the framework, and one end of the flexible rope is fixedly connected with the front end of the framework.