CN108106851B - Small unmanned aerial vehicle engine push-pull force test acquisition test system - Google Patents
Small unmanned aerial vehicle engine push-pull force test acquisition test system Download PDFInfo
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- CN108106851B CN108106851B CN201810157148.4A CN201810157148A CN108106851B CN 108106851 B CN108106851 B CN 108106851B CN 201810157148 A CN201810157148 A CN 201810157148A CN 108106851 B CN108106851 B CN 108106851B
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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
- G01M15/00—Testing of engines
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0033—Force sensors associated with force applying means applying a pulling force
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L5/00—Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
- G01L5/0028—Force sensors associated with force applying means
- G01L5/0038—Force sensors associated with force applying means applying a pushing force
Abstract
The invention discloses a small unmanned aerial vehicle engine push-pull force test acquisition test system, which comprises a test platform and a data acquisition system; the test platform comprises a push-pull force scale, a guide rod rear connecting plate, a guide rod front connecting plate, a guide rod base, an engine connecting plate, a vibration damper and a test table board. The data acquisition system comprises a data receiver, a data processing module, a tachometer, an ammeter, a power supply, a high-voltage device, a signal receiver, a first conversion interface, an engine voltage stabilizing module, a second conversion interface, a lighter, an oil tank and an oil meter. According to the test acquisition test system, the test platform avoids the reason of test errors caused by structural design, so that test data is accurate, and the precision meets the design requirements. The invention is additionally provided with a test system with other values, and all the tested data are input into the data processing module through the data receiver, thereby greatly facilitating the test process and the recording mode.
Description
Technical Field
The invention relates to an engine push-pull force test and acquisition system, in particular to a small unmanned aerial vehicle engine push-pull force test and acquisition test system.
Background
The engine push-pull force can be measured through a ground test in the process of estimating the push-pull force of the engine in the air flight of the unmanned aerial vehicle, and the reasonable design and manufacture of the ground test platform are important for the engine push-pull force test. Only if the ground test platform is designed and manufactured, and the vibration reduction measures are complete, the authenticity of a test result can be ensured when the ground engine push-pull force test is carried out, and then test data support is provided for the thrust efficiency prediction of the unmanned aerial vehicle engine in air flight.
At present most unmanned aerial vehicle engine test bench all is furnished with automatic test and equips, and the test platform of hardware is the most basic test guarantee platform, and only test structure reasonable in design, the damping measure is appropriate, and the final test error who brings reduces, and the test result just can be accurate. For the test of large aircraft engines, corresponding tests and tests can be undertaken by large enterprises generally, and complete engine test benches are equipped in domestic aviation enterprises for specially producing engines, such as dawn engines and other enterprises, so that corresponding test data can be automatically extracted after the engines work on the ground. Because the design of the equipment system is complex, the whole set of system is high in design and manufacturing cost, and common small-sized enterprises are difficult to bear corresponding cost, so that some simple equipment can be used for replacing the equipment. Some small-size aviation enterprises, especially in recent years along with unmanned aerial vehicle in the domestic rapid development, the enterprise of a batch of special development unmanned aerial vehicle appears in the country, and these enterprises are when carrying out unmanned aerial vehicle engine ground test, may use simpler test platform, for example one end installation pulling force is called on test engine's mount, through mobilizable dull and stereotyped, the engine is connected to the other end. Thus, after the engine rotates, the movable flat plate is pulled, and then the pulling scale reads the magnitude of the pulling force. The testing platform is too simple in structure, the pulling direction of the engine and the connecting pulling head of the scale cannot be ensured to be coaxial, and meanwhile, due to the friction between the moving plate and the lower surface, the testing error is increased, and further the error of the engine push-pull force testing is caused.
Disclosure of Invention
The invention aims to provide a small unmanned aerial vehicle engine push-pull force test acquisition testing system, which can ensure that the developed small unmanned aerial vehicle engine push-pull force testing system has accurate test data.
In order to solve the technical problem, the invention aims to realize that:
the invention relates to a small unmanned aerial vehicle engine push-pull force test acquisition test system, which comprises a test platform and a data acquisition system; wherein the content of the first and second substances,
the test platform comprises a push-pull force scale, a guide rod rear connecting plate, a guide rod front connecting plate, a guide rod base, an engine connecting plate, a vibration damper and a test table board; the push-pull scale is fixedly connected with the test table board, and a mandril is arranged on the push-pull scale; a guide rod is fixed between the guide rod rear connecting plate and the guide rod front connecting plate, and the guide rod penetrates through a guide rod base fixed with the test table top; the engine connecting plate is fixedly connected with the guide rod front connecting plate, and a damping device is arranged between the engine connecting plate and the guide rod front connecting plate; the push-pull force scale connecting hole arranged on the ejector rod and the guide rod rear connecting plate is coaxial;
the data acquisition system comprises a data receiver, a data processing module, a tachometer, an ammeter, a power supply, a high-voltage device, a signal receiver, a first conversion interface, an engine voltage stabilizing module, a second conversion interface, a lighter, an oil tank and an oil meter;
one end of the data receiver is connected with the data processing module, and the other end of the data receiver is connected with the push-pull force scale and the tachometer; the igniter is connected with the tachometer and the engine; an ammeter is connected between the power supply and the voltage regulator; the voltage regulator is also connected with the first conversion interface, the signal receiver and the engine voltage stabilization module; the first conversion interface is also connected with an oil meter and a tachometer; the signal receiver is connected with the engine; the engine voltage stabilizing module is connected with the engine through a second conversion interface; the oil tank is connected with the fuel gauge and the engine and provides fuel for the engine;
as a further explanation of the scheme, the push-pull force scale is fixedly connected with the test table top through the connecting block.
As a further explanation of the above solution, the damping device is a damping pad.
As a further explanation of the above scheme, a flange roller bearing is arranged between the guide rod and the guide rod base; the guide rod base is embedded in the flange roller bearing.
As a further explanation of the scheme, the test table top is fixedly connected with the test table supporting legs through connecting pipes, and the test table supporting legs are provided with stop casters.
As a further explanation of the scheme, the engine connecting plate is provided with four engine fixing holes.
As a further explanation of the above scheme, the engine fixing hole is a strip-shaped hole.
The invention has the beneficial effects that: the invention relates to a small unmanned aerial vehicle engine push-pull force test acquisition test system which comprises a test platform and a data acquisition system. The test platform completely considers the factors causing the test errors of the engine push-pull force, and avoids the reasons of the test errors caused by structural design as much as possible, so that the developed small unmanned aerial vehicle engine push-pull force test system has accurate test data, and the precision meets the design requirements. Meanwhile, the invention also arranges a data acquisition system connected with the test platform, adds a test system with other values, and inputs all the measured data into the data processing module through the data receiver, thus greatly facilitating the test process and the recording mode.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a front view of the test platform;
FIG. 3 is a top view of the test platform;
FIG. 4 is a schematic view of the construction of the connector block;
FIG. 5 is a schematic view of a rear connecting plate of the guide bar;
FIG. 6 is a schematic view of a guide bar construction;
FIG. 7 is a schematic view of a guide bar base construction;
FIG. 8 is a schematic diagram of a guide rod front connecting plate structure;
fig. 9 is a schematic diagram of an engine connecting plate structure.
The designations in the figures illustrate the following: 1-connecting blocks; 101-a connecting block mounting hole; 102-a push-pull force balance mounting hole; 2-weighing by pushing and pulling force; 201-a top rod; 3-connecting the rear guide rod plate; 301-guide rod rear fixing hole; 302-a connecting hole is called by push-pull force; 4-a guide rod; 401-a threaded hole; 5-guide rod base; 501-base mounting holes; 502-flanged roller bearing; 503-set screws; 6-connecting the front guide rod plate; 601-guide rod front fixing hole; 602-a first fixation hole; 7-a vibration damping device; 8-an engine connection plate; 801-second fixation hole; 802-engine fixing hole; 9-test table; 10-connecting pipe; 11-a stand leg; 12-stop casters; 13-a data receiver; 14-a data processing module; 15-a tachometer; 16-an ammeter; 17-a power supply; 18-a voltage regulator; 19-a signal receiver; 20-a first conversion interface; 21-an engine voltage stabilizing module; 22-a second conversion interface; 23-making a lighter; 24-a fuel tank; 25-oil scale; 26-engine.
Detailed Description
The invention is further described with reference to the following figures and specific examples.
Examples
The present embodiment will be described in detail with reference to fig. 1 to 9. The small unmanned aerial vehicle engine push-pull force test acquisition test system related to the embodiment comprises a test platform and a data acquisition system.
In this embodiment, the test platform includes a connection block 1, a push-pull balance 2, a guide rod rear connection plate 3, a guide rod 4, a guide rod base 5, a guide rod front connection plate 6, a vibration damping device 7, an engine connection plate 8, and a test table 9.
The push-pull balance 2 is fixedly connected with the test table board 9 through a connecting block 1, and one end of the push-pull balance 2 is provided with a mandril 201. The connecting block 1 is made of an aluminum block, and the material is convenient to process and connect. Referring to fig. 3, the connecting block 1 is provided with a connecting block mounting hole 101 and a push-pull force balance mounting hole 102. The bolt passes connecting block mounting hole 101 with connecting block 1 and test table top 9 looks fixed connection, has guaranteed the stability of connecting, simultaneously, still is provided with adjustable groove on the test table top 9, the position control of the connecting block 1 of being convenient for. The four push-pull balance mounting holes 102 penetrate through the whole connecting block 1, and are convenient to be connected with the push-pull balance 2.
The guide rod rear connecting plate 3 is provided with four guide rod rear fixing holes 301 and a push-pull balance connecting hole 302, and can be connected with the guide rod 4 through the guide rod rear fixing holes 301 and connected with a push rod 201 arranged on the push-pull balance 2 through the push-pull balance connecting hole 302. The guide rod rear fixing hole 301 is a conical countersunk hole. The push rod 201 is coaxial with the center of the connecting hole 302 of the push-pull balance, so that the stress central axis of the push-pull balance 2 is coaxial with the central axis of the connecting hole, the stress direction is on the same axis, and the measurement is more accurate.
Threaded holes 401 with the depth of M5 are drilled in two ends of the guide rod 4, and the threaded holes are connected with the guide rod rear connecting plate 3 and the guide rod front connecting plate 6 through conical countersunk head screws, so that the guide rod rear connecting plate 3 and the guide rod front connecting plate 6 are parallel after connection. Meanwhile, the surface of the guide rod 4 is subjected to high-hardness treatment, so that the rigidity of the guide rod 4 is ensured to be higher under the action of small vibration load, and the radial deformation of the guide rod 4 during corresponding movement is reduced.
The guide rod base 5 is embedded with a flange roller bearing 502 and is provided with a base mounting hole 501. Bolts pass through the base mounting holes 501 to fix the guide rod base 5 and the test table top 9. In the fixed connection, the direction of the base mounting hole 501 is ensured to be the same as the connecting hole of the connecting block 1, so that the push-pull force balance connecting hole 302 arranged in the connecting plate 3 after the rear guide rod is mounted is coaxial with the center of the ejector rod 201. In this embodiment, the maximum travel of the flanged roller bearing 502 is selected to be 60 mm.
The flange roller bearing 502 is fixed to the guide bar base 5 by four fixing screws 503. The guide rod 4 passes through the flange roller bearing 502, and the flange roller bearing 502 is provided to reduce friction when the guide rod 4 moves longitudinally in the flange roller bearing 502. The flange roller bearings 502 are arranged in parallel, and after the guide rods 4 penetrate through the flange roller bearings 502 and are fixedly connected with the guide rod front connecting plate 6 and the guide rod rear connecting plate 3, the four guide rods 4 are synchronous and consistent when the flange roller bearings 502 move.
Because the surface of the guide rod 4 is subjected to high hardness treatment, the radial deformation of the guide rod 4 is reduced, and the phenomenon that the guide rod 4 is clamped on the flange roller bearing 502 due to the radial deformation of the guide rod 4 can be reduced. In this embodiment, four flange roller bearings 502 are embedded and mounted on the guide bar base 5. Each flange roller bearing 502 is fixedly connected with the guide rod front connecting plate 6 and the guide rod rear connecting plate 3 through a guide rod 4.
The guide rod front connecting plate 6 is connected with the guide rod rear connecting plate 6 through the guide rod 4. Four guide rod front fixing holes 601 and four first fixing holes 602 are arranged on the guide rod front connecting plate 6, the guide rod front fixing holes 601 are positioned at an included angle of 45 degrees with the horizontal and vertical directions, and the first fixing holes 602 are positioned at the horizontal or vertical positions. The guide rod front fixing hole 601 is also a conical countersunk hole, and the guide rod front connecting plate 6 is fixed with the guide rod 4 through a conical countersunk screw.
The guide rod front connecting plate 6 is fixedly connected with the engine connecting plate 8 through bolts, a vibration damping device 7 is arranged between the engine connecting plate 8 and the guide rod front connecting plate 6, and the vibration damping device 7 is a vibration damping pad in the embodiment and is preferably made of rubber. The vibration damping pad is sleeved outside the stud. After the guide rod front connecting plate 6 and the engine connecting plate 8 are fixed, the vibration damping pad lower guide rod front connecting plate 6 is abutted to the engine connecting plate 8, so that the vibration damping effect can be better achieved, the vibration load transmitted to the guide rod 4 is reduced, and the influence on the motion of the guide rod 4 and the test structure of the push-pull force scale 2 is further reduced.
The engine connection plate 8 is provided with an engine fixing hole 802 and a second fixing hole 801. The second fixing hole 801 and the guide rod front connecting plate 6 are also fixed through a conical countersunk head screw. The connecting bolts of the engine connecting plate 8 and the leader connecting plate 6 pass through the first fixing hole 602 and the second fixing hole 801. The number of the engine fixing holes 802 is four, and the engine fixing holes are strip-shaped holes. The engine fixing holes 802 are obliquely arranged and arranged at an included angle of 45 degrees with the horizontal direction and the vertical direction. The whole fixed position that starts can be adjusted in the setting of engine fixed orifices 802 bar, conveniently connects the unmanned aerial vehicle engine of various models.
The test table top 9 is fixedly connected with the test table supporting legs 11 through connecting pipes 10, and the test table supporting legs 11 are provided with stop casters 12. The positioning of the stop casters 12 facilitates movement of the entire test system, and the stop casters 12 are made of rubber to reduce the transmission of vibration loads to the entire system.
The data acquisition system comprises a data receiver 13, a data processing module 14, a tachometer 15, an ammeter 16, a power supply 17, a voltage regulator 18, a signal receiver 19, a first conversion interface 20, an engine voltage stabilizing module 21, a second conversion interface 22, a lighter 23, an oil tank 24 and an oil meter 25.
One end of the data receiver 13 is connected with the data processing module 14, and the other end is connected with the push-pull force scale 2 and the tachometer 15. The data receiver 13 can receive the data in the push-pull scale 2 and the tachometer 15 and transmit the received data to the data processing module 14, in this embodiment, the data processing module 14 is a computer, and can count and display the transmitted data, and the computer is used for counting and displaying the data transmitted by the data receiving module according to the prior art.
The sparker 23 is connected to the tachometer 15 and the engine 26. When the engine 26 is operating, the tachometer 15 communicates the measured speed of the engine 26 to the data receiving module.
The engine 26 is connected with the signal receiver 19, the signal receiver 19 is connected with the voltage regulator 18, and the ammeter 16 is connected between the power supply 17 and the voltage regulator 18. When the power supply 17 is turned on, the voltage is adjusted by the voltage regulator 18, and the motor 26 is turned on after the signal receiver 19 receives the signal. The first conversion interface 20 is also connected with an oil gauge 25 and a tachometer 15. In this embodiment, the power source 17 is a battery with an output voltage of 25V, and can supply power to a spark plug in the engine 26, so that the spark plug can be activated under the action of an igniter.
The engine stabilization module 21 is connected to the engine 26 via a second switching interface 22. The engine stabilization module 21 is also connected to the pressure regulator 18. When the engine 26 works to generate electricity, the three-way alternating current of the generator is converted into direct current with stable voltage through the conversion of the engine voltage stabilizing module 21 and the voltage regulator 18. Ammeter 16 may detect the magnitude of current produced by motor 26 as it passes through ammeter 16.
The engine voltage stabilizing module 21 is connected with the voltage regulator 18, and the voltage regulator 18 is connected with power consumption instruments such as the fuel gauge 25 and the tachometer 15 through the first conversion interface 20. When the engine 26 is operating, power may be supplied to the meter and tachometer 15.
The fuel tank 24 is connected to a fuel gauge 25 and an engine 26, and supplies fuel to the engine 26. The data measured by the fuel gauge 25 are transmitted to the data processing module 14 through the data receiver 13, and are counted and displayed.
The work of the small unmanned aerial vehicle engine 26 push-pull force test and acquisition test system comprises the push-pull force and pull force test and data collection of the engine 26.
After the components of the elements involved in the test platform and the data collection system are connected according to the connection relation, the engine 26 of the small unmanned aerial vehicle is fixed with the connecting plate of the engine 26.
When the tension test of the unmanned aerial vehicle engine 26 is carried out, the ejector rod 21 arranged on the push-pull balance 2 is connected with the tension rod, and then the ejector rod is connected with the guide rod rear connecting plate 3 through the tension rod hook. After connection, after the engine 26 drives the propeller (positive propeller) to rotate, the engine 26 drives the guide rod 4 to move forward and drives the tension rod to move forward due to forward tension generated by the propeller, and the force measured by the push-pull force scale 2 is the tension of the engine 26 of the unmanned aerial vehicle. One end of the tension rod is fixed with the ejector rod 21, and the other end is connected with the guide rod rear connecting plate 3 through a hook. At this time, in the data collection system, the pulling force value tested by the push-pull force scale 2, the rotating speed value of the engine 26 measured by the tachometer 15, the oil quantity value measured by the fuel gauge 25, and the current value measured by the ammeter 16 are transmitted to the data processing module 14 through the data receiver 13, and are counted and displayed in the data processing module 14.
When the thrust test of the unmanned aerial vehicle engine 26 is carried out, the ejector rod 21 arranged on the push-pull scale 2 is connected with the thrust rod, and then the thrust rod is tightly pushed against the rear connecting plate 3 of the guide rod. When connected, the engine 26 rotates to rotate the propeller (counter-propeller), and then the propeller generates backward thrust. At this time, the engine 26 pushes the guide rod 4 to move backwards, so as to drive the thrust rod to move backwards, and the force measured by the push-pull force scale 2 is the thrust of the engine 26 of the unmanned aerial vehicle. The thrust rod is a rigid rod and is fixedly connected with the ejector rod 21 and the guide rod rear connecting plate 3. At this time, in the data collection system, the pulling and pushing force value tested by the pulling and pushing force scale 2, the rotating speed value of the engine 26 measured by the rotating speed meter 15, the oil quantity value measured by the oil quantity meter 25, and the current value measured by the current meter 16 are transmitted to the data processing module 14 through the data receiver 13, and are counted and displayed in the data processing module 14.
Through practical tests of the invention, when testing the DLE60, DLE60W and DLE40 systems, engines of various types can be conveniently connected through adjusting the engine fixing holes of the engine connecting plate. Meanwhile, the sizes of different propellers are tested by changing the sizes of different propellers of the engine rotating shaft. The test platform is relatively stable in the process of testing the push-pull force of the small engine, and the tested value is compared through tests and accords with the actual situation, so that the test platform is reasonable in design and obvious in vibration damping effect, and meets the requirement of small enterprises for carrying out the push-pull force test of the small engine.
It should be understood that numerous modifications and variations could be devised by those skilled in the art in light of the present teachings without departing from the inventive concepts. Therefore, the technical solutions available to those skilled in the art through logic analysis, reasoning and limited experiments based on the prior art according to the concept of the present invention should be within the scope of protection defined by the claims.
Claims (3)
1. A small unmanned aerial vehicle engine push-pull force test acquisition test system is characterized by comprising a test platform and a data acquisition system; wherein the content of the first and second substances,
the test platform comprises a push-pull force scale, a guide rod rear connecting plate, a guide rod front connecting plate, a guide rod base, an engine connecting plate, a vibration damper and a test table board; the push-pull scale is fixedly connected with the test table board, and a mandril is arranged on the push-pull scale; a guide rod is fixed between the guide rod rear connecting plate and the guide rod front connecting plate, and the guide rod penetrates through a guide rod base fixed with the test table top; the engine connecting plate is fixedly connected with the guide rod front connecting plate, and a damping device is arranged between the engine connecting plate and the guide rod front connecting plate; the push-pull force scale connecting hole arranged on the ejector rod and the guide rod rear connecting plate is coaxial;
the test table top is fixedly connected with the test table supporting leg through a connecting pipe, and the test table supporting leg is provided with a stop caster;
the push-pull balance is fixedly connected with the test table board through a connecting block, and a connecting block mounting hole and a push-pull balance mounting hole are formed in the connecting block; the bolt penetrates through the connecting block mounting hole to fixedly connect the connecting block with the test table board; the test table board is also provided with an adjustable groove, so that the position of the connecting block can be conveniently adjusted;
the data acquisition system comprises a data receiver, a data processing module, a tachometer, an ammeter, a power supply, a high-voltage device, a signal receiver, a first conversion interface, an engine voltage stabilizing module, a second conversion interface, a lighter, an oil tank and an oil meter;
one end of the data receiver is connected with the data processing module, and the other end of the data receiver is connected with the push-pull force scale and the tachometer; the igniter is connected with the tachometer and the engine; an ammeter is connected between the power supply and the voltage regulator; the voltage regulator is also connected with the first conversion interface, the signal receiver and the engine voltage stabilization module; the first conversion interface is also connected with an oil meter and a tachometer; the signal receiver is connected with the engine; the engine voltage stabilizing module is connected with the engine through a second conversion interface; the oil tank is connected with the fuel gauge and the engine and provides fuel for the engine;
the engine connecting plate is provided with four engine fixing holes; the engine fixing hole is a strip-shaped hole; the engine fixing holes are obliquely arranged and form an included angle of 45 degrees with the horizontal direction and the vertical direction;
when the tension is tested, a top rod arranged on the push-pull balance is connected with a tension rod, and then the top rod is connected with the guide rod rear connecting plate through a tension rod hook;
when the thrust is tested, the push-pull force scale is provided with a top rod connected with the thrust rod, and then the thrust rod is tightly propped against the rear connecting plate of the guide rod.
2. The system of claim 1, wherein the vibration damping device is a vibration damping pad.
3. The small unmanned aerial vehicle engine push-pull force test acquisition testing system of claim 1, wherein a flange roller bearing is arranged between the guide rod and the guide rod base; the guide rod base is embedded in the flange roller bearing.
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| CN108507790A (en) * | 2018-06-11 | 2018-09-07 | 中国水利水电科学研究院 | A kind of small-sized electric unmanned vehicle engine testboard bay |
| CN109269807A (en) * | 2018-09-07 | 2019-01-25 | 桂林航天工业学院 | Unmanned vehicle engine merges system |
| CN111380690B (en) * | 2020-04-17 | 2022-03-01 | 中国人民解放军空军工程大学航空机务士官学校 | Piston engine output thrust measurer and measuring method |
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