CN111086652A - Unmanned aerial vehicle lift test platform - Google Patents
Unmanned aerial vehicle lift test platform Download PDFInfo
- Publication number
- CN111086652A CN111086652A CN202010044706.3A CN202010044706A CN111086652A CN 111086652 A CN111086652 A CN 111086652A CN 202010044706 A CN202010044706 A CN 202010044706A CN 111086652 A CN111086652 A CN 111086652A
- Authority
- CN
- China
- Prior art keywords
- unmanned aerial
- platform
- aerial vehicle
- layer platform
- cross rods
- 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.)
- Pending
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 29
- 230000003247 decreasing effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 238000005457 optimization Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
Images
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Forklifts And Lifting Vehicles (AREA)
Abstract
The invention discloses an unmanned aerial vehicle lift force test platform, which comprises a scissor table-board mechanism, a vertical base, a balancing weight, an electronic scale, a fixed support and a control system, wherein the scissor table-board mechanism comprises an upper-layer platform, a lower-layer platform and two pairs of cross rods, the two pairs of cross rods are arranged between the upper-layer platform and the lower-layer platform, and the upper-layer platform and the lower-layer platform are self-balanced by taking the center of the cross rods as a fulcrum; the two vertical bases are positioned at two sides of the table-board mechanism of the scissors, and the pin shaft in the middle of the cross rod is supported by the vertical bases; the balancing weight is arranged on the upper end surface of the lower platform; the lower end surface of the lower layer platform is pressed on a scale pan of the electronic scale; the electronic scale is electrically connected with the control system; the fixed bolster sets up at the up end of upper platform, is used for being connected with unmanned aerial vehicle. Compared with the prior art, the invention has the advantages that: lift force of the unmanned aerial vehicle under the working state can be tested simply and conveniently, the error of a test result is small, and good compatibility is achieved.
Description
Technical Field
The invention relates to the technical field of flight performance testing of unmanned aerial vehicles, in particular to a lift force testing platform of an unmanned aerial vehicle.
Background
At present, rotor unmanned aerial vehicle is applied to in many fields such as taking photo by plane, agriculture, alert with safety, and the lift characteristic directly influences unmanned aerial vehicle's load weight and work efficiency as one of rotor unmanned aerial vehicle's important flight performance parameter, but to rotor unmanned aerial vehicle's lift characteristic, there are normative test method and evaluation standard less.
The traditional rotor unmanned aerial vehicle lift force testing device generally adopts a lever testing method, has the defects of complex structure, larger error caused by lift force loss, incapability of well simulating the vertical take-off and landing of the whole unmanned aerial vehicle, poor compatibility and the like, and is difficult to provide support for the evaluation and optimization of the lift force characteristic of the unmanned aerial vehicle.
There is a need for improvement.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide the unmanned aerial vehicle lift force test platform which is simple in structure, simple, convenient and easy to use, small in test result error and good in compatibility.
In order to realize the purpose, the following technical scheme is provided:
an unmanned aerial vehicle lift test platform, its characterized in that includes:
the scissors table-board mechanism comprises an upper layer platform, a lower layer platform and two pairs of cross rods, wherein each pair of cross rods comprises two rods, the middle parts of the two rods are movably hinged through a pin shaft, the two pairs of cross rods are arranged in parallel and at intervals, the lower end surface of the upper layer platform is provided with two parallel and spaced upper sliding grooves, the upper end surface of the lower layer platform is correspondingly provided with two parallel and spaced lower sliding grooves, the upper ends of the cross rods are embedded into the upper sliding grooves, the lower ends of the cross rods are embedded into the lower sliding grooves, the upper ends of the cross rods can freely slide along the length direction of the upper sliding grooves, and the lower ends of the cross rods can freely slide along the length direction of the lower sliding grooves;
the two vertical bases are positioned on two sides of the scissors table-board mechanism, and a pin shaft in the middle of the cross rod is supported by the vertical bases;
the counterweight block is arranged on the upper end surface of the lower-layer platform;
the lower end face of the lower layer platform is pressed on a scale pan of the electronic scale;
the electronic scale is electrically connected with the control system; and
a fixed bolster, the fixed bolster sets up the up end of upper platform, the fixed bolster be used for with unmanned aerial vehicle connects.
Optionally, the weight of the upper platform and the lower platform are equal.
Optionally, the weight of the balancing weight is adjusted by increasing or decreasing the weight. When the weight of the balancing weight is equal to the total weight of the fixing support and the fixing belt assembly, the test object is the net lift force of the unmanned aerial vehicle; when balancing weight and unmanned aerial vehicle, fixed bolster and fixed band subassembly total weight are equal, the test object is unmanned aerial vehicle total lift this moment.
Optionally, the counterweight is connected to the lower platform by a bolt.
Optionally, the fixing bracket comprises an octagonal frame and a connecting rod extending outwards from the center of the frame to the vertex of the frame.
Optionally, the unmanned aerial vehicle is installed including still being used for with fixed band subassembly on the fixed bolster, fixed band subassembly includes fixed band and belt tightener, the inboard one end of fixed band is fixed through bolt and nut on the connecting rod, the middle part of fixed band will unmanned aerial vehicle compresses tightly on the fixed bolster, fixed band outside one end is passed through belt tightener locking, the belt tightener passes through bolt and nut to be fixed on the connecting rod.
Optionally, the round pin axle is stud, and stud includes polished rod portion in the middle and is located the screw thread portion at polished rod portion both ends, and in stud's polished rod portion inserted the crossbar, the screw thread portion cover at stud both ends has and is used for carrying out spacing nut to the crossbar.
After adopting the structure, compared with the prior art, the invention has the advantages that: the upper layer platform and the lower layer platform of the invention are self-balanced by taking the center of the cross rod as a fulcrum, the weight of the balancing weight is mutually balanced with the total weight of the fixed support and the fixed belt component, the lift force of the unmanned aerial vehicle is directly reflected as the pressure acting on the electronic scale, the error of the test result is small, and the invention has good compatibility.
Drawings
FIG. 1 is a schematic structural view of a lift force test platform of an unmanned aerial vehicle according to the present invention;
FIG. 2 is an exploded view of the UAV lift test platform of the present invention;
fig. 3 is an exploded schematic view of a fixed bracket of the unmanned aerial vehicle lift force test platform and the unmanned aerial vehicle.
Detailed Description
Embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
In a first embodiment, referring to fig. 1 to 3, the lift force test platform for the unmanned aerial vehicle provided by the invention comprises a vertical base 7, a scissors table top mechanism 3, an electronic scale 5, a fixed support 4 and a control system 1.
The scissors table top mechanism 3 comprises an upper layer platform 31, a lower layer platform 32 and two pairs of cross rods 33, each pair of cross rods 33 comprises two rods, the middle parts of the two rods are movably hinged through a pin shaft 71, the two rods of each cross rod 33 can rotate around the pin shaft 71 in the middle part of the cross rod, the two pairs of cross rods 33 are arranged in parallel and at intervals, the lower end surface of the upper layer platform 31 is provided with two parallel and spaced upper sliding grooves 310, the upper end surface of the lower layer platform 32 is correspondingly provided with two parallel and spaced lower sliding grooves 320, the upper ends of the cross rods 33 are embedded into the upper sliding grooves 310, the lower ends of the cross rods 33 are embedded into the lower sliding grooves 320, the upper ends of the cross rods 33 can freely slide along the length direction of the upper sliding grooves 310, and the lower ends of the cross rods 33 can freely slide along the.
The two vertical bases 7 are arranged, the two vertical bases 7 are positioned at two sides of the table-board mechanism of the scissors, the pin shaft 71 at the middle part of the cross rod 33 is supported by the vertical bases 7,
the lower end face of the lower-layer platform 32 is pressed on a scale pan of the electronic scale 2, the electronic scale 2 can continuously record data, and the electronic scale 2 is electrically connected with the control system 1 and records the pressure of the electronic scale. When the unmanned aerial vehicle takes off to drive the fixed support 4 and the upper platform 31 to move upwards, the two rods of the cross rod 33 rotate around the pin shaft 71 in the middle of the two rods, the upper ends of the two rods of the cross rod 33 slide along the length direction of the upper chute 310 to be close to each other, the lower ends of the two rods of the cross rod 33 slide along the length direction of the lower chute 320 to be close to each other, the upper platform 31 and the lower platform 32 are self-balanced by taking the center of the cross rod 33 as a fulcrum, and the lift force of the unmanned aerial vehicle 6 is directly reflected as the pressure acting on the electronic scale 2.
Fixed bolster 4 is installed at the up end of upper platform 31, and the fixed bolster is used for 4 to be connected with unmanned aerial vehicle 6.
The pin 71 is a stud bolt. The stud comprises a polished rod portion in the middle and threaded portions located at two ends of the polished rod portion, the polished rod portion of the stud is inserted into the cross rod 33, and the threaded portions at two ends of the stud are sleeved with nuts to limit the cross rod 33.
The weight of the upper-layer platform 31 and the lower-layer platform 32 of the scissors table-board mechanism is equal, the upper-layer platform 31 and the lower-layer platform 32 use the center of the cross rod 33 as a fulcrum for self balancing, and the lower-layer platform 32 is provided with a balancing weight 5. The weight of the balancing weight can be adjusted by increasing or decreasing the weight according to actual conditions.
The center of the upper platform 31 of the scissors table-board mechanism is provided with a threaded hole, and the center of the fixed support 4 is connected with the upper platform 31 through a bolt. The fixing bracket 4 includes an octagonal frame 41, and a connecting rod 42 extending outward from the center of the frame 41 to its apex. Unmanned aerial vehicle 6 passes through the fixed band subassembly and installs on fixed bolster 4.
The fastening band assembly includes a fastening band 101, a band tightener 103, a bolt, and a nut. The inboard one end of fixed band 101 is passed through the bolt and the nut is fixed on connecting rod 42, and unmanned aerial vehicle's fuselage is walked around and is compressed tightly unmanned aerial vehicle on fixed bolster 4 in the middle part of fixed band 101, and the locking of taking the ware 103 through tightening the area in fixed band 101 outside one end, and tightening the area ware 103 is fixed on connecting rod 42 through the bolt and the nut.
Before testing, the weight of the whole unmanned aerial vehicle and the weight of the fixing support 4, the fixing belt 101, the belt tightener 103 and other components are measured to determine the weight of the balancing weight 5, and when the weight of the balancing weight 5 is equal to the total weight of the fixing support 4 and the fixing belt components, the test object is the net lift force of the unmanned aerial vehicle; when the weight of balancing weight 5 and unmanned aerial vehicle, fixed bolster 4 and fixed band subassembly total weight are equal, the test object is unmanned aerial vehicle total lift this moment.
During the test, start unmanned aerial vehicle, unmanned aerial vehicle's lift drives fixed band subassembly, fixed bolster 4 and upper platform 31 rebound, and upper platform 31 and lower floor's platform 32 use the cross bar 33 center as the fulcrum self-balancing, and unmanned aerial vehicle's lift will directly embody the pressure that is used in on the electronic scale 2. The lift force of the unmanned aerial vehicle is controlled through the unmanned aerial vehicle controller, the lift force of the unmanned aerial vehicle is kept for a period of time when reaching the maximum value, and the maximum lift force of the unmanned aerial vehicle can be determined through data recorded by the control system 1.
The above description is only a preferred embodiment of the present invention, and for those skilled in the art, the present invention should not be limited by the description of the present invention, which should be interpreted as a limitation.
Claims (7)
1. An unmanned aerial vehicle lift test platform, its characterized in that includes:
the scissors table-board mechanism comprises an upper layer platform, a lower layer platform and two pairs of cross rods, wherein each pair of cross rods comprises two rods, the middle parts of the two rods are movably hinged through a pin shaft, the two pairs of cross rods are arranged in parallel and at intervals, the lower end surface of the upper layer platform is provided with two parallel and spaced upper sliding grooves, the upper end surface of the lower layer platform is correspondingly provided with two parallel and spaced lower sliding grooves, the upper ends of the cross rods are embedded into the upper sliding grooves, the lower ends of the cross rods are embedded into the lower sliding grooves, the upper ends of the cross rods can freely slide along the length direction of the upper sliding grooves, and the lower ends of the cross rods can freely slide along the length direction of the lower sliding grooves;
the two vertical bases are positioned on two sides of the scissors table-board mechanism, and a pin shaft in the middle of the cross rod is supported by the vertical bases;
the counterweight block is arranged on the upper end surface of the lower-layer platform;
the lower end face of the lower layer platform is pressed on a scale pan of the electronic scale;
the electronic scale is electrically connected with the control system; and
a fixed bolster, the fixed bolster sets up the up end of upper platform, the fixed bolster be used for with unmanned aerial vehicle connects.
2. The unmanned aerial vehicle lift test platform of claim 1, wherein the upper platform and the lower platform are of equal weight.
3. The unmanned aerial vehicle lift test platform of claim 1, wherein the counterweight weight is adjusted by adding or subtracting weights.
4. The unmanned aerial vehicle lift test platform of claim 1, wherein the counterweight is connected to the lower deck platform by bolts.
5. The unmanned aerial vehicle lift test platform of claim 1, wherein the fixed support comprises an octagonal frame and a connecting rod extending outward from a center of the frame to an apex thereof.
6. The unmanned aerial vehicle lift test platform of claim 5, further comprising a fixing strap assembly for mounting the unmanned aerial vehicle on the fixing support, wherein the fixing strap assembly comprises a fixing strap and a tightening device, one end of the inner side of the fixing strap is fixed on the connecting rod through a bolt and a nut, the middle of the fixing strap compresses the unmanned aerial vehicle on the fixing support, one end of the outer side of the fixing strap is locked through the tightening device, and the tightening device is fixed on the connecting rod through a bolt and a nut.
7. The unmanned aerial vehicle lift test platform of any one of claims 1-6, wherein the pin is a stud bolt, the stud bolt comprises a polished rod portion in the middle and threaded portions at two ends of the polished rod portion, the polished rod portion of the stud bolt is inserted into the cross bar, and the threaded portions at two ends of the stud bolt are sleeved with nuts for limiting the cross bar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010044706.3A CN111086652A (en) | 2020-01-15 | 2020-01-15 | Unmanned aerial vehicle lift test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010044706.3A CN111086652A (en) | 2020-01-15 | 2020-01-15 | Unmanned aerial vehicle lift test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN111086652A true CN111086652A (en) | 2020-05-01 |
Family
ID=70399227
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010044706.3A Pending CN111086652A (en) | 2020-01-15 | 2020-01-15 | Unmanned aerial vehicle lift test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111086652A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112478198A (en) * | 2020-12-22 | 2021-03-12 | 东北农业大学 | Multi-rotor unmanned aerial vehicle motor lift force test device and test method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101853623B1 (en) * | 2017-08-21 | 2018-06-08 | (주)에프디크리에이트 | Testing bed for drone |
| CN109229421A (en) * | 2018-09-25 | 2019-01-18 | 昆明理工大学 | A kind of unmanned plane power performance test macro and method |
| CN110116821A (en) * | 2019-05-24 | 2019-08-13 | 农业农村部南京农业机械化研究所 | A kind of test equipment and method for quickly testing electronic multi-rotor unmanned aerial vehicle maximum take-off weight |
| CN211844952U (en) * | 2020-01-15 | 2020-11-03 | 广州海关技术中心 | Unmanned aerial vehicle lift test platform |
-
2020
- 2020-01-15 CN CN202010044706.3A patent/CN111086652A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101853623B1 (en) * | 2017-08-21 | 2018-06-08 | (주)에프디크리에이트 | Testing bed for drone |
| CN109229421A (en) * | 2018-09-25 | 2019-01-18 | 昆明理工大学 | A kind of unmanned plane power performance test macro and method |
| CN110116821A (en) * | 2019-05-24 | 2019-08-13 | 农业农村部南京农业机械化研究所 | A kind of test equipment and method for quickly testing electronic multi-rotor unmanned aerial vehicle maximum take-off weight |
| CN211844952U (en) * | 2020-01-15 | 2020-11-03 | 广州海关技术中心 | Unmanned aerial vehicle lift test platform |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112478198A (en) * | 2020-12-22 | 2021-03-12 | 东北农业大学 | Multi-rotor unmanned aerial vehicle motor lift force test device and test method |
| CN112478198B (en) * | 2020-12-22 | 2023-06-13 | 东北农业大学 | Multi-rotor unmanned aerial vehicle motor lift force test device and test method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103353403B (en) | Six-dimensional parallel-connection test bench for automotive suspension test | |
| CN106052931B (en) | Multi-rope hoisting steel wire rope tension self-balancing test bed and method | |
| EP3255404A1 (en) | System and method for ground vibration testing and weight and balance measurement | |
| CN211844952U (en) | Unmanned aerial vehicle lift test platform | |
| US20150247770A1 (en) | Landing load monitor for carrier-based aircraft | |
| CN110243564A (en) | Arrester hook hanging cable shock loading test and experiment device and test method | |
| CN111086652A (en) | Unmanned aerial vehicle lift test platform | |
| CN113483978B (en) | Free boundary simulation unit and simulation system for aircraft modal test | |
| CN216581098U (en) | Landing test device for undercarriage | |
| US3906779A (en) | Shock-absorber test method and apparatus | |
| CN107607281B (en) | A kind of POS machine falls damage measure device and its test method | |
| CN211033073U (en) | Ground test platform for small-sized vertical take-off and landing fixed-wing unmanned aerial vehicle | |
| CN101915633B (en) | Device for detecting pulling-out force of balance weight of automobile wheels | |
| CN211283585U (en) | Height adjusting mechanism and vehicle chassis checking fixture | |
| CN108956176A (en) | A kind of high-precision hydraulic damper and the dynamic and static test platform of actuator | |
| CN218382145U (en) | Wing static load strength test frame | |
| CN105300709B (en) | Without bar wheel holding aircraft tractor detection simulation test car | |
| RU2746107C1 (en) | Disassembly device | |
| CN104316329A (en) | Apparatus for detecting braking performance of damaged vehicle | |
| KR101638455B1 (en) | Test device for shock absorbers | |
| CN215893944U (en) | Aircraft modal test free boundary simulation unit and simulation system | |
| CN116106134A (en) | Multi-station creep tensile testing machine and control method thereof | |
| US4479560A (en) | Portable pallet weighing apparatus | |
| CN211855845U (en) | Aviation piston engine test bed | |
| CN214040676U (en) | Rotor unmanned aerial vehicle static force loading test platform |
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 |