CN114720085A - Fixed wing aircraft wind resistance performance detection device - Google Patents
Fixed wing aircraft wind resistance performance detection device Download PDFInfo
- Publication number
- CN114720085A CN114720085A CN202210453050.XA CN202210453050A CN114720085A CN 114720085 A CN114720085 A CN 114720085A CN 202210453050 A CN202210453050 A CN 202210453050A CN 114720085 A CN114720085 A CN 114720085A
- Authority
- CN
- China
- Prior art keywords
- wall
- fixed
- wing aircraft
- wind resistance
- fixing
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001514 detection method Methods 0.000 title claims abstract description 42
- 230000007246 mechanism Effects 0.000 claims abstract description 53
- 238000007664 blowing Methods 0.000 claims abstract description 21
- 230000001681 protective effect Effects 0.000 claims description 9
- 238000009434 installation Methods 0.000 claims description 8
- 238000002474 experimental method Methods 0.000 claims description 7
- 238000001125 extrusion Methods 0.000 claims description 7
- 238000007514 turning Methods 0.000 claims description 3
- 238000000034 method Methods 0.000 description 4
- 230000002457 bidirectional effect Effects 0.000 description 3
- 230000006872 improvement Effects 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 238000013459 approach Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 230000008569 process Effects 0.000 description 1
Images
Classifications
-
- 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
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B11/00—Work holders not covered by any preceding group in the subclass, e.g. magnetic work holders, vacuum work holders
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Landscapes
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Indicating Or Recording The Presence, Absence, Or Direction Of Movement (AREA)
Abstract
The invention relates to the technical field of fixed-wing aircraft detection, in particular to a fixed-wing aircraft wind resistance detection device which comprises a blowing mechanism, a base, a fixing mechanism and a detection mechanism, wherein the blowing mechanism comprises a supporting plate fixed on one side of the outer wall of the top of the base, a circular groove is formed in the outer wall of one side of the supporting plate, and the blowing mechanism, the fixing mechanism and the detection mechanism are positioned above the base. The friction force between the fixing block and the airplane wing can be increased, and therefore the fixing stability is improved.
Description
Technical Field
The invention relates to the technical field of fixed-wing aircraft detection, in particular to a device for detecting wind resistance of a fixed-wing aircraft.
Background
Fixed wing aircraft is also known as fixed wing unmanned aerial vehicle, be a fixed wing miniature unmanned aerial vehicle, because of it has less noise and good disguise and by general application, but fixed wing unmanned aerial vehicle also has some problems, for example, duration is relatively poor etc., fixed wing aircraft production processing is accomplished the back, need detect its anti-wind performance, fixed wing aircraft is at the in-process that anti-wind performance test detected, need fix the fixed wing aircraft, the fixed wing aircraft mode of fixing the fixed wing aircraft on the anti-wind performance detection device of current fixed wing aircraft is fixed through the bracing piece.
The invention discloses a fixed-wing aircraft wind resistance detection device with the publication number of CN113532790A, which comprises an aircraft body, wherein a mounting plate is mounted on the aircraft body, a driving mechanism for wind test is arranged on the mounting plate, a supporting rod is connected to the aircraft body in a sliding manner through a pushing mechanism, and the supporting rod is connected to the fixed-wing aircraft through a fixing mechanism convenient to fix. The beneficial effects of the invention are: this fixed wing aircraft wind resistance can detection device, at the in-process that detects, need carry out the in-process that fixes with the organism, offsets organism and first arc, with the electro-magnet circular telegram on the first arc, produces magnetic force under the effect of electromagnetism, attracts the organism fixedly through magnetic force, accomplishes the fixed to the organism, and the fixed operation of whole organism is simple, it is convenient to implement, can be quick fixed with the organism.
However, the above patent has the following disadvantages that the wind direction cannot be changed, and the detection range of the aircraft wing is reduced, and the fixing mode of the above patent is single, and the wind resistance performance of the wing during the detection of the aircraft cannot be simulated, and the use has limitations, so that a device for detecting the wind resistance performance of the fixed-wing aircraft is needed to solve the above problems.
Disclosure of Invention
The invention aims to provide a device for detecting the wind resistance of a fixed-wing aircraft, which is used for solving the problems in the background technology.
The technical scheme of the invention is as follows: a fixed wing aircraft wind resistance performance detection device comprises a blowing mechanism, a base, a fixing mechanism and a detection mechanism, wherein the blowing mechanism comprises a supporting plate fixed on one side of the outer wall of the top of the base, a circular groove is formed in the outer wall of one side of the supporting plate, the blowing mechanism, the fixing mechanism and the detection mechanism are located above the base, the blowing mechanism comprises circular rods rotating on the inner walls of two ends of the circular groove, the outer wall of one side, opposite to the two circular rods, of each circular rod is provided with a same mounting ring, and the inner wall of each mounting ring is provided with an experiment fan;
the fixing mechanism comprises a fixing frame sliding on the inner walls of the two first limiting grooves, a mounting groove is formed in the outer wall of one end of the fixing frame, the inner walls of the two sides of the mounting groove are rotatably connected with the same bidirectional lead screw, sliding blocks are rotatably connected to the two sides of the outer wall of the circumference of the bidirectional lead screw through threads, a fixing block is arranged on the outer wall of one end of each sliding block, and a locking bolt is rotatably connected to the outer wall of one side of the fixing frame;
the detection mechanism comprises a rectangular groove fixed to the other end of the outer wall of the top of the base and provided with equidistant distribution, a fixed column is slidably connected to the inner wall of the rectangular groove, a connecting column is installed on the outer wall of the top of the fixed column, a second limiting groove is formed in the outer wall of one end of the connecting column, a supporting block is slidably connected to the inner wall of the second limiting groove, a connecting plate is installed on the outer wall of one side of the supporting block, and fixing rods which are equidistantly distributed are slidably inserted into the outer wall of one end of the connecting plate.
Preferably, the motor is installed to backup pad one end outer wall, and motor output shaft passes through bolt and corresponding circular pole one end outer wall fixed connection, the PLC controller is installed to backup pad other end outer wall, and the supporting leg is all installed at four turnings of base bottom outer wall, and erection column one end outer wall rotates and is connected with the supporting screw.
Preferably, two-way lead screw one side extends to the outside of mount, and two-way lead screw one side outer wall installs first hand wheel, two the third sliding tray has all been seted up to the relative one side outer wall of fixed block, and the inner wall sliding connection of third sliding tray has the extrusion lug, supporting spring is installed to extrusion lug one side outer wall, supporting spring one side outer wall and the inner wall fixed connection of third sliding tray.
Preferably, rotation axis one end extends to the outside of arc seat, and rotation axis circumference outer wall one end has cup jointed driven gear, arc seat other end outer wall rotates and is connected with the back shaft, and back shaft circumference outer wall has cup jointed the driving gear, and the driving gear meshes with the driven gear outer wall mutually.
Preferably, a protective shell is installed on the outer wall of the other end of the arc seat and located outside the driving gear and the driven gear, a pointer is sleeved at one end of the outer wall of the circumference of the rotating shaft, the outer wall of the pointer is connected with the outer wall of one end of the protective shell in a sliding mode, and a second hand wheel is installed on the outer wall of one end of the supporting shaft.
Preferably, the outer wall of the circumference of the fixing rod is sleeved with a buffer spring, the outer wall of one side of the fixing rod is provided with a pressure sensor, and the outer walls of two sides of the buffer spring are fixedly connected with the pressure sensor and the outer wall of one side, opposite to the connecting plate, of the buffer spring respectively.
Preferably, the outer wall of the other side of the fixing rod is provided with a circular block, and the connecting plate is positioned between the circular block and the buffer spring.
Preferably, the outer walls of the two ends of the supporting block are provided with openings, the inner wall of each opening is connected with a connecting block in a sliding mode, and the outer wall of one end of each connecting block is provided with rubber heads distributed equidistantly.
Preferably, a connecting spring is installed on the outer wall of the other end of the connecting block, and the other end of the connecting spring is fixedly connected with the inner wall of the opening.
The invention provides a fixed wing aircraft wind resistance detection device through improvement, compared with the prior art, the fixed wing aircraft wind resistance detection device has the following improvements and advantages:
one is as follows: according to the invention, the fixing mechanism is arranged, firstly, the distance between the two fixing frames is adjusted according to the width of the airplane wing, then the fixing frames are fixed on the mounting columns by using the locking bolts, the test height of the airplane wing can be adjusted, the first hand wheel on the fixing frames is rotated, the sliding blocks on the two-way screw rod can be driven to mutually approach, so that the fixing blocks can extrude and fix the airplane wing, and the supporting springs and the extrusion bumps on the fixing blocks can increase the friction force between the fixing blocks and the airplane wing, thereby improving the stability of the fixing and simulating the wind resistance performance of the airplane during the flying process;
the second step is as follows: according to the invention, the blowing mechanism is arranged, the experiment fan is started, the wind resistance performance of the airplane wing can be detected, then the motor is started, the experiment fan on the mounting ring is driven to rotate through the circular rod, so that the rotation of the experiment fan can be realized, the wind direction can be quickly adjusted, the performance of the airplane wing can be measured, the second hand wheel is rotated to drive the rotating shaft on the driven gear to rotate through the driving gear on the supporting shaft, so that the mounting column on the rotating shaft is driven to rotate, the fixed position of the airplane wing can be changed, and the detection range of the airplane wing is further improved;
and thirdly: according to the invention, the detection mechanism is arranged, the connecting column is inserted into the proper rectangular groove through the fixing column, so that the distance between the pressure sensor on the fixing rod and the experimental fan is proper, and the subsequent detection is convenient.
Drawings
The invention is further explained below with reference to the figures and examples:
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic side view of the present invention;
FIG. 3 is a schematic view of the driven gear, support shaft and drive gear configuration of the present invention;
FIG. 4 is a schematic view of the detection mechanism of the present invention;
FIG. 5 is a schematic view of the securing mechanism of the present invention;
FIG. 6 is a schematic view of the blowing mechanism of the present invention;
FIG. 7 is a schematic cross-sectional view of the fixing block of the present invention;
FIG. 8 is a cross-sectional structural schematic of the support block of the present invention.
Description of reference numerals:
1. a PLC controller; 2. a blowing mechanism; 201. a support plate; 202. a mounting ring; 203. an experimental fan; 204. a circular rod; 205. an electric motor; 3. a base; 4. mounting a column; 5. a fixing mechanism; 501. a fixed mount; 502. locking the bolt; 503. a first hand wheel; 504. a bidirectional screw rod; 505. a slider; 506. a fixed block; 507. extruding the bump; 508. a support spring; 6. a support screw; 7. an arc-shaped seat; 8. a detection mechanism; 801. connecting columns; 802. a circular block; 803. a connecting plate; 804. fixing the rod; 805. a buffer spring; 806. a pressure sensor; 807. a support block; 808. a connecting spring; 809. connecting blocks; 9. a rectangular groove; 10. a protective housing; 11. a pointer; 12. a second hand wheel; 13. a rotating shaft; 14. a driven gear; 15. a support shaft; 16. a drive gear.
Detailed Description
The present invention is described in detail below, and the technical solutions in the embodiments of the present invention are clearly and completely described, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments in the present invention, belong to the protection scope of the present invention.
The invention provides a device for detecting the wind resistance of a fixed wing aircraft through improvement, and the technical scheme of the device is as follows:
as shown in fig. 1-8, a device for detecting wind resistance of a fixed wing aircraft comprises a blowing mechanism 2, a base 3, a fixing mechanism 5 and a detecting mechanism 8, wherein the blowing mechanism 2 comprises a supporting plate 201 fixed on one side of the outer wall of the top of the base 3, a circular groove is formed in the outer wall of one side of the supporting plate 201, the blowing mechanism 2, the fixing mechanism 5 and the detecting mechanism 8 are located above the base 3, the blowing mechanism 2 comprises circular rods 204 rotating on the inner walls of the two ends of the circular groove, the same mounting ring 202 is mounted on the outer wall of the opposite side of the two circular rods 204, and an experimental fan 203 is mounted on the inner wall of the mounting ring 202;
an arc-shaped seat 7 is installed at one end of the outer wall of the top of the base 3, a rotating shaft 13 is rotatably connected to the bottom of the outer wall of one end of the arc-shaped seat 7, an installation column 4 is sleeved on the outer wall of the circumference of the rotating shaft 13, first limiting grooves are formed in the outer walls of two sides of the installation column 4, the fixing mechanism 5 comprises a fixing frame 501 sliding on the inner walls of the two first limiting grooves, an installation groove is formed in the outer wall of one end of the fixing frame 501, the inner walls of two sides of the installation groove are rotatably connected with the same two-way lead screw 504, sliding blocks 505 are rotatably connected to two sides of the outer wall of the circumference of the two-way lead screw 504 through threads, a fixing block 506 is installed on the outer wall of one end of each sliding block 505, and a locking bolt 502 is rotatably connected to the outer wall of one side of the fixing frame 501;
Further, motor 205 is installed to backup pad 201 one end outer wall, and motor 205 output shaft passes through bolt and corresponding circular rod 204 one end outer wall fixed connection, PLC controller 1 is installed to backup pad 201 other end outer wall, the supporting leg is all installed at four turnings of 3 bottom outer walls of base, 4 one end outer walls of erection column rotate and are connected with supporting screw 6, rubber seat is installed to supporting leg bottom outer wall, open motor 205, it rotates to drive experiment fan 203 on collar 202 through circular rod 204, thereby can realize the rotation to experiment fan 203, can the quick adjustment wind direction, measure the performance of aircraft wing.
Further, one side of the two-way screw rod 504 extends to the outside of the fixing frame 501, the first hand wheel 503 is installed on the outer wall of one side of the two-way screw rod 504, the third sliding grooves are formed in the outer walls of the two opposite sides of the two fixing blocks 506, the inner wall of each third sliding groove is connected with an extrusion bump 507 in a sliding mode, a supporting spring 508 is installed on the outer wall of one side of each extrusion bump 507, and the outer wall of one side of each supporting spring 508 is fixedly connected with the inner wall of each third sliding groove.
Further, rotation axis 13 one end extends to the outside of arc seat 7, and rotation axis 13 circumference outer wall one end has cup jointed driven gear 14, and 7 other ends outer walls of arc seat rotate and be connected with back shaft 15, and back shaft 15 circumference outer wall has cup jointed driving gear 16, and driving gear 16 and the meshing of 14 outer walls of driven gear mutually, and driven gear 14's external diameter is greater than driving gear 16's external diameter, consequently can realize adjusting accurately.
Further, protective housing 10 is installed to 7 other end outer walls of arc seat, and protective housing 10 is located driving gear 16 and driven gear 14's outside, pointer 11 has been cup jointed to 13 circumference outer wall one end of rotation axis, and pointer 11 outer wall and protective housing 10 one end outer wall sliding connection, second hand wheel 12 is installed to 15 one end outer walls of back shaft, it drives the rotation axis 13 rotation on the driven gear 14 through the driving gear 16 on the back shaft 15 to rotate second hand wheel 12, thereby it rotates to drive erection column 4 on the rotation axis 13, can change the fixed position of aircraft wing, thereby further improved the detection range of aircraft wing.
Furthermore, a buffer spring 805 is sleeved on the outer wall of the circumference of the fixing rod 804, a pressure sensor 806 is installed on the outer wall of one side of the fixing rod 804, the outer walls of the two sides of the buffer spring 805 are fixedly connected with the outer wall of the opposite side of the pressure sensor 806 and the outer wall of the opposite side of the connecting plate 803, the model of the pressure sensor 806 is YYJ/GY1-1201, and the pressure sensor 806 is electrically connected with the signal input end of the PLC controller 1 through a signal line.
Further, circular block 802 is installed to the outer wall of the other side of fixed rod 804, and connecting plate 803 is located between circular block 802 and buffer spring 805, through being provided with detection mechanism 8, insert spliced pole 801 on suitable rectangular channel 9 through the fixed column, make pressure sensor 806 on the fixed rod 804 suitable from the distance of experimental fan 203, make things convenient for detection next, fixed rod 804 on the connecting plate 803, buffer spring 805 and pressure sensor 806, when experimental fan 203 blows to the aircraft wing, can drive its outer wall to take place to warp, the aircraft wing that warp can extrude pressure sensor 806 on the fixed rod 804, can detect and detect aircraft wing deformation result under the blowing of experimental fan 203, be convenient for the staff to obtain detection data.
Further, the opening has all been seted up to supporting shoe 807 both ends outer wall, and open-ended inner wall sliding connection has connecting block 809, and the equidistant rubber head that distributes is installed to connecting block 809 one end outer wall.
Further, connecting spring 808 is installed to connecting block 809 other end outer wall, and the connecting spring 808 other end and opening inner wall fixed connection, connecting spring 808, connecting spring 809 and the rubber head on the supporting shoe 807 can make the supporting shoe 807 fix the suitable height on spliced pole 801, make things convenient for next detection and processing.
The working principle is as follows: the device is fixed on a working place through supporting legs, then is externally connected with a power supply, the distance between two fixing frames 501 is adjusted according to the width of the wings of the airplane by arranging a fixing mechanism 5, then the fixing frames 501 are fixed on mounting columns 4 by using locking bolts 502, the testing height of the wings of the airplane can be adjusted, a first hand wheel 503 on the fixing frames 501 is rotated, sliding blocks 505 on a two-way screw rod 504 can be driven to mutually approach, so that the fixing blocks 506 extrude and fix the wings of the airplane, a supporting spring 508 and an extruding lug 507 on the fixing blocks 506 can increase the friction between the fixing blocks 506 and the wings of the airplane, so that the fixing stability is improved, the experimental fan 203 is started by arranging a blowing mechanism 2, the wind resistance performance of the wings of the airplane can be detected, then a motor 205 is started, the experimental fan 203 on the mounting ring 202 is driven to rotate by a round rod 204, thereby, the rotation of the experimental fan 203 can be realized, the wind direction can be rapidly adjusted, the performance of the airplane wing can be measured, the second hand wheel 12 is rotated to drive the rotating shaft 13 on the driven gear 14 to rotate through the driving gear 16 on the supporting shaft 15, so as to drive the mounting column 4 on the rotating shaft 13 to rotate, the fixed position of the airplane wing can be changed, thereby further improving the detection range of the airplane wing, the detection mechanism 8 is arranged, the connecting column 801 is inserted into the proper rectangular groove 9 through the fixing column, so that the distance between the pressure sensor 806 on the fixing rod 804 and the experimental fan 203 is proper, the subsequent detection is convenient, the fixing rod 804, the buffer spring 805 and the pressure sensor 806 on the connecting plate 803 are provided, when the experimental fan 203 blows to the airplane wing, the outer wall of the experimental fan is driven to deform, and the deformed airplane wing extrudes the pressure sensor 806 on the fixing rod 804, the wing deformation result of the airplane under blowing of the experimental fan 203 can be detected, and the detection data can be obtained by workers conveniently.
Claims (9)
1. The utility model provides a fixed wing aircraft wind resistance performance detection device which characterized in that: the device comprises a blowing mechanism (2), a base (3), a fixing mechanism (5) and a detection mechanism (8), wherein the blowing mechanism (2) comprises a supporting plate (201) fixed on one side of the outer wall of the top of the base (3), a circular groove is formed in the outer wall of one side of the supporting plate (201), the blowing mechanism (2), the fixing mechanism (5) and the detection mechanism (8) are located above the base (3), the blowing mechanism (2) comprises circular rods (204) rotating on the inner walls of two ends of the circular groove, the outer wall of one side, opposite to the two circular rods (204), is provided with a same mounting ring (202), and the inner wall of the mounting ring (202) is provided with an experiment fan (203);
an arc-shaped seat (7) is installed at one end of the outer wall of the top of the base (3), a rotating shaft (13) is rotatably connected to the bottom of the outer wall of one end of the arc-shaped seat (7), an installation column (4) is sleeved on the outer wall of the circumference of the rotating shaft (13), first limiting grooves are formed in the outer walls of two sides of the installation column (4), a fixing mechanism (5) comprises a fixing frame (501) which slides on the inner walls of the two first limiting grooves, an installation groove is formed in the outer wall of one end of the fixing frame (501), the inner walls of two sides of the installation groove are rotatably connected with the same two-way lead screw (504), sliding blocks (505) are rotatably connected to two sides of the outer wall of the circumference of the two-way lead screw (504) through threads, fixed blocks (506) are installed on the outer wall of one side of the fixing frame (501), and locking bolts (502) are rotatably connected to the outer wall of one side of the fixing frame (501);
detection mechanism (8) including fixing rectangular channel (9) of seting up the equidistance and distributing at base (3) top outer wall other end, and rectangular channel (9) inner wall sliding connection has the fixed column, and spliced pole (801) are installed to fixed column top outer wall, and spliced pole (801) one end outer wall has seted up the second spacing groove, and the inner wall sliding connection of second spacing groove has supporting shoe (807), connecting plate (803) are installed to supporting shoe (807) one side outer wall, and connecting plate (803) one end outer wall sliding plug has dead lever (804) that the equidistance distributes.
2. The fixed-wing aircraft wind resistance detection device of claim 1, wherein: motor (205) are installed to backup pad (201) one end outer wall, and motor (205) output shaft passes through bolt and corresponding circular pole (204) one end outer wall fixed connection, PLC controller (1) is installed to backup pad (201) other end outer wall, and the supporting leg is all installed at four turnings of base (3) bottom outer wall, and erection column (4) one end outer wall rotates and is connected with supporting screw (6).
3. The fixed-wing aircraft wind resistance detection device of claim 1, wherein: two-way lead screw (504) one side extends to the outside of mount (501), and two-way lead screw (504) one side outer wall installs first hand wheel (503), two the third sliding tray has all been seted up to the relative one side outer wall of fixed block (506), and the inner wall sliding connection of third sliding tray has extrusion lug (507), supporting spring (508) are installed to extrusion lug (507) one side outer wall, the inner wall fixed connection of supporting spring (508) one side outer wall and third sliding tray.
4. The fixed-wing aircraft wind resistance detection device of claim 1, wherein: rotation axis (13) one end extends to the outside of arc seat (7), and rotation axis (13) circumference outer wall one end has cup jointed driven gear (14), arc seat (7) other end outer wall rotates and is connected with back shaft (15), and back shaft (15) circumference outer wall has cup jointed driving gear (16), and driving gear (16) and driven gear (14) outer wall mesh mutually.
5. The device for detecting the wind resistance of the fixed-wing aircraft according to claim 4, wherein: protective housing (10) are installed to arc seat (7) other end outer wall, and protective housing (10) are located the outside of driving gear (16) and driven gear (14), pointer (11) have been cup jointed to rotation axis (13) circumference outer wall one end, and pointer (11) outer wall and protective housing (10) one end outer wall sliding connection, second hand wheel (12) are installed to back shaft (15) one end outer wall.
6. The fixed-wing aircraft wind resistance detection device of claim 1, wherein: buffer spring (805) has been cup jointed to dead lever (804) circumference outer wall, and dead lever (804) one side outer wall installs pressure sensor (806), buffer spring (805) both sides outer wall respectively with pressure sensor (806) and connecting plate (803) relative one side outer wall fixed connection.
7. The device for detecting the wind resistance of the fixed-wing aircraft according to claim 6, wherein: the outer wall of the other side of the fixing rod (804) is provided with a round block (802), and the connecting plate (803) is positioned between the round block (802) and the buffer spring (805).
8. The fixed-wing aircraft wind resistance detection device of claim 1, wherein: the opening has all been seted up to supporting shoe (807) both ends outer wall, and open-ended inner wall sliding connection has connecting block (809), and the rubber head that the equidistance distributes is installed to connecting block (809) one end outer wall.
9. The device for detecting the wind resistance of the fixed-wing aircraft according to claim 8, wherein: and a connecting spring (808) is arranged on the outer wall of the other end of the connecting block (809), and the other end of the connecting spring (808) is fixedly connected with the inner wall of the opening.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210453050.XA CN114720085B (en) | 2022-04-27 | 2022-04-27 | Wind resistance detection device for fixed wing aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210453050.XA CN114720085B (en) | 2022-04-27 | 2022-04-27 | Wind resistance detection device for fixed wing aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114720085A true CN114720085A (en) | 2022-07-08 |
| CN114720085B CN114720085B (en) | 2024-07-30 |
Family
ID=82246244
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210453050.XA Active CN114720085B (en) | 2022-04-27 | 2022-04-27 | Wind resistance detection device for fixed wing aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114720085B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116678587A (en) * | 2023-07-27 | 2023-09-01 | 江苏玄博智能标识科技有限公司 | Sign board wind resistance performance detection equipment |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012046643A1 (en) * | 2010-10-04 | 2012-04-12 | 三菱重工業株式会社 | Wind tunnel test model and wind tunnel test method |
| CN213139182U (en) * | 2020-08-24 | 2021-05-07 | 鄂尔多斯市凯图科技有限公司 | Testing device for unmanned aerial vehicle |
| CN113532790A (en) * | 2021-09-09 | 2021-10-22 | 武汉及时飞智能科技有限公司 | Fixed wing aircraft wind resistance performance detection device |
| CN215064365U (en) * | 2021-06-07 | 2021-12-07 | 苏州赛尔思精密工业有限公司 | Detection tool for vibrator |
| CN113820094A (en) * | 2021-11-23 | 2021-12-21 | 中国飞机强度研究所 | Environment field measuring device and method for indoor blowing test of airplane |
| WO2022040858A1 (en) * | 2020-08-24 | 2022-03-03 | 唐山哈船科技有限公司 | Anti-collision unmanned aerial vehicle for aerial photography and method therefor |
-
2022
- 2022-04-27 CN CN202210453050.XA patent/CN114720085B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2012046643A1 (en) * | 2010-10-04 | 2012-04-12 | 三菱重工業株式会社 | Wind tunnel test model and wind tunnel test method |
| CN213139182U (en) * | 2020-08-24 | 2021-05-07 | 鄂尔多斯市凯图科技有限公司 | Testing device for unmanned aerial vehicle |
| WO2022040858A1 (en) * | 2020-08-24 | 2022-03-03 | 唐山哈船科技有限公司 | Anti-collision unmanned aerial vehicle for aerial photography and method therefor |
| CN215064365U (en) * | 2021-06-07 | 2021-12-07 | 苏州赛尔思精密工业有限公司 | Detection tool for vibrator |
| CN113532790A (en) * | 2021-09-09 | 2021-10-22 | 武汉及时飞智能科技有限公司 | Fixed wing aircraft wind resistance performance detection device |
| CN113820094A (en) * | 2021-11-23 | 2021-12-21 | 中国飞机强度研究所 | Environment field measuring device and method for indoor blowing test of airplane |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116678587A (en) * | 2023-07-27 | 2023-09-01 | 江苏玄博智能标识科技有限公司 | Sign board wind resistance performance detection equipment |
| CN116678587B (en) * | 2023-07-27 | 2023-10-20 | 江苏玄博智能标识科技有限公司 | Sign board wind resistance performance detection equipment |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114720085B (en) | 2024-07-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109018430B (en) | Rotorcraft blade performance test bench | |
| CN114720085A (en) | Fixed wing aircraft wind resistance performance detection device | |
| CN115468705A (en) | Device and method for testing dynamic balance of motor rotor | |
| CN209650579U (en) | A kind of unmanned plane device for testing tensile force | |
| CN105444983B (en) | A kind of model rolling angle measurement device of high-speed wind tunnel | |
| CN113203386B (en) | Motor iron core inner diameter concentricity detection device and detection method thereof | |
| CN214502834U (en) | Unmanned aerial vehicle power test device | |
| CN109238217A (en) | A kind of aluminium-plastic panel flatness automatic checkout system and aluminium-plastic panel flatness detection method | |
| CN219640974U (en) | Remote sensing monitoring device for non-grain farmland | |
| CN115061177B (en) | Physical dose measuring instrument for simulating lung movement for radiotherapy | |
| CN109668025B (en) | Distributed photovoltaic power station monitoring device | |
| CN209570348U (en) | Simple test run rack for aero-engine | |
| CN111409858A (en) | Be used for wing to prevent and remove icing material testing arrangement | |
| CN221563462U (en) | Be used in portable novel pivot elevating gear on unmanned aerial vehicle | |
| CN114590419B (en) | Unmanned aerial vehicle power detection device | |
| CN220884811U (en) | Detection device for wind resistance of airplane | |
| CN111645856B (en) | Be used for unmanned aerial vehicle fuselage levelling device | |
| CN220199595U (en) | Detector for balancing flight angle of unmanned aerial vehicle | |
| CN215436915U (en) | Dihedral unmanned aerial vehicle horn fixation clamp | |
| CN219455442U (en) | Balance weight frame of airplane model | |
| CN213292060U (en) | Car seat is with electronic guide rail convenient to installation | |
| CN109406387A (en) | A kind of frictional coefficient of fiber test device | |
| CN220501031U (en) | Lens mount table for power transmission line inspection | |
| CN220437392U (en) | Automatic detection device is visited with hole to aviation | |
| CN220218559U (en) | Light mechanical arm convenient to disassemble and assemble |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |