CN116767481A - An aircraft device with ultrasonic airflow cutting and drag reduction function - Google Patents

Abstract

The invention relates to an aircraft device with an ultrasonic airflow cutting and drag reduction function, which includes an aircraft body. An airflow blocked part is formed on the aircraft body, and an ultrasonic airflow cutting and drag reducing mechanism is installed on the airflow blocked part. The ultrasonic airflow cutting and drag reducing mechanism includes The cone tip shell, the shock absorbing part, and the ultrasonic vibration source. The cone tip shell is fixedly installed on the air flow blocked part through the shock absorbing part, and the cone tip part on the cone tip shell is set toward the flight direction of the aircraft. The ultrasonic vibration source is installed The installation cavity provided on the inside of the conical tip shell is used to drive the conical tip shell to perform high-frequency ultrasonic vibration. The ultrasonic airflow cutting and drag reduction mechanism is used to generate ultrasonic high-frequency cutting motion when working, and perform ultra-high frequency cutting and dispersion of the air covering the airflow blocked parts to reduce the air viscosity at the blocked airflow parts and reduce the frictional resistance of the aircraft flight. and pressure difference resistance to increase the flight speed and flight range of the aircraft and reduce flight energy consumption.

Description

An aircraft device with ultrasonic airflow cutting and drag reduction function

Technical field

The invention relates to the field of aircraft, in particular to an aircraft that is beneficial to reducing airflow resistance during flight.

Background technique

During the flight of the aircraft in the air, the resistance it endures mainly includes friction resistance, pressure difference resistance, interference resistance, etc. Frictional resistance is mainly caused by the viscosity of the air and the roughness of the surface of the aircraft itself; due to the viscosity of the air, there is a pressure difference between the front and rear of the aircraft, resulting in pressure differential resistance, plus the additional resistance caused by the assembly of various parts of the aircraft - —that is, interference resistance. However, the above three major resistances seriously affect the flight energy consumption, flight speed, flight range, etc. of the aircraft. At present, the only way for experts to reduce these three major drags is to continuously optimize the aerodynamics of the aircraft, but it is very difficult to achieve improvement.

Contents of the invention

The object of the present invention is to solve the above problems and deficiencies, and provide an aircraft device with an ultrasonic airflow cutting and drag reducing function. The aircraft device adopts an ultrasonic airflow cutting and drag reducing mechanism installed on the airflow blocked part of the aircraft, and utilizes ultrasonic airflow to cut. When the drag reduction mechanism works, it generates ultrasonic high-frequency cutting motion, cutting and breaking up the air covering the blocked parts of the airflow at ultra-high frequency, so as to reduce the air viscosity at the blocked parts of the airflow, thereby reducing the frictional resistance and pressure difference of the aircraft flight. resistance, thereby increasing the flight speed and flight range of the aircraft and reducing the flight energy consumption of the aircraft.

The technical solution of the present invention is realized as follows: an aircraft device with ultrasonic airflow cutting and drag reduction function, including an aircraft body, an airflow blocked part is formed on the aircraft body, and the characteristic is that the airflow blocked part is also equipped with an Ultrasonic airflow cutting resistance reduction mechanism, the ultrasonic airflow cutting resistance reduction mechanism includes a cone tip shell, a shock-absorbing component, and an ultrasonic vibration source, the cone tip shell is fixedly installed on the airflow blocked part through the shock-absorbing component, and the The cone tip portion on the cone tip shell is arranged toward the flight direction of the aircraft. The ultrasonic vibration source is installed in an installation cavity provided on the inside of the cone tip shell to drive the cone tip shell to make high-frequency ultrasonic vibrations.

Furthermore, a shock-absorbing mounting seat is also provided on the inner side of the conical tip shell. One end of the shock-absorbing component is fixedly connected to the shock-absorbing mounting seat, and the other end of the shock-absorbing component is connected to the airflow blocked part. phase fixed connection.

Furthermore, the cone tip shell is composed of an outer enclosure plate, an inner cavity, and an inner support frame, and the installation cavity is provided in the inner cavity.

Beneficial effects of the present invention: The present invention adopts an ultrasonic airflow cutting and drag-reducing mechanism installed on the airflow-blocked part of the aircraft. The ultrasonic airflow cutting and drag-reducing mechanism is used to generate ultrasonic high-frequency cutting motion when working, and the air covering the airflow-blocked part is Perform ultra-high frequency cutting and dispersion to reduce the viscosity of the air in the areas where the airflow is blocked, thereby reducing the frictional resistance and pressure differential resistance of the aircraft's flight, thereby increasing the aircraft's flight speed and flight range, and reducing the aircraft's flight energy consumption. Moreover, through the use of shock-absorbing components, the present invention not only satisfies the assembly and connection of the airflow-impeded parts and the ultrasonic airflow cutting drag-reducing mechanism, but also effectively prevents the high-frequency vibration generated by the ultrasonic airflow cutting and drag-reducing mechanism from being transmitted to the aircraft body. , preventing the occurrence of resonance and ensuring the quietness of the internal space of the aircraft body.

Description of drawings

Figure 1 is a schematic diagram of the principle structure of the present invention.

Figure 2 is a partially enlarged cross-sectional structural schematic diagram of the handpiece part of the present invention.

Figure 3 is a partially enlarged cross-sectional structural schematic diagram of the wing part of the present invention.

Detailed ways

As shown in Figures 1 to 3, an aircraft device with an ultrasonic airflow cutting and drag reduction function according to the present invention includes an aircraft body 1, and an airflow obstruction portion 2 is formed on the aircraft body 1. In order to achieve the object proposed by the present invention, an ultrasonic airflow cutting resistance reducing mechanism 3 is also installed on the airflow blocked part 2. The ultrasonic airflow cutting resistance reducing mechanism 3 includes a cone tip shell 31, a shock absorbing component 32, an ultrasonic vibration Source 33, the cone tip shell 31 is fixedly installed on the air flow blocked part 2 through the shock absorbing component 32, and the cone tip part on the cone tip shell 31 is arranged towards the flight direction of the aircraft, the ultrasonic vibration source 33 It is installed in the installation cavity 311 provided on the inside of the cone tip shell 31 to drive the cone tip shell 31 to perform high-frequency ultrasonic vibration. During operation, the ultrasonic vibration source 33 is used to drive the cone tip shell 31 to perform ultrasonic high-frequency cutting motion to perform ultra-high frequency cutting and dispersion of the air covering the air flow blocked part to reduce the air viscosity at the air flow blocked part, thereby achieving Reduce the friction resistance and pressure difference resistance of the aircraft flight, thereby increasing the aircraft's flight speed and flight range, and reducing the aircraft's flight energy consumption. Secondly, the use of shock-absorbing components 32 not only satisfies the assembly connection between the airflow-impeded parts and the ultrasonic airflow cutting drag-reducing mechanism, but also effectively prevents the high-frequency vibration generated by the ultrasonic airflow cutting drag-reducing mechanism from being transmitted to the aircraft body, preventing The generation of resonance ensures the quietness of the internal space of the aircraft body. The shock absorbing component 32 is a soft rubber shock absorbing column, a spring column, an airbag shock absorbing component, or a hydraulic cylinder component. As shown in Figures 2 and 3, this embodiment uses a hydraulic cylinder component together with a return spring set on the hydraulic cylinder component as the shock absorbing component of this embodiment.

In addition, in order to enable the shock-absorbing component 32 to be easily and conveniently installed between the cone tip shell 31 and the airflow blocked part 2, as shown in Figures 2 and 3, there is also a configuration on the inside of the cone tip shell 31. There is a shock-absorbing mounting base 312 . One end of the shock-absorbing component 32 is fixedly connected to the shock-absorbing mounting base 312 , and the other end of the shock-absorbing component 32 is fixedly connected to the airflow blocked part 2 . In order to make the cone tip shell have a simple structure and be easy to process, the cone tip shell 31 is composed of an outer enclosure 313, an inner cavity 314, and an inner support frame 315. The installation cavity 311 is provided in the inner cavity 314. . The cone tip shell 31 is usually processed and manufactured using the same material as the aircraft. The ultrasonic vibration source 33 is an ultrasonic vibration motor or an ultrasonic transducer.

The above description of the structural solution is an embodiment of the preferred embodiment of the present invention, but it does not represent a limitation on the protection scope of the technical solution of the present invention. It should be pointed out here that for those of ordinary skill in the art, several deformations and improvements can be made without departing from the concept of the present invention. These deformations and improvements all belong to the protection scope of the present invention and fall within the scope of the present invention. protection scope of the present invention.

Claims (5)

1. The utility model provides an aircraft device with ultrasonic wave air current cutting falls and hinders function, includes aircraft body (1), be formed with air current obstructed position (2) on aircraft body (1), its characterized in that: still install ultrasonic wave air current cutting resistance-reducing mechanism (3) on air current obstructed position (2), ultrasonic wave air current cutting resistance-reducing mechanism (3) are including awl point shell spare (31), damping part (32), ultrasonic vibration source (33), awl point shell spare (31) are through damping part (32) fixed mounting on air current obstructed position (2), just awl point position on awl point shell spare (31) is towards aircraft direction of flight setting, ultrasonic vibration source (33) are installed in installation cavity (311) that are equipped with in awl point shell spare (31) inboard to drive awl point shell spare (31) do high-frequency ultrasonic vibration.

2. The aircraft device with ultrasonic airflow cutting drag reduction function according to claim 1, wherein: the inner side of the conical tip shell (31) is also provided with a damping installation seat (312), one end of the damping component (32) is fixedly connected with the damping installation seat (312), and the other end of the damping component (32) is fixedly connected with the airflow blocking part (2).

3. The aircraft device with ultrasonic airflow cutting drag reduction function according to claim 1, wherein: the conical tip shell (31) is composed of an outer side coaming (313), an inner cavity (314) and an inner supporting frame (315), and the mounting cavity (311) is arranged in the inner cavity (314).

4. An aircraft device with ultrasonic airflow cutting drag reduction function according to any one of claims 1-3, characterized in that: the shock absorbing component (32) is a soft rubber shock absorbing column, a spring column, an air bag shock absorbing component or a hydraulic cylinder component.

5. An aircraft device with ultrasonic airflow cutting drag reduction function according to any one of claims 1-3, characterized in that: the ultrasonic vibration source (33) is an ultrasonic vibration motor or an ultrasonic transducer.