CN112362288A - Automatic adjusting system for attack angle of wind tunnel test unmanned aerial vehicle - Google Patents
Automatic adjusting system for attack angle of wind tunnel test unmanned aerial vehicle Download PDFInfo
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- CN112362288A CN112362288A CN202011423296.XA CN202011423296A CN112362288A CN 112362288 A CN112362288 A CN 112362288A CN 202011423296 A CN202011423296 A CN 202011423296A CN 112362288 A CN112362288 A CN 112362288A
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- 230000001105 regulatory effect Effects 0.000 claims description 3
- 230000005484 gravity Effects 0.000 abstract description 4
- 238000000034 method Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 238000005259 measurement Methods 0.000 description 5
- 230000007246 mechanism Effects 0.000 description 3
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 2
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Abstract
The invention discloses an automatic adjusting system for an attack angle of an unmanned aerial vehicle in a wind tunnel test, which comprises a stepping motor, a motor controller, a lead screw, a positioning bracket, an aircraft support rod, an angle adjusting slide block, an angle adjuster, a sliding chute, a control box, a lead screw slide block and a base. The lead screw sliding block is arranged on a lead screw, and the lead screw is arranged on the motor controller and is connected with the stepping motor; the unmanned aerial vehicle is fixed on an airplane support rod, the airplane support rod is installed on an angle adjusting slider, the angle adjusting slider is hinged to an angle adjuster, and the angle adjuster is fixed on a lead screw slider; the front section of the positioning bracket is hinged with the airplane support rod, and the rear end of the positioning bracket is connected with the sliding chute; the base is fixed at the slide rail lower extreme, and the control box is fixed at the slide rail back, is equipped with power, singlechip and touch-control board in the control box. The angle of attack is adjusted under the action of the airplane strut, the angle adjusting slide block and the angle adjuster; the movement distance of the screw rod sliding block is calculated through the single chip microcomputer, and the stepping motor is controlled to enable the gravity center of the unmanned aerial vehicle to be located in the middle section of the wind field.
Description
Technical Field
The invention relates to the technical field of wind tunnel test measurement, in particular to an automatic adjusting system for an attack angle of an unmanned aerial vehicle.
Background
Aerodynamics is one of the most active and potential developing disciplines in the world science field, and wind tunnel tests are the most effective measures in the field of aerodynamic research. In the process of developing various aircrafts such as airplanes and missiles, the wind tunnel is an indispensable experimental facility. The air flow required by the experiment can be artificially generated and controlled in the wind tunnel, the state of the air flow around the aircraft in the flying process can be simulated, and the effect of the air flow on the aircraft can be quantitatively observed. By observing the physical phenomena occurring in the wind tunnel, the aerodynamic characteristics of the aircraft can be studied accordingly, and therefore, the wind tunnel test is an indispensable measure for aerodynamic experiments as the most effective tool.
The wind tunnel test researches the gas flow and the interaction between the gas flow and a model by controlling the airflow speed, the temperature, the pressure and the like of the aircraft arranged in the wind tunnel so as to know the aerodynamic characteristics of the actual aircraft. The aircraft usually needs to acquire test data of a plurality of attack angles, angle adjustment is carried out through the wind tunnel attack angle mechanism, and the aircraft needs to be ensured to be positioned in the middle section of a wind speed field in the attack angle adjustment process so as to obtain accurate test data. At present, most of adjusting devices of large wind tunnel angle-of-attack mechanisms are formed by integrating a model supporting rod and a curved knife plate, and the postures of the adjusting devices are adjusted along with the curved knife plate. The attack angle range of the structure in a limited space is relatively narrow, and the posture adjustment range of the attack angle is limited. The small wind tunnel cannot be provided with the attack angle adjusting mechanism due to the limited spatial position, a quadrant instrument is usually adopted for measuring the attack angle of the aircraft, the quadrant instrument cannot accurately measure the gravity center angle of the aircraft, and the attack angle of an aircraft strut is usually adopted as the attack angle of the aircraft. As can be seen from fig. 1, the aircraft support generally adopts a cantilever beam structure to reduce the interference of the support to the wake flow of the aircraft, and when the quadrant performs angle of attack measurement, the angle of the strut is deviated due to the action of the self weight of the instrument, so that the measurement deviation of the angle of attack of the aircraft is caused; meanwhile, the position of the gravity center of the aircraft in the wind field shifts along with the change of the attack angle, and the height of the base is usually required to be adjusted to keep the aircraft in the middle of the wind field.
Disclosure of Invention
The invention aims to solve the problems of large error and low efficiency in the measurement of the attack angle of the conventional wind tunnel test, and provides an automatic adjusting system for the attack angle of an unmanned aerial vehicle.
The utility model provides a wind tunnel test unmanned aerial vehicle angle of attack automatic regulating system, its characterized in that includes (as shown in fig. 1, 2) step motor 1, machine controller 2, lead screw 3, locating support 4, unmanned aerial vehicle 5, aircraft branch 6, angle adjusting slider 7, angle adjuster 8, slide rail 9, spout 10, control box 11, locating pin 12, base 13 and lead screw slider 14.
The lead screw slider 14 is arranged on the lead screw 3, and the lead screw 3 is arranged on the motor controller 2 and is connected with the stepping motor 1; the unmanned aerial vehicle 5 is fixed on an airplane support rod 6, the airplane support rod 6 is installed on an angle adjusting slider 7, the angle adjusting slider 7 is hinged on an angle adjuster 8, and the angle adjuster 8 is fixed on a lead screw slider 14; the front section of the positioning bracket 4 is hinged with the airplane support rod 6, and the rear end is connected with the sliding groove 10; the base 13 is fixed at the lower extreme of slide rail 9, and control box 11 is fixed on slide rail 9, is equipped with power, singlechip, control panel in the control box 11.
The angle of attack of the unmanned aerial vehicle can be adjusted under the action of the aircraft support rod 6, the angle adjusting slide block 7 and the angle adjuster 8; the calculation of unmanned aerial vehicle focus height can be carried out through the operation of singlechip in control box 11, sets up corresponding angle at the touch-control board to send the signal of telecommunication by the controller, control step motor 1 motion makes unmanned aerial vehicle's focus keep at same height.
The invention has the advantages that: the automatic unmanned aerial vehicle attack angle adjusting system can quickly adjust the attack angle of the unmanned aerial vehicle and automatically adjust the gravity center of the unmanned aerial vehicle, so that the unmanned aerial vehicle is ensured to be in the optimal wind speed section, the wind tunnel test angle adjusting efficiency is improved, and the accuracy of wind tunnel test data is also improved. The rapid adjustment of 0-90 degrees can be carried out through the design of different limiting holes in the angle adjuster; the measurement accuracy and efficiency of pitch angle in the wind tunnel test process are improved. The automatic adjustment of the height of the unmanned aerial vehicle in the wind field is completed by calculating and controlling the up-and-down operation of the screw rod sliding block through the single chip microcomputer. Base and fixed bolster adopt triangle-shaped overall arrangement mode, have not only reduced system's weight, have also improved unmanned aerial vehicle's overall stability in the test process. Aircraft branch adopts the afterbody mounting means, can furthest's the fuselage pneumatics that remains unmanned aerial vehicle to reduce the wake of branch and disturb. The automatic adjusting system for the attack angle of the unmanned aerial vehicle is simple in structure and reasonable in layout, automatic adjustment of the attack angle is achieved, the test process can be simplified, and the working efficiency is improved.
Drawings
FIG. 1: provided is a schematic diagram of an automatic adjusting system for an attack angle of an unmanned aerial vehicle.
FIG. 2: angle adjuster front view.
Detailed Description
The base 13 is formed by welding triangular iron, so that the strength of the base and the stability of a system are improved. The lead screw 3 and the base 13 are fixed together through bolts and form a triangular layout with the base 13, so that the pitching stability of the lead screw 3 is enhanced. The stepping motor 1 is installed on the top end of the screw rod and is connected with the screw rod 3 through the motor controller 2.
The angle regulator 8 is fixed on the screw rod sliding block 14 through a bolt, moves up and down along with the screw rod sliding block 14 to carry out height regulation, and is fixed in height by the positioning support 4. One section bolted connection of locating support 4 is on spout 10, and spout 10 is in lead screw 3 both sides, and the other end articulates on aircraft branch 6 through the pin, and locating support 4, aircraft branch 6 and lead screw 3 three become triangle-shaped stable structure, reach highly fixed, the angle is stable purpose. 6 one end of aircraft branch is connected with unmanned aerial vehicle 5, and the other end is fixed with 7 tight fittings of angle adjusting slider, and angle adjusting slider 7 is the U type, transfers machine 8 to be connected through rotation axis and angle, accomplishes angle location through locating pin 12 and angle regulator 8. The pitch angle of the unmanned aerial vehicle 5 is adjusted by the aircraft pole support 6, and the aircraft pole support 6 and the angle adjusting slide block 7 move synchronously.
The control box 11 is arranged at the back of the screw rod 3, and a power supply, a singlechip and a control panel are arranged in the control box. The power supply adopts a 5v battery to supply power for the singlechip and the control panel. The control panel is connected with the single chip microcomputer and can input height and angle data. The single chip microcomputer mainly performs data operation, is connected with the motor controller 2 in a wire form, converts an operation result into an electric signal, and performs motion adjustment of the stepping motor 1.
Before the wind tunnel test, the angle regulator 8 is adjusted to 0 degree, and the screw rod slide block 14 is adjusted to the middle position of the slide rail. The base 13 is adjusted to be in a horizontal state, so that the aircraft support 6 is positioned at the middle position of the wind speed field.
The front view of the angle regulator is shown in fig. 2, the angle regulator 8 is fan-shaped, is provided with an angle positioning hole of 10-80 degrees, and when the angle regulating slide block 7 is positioned at the horizontal position and the vertical position, the pitch angles are 0 degree and 90 degree, and the angle regulation within the range of 0-90 degree can be realized. The angle adjusting slide block 7 is U-shaped, is fixedly connected with the angle adjuster 8 through a rotating shaft, and is positioned at different angles through a positioning pin 12. The angle adjustment is carried out according to the test requirements, and the angle slider 7 is slid to a 40-degree hole of the angle adjuster 8 by taking 40 degrees as an example and is fixed by the positioning pin 12.
During the height adjustment, the distance h between the top end of the airplane support rod 7 and the ground is measured by using a meter ruler to measure the distance h between the angle adjuster 8 and the ground at 0 degree and 40 degree0And h1The measured size is input into a single chip microcomputer of the control box 11, the angle value of the angle regulator 8 is input into the single chip microcomputer through a control panel, the movement distance of the screw rod sliding block 14 is obtained through calculation of the single chip microcomputer, a control signal is transmitted to the motor controller 2, the motor controller 2 controls the stepping motor 1 to drive the screw rod 3 to rotate, and the screw rod sliding block 14 is controlled to move to the designated height. Angle modulation ware 8 passes through screw thread fixed connection (as shown in fig. 2) with lead screw slider 14, can accomplish the regulation of unmanned aerial vehicle height through lead screw slider 14's motion to ensure that it is located the wind field interlude.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are merely exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (3)
1. The utility model provides a wind tunnel test unmanned aerial vehicle angle of attack automatic regulating system, its characterized in that includes (as shown in fig. 1, 2) step motor 1, machine controller 2, lead screw 3, locating support 4, unmanned aerial vehicle 5, aircraft branch 6, angle adjusting slider 7, angle adjuster 8, slide rail 9, spout 10, control box 11, locating pin 12, base 13 and lead screw slider 14.
2. The automatic angle-of-attack adjusting system for the wind tunnel test unmanned aerial vehicle as claimed in claim 1, wherein the lead screw slider 14 is mounted on a lead screw 3, and the lead screw 3 is mounted on the motor controller 2 and connected to the stepping motor 1; the unmanned aerial vehicle 5 is fixed on an airplane support rod 6, the airplane support rod 6 is installed on an angle adjusting slider 7, the angle adjusting slider 7 is hinged on an angle adjuster 8, and the angle adjuster 8 is fixed on a lead screw slider 14; the front section of the positioning bracket 4 is hinged with the airplane support rod 6, and the rear end is connected with the sliding groove 10; the base 13 is fixed at the lower extreme of slide rail 9, and control box 11 is fixed on slide rail 9, is equipped with power, singlechip, control panel in the control box 11.
3. The automatic adjusting system for the attack angle of the unmanned aerial vehicle in the wind tunnel test of claim 1 is characterized in that the attack angle of the unmanned aerial vehicle can be adjusted under the action of an aircraft strut 6, an angle adjusting slider 7 and an angle adjuster 8; the calculation of unmanned aerial vehicle focus height can be carried out through the operation of singlechip in control box 11, sets up corresponding angle at the touch-control board to send the signal of telecommunication by the controller, control step motor 1 motion makes unmanned aerial vehicle's focus keep at same height.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011423296.XA CN112362288A (en) | 2020-12-08 | 2020-12-08 | Automatic adjusting system for attack angle of wind tunnel test unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011423296.XA CN112362288A (en) | 2020-12-08 | 2020-12-08 | Automatic adjusting system for attack angle of wind tunnel test unmanned aerial vehicle |
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| CN112362288A true CN112362288A (en) | 2021-02-12 |
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| CN202011423296.XA Pending CN112362288A (en) | 2020-12-08 | 2020-12-08 | Automatic adjusting system for attack angle of wind tunnel test unmanned aerial vehicle |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113048118A (en) * | 2021-03-24 | 2021-06-29 | 大连理工大学 | Hydraulic supporting device for adjusting attack angle |
| CN113970418A (en) * | 2021-10-26 | 2022-01-25 | 中国航空工业集团公司哈尔滨空气动力研究所 | Variable attack angle device for wind tunnel test |
| CN113998144A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Measuring device of adjustable counter weight |
| CN114034463A (en) * | 2022-01-10 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Single-point abdominal support device of two-stage attack angle mechanism and control method |
-
2020
- 2020-12-08 CN CN202011423296.XA patent/CN112362288A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113048118A (en) * | 2021-03-24 | 2021-06-29 | 大连理工大学 | Hydraulic supporting device for adjusting attack angle |
| CN113048118B (en) * | 2021-03-24 | 2022-02-18 | 大连理工大学 | Hydraulic supporting device for adjusting attack angle |
| CN113970418A (en) * | 2021-10-26 | 2022-01-25 | 中国航空工业集团公司哈尔滨空气动力研究所 | Variable attack angle device for wind tunnel test |
| CN113998144A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Measuring device of adjustable counter weight |
| CN114034463A (en) * | 2022-01-10 | 2022-02-11 | 中国空气动力研究与发展中心低速空气动力研究所 | Single-point abdominal support device of two-stage attack angle mechanism and control method |
| CN114034463B (en) * | 2022-01-10 | 2022-03-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Single-point abdominal support device of two-stage attack angle mechanism and control method |
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