CN114136637B - Ground test bed system of aviation piston engine - Google Patents
Ground test bed system of aviation piston engine Download PDFInfo
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- CN114136637B CN114136637B CN202111595079.3A CN202111595079A CN114136637B CN 114136637 B CN114136637 B CN 114136637B CN 202111595079 A CN202111595079 A CN 202111595079A CN 114136637 B CN114136637 B CN 114136637B
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- 238000012360 testing method Methods 0.000 title claims abstract description 39
- 230000003139 buffering effect Effects 0.000 claims abstract description 20
- 238000001816 cooling Methods 0.000 claims description 13
- 230000007246 mechanism Effects 0.000 claims description 10
- 239000000446 fuel Substances 0.000 claims description 3
- 230000035939 shock Effects 0.000 abstract description 3
- 230000009471 action Effects 0.000 description 19
- 230000000694 effects Effects 0.000 description 14
- 238000001514 detection method Methods 0.000 description 10
- 238000009434 installation Methods 0.000 description 7
- 238000013016 damping Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 6
- 230000009467 reduction Effects 0.000 description 5
- 230000008569 process Effects 0.000 description 3
- 239000003381 stabilizer Substances 0.000 description 3
- 230000033228 biological regulation Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000004075 alteration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 230000001276 controlling effect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000003912 environmental pollution Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
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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
- G01M15/02—Details or accessories of testing apparatus
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Abstract
The application belongs to the technical field of test bed, in particular to an aero-piston engine ground test bed system, which comprises a base, wherein a baffle is arranged at the top of the base, a front support and a rear support are respectively arranged at the top of the base, a cross beam is arranged between the front support and the rear support, the front support is positioned at one end of the rear support far away from the baffle, a buffer corrugated pipe is arranged at the top of the rear support, an engine is arranged at the top of the buffer corrugated pipe, a connecting belt is arranged at the top of the engine, and a center console is arranged at one side of the baffle far away from the engine; the air inlet has been seted up to the one end that the baffle was kept away from to the rear bracket, the other end of rear bracket is equipped with the tie-beam, the other end and the baffle fixed connection of tie-beam, this test bed not only can improve the shock attenuation buffering effect to the engine, adapts to the various airspeed of engine, guarantees the stability of engine, avoids base and its resonance when the engine shakes simultaneously, improves the travelling comfort of operation and the durability of device.
Description
Technical Field
The application belongs to the technical field of test bed, and particularly relates to a ground test bed system of an aviation piston engine.
Background
The aeroengine is a thermodynamic device with high technical difficulty, complex working conditions, harsh maintenance requirements and high development and use cost. The aircraft engine has a very complex structure, plays a vital role in the reliability, safety and performance of the operation of the aircraft, and in the life cycle of the aircraft engine, the aircraft engine is required to be tested regularly according to regulations to detect the quality of each performance of the engine in order to ensure the flight safety.
Chinese patent No. CN2020112581858 discloses a piston engine test stand with clutch for unmanned aerial vehicle and method thereof, which belongs to unmanned aerial vehicle field; comprises a frame body, an engine mounting plate, a starting motor servo control cabinet and a starting motor servo mechanism; the frame body is of a truss structure with unequal heights at two ends and is used for supporting the whole device; the starting motor servo control cabinet is arranged at the bottom of the frame body and remotely controls the starting motor servo mechanism through a cable and a control handle; the starting motor mounting plate is horizontally fixed at one end of the frame body, which is low, through a starting motor servo mechanism and is used for mounting a starting motor assembly; the engine mounting plate is horizontally fixed at one end of the frame body and is used for mounting a piston engine; the piston engine test bed is troublesome in test, poor in versatility and poor in stability.
Meanwhile, when the aviation piston engine is installed, the requirement on the positioning accuracy of the engine is high, the adaptability is poor, test run detection cannot be carried out on a plurality of aviation piston engines, the vibration of the aviation piston engines can influence the detection result in the test run process, a high-temperature environment can be generated when the engine is started, and the structure inside a test run bench can be damaged.
Meanwhile, the airspeed of the engine can be changed when the propeller is used for adjusting speed, so that the balance of the test bed is damaged, the test bed is mainly caused to topple backwards when the airspeed is accelerated, and the test bed is caused to topple forwards when the airspeed is too fast due to the fact that the front end of the piston engine is too heavy.
Disclosure of Invention
Aiming at the problems, the application provides the ground test bed system of the aviation piston engine, which not only can improve the damping and buffering effects on the engine, adapt to various airspeeds of the engine and ensure the stability of the engine, but also can avoid resonance between the base and the engine when the engine vibrates, thereby improving the operation comfort and durability.
In order to achieve the above purpose, the present application provides the following technical solutions: the ground test bed system of the aviation piston engine comprises a base, wherein a baffle is arranged at the top of the base, a front support and a rear support are respectively arranged at the top of the base, a cross beam is arranged between the front support and the rear support, the front support is positioned at one end, far away from the baffle, of the rear support, a buffer corrugated pipe is arranged at the top of the rear support, an engine is arranged at the top of the buffer corrugated pipe, a connecting belt is arranged at the top of the engine, and a center console is arranged at one side, far away from the engine, of the baffle;
the air inlet is formed in one end, far away from the baffle, of the rear support, a connecting beam is arranged at the other end of the rear support, the other end of the connecting beam is fixedly connected with the baffle, a first air channel is formed in the connecting beam, the other end of the air inlet is communicated with the first air channel through a first air valve, a first vertical air channel is formed in the baffle and is communicated with the first air channel, a lead weight is connected in the first vertical air channel in a sliding mode, the top of the lead weight is fixedly connected with the connecting belt, and a first air outlet is formed in one side, close to the engine, of the first vertical air channel;
the top of the air inlet is communicated with a second air passage, the second air passage is communicated with a buffer corrugated pipe, the bottom of the air inlet is provided with a third air passage through a second air valve, the bottom of the third air passage is provided with a spring, the bottom of the spring is provided with a sliding block, and the bottom of the sliding block penetrates through the base to be provided with a sucker; a fourth air passage is arranged in the cross beam, and the third air passage is communicated with the fourth air passage through a third air valve; the inside of the front bracket is provided with a second vertical air passage, the fourth air passage is communicated with the second vertical air passage, two sides of the second vertical air passage are provided with second air outlets, the inside of the second vertical air passage is connected with a traction block in a sliding manner, the top of the traction block is provided with a pull rope, and the top of the pull rope penetrates through the front bracket and is fixedly connected with the bottom of the engine;
when the airspeed of the engine is controlled to be reduced by the center console, the airflow reaching the first vertical air passage along the air inlet and the first air passage is reduced, and the lead weight drives the connecting belt to increase the tension on the top of the front end of the engine; when the airspeed of the engine is controlled to be increased by the center console, air flow reaches a third air passage along the air inlet, the sliding block stretches the spring and drives the sucker to be contacted with the ground, air flow reaches a second vertical air passage along the fourth air passage, the air flow drives the traction block to be downward, and the traction block drives the pull rope to increase the pulling force of the pull rope to the bottom of the front end of the engine.
Compared with the prior art, the application has the following beneficial effects:
1. the application solves the problem of detecting precision of the engine by arranging the base, the center console, the engine, the front bracket, the rear bracket, the screw propeller and other parts, places the engine on the top of the rear bracket, communicates each circuit of the center console with the engine, connects the connecting belt with the top of the engine, adjusts and controls each working state of the engine by means of the control component, and when the airspeed of the engine needs to be changed, only adjusts the pitch-changing mechanism by the control component, further adjusts the screw propeller speed regulator, changes the attack angle of the screw propeller, and can realize the adjustment of the airspeed of the engine, and simultaneously detects each performance data of the engine under the working state by means of sensors such as rotating speed, pressure, flow, current and the like, thereby improving the detecting result and ensuring the detecting precision.
2. According to the application, through the mutual matching of the components such as the first air passage, the second air passage, the first vertical air passage, the buffer corrugated pipe, the third air passage, the sucking disc, the fourth air passage, the second vertical air passage, the traction block and the like, the problem of engine stability during the change of the airspeed of the engine is solved, in normal use, the air flow generated by the rotation of the propeller reaches the second air passage along the air inlet, and is filled through the buffer corrugated pipe, so that the air flow has a damping and buffering effect, meanwhile, the redundant air flow reaches the first vertical air passage along the first air passage, wind force is applied to the bottom of the lead weight, the lead weight is stable under the action of the tension of the connecting belt and the wind force, and when the airspeed is reduced, the wind force at the bottom of the lead weight is reduced, and the lead weight drives the connecting belt to increase the tension of the top of the front end of the engine; when airspeed increases, unnecessary air current gets into the third air flue and drives the slider and move downwards, the slider drives sucking disc downwards and ground contact, unnecessary air current reaches the second along the fourth air flue and erects the air flue, and then drive the traction block and drive the stay cord downwards, the stay cord drives engine front end bottom downwards, the device can guarantee the stability of engine when airspeed increases or reduces to the engine well, not only possess fine shock attenuation buffering effect to the work of engine, can also protect the engine simultaneously, improve the security performance of engine, can also improve the cooling effect to the engine simultaneously, guarantee the durability of its work, improve the installation and dismantle efficiency, guarantee the stability of each part.
3. The application solves the stability control of the base and the engine by arranging the second air passage, the third air passage, the air inlet, the first air passage and other parts, when the engine vibrates, the air flow in the buffer corrugated pipe reaches the third air passage when the buffer corrugated pipe is extruded by the engine vibrating downwards, the air flow drives the sliding block and the sucker to move downwards, the sucker contacts with the ground to ensure the stability of the base, the air flow reaching the first air passage along the air inlet is reduced, the air flow in the first vertical air passage is reduced, the wind force born by the bottom of the lead weight is reduced, the lead weight is downwards and drives the connecting belt to increase the tension of the top of the front end of the engine, the stability of the engine is ensured when the engine vibrates, the device can ensure the stability of the engine when the engine shakes, and simultaneously, the flow direction of the air flow in the buffer corrugated pipe is used for effectively supporting and fixing the base, the resonance of the base along with the vibration of the engine is avoided, the operator and each part are damaged, the tensile force of the top of the engine caused by the connecting belt to the excessive downward moving distance of the engine is also improved, and the damage to the device is avoided.
Drawings
FIG. 1 is a schematic diagram of the structure of the present application;
FIG. 2 is a schematic front view of the present application;
FIG. 3 is a schematic view in partial cross-section from the left side of the present application;
FIG. 4 is an enlarged schematic view of FIG. 3 at A;
FIG. 5 is an enlarged schematic view of FIG. 3 at B;
FIG. 6 is an enlarged schematic view of FIG. 3 at C;
FIG. 7 is an enlarged schematic view of FIG. 3 at D;
fig. 8 is an enlarged schematic view of fig. 3 at E.
Reference numerals: 1. a base; 2. a baffle; 3. an observation window; 4. a front bracket; 5. a rear bracket; 6. a support beam; 7. a tripod; 8. a moving wheel; 9. a support leg; 10. an engine; 11. a propeller; 12. a riser; 13. a wire hole; 14. a connecting rod; 15. a connecting belt; 16. an air inlet; 17. a first airway; 18. a second airway; 19. a buffer bellows; 20. a first air valve; 21. a first air outlet; 22. a lead weight; 23. a third airway; 24. a second air valve; 25. a fourth airway; 26. a third air valve; 27. a slide block; 28. a suction cup; 29. a pull rope; 30. a traction block; 31. a second air outlet; 32. a central control platform; 33. a connecting beam; 34. a first vertical air passage; 35. a cross beam; 36. a second vertical air passage; 37. a cooling hole; 38. and (3) a spring.
Detailed Description
The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
First embodiment
As shown in fig. 1 and 2, an aero-piston engine ground test bed system comprises a base 1, the top of the base 1 is provided with a baffle 2, the baffle 2 is located at the middle part of the base 1 and is located at the rear, the top of the base 1 is respectively provided with a front support 4 and a rear support 5, a cross beam 35 is arranged between the front support 4 and the rear support 5, the cross beam 35 is used for guaranteeing stability between the front support 4 and the rear support 5, the front support 4 is located at one end of the rear support 5 away from the baffle 2, the top of the rear support 5 is provided with a buffering corrugated pipe 19, the top of the buffering corrugated pipe 19 is provided with an engine 10, the buffering corrugated pipe 19 is used for damping and buffering the engine 10, stability of the engine 10 during test is guaranteed, the top of the engine 10 is provided with a connecting belt 15, the connecting belt 15 is used for bolting the top of the engine 10, stability of the engine 10 is guaranteed, the connecting belt 15 is made of a tensile material for adapting to the engine 10 with various types of weight, one side of the engine 10 away from the baffle 2 is provided with a propeller 11, the propeller 11 is internally provided with a propeller speed regulator through a pitch regulating mechanism, the pitch regulating mechanism can regulate the angle of the propeller 11, and then the engine 10 can realize the regulation of the engine 10 in a normal running range of the engine 10 when the engine 10 is used, and the normal running or the engine 10 is taken off.
The baffle 2 is equipped with well accuse platform 32 far away from one side of engine 10, well accuse platform 32 electric connection each electrical components, well accuse platform 32 includes control module and display device, control module electric connection control system, control system electric connection fuel supply unit, starting drive and magneto switch, control system adopts hard transmission control, control panel gives control system out mechanical signal and signal of telecommunication, control system transfers to fuel control unit, starting drive and magneto system after resolving.
The display device is electrically connected with the instrument system, the bottom of the engine 10 is connected with the rotation speed, flow, pressure and current sensors, the instrument system is electrically connected with the sensors, and then various basic performances of the engine 10, such as rotation speed, flow, pressure and current, can be detected through the sensors, and the detection result is displayed on the display device, so that the control performance and the data detection performance of the device are further improved, and the accuracy of detection and the stability of data are ensured.
The inside of baffle 2 is equipped with observation window 3, and the inside windshield that is equipped with of observation window 3 can avoid producing the strong wind at engine 10 during operation to cause the influence to operating personnel through the windshield to can guarantee effectively that operating personnel observe engine 10 at engine 10 during operation through observation window 3, avoid engine 10 to appear unexpected and cause the damage.
The two front brackets 4 and the rear bracket 5 are respectively provided with a supporting beam 6, the two sides of the rear bracket 5 are respectively provided with a tripod 7, the bottom of the tripod 7 is fixedly connected with the top of the base 1, the stability of the front bracket 4 and the rear bracket 5 can be ensured through the supporting beams 6, the stability of the engine 10 is further ensured to be improved when the engine 10 is supported, the tripod 7 can further ensure the required stability and durability by virtue of the triangular structure of the tripod 7, and the service life of the device is prolonged.
The bottom one side of base 1 is equipped with removes round 8, and the opposite side of removing round 8 is equipped with stabilizer blade 9, and stabilizer blade 9 is located the one end that is close to baffle 2, removes round 8 and is convenient for transport, and stabilizer blade 9 carries out temporary support protection to base 1.
The top of back support 5 is equipped with riser 12, and the inside of riser 12 is excavated wired hole 13, and one side that engine 10 was kept away from to riser 12 is equipped with connecting rod 14, and the other end and the baffle 2 fixed connection of connecting rod 14, riser 12 are used for carrying out the calibration effect when engine 10 installs, and after the afterbody of engine 10 contacted the calibration with riser 12, pass the required connecting wire of each control assembly and display device and peg graft fixedly with engine 10 corresponding position in wired hole 13 to avoid leading to the fact the hindrance to each circuit wind rocking at engine 10 during operation, thereby reduce detection precision, take place the incident even.
When the device is used, the base 1 is transported to the test bed, then the engine 10 is hoisted to the top of the test bed, the engine 10 is positioned, the tail of the engine 10 is in contact alignment with the vertical plate 12, the bottom of the engine 10 is in contact with the top of the buffer corrugated pipe 19, the connecting belt 15 is bolted to the top of the front end of the engine 10, at the moment, all lines of the control assembly and the display device are communicated with the bottom of the engine 10, after the engine 10 is started, the device detection precision can be effectively improved by means of the damping effect of the buffer corrugated pipe 19 on the engine 10, and safety accidents during detection are avoided.
Meanwhile, when the airspeed of the engine 10 needs to be changed, the control assembly is used for adjusting and controlling various working states of the engine 10, and the pitch-changing mechanism is only required to be adjusted by the control assembly, so that the propeller speed regulator is adjusted, the attack angle of the propeller 11 is changed, the airspeed of the engine 10 can be adjusted, and meanwhile, various performance data of the engine 10 in a working state are detected by means of sensors such as rotating speed, pressure, flow and current, so that the detection result is improved, and the detection accuracy is ensured.
Second embodiment
In actual use, as shown in fig. 3-7, when the airspeed of the engine 10 decreases, the wind speed generated by the propeller 11 on one side of the engine 10 decreases, so that the engine 10 pulls the connecting belt 15 downward under the action of its own weight, and when the wind speed generated by the propeller 11 on one side of the engine 10 increases, the propeller 11 end of the engine 10 lifts upward to cause toppling over of the base 1 or the baffle 2, and at the same time, heat is generated during operation of the engine 10, so as to ensure that the base 1 and the baffle 2 are not damaged when the airspeed of the engine 10 changes during use, and avoid the generated wind from being discharged randomly, thereby causing environmental pollution and damage, and improving the cooling effect on the engine 10 and the base 1 and the baffle 2, the aircraft piston engine ground test bed system further comprises: an air inlet 16 is formed in one end, far away from the baffle plate 2, of the rear support 5, air flow generated when the engine 10 drives the propeller 11 to rotate can backwards reach the rear support 5 and enter along the air inlet 16, a connecting beam 33 is arranged at the other end of the rear support 5, the other end of the connecting beam 33 is fixedly connected with the baffle plate 2, a first air channel 17 is arranged in the connecting beam 33, the other end of the air inlet 16 is communicated with the first air channel 17 through a first air valve 20, the connecting beam 33 not only can ensure the stability of the rear support 5, but also is communicated with the air inlet 16 through the first air channel 17, and wind reaching the air inlet 16 can enter the first air channel 17 through the first air valve 20.
The inside of baffle 2 is equipped with first vertical air flue 34, first vertical air flue 34 is linked together with first air flue 17, and the air current in the first air flue 17 can reach in the first vertical air flue 34, the inside sliding connection of first vertical air flue 34 has plummet 22, the top and the connecting band 15 fixed connection of plummet 22, plummet 22 can carry out pulling force support to connecting band 15 by self gravity, and then guarantee the stability of engine 10, the air current that gets into in the first vertical air flue 34 can exert effort to the bottom of plummet 22, make plummet 22 weaken the effort of connecting band 15, thereby guarantee that the front end of engine 10 is in stable equilibrium state, further improve the stability performance of device, and when the screw 11 angle of attack of engine 10 front end reduces, the airspeed of engine 10 reduces simultaneously, the wind speed that produces reduces, the front end of engine 10 has the trend of downward sloping, the wind-force effect that the plummet 22 receives reduces through air inlet 16, the wind speed that first air flue 17 reached in the first vertical air flue 34, the bottom of plummet 22 increases to connecting band 15, the effort that the other end of connecting band 15 also can exert effort to the bottom of plummet 22, thereby guarantee that the front end of connecting band 15 is in a stable state and the air current can be in a stable state of the first exhaust 21 is in the same place of engine 10, and further be in a stable state of being close to the first air outlet 10, and further be equipped with the first air outlet device 21.
The flow stability of air current can be guaranteed through the induced air mechanism of each stage to because the diameter of first air flue 17 to first vertical air flue 34 reduces gradually, consequently the air current possesses good cooling effect in the passageway that the diameter reduces gradually, further improve the cooling effect of device, avoid engine 10 during operation high temperature to cause the damage to each part, the afterbody of air current relative distribution engine 10 that flows along first gas outlet 21 simultaneously, riser 12 is located the even array all around of line hole 13 and is equipped with multiunit cooling hole 37, this wind-force carries out wind-force cooling to the afterbody of engine 10 through cooling hole 37 around the line hole 13, avoid engine 10 afterbody to damage because of the high temperature.
The top of the air inlet 16 is communicated with a second air passage 18, the second air passage 18 is in a normally open state, the bottom of the engine 10 is provided with a fixed block matched with the buffer corrugated pipe 19, the second air passage 18 is communicated with the buffer corrugated pipe 19, so that air flow reaching the second air passage 18 along the air inlet 16 can enter the buffer corrugated pipe 19 to further charge the buffer corrugated pipe 19, the buffer corrugated pipe 19 is in a full state when the engine 10 is actually operated, the durability of the buffer corrugated pipe 19 is guaranteed when the engine 10 is in long-term use, meanwhile, before the engine 10 is started, no air exists in the buffer corrugated pipe 19, the buffer corrugated pipe 19 is in a compressed state, the bottom of the engine 10 can be guaranteed to be in hard contact with the top of the rear bracket 5 when the engine 10 is installed, therefore, the installation stability can be effectively improved, the installation shaking of the engine 10 caused by the buffering vibration reduction effect of the buffering corrugated pipe 19 during installation is avoided, the engine 10 cannot be accurately aligned to the installation position finally, meanwhile, when the engine 10 works, the buffering corrugated pipe 19 can be inflated by means of air flow generated by the propeller 11 and has the vibration reduction and buffering effect, the protection of the engine 10 is effectively improved, after the test engine 10 is closed, the air flow is lost in the buffering corrugated pipe 19, the air is re-deflated and contracted, the rear bracket 5 directly supports the bottom of the engine 10, and therefore the engine 10 can be directly taken out from the top of the rear bracket 5, the device has the advantages of more practical effect, high installation efficiency and high safety, and the corresponding vibration reduction and buffering effect cannot be lost.
The bottom of the air inlet 16 is provided with a third air passage 23 through a second air valve 24, a spring 38 is arranged in the third air passage 23, the bottom of the spring 38 is provided with a sliding block 27, and the bottom of the sliding block 27 penetrates through the base 1 and is provided with a sucking disc 28; the air pressure value required by the opening of the first air valve 20 is smaller than that of the second air valve 24, so when the attack angle of the propeller 11 is increased by the center console 32 to increase the wind speed, the front end of the engine 10 has a tendency to incline upwards and turn over, the second air valve 24 is completely opened, the wind speed in the first vertical air passage 34 is increased, the wind force controls the lead weight 22 to move upwards to the maximum position, the lead weight 22 loses the tension on the connecting belt 15, the connecting belt 15 loses the tension on the top of the engine 10, the top of the engine 10 is prevented from inclining under the tension of the pull-in belt 15, meanwhile, the redundant air flow in the first vertical air passage 34 cannot be discharged due to the limited air outlet efficiency of the first air outlet 21, therefore, the redundant air flow can reach the inside of the third air passage 23 along the second air valve 24, the sliding block 27 can be driven to move downwards by wind force, the sucker 28 can be driven to move downwards and contact with the ground when the sliding block 27 moves downwards, the bottom of the sucker 28 contacts with the ground, the air in the sucker 28 is discharged when the sucker 28 is extruded with the ground, the sucker 28 is sucked with the ground to ensure the stability of the base 1, the stability of the base 1 can be ensured by the sucking action of the sucker 28 and the ground, the phenomenon that the front end of the engine 10 is overturned upwards due to the overlarge wind speed generated by the engine 10 is avoided, and after the rotating speed is restored again, the sliding block 27 can be driven to move upwards under the action of the spring 38, so that the sucker 28 is driven to separate from the ground, and the original state is restored.
The cross beam 35 is internally provided with a fourth air passage 25, and the third air passage 23 is communicated with the fourth air passage 25 through a third air valve 26; when the sliding block 27 moves downwards to the maximum position, the sucking disc 28 contacts with the ground, at this time, the air flow in the third air passage 23 can reach the fourth air passage 25 through the third air valve 26, the second vertical air passage 36 is arranged in the front bracket 4, the fourth air passage 25 is communicated with the second vertical air passage 36, the air flow in the fourth air passage 25 can reach the inside of the second vertical air passage 36, the two sides of the second vertical air passage 36 are both provided with the second air outlets 31, the traction block 30 is slidably connected in the second vertical air passage 36, the top of the traction block 30 is provided with the pull ropes 29, the top of the pull ropes 29 passes through the front bracket 4 and is fixedly connected with the bottom of the engine 10, at this time, the air flow in the second vertical air passage 36 can apply an acting force to the top of the traction block 30, so that the traction block 30 moves downwards, and the other end of the pull ropes 29 is fixedly connected with the bottom of the front end of the engine 10, therefore, the front end of the engine 10 is prevented from being inclined upwards by the aid of the pull ropes 29, the redundant air flow can be discharged along the second air outlets 31, and other components can not be damaged.
When the engine 10 is required to be mounted on a test bed, the bottom of the buffer corrugated pipe 19 is in a compressed state because no gas enters the buffer corrugated pipe 19, the tail of the engine 10 is only required to be aligned with one side of the vertical plate 12, the bottom of the engine 10 is placed at the top of the rear bracket 5, one side of the connecting belt 15 is bolted with the top of the engine 10, the other end of the connecting belt 15 is fixedly connected with the top of the lead weight 22, the lead weight 22 is in sliding connection in the first vertical air passage 34, and the top of the front end of the engine 10 is stretched and fixed by the lead weight 22 and the connecting belt 15, so that the engine 10 is in a stable state when not working, and the line of the center console 32 is connected with each position of the engine 10 through the line hole 13.
When the engine 10 is fixed and the test is started, the engine 10 starts the propeller 11 to start rotating, then the air flow generated by the propeller 11 flows backwards and reaches the inside of the air inlet 16, and reaches the inside of the buffer corrugated pipe 19 through the second air passage 18 upwards along the air inlet 16, the buffer corrugated pipe 19 inflates and supports the bottom of the engine 10, at the moment, the bottom of the engine 10 can be supported by the action of the buffer corrugated pipe 19, and when the engine 10 is started, the buffer corrugated pipe 19 is in an inflated state, so that the engine 10 has a good damping and buffering effect, and vibration generated by the engine 10 can be buffered, and the stability of the engine 10 during running is ensured.
Meanwhile, since the buffer bellows 19 is in a unidirectional circulation state, after the buffer bellows 19 is fully inflated and stabilized, the redundant air flow can reach the first air passage 17 through the first air valve 20, and reach the inside of the first vertical air passage 34 along the first air passage 17, and a supporting force is applied to the bottom of the lead weight 22 in the first vertical air passage 34, so that the lead weight 22 is in a stable state under the action of wind force at the bottom and the tensile force of the top connecting belt 15, and the redundant air flow can be discharged along the first air outlet 21.
The air flow discharged along the first air outlet 21 can reach the position of the vertical plate 12, and reaches the tail part of the engine 10 along the cooling hole 37 in the vertical plate 12 so as to radiate the heat of the tail part of the engine 10, and the air flow is matched with the rotation of the propeller 11 to realize the omnibearing dead-angle-free wind cooling of the engine 10, so that the rotating stability and the cooling effect of the engine 10 are ensured.
When the middle console 32 controls the pitch-changing mechanism to speed the propeller speed regulator, so that the attack angle of the propeller 11 is reduced, and the airspeed generated by the engine 10 is reduced, the front end of the engine 10 has a downward inclination trend due to the reduction of the airspeed, and the wind speed generated by the propeller 11 is synchronously reduced, at the moment, the air flow entering along the air inlet 16 is reduced when the wind speed is reduced, and the air quantity in the buffer bellows 19 is not reduced because the second air passage 18 is in a unidirectional circulation state, the air flow reaching the first air passage 17 along the first air valve 20 is reduced, the air flow reaching the first vertical air passage 34 along the first air passage 17 is synchronously reduced, the wind force borne by the bottom of the lead weight 22 is reduced, the top of the lead weight 22 increases the tension of the connecting belt 15 under the action of dead weight, and the tension of the connecting belt 15 on the top of the front end of the engine 10 is increased, so that the front end of the engine 10 does not have a downward inclination trend due to the reduction of the airspeed, the stability of the engine 10 in a test is further improved, and the front end of the engine 10 is prevented from falling down.
When the corresponding center console 32 controls to increase the attack angle of the propeller 11 and thus the airspeed when the engine 10 rotates, the wind speed generated by the engine 10 increases, so that the front end of the engine 10 has a tendency to incline upwards, and when the front end of the engine 10 inclines upwards because the tail part of the engine 10 is connected with the rear bracket 5 and the vertical frame 12, there is a danger that the base 1 and the baffle 2 are driven to incline when the front end of the engine 10 inclines upwards, at this time, the wind speed reaching the air inlet 16 increases, so that the air flow reaching the first air passage 17 through the first air valve 20 increases, the bottom of the plummet 22 moves upwards under the action of wind force and reaches the maximum degree, at this time, because the exhaust efficiency of the first air outlet 21 is certain, the redundant air flow cannot be exhausted along the first air outlet 21, then the air flow at the air inlet 16 end reaches the third air passage 23 along the second air valve 24, and drives the sliding 27 to stretch the spring 38 to move downwards in the third air passage 23 under the action of wind force, the sliding 27 drives the sucker 28 to move downwards when moving downwards, the bottom of the sucker 28 contacts with the ground to remove the air in the sucker, so that the bottom of the sucker 28 is in a vacuum state, the sucker 28 is in extrusion contact with the ground to fix the base 1 at the moment, the base 1 is ensured to be in a stable state under the condition, when the wind speed is recovered, the air flow does not exist in the third air passage 23, the sliding block 27 is driven to recover to the original position under the action of the elastic force of the spring 38, and meanwhile, the sucker 28 and the ground are separated from the suction state to recover to the original state.
Meanwhile, as the third air passage 23 belongs to the unidirectional circulation condition, after the sucking disc 28 is contacted with the ground, redundant air flows can pass through the third air valve 26 to reach the fourth air passage 25 and reach the second vertical air passage 36 along the fourth air passage 25, the traction block 30 can be driven to move downwards by virtue of the wind force in the second vertical air passage 36, the traction block 30 can be driven to move downwards when moving downwards, the other end of the traction block 29 is fixedly connected with the bottom of the front end of the engine 10, the traction block 29 can drive the front end of the engine 10 to move downwards, the front end of the engine 10 is effectively prevented from tilting upwards under the action of airspeed, the whole device is further prevented from overturning, the redundant air flows can be discharged along the second air outlet 31, the stability of the whole device is ensured, and the damage of the device caused by unsmooth air flow is avoided.
When the test is finished, only the center console 32 is needed to control the engine 10 to stop, the propeller 11 stops rotating, the propeller 11 does not generate air flow, the air inlet 16 does not pass through the air flow, the buffer corrugated pipe 19 does not have air flow, the buffer corrugated pipe 19 can shrink under the action of the engine 10, the bottom of the engine 10 is in direct contact with the top of the rear bracket 5, meanwhile, the buffer corrugated pipe 19 shrinks downwards, in order to ensure the stability of the engine 10, the air flow in the first vertical air channel 34 synchronously disappears, the bottom of the lead weight 22 loses the wind force effect, the tension of the top of the lead weight 22 on the top of the connecting belt 15 is increased, and the tension of the top of the connecting belt 15 on the top of the engine 10 is increased, so that when the engine 10 moves downwards along with the shrinkage of the buffer corrugated pipe 19, the engine 10 slowly and stably descends, the damage to the bottom of the engine 10 caused by the contact between the instantaneous descent of the engine 10 and the top of the rear bracket 5 is avoided, and safety accidents are caused.
The device can guarantee the stability of engine 10 when airspeed increases or reduces to engine 10 well, not only plays fine shock attenuation buffering effect to the work of engine 10, protects engine 10, improves the security performance of engine 10, can also improve the cooling effect to engine 10 simultaneously, guarantees the durability of its work, improves the installation and disassembly efficiency simultaneously, guarantees the stability of each part.
Third embodiment
As can be seen from the second embodiment, during actual use, the engine 10 will vibrate during operation, and the buffer bellows 19 will have a good damping effect on the vibration of the engine 10, but since the gas in the buffer bellows 19 will squeeze and expand synchronously with the vibration of the engine 10, and the vibration of the base 1 will be driven during vibration of the engine 10, so as to damage the operators and the devices at the top, in order to solve the above problems, it is ensured that all parts are still in an absolute stable state during vibration of the engine 10, and the ground test bed system of the aviation piston engine is in actual use: because the second air passage 18 and the third air passage 23 are distributed relatively, the air inlet 16 and the first air passage 17 are distributed opposite to each other, so that when each device is in a stable state and the engine 10 stably works, the engine 10 can move downwards due to the driving of the turbine structure in the engine 10, the engine 10 can downwards squeeze the buffering corrugated pipe 19 at the moment, and the buffering corrugated pipe 19 can exert upward acting force on the engine 10 at the top by means of good compression deformation effect of the engine, so that the engine 10 is prevented from being directly contacted with the rear bracket 5 in a hard compression manner when shaking to cause damage of the engine.
Meanwhile, the air flow in the buffer corrugated pipe 19 can move downwards under the action of extrusion, and because the buffer corrugated pipe 19 and the third air passage 23 are distributed relatively, the air pressure in the buffer corrugated pipe 19 can directly pass through the second air valve 24 and reach the third air passage 23, at the moment, the air flow can drive the sliding block 27 to move downwards in the third air passage 23, and the sliding block 27 can drive the sucker 28 to move downwards to be in contact with the ground when moving downwards, the stability of the base 1 can be ensured by virtue of the contact of the sucker 28 and the ground, and the base 1 is prevented from shaking at the same frequency when the engine 10 shakes so as to damage the top operators and all parts.
Meanwhile, the air inlet 16 is opposite to the first air passage 17, and the second air passage 18 is located in the vertical direction of the air inlet 16, so when the air in the buffer corrugated pipe 19 reaches the third air passage 23 along the second air passage 18, the air flow can be blocked to the air flow along the direction of the air inlet 16 to the first air passage 17, turbulence is generated, the air flow along the air inlet 16 to the first air passage 17 is reduced, the wind force acting on the bottom of the lead drop 22 in the first vertical air passage 34 is reduced, the acting force of the lead drop 22 on the connecting belt 15 at the top is increased under the action of dead weight, the acting force of the connecting belt 15 on the top of the engine 10 is increased, the downward vibration amplitude of the engine 10 is ensured to be reduced under the action of the tension of the connecting belt 15, the stability of the engine 10 is ensured, when the downward vibration of the engine 10 is finished and the upward movement of the buffer corrugated pipe 19 is finished, the downward movement of the air flow in the buffer corrugated pipe 19 is finished, the slider 27 is restored to the original position under the action of the return spring 38, the air flow in the third air passage 23 is driven to reversely enter the air inlet 16, the air flow entering along the air inlet 16 is synchronously, and the air flow entering along the air inlet 16 is ensured to be full of the air flow of the first corrugated pipe 20, and the normal air flow in the first air passage is restored.
The device can guarantee the stability of engine 10 when the transient state that engine 10 rocked, supports base 1 effectively with the help of the flow direction of the air current in the buffering bellows 19 simultaneously and fixes, guarantees the stability of base 1, avoids base 1 to take place resonance along with the vibrations of engine 10 and then cause the damage to operating personnel and each part to can also improve the pulling force of connecting band 15 to engine 10 top, and then avoid engine 10 downwardly moving distance too big, thereby cause the damage to the device.
It is noted that relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present application have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made therein without departing from the principles and spirit of the application, the scope of which is defined in the appended claims and their equivalents.
Claims (10)
1. The ground test bed system of the aviation piston engine comprises a base, and is characterized in that a baffle is arranged at the top of the base, a front support and a rear support are respectively arranged at the top of the base, a cross beam is arranged between the front support and the rear support, a buffer corrugated pipe is arranged at the top of the rear support, an engine is arranged at the top of the buffer corrugated pipe, a connecting belt is arranged at the top of the engine, and a center console is arranged at one side, far away from the engine, of the baffle;
the rear support is provided with an air inlet at one end far away from the baffle, the other end of the rear support is provided with a connecting beam, the other end of the connecting beam is fixedly connected with the baffle, a first air passage is arranged in the connecting beam, the other end of the air inlet is communicated with the first air passage through a first air valve, a first vertical air passage is arranged in the baffle and is communicated with the first air passage, a lead weight is slidingly connected in the first vertical air passage, the top of the lead weight is fixedly connected with a connecting belt, and a plurality of groups of first air outlets are uniformly arranged on one side, close to an engine, of the first vertical air passage;
the top of the air inlet is communicated with a second air passage, the second air passage is communicated with a buffer corrugated pipe, the bottom of the air inlet is communicated with a third air passage through a second air valve, the bottom of the third air passage is provided with a spring, the bottom of the spring is provided with a sliding block, the bottom of the sliding block penetrates through a base to be provided with a sucking disc, the inside of the cross beam is provided with a fourth air passage, and the third air passage is communicated with the fourth air passage through a third air valve; the inside of the front support is provided with a second vertical air passage, the fourth air passage is communicated with the second vertical air passage, two sides of the second vertical air passage are provided with a plurality of groups of second air outlets, the inside of the second vertical air passage is connected with a traction block in a sliding manner, the top of the traction block is provided with a pull rope, and the top of the pull rope penetrates through the front support and is fixedly connected with the bottom of the front end of the engine;
when the airspeed of the engine is controlled to be reduced by the center console, the air flow reaching the first vertical air passage along the air inlet and the first air passage is reduced, and the lead weight drives the connecting belt to increase the tension of the connecting belt to the top of the front end of the engine; when the airspeed of the engine is controlled to be increased by the center console, the air flow reaches the third air passage along the air inlet, the sliding block stretches the spring and drives the sucker to be contacted with the ground, the air flow reaches the second vertical air passage along the fourth air passage, and the traction block downwards drives the pull rope to increase the pulling force of the pull rope to the bottom of the front end of the engine.
2. The ground test bed system of an aviation piston engine according to claim 1, wherein a propeller is arranged on one side of the engine away from the baffle plate, and a propeller speed regulator is arranged inside the propeller through a distance changing mechanism.
3. The aircraft piston engine ground test bed system of claim 1, wherein an observation window is provided in the interior of the baffle, and a windshield is provided in the interior of the observation window.
4. The ground test bed system of the aviation piston engine according to claim 1, wherein a supporting beam is arranged between the two front brackets and the rear bracket, triangular brackets are arranged on two sides of the rear bracket, the bottom of each triangular bracket is fixedly connected with the top of the base, and the front bracket is positioned at one end of the rear bracket far away from the baffle.
5. The aircraft piston engine ground test bed system of claim 1, wherein one side of the bottom of the base is provided with a moving wheel, and the other side of the moving wheel is provided with a support leg, and the support leg is located at one end close to the baffle.
6. The ground test bed system of the aviation piston engine according to claim 1, wherein a vertical plate is arranged at the top of the rear support, a wired hole is formed in the vertical plate, a connecting rod is arranged on one side, away from the engine, of the vertical plate, the other end of the connecting rod is fixedly connected with the baffle, and a plurality of groups of cooling holes are uniformly arranged on the periphery of the vertical plate, which is located in the wired hole.
7. The ground test bed system of the aviation piston engine according to claim 1, wherein the center console is electrically connected with each electrical element, the center console comprises a control assembly and a display device, the control assembly is electrically connected with the control system, and the control system is electrically connected with the fuel supply device, the starting device and the magneto switch.
8. The ground test bed system of an aviation piston engine according to claim 7, wherein the display device is electrically connected with an instrument system, the bottom of the engine is connected with rotation speed, flow, pressure and current sensors, and the instrument system is electrically connected with each sensor.
9. The ground test bed system of the aviation piston engine according to claim 1, wherein the air pressure value required by opening the first air valve is smaller than that of the second air valve, the second air passage is in a normally open state, a fixed block matched with the buffering corrugated pipe is arranged at the bottom of the engine, the air inlet is distributed relatively to the first air passage, the second air passage is distributed relatively to the third air passage, and the first air passage and the second air passage are arranged vertically.
10. The ground test bed system of the aviation piston engine according to claim 1, wherein the bottom of the sucker is contacted with the ground, the sucker is extruded with the ground to exhaust the gas inside the sucker, and the sucker is sucked with the ground to stabilize the base.
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