Thrust vector vertical take-off and landing aircraft

Abstract

The utility model provides a thrust vector vertical take-off and landing aircraft, which relates to the technical field of aircrafts and comprises a duct and a first mounting seat, four control steering engines are arranged on the surface of the first mounting seat, a fixed frame is arranged on the side surface of the first mounting seat, a guide plate is arranged on the surface of the fixed frame, and a support rod is arranged on the surface of the first mounting seat. The first rotor wing and the second rotor wing which are arranged on the upper layer and the lower layer are adopted, the rotating directions of the first rotor wing and the second rotor wing are opposite, the coaxial propeller layout is adopted, the reverse torsion of the rotor wings is effectively counteracted, the four flow guide plates on the lower portion are arranged in an X shape and are in coordinated linkage during pitching and rolling movement, and the airflow direction and acting force can be flexibly and accurately regulated and controlled according to the flight attitude requirement; the external duct design can increase the air velocity from the first rotor wing and the second rotor wing to the flow guide plate, enough strong airflow acting force is provided for the aircraft, meanwhile, the duct is made of hard foaming polyurethane, when the aircraft collides with foreign matter, the first rotor wing and the second rotor wing are effectively protected, and the fault risk and the maintenance cost are reduced.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of aircraft technology, especially thrust vector vertical take-off and landing aircraft. BACKGROUND

[0002] According to the vertical take-off and landing aircraft of Chinese patent publication No. CN220465803U, it relates to the field of aircraft technology. The two sides of the fuselage are fixedly installed with support arms, the number of support arms is two groups, the outer side of the bottom of the support arm is installed with a connecting plate, the bottom of the connecting plate is connected with a strut, the front end and the rear end of the strut are installed with a lifting mechanism, and the bottom of the fuselage has a shock absorbing landing gear. The aircraft can take off vertically under the action of the lifting mechanism, the number of lifting mechanisms is four groups, and each group of motors drives the helical blades to rotate at the same speed, so that the take-off speed is fast, and the shock absorbing landing gear is used to make the base of the aircraft contact the ground when the aircraft lands, and the impact force is generated on the ground when the aircraft descends, so that the aircraft is more stable when landing, and damage to the main body caused by hard landing is avoided.

[0003] The above-mentioned document and the prior art have the following problems: the current traditional flow guide design of the aircraft is not flexible and efficient enough, when the attitude is adjusted, such as pitching and rolling, the airflow direction and force distribution cannot be accurately and quickly changed, leading to unsmooth attitude conversion and response lag, which is difficult to meet the high-precision flight demand, in addition, the airflow generated by the rotation of the rotor itself has limited flow rate, which cannot provide sufficient airflow force for the aircraft, making the control response not sensitive, and once the aircraft collides with foreign matter during flight, the rotor is easily damaged, which not only causes the aircraft to be unable to fly normally, but also increases the risk of failure and maintenance cost. UTILITY MODEL CONTENTS

[0004] The utility model aims at solving the shortcomings in the prior art and provides a thrust vector vertical take-off and landing aircraft.

[0005] In order to achieve the above-mentioned purpose, the utility model adopts the following technical scheme: a thrust vector vertical take-off and landing aircraft, comprising a duct and a first mounting seat, the surface of the first mounting seat is provided with four control rudders, the side surface of the first mounting seat is provided with a fixed frame, the surface of the fixed frame is provided with a flow guide plate, the surface of the first mounting seat is provided with a support rod, the surface of the support rod is provided with a second mounting seat, the surface of the second mounting seat is provided with a driving assembly, and the surfaces of two driving assemblies are respectively provided with a first rotor and a second rotor.

[0006] Preferably, the driving assembly comprises a servo motor, a first gear, a second gear and a rotating shaft, the output end of the servo motor is provided with the first gear, the side surface of the first gear is provided with the second gear, and the surface of the second gear is provided with the rotating shaft.

[0007] Preferably, the fixed frame and the guide plates are circumferentially arranged in four groups, and the duct is connected to the surface of the fixed frame.

[0008] Preferably, rotating rods are arranged between the fixed frame and the guide plates, and the fixed frame and the guide plates are rotationally connected through the rotating rods.

[0009] Preferably, the surface of the supporting rod is provided with landing gears, and the two sides of the second mounting seat are provided with batteries.

[0010] Preferably, the two driving assemblies are centrally symmetrical, the end of the rotating shaft is provided with a connecting seat, and the two rotating shafts are respectively connected to the surfaces of the first rotor and the second rotor through the connecting seat.

[0011] Preferably, the landing gears are circumferentially arranged in four groups, and the landing gears are arranged between the first mounting seat and the second mounting seat.

[0012] Beneficial effects

[0013] In the utility model, the first rotor and the second rotor are arranged in two layers, the rotation directions of the first rotor and the second rotor are opposite, and the coaxial propellers are arranged, the rotor counter-torque is effectively offset, the fuselage self-rotation caused by the counter-torque is avoided, the structure is simplified, the flight stability and the control precision are improved, the four lower guide plates are arranged in X shape and are coordinately linked in the pitching and rolling movement, the air flow direction and the acting force can be flexibly and accurately controlled according to the flight attitude requirement, the attitude change is more stable and the response is more rapid, the drawbacks that the traditional guide design is not flexible and efficient in attitude adjustment are overcome, in addition, the external duct design can increase the air flow speed of the first rotor and the second rotor to the guide plate, provides sufficient air flow acting force for the aircraft, significantly improves the control force of the aircraft, and makes the flight action more agile and accurate, simultaneously, the duct is made of hard foamed polyurethane, when the aircraft collides with foreign matters, the material firstly bears the impact force and buffers by virtue of the strength and buffering performance, effectively protects the first rotor and the second rotor, reduces the damage probability, and reduces the failure risk and the maintenance cost. BRIEF DESCRIPTION OF DRAWINGS

[0014] Figure 1 It is the overall structural drawing of the utility model;

[0015] Figure 2 It is the internal structure drawing of the utility model;

[0016] Figure 3The structural diagram of the driving assembly of the utility model is shown in the figure.

[0017] Figure 4 The structural diagram of the guide plate of the utility model is shown in the figure.

[0018] Figure 5 The front view of the utility model is shown in the figure.

[0019] Legend:

[0020] 1, duct; 2, first mounting seat; 3, support rod; 4, second mounting seat; 5, driving assembly; 501, servo motor; 502, first gear; 503, second gear; 504, rotating shaft; 6, connecting seat; 7, first rotor; 8, second rotor; 9, control steering machine; 10, fixed frame; 11, rotating rod; 12, guide plate; 13, landing gear; 14, battery. DETAILED DESCRIPTION

[0021] In order to make the technical means, creative features, purposes and effects realized by the utility model easy to understand, the utility model is further described below in combination with specific embodiments and drawings, but the following embodiments are only preferred embodiments of the utility model, not all. Based on the embodiments in the embodiments, other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the utility model.

[0022] The specific embodiments of the utility model are described below in combination with the drawings. Embodiment one:

[0024] Reference Figures 1-5, thrust vector vertical take-off and landing aircraft, comprising a duct 1 and a first mounting seat 2, the duct 1 is connected with the surface of the fixed frame 10, the surrounding structure of the duct 1 can increase the air flow velocity of the first rotor 7 and the second rotor 8 to the guide vane 12, the air flow velocity through the guide vane 12 is accelerated, thereby improving the control force of the aircraft, making the aircraft more agile and accurate in steering, pitching, rolling and other actions, on the other hand, the duct 1 is made of hard foamed polyurethane, when the aircraft hits foreign matter, the material first bears the impact force and buffers due to its strength and buffering performance, and plays a certain protective role for the first rotor 7 and the second rotor 8 inside, the surface of the first mounting seat 2 is provided with a support rod 3, the support rod 3 connects the first mounting seat 2 and the second mounting seat 4, and plays a role of supporting and stabilizing the structure, the surface of the support rod 3 is provided with landing gear 13, the landing gear 13 is arranged in a circular array with four groups, and the landing gear 13 is arranged between the first mounting seat 2 and the second mounting seat 4, the landing gear 13 provides stable support during the take-off and landing process of the aircraft, the two sides of the second mounting seat 4 are provided with a battery 14, the battery 14 mainly provides power for all electrical equipment in the aircraft, including the operation of servo motor 501, control steering gear 9 and other equipment, which depends on the power provided by the battery 14, ensuring the normal flight of the aircraft.

[0025] The first mounting seat 2 is a basic mounting component, which provides mounting positions for other key components. The surface of the first mounting seat 2 is provided with four control rudders 9, which are mainly used to control the attitude of the aircraft. By receiving signals from the flight control system, the control rudders 9 can accurately adjust the angle of the guide vanes 12 on the fixed frame 10. For example, when turning is needed, the control rudders 9 can change the direction of the airflow by the guide vanes 12, generate a lateral force, and realize the turning action of the aircraft. The control rudders 9 drive the guide vanes 12 to move through the pull rod structure arranged between the control rudders 9 and the guide vanes 12. The side surface of the first mounting seat 2 is provided with the fixed frame 10, and the surface of the fixed frame 10 is provided with the guide vanes 12. The guide vanes 12 play a key role in guiding airflow during the flight of the aircraft. They can rotate according to the instructions of the control rudders 9. During the pitching and rolling movements of the aircraft, the four X-shaped guide vanes 12 coordinate and link to accurately change the direction of the airflow and the force acting on the lower part of the aircraft. For example, during the pitching action, the guide vanes 12 can change the upward and downward force of the airflow, causing the head or tail of the aircraft to rise or fall. During the rolling action, the left and right airflow forces are changed to achieve the rolling of the fuselage. The fixed frame 10 and the guide vanes 12 are arranged in a circular array with four groups. The fixed frame 10 and the guide vanes 12 are connected by the rotating rod 11. The fixed frame 10 provides a stable support structure for the guide vanes 12. It is arranged in a circular array with four groups, which helps to evenly distribute and guide the airflow. The fixed frame 10 is connected to the guide vanes 12 through the rotating rod 11, so that the guide vanes 12 can rotate around the rotating rod 11 to change the direction of the airflow flexibly according to the flight attitude requirements.

[0026] The surface of the support rod 3 is provided with a second mounting seat 4, which is mainly used for mounting a driving assembly 5 and a battery 14. The surface of the second mounting seat 4 is provided with the driving assembly 5, which comprises a servo motor 501, a first gear 502, a second gear 503 and a rotating shaft 504. The servo motor 501 is a power source of the driving assembly 5 and starts to work after receiving a signal of a flight control system. The power at the output end of the servo motor 501 is transmitted to the rotating shaft 504 through a track, the first gear 502 and the second gear 503. The output end of the servo motor 501 is provided with the first gear 502. The side surface of the first gear 502 is provided with the second gear 503. The first gear 502 and the second gear 503 constitute a transmission mechanism. The surface thereof is driven through a track. The surface of the second gear 503 is provided with the rotating shaft 504. The rotating shaft 504 rotates under the drive of the first gear 502 and the second gear 503 and transmits the power to the first rotor 7 and the second rotor 8 through the connecting seat 6, so that the first rotor 7 and the second rotor 8 rotate to generate lift. The two driving assemblies 5 are centrally symmetrical. The rotational directions of the first rotor 7 and the second rotor 8 are opposite through the centrally symmetrical driving assemblies 5. The rotor counter-torque is effectively offset, so that the fuselage spinning problem caused by the counter-torque is avoided. The end of the rotating shaft 504 is provided with the connecting seat 6. The two rotating shafts 504 are connected with the surfaces of the first rotor 7 and the second rotor 8 through the connecting seat 6. The surfaces of the two driving assemblies 5 are respectively provided with the first rotor 7 and the second rotor 8. The first rotor 7 and the second rotor 8 rotate under the drive of the driving assembly 5 to generate upward lift. The rotational directions of the first rotor 7 and the second rotor 8 are opposite, so that the aircraft can take off and land vertically.

[0027] The operation process of the thrust vector vertical take-off and landing aircraft is as follows: before flight, the battery 14 supplies power to the whole aircraft system, starts the servo motor 501, the servo motor 501 outputs power, drives the first gear 502 to rotate, drives the second gear 503 to rotate through the track, so that the rotating shaft 504 rotates, the rotating shaft 504 drives the first rotor 7 and the second rotor 8 to rotate through the connecting seat 6 to generate lift. At the same time, the four control rudders 9 on the first mounting seat 2 receive the flight control system signal, accurately adjust the angle of the guide vane 12 on the fixed frame 10 through the pull rod structure, when turning during flight, the control rudder 9 drives the guide vane 12 to change the direction of the air flow to generate a lateral force, when pitching, the guide vane 12 changes the upward and downward air forces to make the head or tail of the aircraft rise or fall, when rolling, the guide vane 12 changes the left and right air forces to realize the rolling of the fuselage. The duct 1 increases the air flow speed of the first rotor 7 and the second rotor 8 to the guide vane 12 to improve the control force, on the other hand, it protects the rotor when hitting foreign objects. The landing gear 13 provides stable support during take-off and landing. The whole aircraft realizes vertical take-off and landing and flexible flight attitude adjustment and control through the cooperation of each part to complete various flight tasks. Specific embodiment two:

[0029] Refer toFigure 3 , the thrust vector vertical take-off and landing aircraft, based on the basic structure in embodiment one, further discloses the following, the support rod 3 penetrates the second gear 503 and the connecting seat 6, the support rod 3 does not directly contact with the second gear 503 and the connecting seat 6, and the inside of the rotating shaft 504 is provided with a bearing, the rotating shaft 504 is rotatably connected with the support rod 3 through the bearing, potential interference of the support rod 3 to the second gear 503, the rotating shaft 504 and the rotating action of the first rotor 7 and the second rotor 8 is avoided, so that the fluency and efficiency of the aircraft in the process of vertical take-off and thrust vector adjustment are ensured.

[0030] In summary:

[0031] 1, the first rotor 7 and the second rotor 8 are arranged in two layers, the rotating directions of the first rotor 7 and the second rotor 8 are opposite, and the coaxial propeller layout is adopted, the rotor counter-torque is effectively offset, the fuselage spinning problem caused by the counter-torque is avoided, the structure is simplified, and the flight stability and control precision are improved, the lower 4 guide vanes 12 are arranged in X shape and are coordinated and linked in the pitching and rolling movement, the air flow direction and force can be flexibly and accurately regulated according to the flight attitude requirement, the attitude change is more stable and the response is more rapid, the disadvantages of the traditional guide design that is not flexible and efficient in attitude adjustment are overcome, in addition, the external duct 1 can increase the air flow rate of the first rotor 7 and the second rotor 8 to the guide vanes 12, and provide sufficient air flow force for the aircraft, the control force of the aircraft is significantly improved, the flight action can be more agile and accurate, and at the same time, the duct 1 is made of hard foamed polyurethane, when the aircraft collides with foreign matters, the material firstly bears the impact force and buffers due to the strength and buffering performance, the first rotor 7 and the second rotor 8 are effectively protected, the damage probability is reduced, and the failure risk and maintenance cost are reduced.

[0032] In the utility model, unless another definite provision and limitation, first feature is in second feature "on" or "under", can include that first and second features are directly contacted, also can include that first and second features are not directly contacted but are contacted through other features between them.Moreover, first feature is in second feature "on", "above" and "upper surface", includes that first feature is directly above and obliquely above second feature, or only indicates that the horizontal height of first feature is higher than second feature.First feature is in second feature "under", "below" and "lower surface", includes that first feature is directly below and obliquely below second feature, or only indicates that the horizontal height of first feature is less than second feature.

[0033] The basic principle, main features and advantages of the present application are shown and described above. It should be understood by those skilled in the art that the present application is not limited by the above examples, and the above examples and descriptions in the specification are only preferred examples of the present application and are not intended to limit the present application. Without departing from the spirit and scope of the present application, various changes and improvements can be made to the present application, and these changes and improvements all fall within the scope of the claimed present application. The scope of protection of the present application is defined by the appended claims and their equivalents.

Claims

1. Thrust vectoring vertical take-off and landing aircraft comprising a duct (1) and a first mounting seat (2), characterized in that: The surface of the first mounting base (2) is provided with four control rudders (9), the side of the first mounting base (2) is provided with a fixed frame (10), the surface of the fixed frame (10) is provided with a guide plate (12), the surface of the first mounting base (2) is provided with a support rod (3), the surface of the support rod (3) is provided with a second mounting base (4), the surface of the second mounting base (4) is provided with a drive assembly (5), and the surfaces of the two drive assemblies (5) are respectively provided with a first rotor (7) and a second rotor (8).

2. The thrust -vectoring vertical take-off and landing aircraft of claim 1, wherein: The drive assembly (5) comprises a servo motor (501), a first gear (502), a second gear (503) and a rotating shaft (504), the output end of the servo motor (501) is provided with the first gear (502), the side of the first gear (502) is provided with the second gear (503), and the surface of the second gear (503) is provided with the rotating shaft (504).

3. The thrust -vectoring vertical take-off and landing aircraft of claim 1, wherein: The fixed frame (10) and the guide plate (12) are circumferentially arranged in four groups, and the surface of the duct (1) is connected with the fixed frame (10).

4. The thrust -vectoring vertical take-off and landing aircraft of claim 1, wherein: The rotating rod (11) is arranged between the fixed frame (10) and the guide plate (12), and the fixed frame (10) and the guide plate (12) are rotatably connected through the rotating rod (11).

5. The thrust -vectoring vertical take-off and landing aircraft of claim 1, wherein: The surface of the support rod (3) is provided with a landing gear (13), and the two sides of the second mounting base (4) are provided with a battery (14).

6. The thrust -vectoring vertical take-off and landing aircraft of claim 2, wherein: The two drive assemblies (5) are centrally symmetrical, the end of the rotating shaft (504) is provided with a connecting seat (6), and the surfaces of the two rotating shafts (504) are respectively connected with the surfaces of the first rotor (7) and the second rotor (8) through the connecting seat (6).

7. The thrust -vectoring vertical take-off and landing aircraft of claim 5, wherein: The landing gear (13) is circumferentially arranged in four groups, and the landing gear (13) is arranged between the first mounting base (2) and the second mounting base (4).

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