CN115924122A - Device for testing deflection angle of aircraft steering engine - Google Patents
Device for testing deflection angle of aircraft steering engine Download PDFInfo
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- CN115924122A CN115924122A CN202310157495.8A CN202310157495A CN115924122A CN 115924122 A CN115924122 A CN 115924122A CN 202310157495 A CN202310157495 A CN 202310157495A CN 115924122 A CN115924122 A CN 115924122A
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Abstract
The invention relates to the technical field of steering engine testing, and discloses a device for testing the deflection angle of a steering engine of an aircraft, which comprises a shell, a wing plate, a first frame and a second frame, wherein one side of the shell is provided with an air outlet, the wing plate is vertically arranged in the air outlet, the other side of the shell is fixedly provided with a main air pipe, the upper end of the shell is fixedly connected with an installation frame, the installation frame is connected with a measuring mechanism, the measuring mechanism is used for testing the change of the mechanical deflection angle of the steering engine when the wing plate is subjected to wind, and the influence of mechanical clearance on the mechanical deflection angle of the steering engine can be tested under the windless condition, the shell is internally provided with a turbulence mechanism, and the turbulence mechanism is used for providing transverse wind to act on two sides of the wing plate when testing. This a device for testing aircraft steering wheel declination can simulate the operating mode of multiple different wind directions, and the test steering wheel is to the controllability of mechanical declination under complicated air current condition, and the influence volume of clearance that test steering wheel drive mechanism itself exists to mechanical declination that in addition can be quick.
Description
Technical Field
The invention relates to the technical field of steering engine testing, in particular to a device for testing deflection angle of an aircraft steering engine.
Background
The aircraft steering engine generally comprises a driving system, a transmission system, a rudder blade and a control system, wherein the transmission system belongs to a servo system with higher precision, the control system controls a motor to rotate so that the rudder blade deflects and further changes the flight direction of the aircraft, under the condition of an aerospace craft, the working condition of the aircraft steering engine is quite complex, for example, the transmission precision is required to be high under the condition of frequent reversing, the vibration stability is required to be good under the condition of relatively higher transmission speed, the size is required to be small, the weight is light and the reliability is required to be good under the condition of relatively higher load mass ratio, however, a mechanical gap exists in a transmission mechanism, the gap can be caused by large load or overload, the precision of the transmission system and the precision of the control system are directly influenced due to the existence of the gap, the load mass ratio of the transmission mechanism is large, the rigidity of parts is limited, and the precision of the transmission system can be reduced by the elastic deformation of the components.
At present, when the transmission precision of the steering engine is tested, the steering engine is fixed on a mechanical deflection angle testing device in an idle state by adopting a technical means that the electrical zero position of the steering engine is required to be consistent with the mechanical zero position, a tester is utilized to input control signals of different angles to each steering engine respectively, and the mechanical deflection angle corresponding to the steering engine is read in sequence to meet the requirement and the load capacity.
The above prior art obviously has obvious defects that although the tester can input control signals of different angles to the steering engine, the tester is not suitable for testing the influence of airflows in different wind directions on a transmission system, and in addition, the influence of gaps existing in a transmission mechanism of the steering engine on the mechanical deflection angle cannot be quickly tested.
Disclosure of Invention
Technical problem to be solved
Aiming at the defects of the prior art, the invention provides a device for testing the deflection angle of an aircraft steering engine, which has the advantages of simulating working conditions of various different wind directions, testing the control capability of the steering engine on the mechanical deflection angle under the condition of complex airflow, rapidly testing the influence of the clearance of a steering engine transmission mechanism on the mechanical deflection angle and the like, and solves the problems that the traditional testing equipment is not suitable for testing the influence of airflow in different wind directions on a transmission system and cannot rapidly test the influence of the clearance of the steering engine transmission mechanism on the mechanical deflection angle.
(II) technical scheme
In order to achieve the purpose, the invention provides the following technical scheme: a device for testing the deflection angle of an aircraft steering engine comprises a shell, a wing plate, a first rack and a second rack, wherein an air outlet is formed in one side of the shell, the wing plate is vertically arranged in the air outlet, a main air pipe is fixed to the other side of the shell, an installation frame is fixedly connected to the upper end of the shell, and a measuring mechanism is connected to the installation frame;
the measuring mechanism is used for testing the change of the mechanical deflection angle of the steering engine when the wing plate is subjected to wind, and can test the influence of mechanical clearance on the mechanical deflection angle of the steering engine under the windless condition;
the vortex mechanism is arranged in the shell and used for providing cross wind to act on two sides of the wing plate during testing, so that the wing plate is positioned in air flows with different wind directions to test the stability of the steering engine during deflection angle adjustment.
Preferably, the inner walls of the upper end and the lower end of the shell are respectively and rotatably connected with a rotating shaft and a connecting shaft through rolling bearings, and the opposite ends of the rotating shaft and the connecting shaft are fixedly connected with wing plates through bolts;
be connected with solid fixed ring on the axle wall of pivot, gu fixed ring's one side links to each other with measuring mechanism, gu fixed ring's opposite side fixedly connected with pointer, and fixedly connected with vibration sensor on the pointer, the lateral wall fixedly connected with and the pointer matched with dial plate of mounting bracket.
Preferably, the measuring mechanism comprises a connecting frame, the connecting frame is connected with a fixing ring, one end of the connecting frame is fixedly connected with a half gear ring, a gear is meshed with the inner side of the half gear ring, the upper end of the gear is fixedly connected with a gear shaft, the upper end of the mounting frame is fixedly connected with a mounting plate and a transverse plate through a plurality of stand columns, and the gear shaft is rotatably connected with the side wall of the mounting plate through a roller bearing;
the upper end of the transverse plate is connected with a transmission mechanism, and the transmission mechanism is connected with a gear shaft and used for driving the half gear ring.
Preferably, drive mechanism includes electro-magnet and permanent magnet, the permanent magnet is fixed in the upper end of diaphragm, the bar through-hole has been seted up to the upper end of diaphragm, be equipped with the connecting block in the bar through-hole, the one end of connecting block and the lower extreme fixed connection of electro-magnet, the lower extreme fixedly connected with slide of diaphragm, slide sliding connection has the draw runner, one side fixedly connected with rack of draw runner, rack and gear shaft meshing.
Preferably, the turbulence mechanism comprises a three-way pipe and two guide plates which are obliquely arranged, the two guide plates are symmetrically fixed in the shell, one side of each guide plate is fixedly connected with the box body, the side wall of the box body is provided with an air outlet, the air outlet is obliquely oriented to the wing plate, the three-way pipe is fixedly connected with two guide pipes, one ends of the two guide pipes, far away from the three-way pipe, penetrate through the side wall of the shell and are fixedly connected with one sides of the guide plates, and one sides of the guide pipes penetrate through the guide plates and are fixedly connected with one sides of the box body;
the air exhaust end of the first fan is fixedly connected with the three-way pipe through a first threaded pipe.
Preferably, the transmission shaft is rotatably connected in the shell through a needle bearing, the side wall of the box body is rotatably connected with the shaft wall of the transmission shaft through a seal bearing, a flow guide assembly is arranged in the box body and fixed on the shaft wall of the transmission shaft, an adjusting motor is fixedly connected on the mounting frame, and the output end of the adjusting motor is fixedly connected with the upper end of the transmission shaft.
Preferably, the guide assembly is composed of two guide plates which are obliquely arranged, and the two guide plates are fixed on the shaft wall of the transmission shaft.
Preferably, the one end of box body is equipped with two portions of airing exhaust, two the portion of airing exhaust is the both sides that V-arrangement distributes and is located the pterygoid lamina respectively, the one end of portion of airing exhaust all is equipped with the elbow, the air exit is seted up in elbow department, the first air velocity transducer of elbow department fixedly connected with.
Preferably, the first rack is fixedly connected with a second fan, an air exhaust end of the second fan is fixedly connected with one end of the main air pipe through a second threaded pipe, one side of the shell is fixedly connected with a second air speed sensor, and the second air speed sensor is located at a pipe orifice of the main air pipe.
Preferably, the steering engine mounting seat is fixedly connected to the upper end of the shell, and the second rack is fixed to the lower end of the shell.
(III) advantageous effects
Compared with the prior art, the invention provides a device for testing the deflection angle of the steering engine of an aircraft, which has the following beneficial effects:
1. when the steering engine body testing device is used, the steering engine body is installed, the tester is connected with the steering engine body to enable the steering engine body to drive the rotating shaft to enable the pointer to point to the 0 scale of the dial plate, then the measuring mechanism is used for testing the mechanical clearance of the steering engine body under the windless condition, and then the first fan and the second fan work to generate air flow, so that the control accuracy and the stability of the steering engine body can be tested under various working conditions.
2. When the measuring mechanism is used, when the mechanical clearance of an aircraft steering engine is measured, a tester is used for controlling a steering engine body to enable a pointer to return to zero, then an electromagnet is started to work, magnetic attraction force is generated between the electromagnet and a permanent magnet when the electromagnet works, the magnetic attraction force acts on the electromagnet to enable a connecting block to drive a rack to move, the rack moves to drive a gear shaft to rotate, the gear shaft rotates to drive a semi-toothed ring to rotate, the semi-toothed ring rotates to drive a connecting frame to rotate a rotating shaft, torsion generated when the rotating shaft rotates acts on the output end of the steering engine body, meanwhile, the pointing angle of the pointer arranged on the rotating shaft changes, the numerical value is recorded at the moment, then the magnetic pole direction of the electromagnet is changed, magnetic repulsion force is generated between the magnetic pole direction of the electromagnet and the permanent magnet, at the moment, the measuring mechanism drives the rotating shaft to rotate reversely to enable the angle of the pointer to change reversely, the numerical value is recorded at the moment, finally the numerical value recorded twice is added, the final numerical value is the mechanical deflection value generated by the mechanical clearance of the steering engine, and when formal simulation test is carried out, the power supply of the electromagnet is disconnected, the testing device is in a natural state free from external force, and meanwhile, the mechanical deflection change of the steering engine in the whole test process can be read by matching of the pointer and the pointer.
3. When the vortex mechanism is used, the two air exhaust parts are used for guiding airflow to the two sides of the wing plate, and the flow direction of the airflow can be changed by swinging the vortex assembly, so that the airflow speed and the airflow acting on the side surfaces of the wing plate can be adjusted at will, natural airflow can be simulated by matching with the airflow conveyed by the main air pipe, and the control precision and the control stability of an aircraft steering engine under complex working conditions can be tested conveniently.
Drawings
FIG. 1 is a schematic structural diagram of a device for testing the deflection angle of an aircraft steering engine according to the present invention;
FIG. 2 is a cross-sectional view of a housing of the device for testing aircraft steering engine deflection angle according to the present invention;
FIG. 3 is a cross-sectional view of a box body in the device for testing the deflection angle of the steering engine of the aircraft, which is provided by the invention;
FIG. 4 is a first structural schematic diagram of a measuring mechanism in the device for testing the deflection angle of the steering engine of the aircraft provided by the invention;
FIG. 5 is a schematic structural diagram II of a measuring mechanism in the device for testing the deflection angle of the steering engine of the aircraft provided by the invention;
FIG. 6 is a third schematic structural diagram of a measuring mechanism in the device for testing the deflection angle of the aircraft steering engine provided by the invention;
FIG. 7 is a cross-sectional view of a transverse plate and a mounting plate in FIG. 5 of the device for testing aircraft steering engine deflection angle according to the present invention;
FIG. 8 is a schematic structural diagram of a transverse plate and a mounting plate in FIG. 5 of the device for testing the deflection angle of the steering engine of the aircraft according to the present invention;
fig. 9 is a schematic structural diagram of a pointer, a rotating shaft and a half gear ring in fig. 4 of the device for testing the deflection angle of the steering engine of the aircraft provided by the invention.
In the figure: 1. a housing; 2. a wing plate; 3. a mounting frame; 4. a steering engine body; 5. a steering engine mounting seat; 6. adjusting the motor; 7. a conduit; 8. a second fan; 9. a first fan; 10. a three-way pipe; 11. a first frame; 12. a second frame; 13. a guide plate; 14. a drive shaft; 15. a rotating shaft; 16. a main air duct; 17. a case body; 18. a first wind speed sensor; 19. a baffle; 20. an exhaust section; 21. bending the pipe; 22. an air outlet; 23. a vibration sensor; 24. a dial plate; 25. a pointer; 26. a connecting frame; 27. a half gear ring; 28. mounting a plate; 29. a permanent magnet; 30. a transverse plate; 31. an electromagnet; 32. a second wind speed sensor; 33. a slide base; 34. a rack; 35. a gear; 36. a slide bar; 37. a gear shaft.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Example 1:
referring to the attached drawings 1-9, a device for testing the deflection angle of an aircraft steering engine comprises a shell 1, a wing plate 2, a first frame 11 and a second frame 12, wherein an air outlet is formed in one side of the shell 1, the wing plate 2 is vertically arranged in the air outlet, the inner walls of the upper end and the lower end of the shell 1 are respectively and rotatably connected with a rotating shaft 15 and a connecting shaft through rolling bearings, one opposite ends of the rotating shaft 15 and the connecting shaft are respectively and fixedly connected with the wing plate 2 through bolts, a fixing ring is connected to the shaft wall of the rotating shaft 15, one side of the fixing ring is connected with a measuring mechanism, the other side of the fixing ring is fixedly connected with a pointer 25, a vibration sensor 23 is fixedly connected to the pointer 25, a dial plate 24 matched with the pointer 25 is fixedly connected to the side wall of the mounting frame 3, a main air pipe 16 is fixed to the other side of the shell 1, the upper end of the shell 1 is fixedly connected with the mounting frame 3, the measuring mechanism is connected to the mounting frame 3, and is used for testing the change of the mechanical deflection angle of the steering engine when the wing plate 2 is subjected to wind, and the mechanical deflection angle of the steering engine under the windless condition;
be equipped with the vortex mechanism in casing 1, the vortex mechanism is used for providing the both sides that the crosswind acted on pterygoid lamina 2 when testing, make pterygoid lamina 2 be in the stability when testing steering wheel regulation declination in the air current of different wind directions, fixedly connected with second fan 8 on the first frame 11, the end of airing exhaust of second fan 8 passes through the one end fixed connection of second screwed pipe with main tuber pipe 16, one side fixedly connected with second air velocity transducer 32 of casing 1, second air velocity transducer 32 is located the mouth of pipe department of main tuber pipe 16, the upper end fixedly connected with steering wheel mount pad 5 of casing 1, steering wheel body 4 of examination of awaiting measuring through steering wheel mount pad 5 fixed mounting, use the shaft coupling to be connected with the same axle center with the upper end of pivot 15 with the output of steering wheel body 4, the lower extreme at casing 1 is fixed to second frame 12.
When the device is used, the output end of the steering engine body 4 is coaxially connected with the upper end of the rotating shaft 15 by using a coupling, then the steering engine body 4 is connected by using an existing tester (not shown in the figure) to drive the rotating shaft 15 to enable the pointer 25 to point to the 0 scale of the dial plate 24, then a measuring mechanism is used for testing the mechanical gap of the steering engine body 4 and the influence of the existence of the gap on the mechanical deflection angle of the steering engine, then the second fan 8 is started to work to generate air flow, the air flow enters the shell 1 along the second threaded pipe and the main air pipe 16, at the moment, the inclination angle of the wing plate 2 is controlled by the steering engine body 4, the contact angle of the wing plate 2 and the air flow is changed, and the control precision and the stability of the steering engine body 4 under various working conditions can be simulated, and the device is specifically as follows:
firstly, the mechanical deflection angle of the steering engine body 4 is unchanged, namely the pointer 25 points to the scale of 0 of the dial plate 24, at the moment, the wing plate 2 and the airflow direction are in a relatively parallel state, certain airflow speed is kept, and after the airflow speed is stabilized, the influence of the mechanical clearance of the steering engine body 4 on the control precision and the control stability of the steering engine body can be comprehensively judged by reading corresponding data of a tester, observing the angle change of the pointer 25 and the numerical value of a vibration sensor;
after recording each item of data, start vortex mechanism and provide the crosswind and act on the both sides of pterygoid lamina 2, make pterygoid lamina 2 be in the air current of different wind directions, again through recording each item of data to this judges the influence of the mechanical clearance that steering wheel body 4 exists to its control accuracy and control stability.
Secondly, the mechanical deflection angle of the steering engine body 4 generates the change of a fixed angle, control signals with different angles are respectively input to the steering engine body 4 by utilizing a tester, so that the steering engine body 4 drives the rotating shaft 15 to change the angle of the wing plate 2, the stress condition of wings in airflow when an aircraft ascends or descends can be simulated, and at the moment, the control precision and the control stability of the aircraft are calculated by reading and recording corresponding data;
after recording each item data, start vortex mechanism and provide the air current and act on the both sides of pterygoid lamina 2, make pterygoid lamina 2 be in the air current of different wind directions, record each item data once more, and then realize judging control accuracy and the control stability at lift in-process steering wheel body 4.
And thirdly, when the mechanical deflection angle of the steering engine body 4 is fixed at a specific angle, the air flow speeds provided by the first fan 9 and the second fan 8 are controlled and adjusted at will through an external controller, and the control precision and the control stability of the steering engine body 4 are tested when the mechanical deflection angle of a simulated aircraft is fixedly changed in unstable air flow.
Fourthly, the mechanical deflection angle of the steering engine body 4 generates continuous alternate change, a signal of continuous angle change is given through a tester, the steering engine body 4 is made to perform continuous reciprocating control action, different air flows are provided by controlling the first fan 9 and the second fan 8, and when the simulated aircraft continuously generates mechanical deflection angle change in unstable air flows, the control precision and the control stability of the steering engine body 4 are tested.
Fifthly, the mechanical deflection angle through tester control steering wheel body 4 is fixed to a certain angle, even pterygoid lamina 2 is in a certain deflection angle, can only open the vortex mechanism this moment, and make one side gas flow of vortex mechanism be in the maximum value, pterygoid lamina 2 receives single crosswind this moment, and then can utilize the resistance of air current effect on pterygoid lamina 2, test aircraft steering wheel transmission system's mechanical strength and elastic deformation volume, a maximum load capacity for testing aircraft steering wheel transmission system, also can be through adjusting pterygoid lamina 2 to the maximum deflection angle simultaneously, open second fan 8 and with the amount of wind crescent, test.
Example 2: the difference is based on example 1;
referring to fig. 4-9, the measuring mechanism includes a connecting frame 26, the connecting frame 26 is connected to the fixing ring, one end of the connecting frame 26 is fixedly connected to a half-gear ring 27, a gear 35 is engaged with the inner side of the half-gear ring 27, the upper end of the gear 35 is fixedly connected to a gear shaft 37, the upper end of the mounting frame 3 is fixedly connected to a mounting plate 28 and a transverse plate 30 through a plurality of columns, the gear shaft 37 is rotatably connected to the side wall of the mounting plate 28 through a roller bearing, the upper end of the transverse plate 30 is connected to a transmission mechanism, and the transmission mechanism is connected to the gear shaft 37 for driving the half-gear ring 27;
the transmission mechanism comprises an electromagnet 31 and a permanent magnet 29, the permanent magnet 29 is fixed at the upper end of a transverse plate 30, a strip-shaped through hole is formed in the upper end of the transverse plate 30, a connecting block is arranged in the strip-shaped through hole, one end of the connecting block is fixedly connected with the lower end of the electromagnet 31, a sliding seat 33 is fixedly connected with the lower end of the transverse plate 30, a sliding strip 36 is slidably connected with the sliding seat 33, a rack 34 is fixedly connected with one side of the sliding strip 36, and the rack 34 is meshed with a gear shaft 37.
When the measuring mechanism is used for measuring the mechanical clearance of an aircraft steering engine, the tester controls the steering engine body 4 to enable the pointer 25 to return to zero, then the electromagnet 31 is started to work, magnetic attraction force is generated between the electromagnet 31 and the permanent magnet 29 when the electromagnet 31 works, the magnetic attraction force acts on the electromagnet 31 to enable the connecting block to drive the rack 34 to move, the rack 34 moves to drive the gear shaft 37 to rotate, the gear shaft 37 rotates to drive the gear 35 to enable the semi-toothed ring 27 to rotate, the semi-toothed ring 27 rotates to drive the connecting frame 26 to enable the rotating shaft 15 to rotate, torsion generated when the rotating shaft 15 rotates acts on the output end of the steering engine body 4, meanwhile, the angle pointed by the pointer 25 arranged on the rotating shaft 15 changes, at the moment, the numerical value is recorded, then the magnetic pole direction of the electromagnet 31 is changed, magnetic repulsion force is generated between the rotating shaft 15 and the permanent magnet 29, at the moment, the measuring mechanism drives the rotating shaft 15 to rotate reversely to enable the angle of the pointer 25 to change, at the numerical value is recorded at the moment, the two recorded numerical values are added, and finally the obtained numerical value is the mechanical deflection value generated by the mechanical clearance of the steering engine, and the mechanical deflection value is used for reading the whole mechanical deflection angle of the steering engine in the whole process of the steering engine when the simulation test.
Example 3: the difference is based on example 1;
referring to the attached drawings 2-3, the turbulent flow mechanism comprises a three-way pipe 10 and two guide plates 13 which are obliquely arranged, the two guide plates 13 are symmetrically fixed in a shell 1, one side of each guide plate 13 is fixedly connected with a box body 17, the side wall of each box body 17 is provided with an air outlet 22, each air outlet 22 is obliquely arranged towards a wing plate 2, one end of each box body 17 is provided with two air exhaust parts 20, the two air exhaust parts 20 are distributed in a V shape and are respectively positioned at two sides of each wing plate 2, one end of each air exhaust part 20 is provided with an elbow 21, each air outlet 22 is arranged at the corresponding elbow 21, the corresponding elbow 21 is fixedly connected with a first air speed sensor 18, the three-way pipe 10 is fixedly connected with two guide pipes 7, one ends, far away from the three-way pipe 10, of the two guide pipes 7 penetrate through the side wall of the shell 1 and are fixedly connected with one side of each guide plate 13, one side of each guide pipe 7 is fixedly connected with one side of each box body 17, a first fan 9 is fixedly connected to a first rack 11, and the air exhaust end of each first fan 9 is fixedly connected with the three-way pipe 10 through a first threaded pipe;
be connected with transmission shaft 14 through bearing rotation in the casing 1, the lateral wall of box body 17 rotates through sealed bearing and transmission shaft 14 to be connected, be equipped with the water conservancy diversion subassembly in the box body 17, the water conservancy diversion subassembly is fixed on the axle wall of transmission shaft 14, the water conservancy diversion subassembly comprises guide plate 19 that two slopes set up, two guide plates 19 are all fixed on the axle wall of transmission shaft 14, fixedly connected with adjusting motor 6 on the mounting bracket 3, adjusting motor 6's output and transmission shaft 14's upper end fixed connection.
When the air flow steering engine is used, air flow generated by the operation of a first fan 9 enters a three-way pipe 10 through a first threaded pipe, the air flow in the three-way pipe 10 enters a box body 17 through a guide pipe 7, two air exhaust parts 20 arranged on the box body 17 guide the air flow to two sides of a wing plate 2, so that lateral air flow can be provided at two sides of the wing plate 2, a transmission shaft 14 is rotated by controlling an adjusting motor 6, the transmission shaft 14 drives a flow disturbing component to swing when rotating, the flow direction of the air flow is changed by a flow guide plate 19 when the flow disturbing component swings, the air flow speed and the air flow discharged by the two air exhaust parts 20 are changed, finally the air flow speed and the air flow acting on the side surface of the wing plate 2 can be adjusted at will, natural air flow can be simulated by matching with the air flow conveyed by a main air pipe 16, the influence of the air flow on mechanical deflection angle under complex working conditions can be tested, and the control accuracy and the control stability of the air vehicle under complex working conditions can be tested conveniently.
It is noted that the term "comprises" or any other variation thereof is intended to cover a non-exclusive inclusion, such that a device comprising a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such device and, in the absence of further limitation, such element defined by the phrase "comprising 8230;" does not exclude the presence of other like elements in a device comprising such elements.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (10)
1. The utility model provides a device for testing aircraft steering wheel declination, includes casing (1), pterygoid lamina (2), first frame (11) and second frame (12), its characterized in that: an air outlet is formed in one side of the shell (1), the wing plate (2) is vertically arranged in the air outlet, a main air pipe (16) is fixed to the other side of the shell (1), an installation frame (3) is fixedly connected to the upper end of the shell (1), and a measuring mechanism is connected to the installation frame (3);
the measuring mechanism is used for testing the change of the mechanical deflection angle of the steering engine when the wing plate (2) is subjected to wind, and can test the influence of mechanical clearance on the mechanical deflection angle of the steering engine under the windless condition;
the testing device is characterized in that a turbulence mechanism is arranged in the shell (1), and the turbulence mechanism is used for providing cross wind to act on two sides of the wing plates (2) during testing, so that the wing plates (2) are positioned in airflows with different wind directions to test the stability of the steering engine during adjusting deflection angles.
2. The device for testing the deflection angle of the steering engine of the aircraft according to claim 1, wherein: the inner walls of the upper end and the lower end of the shell (1) are respectively and rotatably connected with a rotating shaft (15) and a connecting shaft through rolling bearings, and the opposite ends of the rotating shaft (15) and the connecting shaft are fixedly connected with the wing plates (2) through bolts;
be connected with solid fixed ring on the axle wall of pivot (15), gu fixed ring's one side links to each other with measuring mechanism, gu fixed ring's opposite side fixedly connected with pointer (25), and fixedly connected with vibration sensor (23) on pointer (25), the lateral wall fixedly connected with and pointer (25) matched with dial plate (24) of mounting bracket (3).
3. The device for testing the deflection angle of the steering engine of the aircraft according to claim 2, wherein: the measuring mechanism comprises a connecting frame (26), the connecting frame (26) is connected with a fixing ring, a half gear ring (27) is fixedly connected to one end of the connecting frame (26), a gear (35) is meshed to the inner side of the half gear ring (27), a gear shaft (37) is fixedly connected to the upper end of the gear (35), a mounting plate (28) and a transverse plate (30) are fixedly connected to the upper end of the mounting frame (3) through a plurality of stand columns, and the gear shaft (37) is rotatably connected with the side wall of the mounting plate (28) through a roller bearing;
the upper end of the transverse plate (30) is connected with a transmission mechanism, and the transmission mechanism is connected with a gear shaft (37) and used for driving the half gear ring (27).
4. The device for testing the deflection angle of the steering engine of the aircraft according to claim 3, wherein: drive mechanism includes electro-magnet (31) and permanent magnet (29), the upper end at diaphragm (30) is fixed in permanent magnet (29), the bar through-hole has been seted up to the upper end of diaphragm (30), be equipped with the connecting block in the bar through-hole, the one end of connecting block and the lower extreme fixed connection of electro-magnet (31), the lower extreme fixedly connected with slide (33) of diaphragm (30), slide (33) sliding connection has draw runner (36), one side fixedly connected with rack (34) of draw runner (36), rack (34) and gear shaft (37) meshing.
5. The device for testing the deflection angle of the steering engine of the aircraft according to claim 1, wherein: the flow disturbing mechanism comprises a three-way pipe (10) and two guide plates (13) which are obliquely arranged, the two guide plates (13) are symmetrically fixed in the shell (1), one side of each guide plate (13) is fixedly connected with a box body (17), the side wall of each box body (17) is provided with an air outlet (22), each air outlet (22) is obliquely towards the wing plate (2), the three-way pipe (10) is fixedly connected with two guide pipes (7), one ends of the two guide pipes (7) far away from the three-way pipe (10) penetrate through the side wall of the shell (1) and are fixedly connected with one sides of the guide plates (13), and one sides of the guide pipes (7) penetrate through the guide plates (13) and are fixedly connected with one sides of the box bodies (17);
the first frame (11) is fixedly connected with a first fan (9), and the air exhaust end of the first fan (9) is fixedly connected with the three-way pipe (10) through a first threaded pipe.
6. The device for testing the deflection angle of the steering engine of the aircraft according to claim 5, wherein: the novel multifunctional adjustable bearing box is characterized in that a transmission shaft (14) is rotatably connected into the shell (1) through a needle bearing, the side wall of the box body (17) is rotatably connected with the shaft wall of the transmission shaft (14) through a sealing bearing, a flow guide assembly is arranged in the box body (17) and fixed on the shaft wall of the transmission shaft (14), an adjusting motor (6) is fixedly connected onto the mounting rack (3), and the output end of the adjusting motor (6) is fixedly connected with the upper end of the transmission shaft (14).
7. The device for testing the deflection angle of the steering engine of the aircraft according to claim 6, wherein: the flow guide assembly is composed of two obliquely arranged flow guide plates (19), and the two flow guide plates (19) are fixed on the shaft wall of the transmission shaft (14).
8. The device for testing the deflection angle of the steering engine of the aircraft according to claim 5, wherein: one end of box body (17) is equipped with two portions of airing exhaust (20), two portion of airing exhaust (20) are the both sides that V-arrangement distributes and be located pterygoid lamina (2) respectively, the one end of portion of airing exhaust (20) all is equipped with elbow (21), air exit (22) are seted up in elbow (21) department, first air velocity transducer (18) of fixedly connected with are located in elbow (21).
9. The device for testing the deflection angle of the steering engine of the aircraft according to claim 1, wherein: the air-conditioning system is characterized in that a second fan (8) is fixedly connected to the first frame (11), the air exhaust end of the second fan (8) is fixedly connected with one end of the main air pipe (16) through a second threaded pipe, a second air speed sensor (32) is fixedly connected to one side of the shell (1), and the second air speed sensor (32) is located at the pipe orifice of the main air pipe (16).
10. The device for testing the deflection angle of the steering engine of the aircraft according to claim 1, wherein: the upper end fixedly connected with steering wheel mount pad (5) of casing (1), the lower extreme in casing (1) is fixed in second frame (12).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310157495.8A CN115924122A (en) | 2023-02-23 | 2023-02-23 | Device for testing deflection angle of aircraft steering engine |
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| CN202310157495.8A CN115924122A (en) | 2023-02-23 | 2023-02-23 | Device for testing deflection angle of aircraft steering engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116692022A (en) * | 2023-07-13 | 2023-09-05 | 上海莘汭驱动技术有限公司 | Calibrating device for unmanned aerial vehicle steering engine system installation and using method thereof |
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2023
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116692022A (en) * | 2023-07-13 | 2023-09-05 | 上海莘汭驱动技术有限公司 | Calibrating device for unmanned aerial vehicle steering engine system installation and using method thereof |
| CN116692022B (en) * | 2023-07-13 | 2024-03-08 | 上海莘汭驱动技术有限公司 | Calibrating device for unmanned aerial vehicle steering engine system installation and using method thereof |
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