CN116767481A - Aircraft device with ultrasonic airflow cutting resistance-reducing function - Google Patents
Aircraft device with ultrasonic airflow cutting resistance-reducing function Download PDFInfo
- Publication number
- CN116767481A CN116767481A CN202011469739.9A CN202011469739A CN116767481A CN 116767481 A CN116767481 A CN 116767481A CN 202011469739 A CN202011469739 A CN 202011469739A CN 116767481 A CN116767481 A CN 116767481A
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- Prior art keywords
- ultrasonic
- aircraft
- airflow
- cone
- damping
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- 238000013016 damping Methods 0.000 claims abstract description 22
- 230000000903 blocking effect Effects 0.000 claims abstract description 19
- 238000009434 installation Methods 0.000 claims abstract description 7
- 230000035939 shock Effects 0.000 claims description 7
- 238000005265 energy consumption Methods 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 238000010276 construction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transducers For Ultrasonic Waves (AREA)
Abstract
The invention relates to an aircraft device with an ultrasonic airflow cutting resistance-reducing function, which comprises an aircraft body, wherein an airflow blocking part is formed on the aircraft body, an ultrasonic airflow cutting resistance-reducing mechanism is further arranged on the airflow blocking part, the ultrasonic airflow cutting resistance-reducing mechanism comprises a cone-tip shell piece, a damping part and an ultrasonic vibration source, the cone-tip shell piece is fixedly arranged on the airflow blocking part through the damping part, the cone-tip part on the cone-tip shell piece is arranged towards the flight direction of the aircraft, and the ultrasonic vibration source is arranged in an installation cavity arranged on the inner side of the cone-tip shell piece so as to drive the cone-tip shell piece to perform high-frequency ultrasonic vibration. The ultrasonic high-frequency cutting motion is generated when the ultrasonic airflow cutting resistance reducing mechanism works, and the air covering the airflow blocking position is subjected to ultrahigh-frequency cutting and scattering, so that the air viscosity of the airflow blocking position is reduced, the friction resistance and the pressure difference resistance of the aircraft are reduced, the flight speed and the flight range of the aircraft are improved, and the flight energy consumption is reduced.
Description
Technical Field
The invention relates to the field of aircrafts, in particular to an aircraft which is beneficial to reducing air flow resistance in the flying process.
Background
The resistance born by the aircraft in the air flight process mainly comprises friction resistance, pressure difference resistance, interference resistance and the like. Frictional resistance is mainly caused by air viscosity and unsmooth surface of the aircraft; and the pressure difference resistance caused by the pressure difference between the front and the rear of the aircraft due to the air viscosity, and the additional resistance generated by assembling the components of the aircraft, namely the interference resistance. However, the three aforementioned resistances seriously affect the flight energy consumption, the flight speed, the flight range, etc. of the aircraft. Currently, the only means for reducing these three drag forces is to improve the drag force by continuously optimizing the aerodynamics of the aircraft, but the difficulty in achieving the drag force is quite large.
Disclosure of Invention
The invention aims to solve the problems and the defects, and provides an aircraft device with an ultrasonic airflow cutting resistance-reducing function.
The technical scheme of the invention is realized as follows: the utility model provides an aircraft device with ultrasonic wave air current cutting resistance-reducing function, includes the aircraft body, be formed with the air current and hinder the position on the aircraft body, its characteristics lie in still install ultrasonic wave air current cutting resistance-reducing mechanism on the air current is hindered the position, ultrasonic wave air current cutting resistance-reducing mechanism includes awl point shell spare, damping part, ultrasonic vibration source, awl point shell spare passes through damping part fixed mounting on the air current is hindered the position, just awl point position on the awl point shell spare is towards aircraft direction of flight setting, ultrasonic vibration source installs in the installation cavity that the awl point shell spare inboard was equipped with to drive awl point shell spare makes high-frequency ultrasonic vibration.
Further, a damping mounting seat is further arranged on the inner side of the conical tip shell, one end of the damping component is fixedly connected with the damping mounting seat, and the other end of the damping component is fixedly connected with the air flow blocking part.
Still further, the conical tip shell member comprises outside bounding wall, interior cavity, interior support frame, the installation cavity sets up in interior cavity.
The invention has the beneficial effects that: according to the invention, the ultrasonic airflow cutting resistance-reducing mechanism is arranged on the airflow blocking part on the aircraft, and ultrasonic high-frequency cutting motion is generated when the ultrasonic airflow cutting resistance-reducing mechanism works, so that the air covering the airflow blocking part is subjected to ultrahigh-frequency cutting and scattering, the air viscosity of the airflow blocking part is reduced, and further the friction resistance and the pressure difference resistance of the aircraft in flight are reduced, so that the flight speed and the flight range of the aircraft are improved, and the flight energy consumption of the aircraft is reduced. In addition, the invention not only satisfies the assembly connection of the air flow blocking part and the ultrasonic air flow cutting resistance reducing mechanism, but also effectively prevents the high-frequency vibration generated by the ultrasonic air flow cutting resistance reducing mechanism from being transmitted to the aircraft body, prevents the occurrence of co-vibration, and ensures the static dissipative property of the inner space of the aircraft body.
Drawings
Fig. 1 is a schematic diagram of the principle structure of the present invention.
Fig. 2 is a partially enlarged cross-sectional schematic view of the nose portion of the present invention.
FIG. 3 is an enlarged partial cross-sectional structural schematic view of a wing portion of the present invention.
Detailed Description
As shown in fig. 1 to 3, the aircraft device with the ultrasonic airflow cutting resistance-reducing function according to the present invention includes an aircraft body 1, and an airflow blocking portion 2 is formed on the aircraft body 1. In order to achieve the purpose of the present invention, the airflow blocking portion 2 is further provided with an ultrasonic airflow cutting resistance reducing mechanism 3, the ultrasonic airflow cutting resistance reducing mechanism 3 includes a cone-tip shell 31, a damping member 32, and an ultrasonic vibration source 33, the cone-tip shell 31 is fixedly installed on the airflow blocking portion 2 through the damping member 32, the cone-tip portion on the cone-tip shell 31 is disposed towards the flight direction of the aircraft, and the ultrasonic vibration source 33 is installed in an installation cavity 311 disposed inside the cone-tip shell 31 to drive the cone-tip shell 31 to perform high-frequency ultrasonic vibration. During operation, the cone-tip shell 31 is driven by the ultrasonic vibration source 33 to perform ultrasonic high-frequency cutting motion, and the air covering the air flow blocking part is subjected to ultrahigh-frequency cutting and scattering, so that the air viscosity of the air flow blocking part is reduced, and further the friction resistance and the pressure difference resistance of the aircraft are reduced, thereby improving the flight speed and the flight range of the aircraft, and reducing the flight energy consumption of the aircraft. Secondly, the damping part 32 is used, so that the assembly connection of the air flow blocking part and the ultrasonic air flow cutting resistance reducing mechanism is met, high-frequency vibration generated by the ultrasonic air flow cutting resistance reducing mechanism is effectively prevented from being transmitted to the aircraft body, the occurrence of resonance is prevented, and the static loss of the inner space of the aircraft body is ensured. The shock absorbing member 32 is a soft rubber shock absorbing column, a spring column, an air bag shock absorbing member, or a hydraulic cylinder member. As shown in fig. 2 and 3, the present embodiment employs a cylinder member together with a return spring fitted over the cylinder member as a shock absorbing member of the present embodiment.
In addition, in order to make the damping component 32 simply and conveniently installed between the conical tip shell 31 and the airflow blocking portion 2, as shown in fig. 2 and 3, a damping mounting seat 312 is further disposed on the inner side of the conical tip shell 31, one end of the damping component 32 is fixedly connected with the damping mounting seat 312, and the other end of the damping component 32 is fixedly connected with the airflow blocking portion 2. In order to make the cone tip shell member simple in construction and easy to process, the cone tip shell member 31 is composed of an outer side enclosing plate 313, an inner cavity 314 and an inner supporting frame 315, and the mounting cavity 311 is arranged in the inner cavity 314. The cone tip shell 31 is typically fabricated and manufactured from the same materials as the aircraft. The ultrasonic vibration source 33 is an ultrasonic vibration motor or an ultrasonic transducer.
The above description of the structural schemes is an embodiment of the preferred embodiments of the present invention, but it does not represent a limitation of the protection scope of the technical scheme of the present invention. It should be noted herein that, for those skilled in the art, several variations and modifications can be made without departing from the concept of the present invention, and these variations and modifications fall within the 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.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011469739.9A CN116767481A (en) | 2020-12-15 | 2020-12-15 | Aircraft device with ultrasonic airflow cutting resistance-reducing function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011469739.9A CN116767481A (en) | 2020-12-15 | 2020-12-15 | Aircraft device with ultrasonic airflow cutting resistance-reducing function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116767481A true CN116767481A (en) | 2023-09-19 |
Family
ID=88012065
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011469739.9A Pending CN116767481A (en) | 2020-12-15 | 2020-12-15 | Aircraft device with ultrasonic airflow cutting resistance-reducing function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116767481A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113602369A (en) * | 2021-02-10 | 2021-11-05 | 唐腊辉 | Ultrasonic airflow cutting resistance reducing device for vehicle |
-
2020
- 2020-12-15 CN CN202011469739.9A patent/CN116767481A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113602369A (en) * | 2021-02-10 | 2021-11-05 | 唐腊辉 | Ultrasonic airflow cutting resistance reducing device for vehicle |
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