CN112208788B - Aircraft fuel system detection test bench - Google Patents
Aircraft fuel system detection test bench Download PDFInfo
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- CN112208788B CN112208788B CN202011017335.6A CN202011017335A CN112208788B CN 112208788 B CN112208788 B CN 112208788B CN 202011017335 A CN202011017335 A CN 202011017335A CN 112208788 B CN112208788 B CN 112208788B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The invention discloses a detection test bed for an aircraft fuel system, which belongs to the field of aircraft fuel systems and adopts the technical scheme that the detection test bed comprises an operation table, a carrying mechanism, a clamping mechanism, a control module and a driving module; the carrying module comprises a lifting frame arranged at the center below the operating platform, a feeding port corresponding to the top of the lifting frame is formed in the center of the top of the operating platform, a lifting plate is connected to the inner wall of the lifting frame in a sliding mode along the vertical direction, an oil pump platform is connected to the top of the lifting plate in a rotating mode, and three groups of lifting grooves are formed in the top of the oil pump platform; the clamping mechanism comprises two guide rails which are symmetrically arranged on the front side and the rear side of the top of the operating platform, and the sliding mechanisms which are distributed on two sides of the feeding port are connected to the guide rails in a sliding mode along the extending direction of the guide rails.
Description
Technical Field
The invention relates to the technical field of aircraft fuel systems, in particular to a test bed for detecting an aircraft fuel system.
Background
The fuel oil system of the airplane has the functions of storing fuel oil and ensuring that the fuel oil can be continuously supplied to the engine according to the pressure and flow required by the engine in any specified state (such as various flight heights and flight postures), and in addition, the fuel oil system can also complete additional functions of other systems on a cooler, balancing the airplane, keeping the gravity center of the airplane within a specified range and the like.
In aircraft fuel oil system, the most important part belongs to the fuel pump, in aircraft fuel pump test process, because the shape of oil pump is special, the pump will laminate very tightly with the faying face when the experiment, and the clamping of now again all leans on bolted connection fixed on the test bench, because aircraft fuel pump itself embodies great, it is comparatively difficult on the test bench to carry, the upset of oil pump is also comparatively difficult, be not convenient for detect each position of oil pump, adopt bolt fastening efficiency lower simultaneously, it is very inconvenient to dismantle, degree of automation is lower.
Disclosure of Invention
1. Technical problem to be solved
Aiming at the problems in the prior art, the invention aims to provide an aircraft fuel system detection test bed which has the advantages that an aircraft oil pump can be conveniently transported to a workbench, meanwhile, the fixation and the disassembly are more convenient, and the omnibearing detection of the oil pump is convenient.
2. Technical scheme
In order to solve the above problems, the present invention adopts the following technical solutions.
An aircraft fuel system detection test bed comprises an operation table, a carrying mechanism, a clamping mechanism, a control module and a driving module;
the carrying mechanism comprises a lifting frame arranged at the center below the operating platform, a feeding hole corresponding to the top of the lifting frame is formed in the center of the top of the operating platform, a lifting plate is connected to the inner wall of the lifting frame in a sliding mode along the vertical direction, an oil pump platform is connected to the top of the lifting plate in a rotating mode, and three groups of lifting grooves are formed in the top of the oil pump platform;
the clamping mechanism comprises two guide rails which are symmetrically arranged on the front side and the rear side of the top of the operation table, sliding mechanisms which are distributed on two sides of the feeding hole are connected to the guide rails in a sliding mode along the extending direction of the guide rails, transverse cylinders are symmetrically arranged on two sides of the top of the operation table, cylinder shafts of the two transverse cylinders are fixedly connected with the two sliding mechanisms respectively, the top of the sliding mechanism on the left side is fixedly connected with a lifting clamp tool, and the top of the sliding mechanism on the right side is fixedly connected with a rotating clamp tool;
the control module comprises an electric appliance cabinet arranged in the operation table, and a display and an alarm which are arranged on one side of the top of the operation table, and a PLC (programmable logic controller) is arranged in the electric appliance cabinet;
the driving module comprises an air pump for driving the transverse air cylinder, and the air pump is arranged in the operating platform.
Furthermore, the front end of the lifting frame is provided with an inclined sliding table attached to the upper surface of the oil pump table.
Furthermore, sliding openings are formed in two sides of the lifting frame, a lifting support fixedly connected with a lifting plate is connected to the inner wall of each sliding opening in a sliding mode, a first motor is arranged at the bottom of the lifting frame, a rotating shaft is connected to the bottom of the lifting frame in a rotating mode, the first motor is connected with the rotating shaft through gear meshing, first bevel gears located on two sides of the lifting frame are arranged at two ends of the rotating shaft in a penetrating mode, screw rods are connected to two sides of the lifting frame in a rotating mode, the screw rods penetrate through the lifting support and are in threaded connection with the lifting support, and second bevel gears connected with the first bevel gears in meshing mode are fixedly connected to the surfaces of the screw rods.
Furthermore, the top of the lifting plate is rotatably connected with a rotary cylinder, the oil pump platform is rotatably arranged on the lifting plate through the rotary cylinder, and the angle rotation range of the rotary cylinder is 0-90 degrees.
Furthermore, slide mechanism is including the card on the guide rail and along the gliding slide of guide rail extending direction, the top fixedly connected with mounting panel of slide.
Further, the lifting fixture tool comprises a Y-axis moving platform fixedly connected to the left side of the top of the sliding mechanism, a bearing seat fixedly connected to one side of the Y-axis moving platform, a clamping plate rotatably connected to one side of the bearing seat, a lifting rod fixedly connected to the lower end of one side of the clamping plate and matched with the lifting groove, a longitudinal cylinder fixedly mounted to the upper end of one side of the clamping plate, and a pressing rod fixedly connected to the bottom of the longitudinal cylinder.
Furthermore, one side of cardboard is provided with oil pump pressure induction zone, the inside in oil pump pressure induction zone is provided with pressure sensor.
Further, the rotary fixture frock is including fixing two fixed plates that are located the right side slide mechanism top, is located the right side one side fixedly connected with second motor of fixed plate, the output shaft of second motor runs through the right side fixed plate and fixedly connected with action wheel, right side the opposite side of fixed plate is rotated and is connected with from the driving wheel, the surface transmission from driving wheel and action wheel is connected with the belt, the action wheel and the equal fixedly connected with rotation axis of one end from the driving wheel, the one end of rotation axis runs through left fixed plate and fixedly connected with three anchor clamps.
Further, the three-head clamp comprises a clamping seat, a spring seat is arranged on one side of the clamping seat, a chuck is fixedly connected to one side of the spring seat, a limiting shaft is fixedly connected to the center of one side, close to the clamping seat, of the chuck, and one end of the limiting shaft is in clearance fit with the center of the clamping seat and is rotatably connected with the clamping seat.
Furthermore, the opposite sides of the ram and the pressure lever are both arc-shaped, and rubber pads are arranged on the opposite sides of the ram and the pressure lever.
3. Advantageous effects
Compared with the prior art, the invention has the advantages that:
(1) when the oil pump is transferred to the operation table, the oil pump is pushed onto the oil pump table through the inclined sliding table to adjust the position of the oil pump table, then the PLC controls the first motor to operate, the first motor operates to drive the rotating shaft to rotate through the gear, further, the first bevel gear is driven through the rotating shaft, the screw rod rotates through the second bevel gear, the lifting support is moved upwards through the rotation of the screw rod, the lifting plate and the oil pump table are driven to ascend to the feeding port, and the height of the oil pump table is higher than that of the guide rail at the moment, so that the handling of the oil pump of the aircraft is completed, and the oil pump is safer and more reliable than manual handling;
(2) when the oil pump platform rises to the highest position, the transverse cylinder on the left side pushes the sliding mechanism to move so as to drive the ram to move into the lifting groove, after the ram enters the highest position, the longitudinal cylinder pushes the pressure rod downwards to move downwards so that the pressure rod presses the oil pump of the airplane, the Y-axis moving platform drives the bearing seat to move upwards, at the moment, the oil pump of the airplane can be lifted from the oil pump platform, after the oil pump is fixed by the lifting clamp tool, the transverse cylinder on the right side pushes the sliding mechanism enough to enable the three-head clamp to approach the oil pump for clamping the oil pump, then in the test process, when the position of the oil pump needs to be adjusted, the driving wheel can be driven to rotate by the second motor, the driven wheel can be synchronously rotated by the belt, so that the three-head clamp can be driven to rotate by a plurality of rotating shafts, the three-head clamp and the oil pump can be matched with the rotating capacity of the bearing seat so that the oil pump of the airplane can rotate, the detection of each position is convenient;
(3) the opposite sides of the ram and the compression bar are arranged to be arc-shaped, so that the ram and the compression bar can be attached to the oil pump conveniently, the rubber pad is used for protecting the oil pump and preventing the oil pump from being damaged by clamping, and the spring seat is used for reducing the pressure of the chuck on the oil pump and preventing the chuck from crushing the oil pump.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is an elevational, cross-sectional view of the present invention;
FIG. 3 is a schematic structural view of a rotary clamp tool of the present invention;
FIG. 4 is a cross-sectional view of a rotary fixture tool of the present invention;
FIG. 5 is a schematic structural view of the lifting fixture apparatus of the present invention;
FIG. 6 is a cross-sectional view of the lift clamp assembly of the present invention;
FIG. 7 is a schematic structural view of a carrying mechanism according to the present invention;
fig. 8 is an enlarged view of the invention at a in fig. 4.
The reference numbers in the figures illustrate:
1. an operation table; 2. a lifting frame; 3. a feeding port; 4. lifting the plate; 5. an oil pump table; 6. picking up the groove; 7. a guide rail; 8. a sliding mechanism; 801. a slide base; 802. mounting a plate; 9. a transverse cylinder; 10. a cylinder shaft; 11. lifting the fixture tool; 1101. a Y-axis moving platform; 1102. a bearing seat; 1103. clamping a plate; 1104. a ram; 1105. a longitudinal cylinder; 1106. a pressure lever; 1107. an oil pump pressure sensing zone; 12. rotating the fixture tool; 1201. a fixing plate; 1202. a second motor; 1203. a driven wheel; 1204. a rotating shaft; 1205. a holder; 1206. a spring seat; 1207. a chuck; 1208. a limiting shaft; 1209. a driving wheel; 13. an electric appliance cabinet; 14. a display; 15. an alarm; 16. an air pump; 17. inclining the sliding table; 18. a sliding port; 19. lifting the support; 20. a first motor; 21. a rotating shaft; 22. a first bevel gear; 23. a screw rod; 24. a rotating cylinder; 25. a second bevel gear.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention; it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments, and all other embodiments obtained by those skilled in the art without any inventive work are within the scope of the present invention.
Referring to fig. 1 to 8, in the embodiment of the present invention, an aircraft fuel system detection test bed includes an operation table 1, a carrying mechanism, a clamping mechanism, a control module, and a driving module; the carrying mechanism comprises a lifting frame 2 arranged at the center below the operating platform 1, a feeding port 3 corresponding to the top of the lifting frame 2 is formed in the center of the top of the operating platform 1, a lifting plate 4 is connected to the inner wall of the lifting frame 2 in a sliding mode along the vertical direction, an oil pump platform 5 is connected to the top of the lifting plate 4 in a rotating mode, and three groups of lifting grooves 6 are formed in the top of the oil pump platform 5; the driving module comprises an air pump 16 for driving the transverse air cylinder 9, and the air pump 16 is arranged inside the operating platform 1; the control module comprises an electric appliance cabinet 13 arranged in the operation platform 1, and a display 14 and an alarm 15 which are arranged on one side of the top of the operation platform 1, wherein the display 14 is used for displaying the pressure at the outlet of the oil pump, the alarm 15 is used for giving an alarm when the pressure is abnormal, so that a prompt effect is achieved, and a PLC (programmable logic controller) is arranged in the electric appliance cabinet 13; the front end of crane 2 is provided with the slope slip table 17 with the laminating of oil pump platform 5 upper surface, and the staff of being convenient for pushes away the oil pump on oil pump platform 5 with the help of slope slip table 17.
Clamping mechanism includes two symmetry settings at the guide rail 7 of 1 top front side of operation panel and top rear side, on the guide rail 7 and along the extending direction sliding connection of guide rail 7 have the slide mechanism 8 that distributes in material loading mouth 3 both sides, the top bilateral symmetry of operation panel 1 is provided with horizontal cylinder 9, the cylinder axle 10 of two horizontal cylinders 9 respectively with two slide mechanism 8 fixed connection, be located the top fixedly connected with lift anchor clamps frock 11 of left slide mechanism 8, the top fixedly connected with rotary fixture frock 12 of slide mechanism 8 that is located the right side.
Referring to fig. 1, the sliding mechanism 8 includes a sliding base 801 clamped on the guide rail 7 and sliding along the extending direction of the guide rail 7, a mounting plate 802 is fixedly connected to the top of the sliding base 801, the mounting plate 802 is used for mounting the lifting fixture tool 11 and the rotating fixture tool 12, and the sliding base 801 is clamped on the guide rail 7 to slide, so that certain guiding and limiting effects are achieved.
Referring to fig. 3 and 4, the rotating fixture tool 12 includes two fixing plates 1201 fixed on the top of the sliding mechanism 8 on the right side, one side of the fixing plate 1201 on the right side is fixedly connected with a second motor 1202, an output shaft of the second motor 1202 penetrates through the fixing plate 1201 on the right side and is fixedly connected with a driving wheel 1209, the other side of the fixing plate 1201 on the right side is rotatably connected with a driven wheel 1203, the surfaces of the driven wheel 1203 and the driving wheel 1209 are in transmission connection with a belt, one ends of the driving wheel 1209 and the driven wheel 1203 are both fixedly connected with a rotating shaft 1204, one end of the rotating shaft 1204 penetrates through the fixing plate 1201 on the left side and is fixedly connected with a three-head fixture, after the oil pump is fixed by the lifting fixture tool 11, the transverse cylinder 9 on the right side pushes and slides enough to enable the three-head fixture to approach the oil pump for clamping the oil pump, and then when the position of the oil pump needs to be adjusted in the test process, the driving wheel 1209 can be driven by the second motor 1202 to rotate, and the driven wheel 1203 synchronously rotates by means of a belt, so that the three-head clamp is driven by the plurality of rotating shafts 1204 to rotate, and the aircraft oil pump can rotate by means of friction between the three-head clamp and the oil pump and matching with the rotating capacity of the bearing seat 1102, so that detection of each position of the aircraft oil pump is facilitated. Referring to fig. 5, the opposite sides of the ram 1104 and the press rod 1106 are both provided with arc shapes, and the opposite sides of the ram 1104 and the press rod 1106 are both provided with rubber pads, the inner sides of the ram 1104 and the press rod 1106 are provided with arc shapes, so that the ram 1104 and the press rod 1106 can be attached to the oil pump conveniently, and the rubber pads are used for protecting the oil pump.
Referring to fig. 5 and 6, the lifting fixture 11 includes a Y-axis moving platform 1101 fixedly connected to the top of a sliding mechanism 8 on the left side, a bearing seat 1102 is fixedly connected to one side of the Y-axis moving platform 1101, a clamping plate 1103 is rotatably connected to one side of the bearing seat 1102, a lifting lever 1104 matched with the lifting slot 6 is fixedly connected to the lower end of one side of the clamping plate 1103, a longitudinal cylinder 1105 is fixedly installed at the upper end of one side of the clamping plate 1103, a pressing rod 1106 is fixedly connected to the bottom of the longitudinal cylinder 1105, when the oil pump platform 5 ascends to the highest position, the left transverse cylinder 9 pushes the sliding mechanism 8 to move, so as to drive the ram 1104 to move into the picking groove 6, after the ram 1104 enters into position, the longitudinal cylinder 1105 pushes the pressure lever 1106 downwards to move downwards, so that the pressure lever 1106 compresses the oil pump of the aircraft, the Y-axis moving platform 1101 drives the bearing seat 1102 to move upwards, and at the moment, the oil pump of the aircraft can be lifted from the oil pump table 5.
Referring to fig. 6, one side of the snap-gauge 1103 is provided with an oil pump pressure sensing area 1107, the inside of the oil pump pressure sensing area 1107 is provided with a pressure sensor, when the oil pump is clamped, the outlet of the oil pump corresponds to the oil pump pressure sensing area 1107, oil is supplied to the inside of the oil pump in the test process, the pressure at the outlet of the oil pump is detected by the pressure sensor, and the sealing performance of the oil pump is detected.
Referring to fig. 1 and 7, the two sides of the lifting frame 2 are respectively provided with a sliding opening 18, the inner wall of the sliding opening 18 is slidably connected with a lifting support 19 fixedly connected with the lifting plate 4, the bottom of the lifting frame 2 is provided with a first motor 20, the bottom of the lifting frame 2 is also rotatably connected with a rotating shaft 21, the first motor 20 is in gear engagement with the rotating shaft 21, two ends of the rotating shaft 21 both penetrate through the lifting frame 2 and are fixedly connected with first bevel gears 22 positioned at two sides of the lifting frame 2, two sides of the lifting frame 2 are also rotatably connected with lead screws 23, the lead screws 23 penetrate through the lifting support 19 and are in threaded connection with the lifting support 19, the surface of the lead screws 23 is fixedly connected with second bevel gears 25 in gear engagement with the first bevel gears 22, when the oil pump is transferred to the operation platform 1, the oil pump is pushed onto the oil pump platform 5 by means of the inclined sliding table 17 to adjust the position of the oil pump, and then the PLC controller controls the first motor 20 to operate, the first motor 20 runs to drive the rotating shaft 21 to rotate through a gear, further drives the first bevel gear 22 through the rotating shaft 21, and enables the screw rod 23 to rotate by means of the second bevel gear 25, the screw rod 23 rotates to enable the lifting support 19 to move upwards, further drives the lifting plate 4 and the oil pump platform 5 to lift to the feeding port 3, and at the moment, the height of the oil pump platform 5 is higher than that of the guide rail 7, so that the oil pump is carried, and compared with manual carrying, the automatic lifting device is safer and more reliable.
Referring to fig. 7, the top of the lifting plate 4 is rotatably connected with a rotary cylinder 24, the oil pump platform 5 is rotatably arranged on the lifting plate 4 through the rotary cylinder 24, the angle rotation range of the rotary cylinder 24 is 0-90 °, when the oil pump platform 5 is lifted to the maximum height, the rotary cylinder 24 rotates 90 °, the position of the oil pump platform 5 is rotated to be flush with the sliding mechanism 8, and the aircraft oil pump is conveniently lifted by a subsequent lifting rod 1104.
Referring to fig. 8 three-head clamp includes holder 1205, one side of holder 1205 is provided with spring holder 1206, one side fixedly connected with chuck 1207 of spring holder 1206, and chuck 1207 is close to the spacing axle 1208 of one side center fixedly connected with of holder 1205, the one end clearance fit of spacing axle 1208 is connected to the center of holder 1205 and rotates with holder 1205, spring holder 1206 comprises the inside buffing pad that sets up the spring for reduce the pressure of chuck 1207 to the oil pump, prevent that chuck 1207 from crushing the oil pump.
The working principle of the invention is as follows: when the oil pump is transferred to the operation table 1, the oil pump is pushed onto the oil pump table 5 by the aid of the inclined sliding table 17 to adjust the position of the oil pump, then the PLC controls the first motor 20 to operate, the first motor 20 operates to drive the rotating shaft 21 to rotate through the gear, the first bevel gear 22 is further driven by the rotating shaft 21, the screw 23 rotates by the aid of the second bevel gear 25, the screw 23 rotates to enable the lifting support 19 to move upwards, the lifting plate 4 and the oil pump table 5 are further driven to ascend to the material loading opening 3, at the moment, the height of the oil pump table 5 is higher than that of the guide rail 7, the oil pump is conveyed, compared with manual conveying, the conveying is safer and more reliable, when the oil pump table 5 ascends to the highest position, the transverse air cylinder 9 on the left side pushes the sliding mechanism 8 to move so as to drive the ram 1104 to move into the ram slot 6, after the ram enters into place, the longitudinal air cylinder 1105 pushes the press down the ram 1106 to press the oil pump 1104, the bearing seat 1102 is driven by the Y-axis moving platform 1101 to move upwards, the oil pump of the airplane can be lifted from the oil pump platform 5 at the moment, after the oil pump is fixed well by the lifting clamp tool 11, the transverse cylinder 9 on the right side can be pushed to slide enough, the three-head clamp is close to the oil pump and used for clamping the oil pump, then in the test process, when the position of the oil pump needs to be adjusted, the driving wheel 1209 can be driven to rotate by the second motor 1202, the driven wheel 1203 can be synchronously rotated by means of a belt, the three-head clamp is driven to rotate by the rotating shafts 1204, friction is generated between the three-head clamp and the oil pump, the rotating capacity of the bearing seat 1102 is matched, the oil pump of the airplane can rotate, and the detection of each position of the oil pump is facilitated.
The foregoing is only a preferred embodiment of the present invention; the scope of the invention is not limited thereto. Any person skilled in the art should be able to cover the technical scope of the present invention by equivalent or modified solutions and modifications within the technical scope of the present invention.
Claims (10)
1. The utility model provides an aircraft fuel system detection test bench, includes operation panel (1), its characterized in that: the device also comprises a carrying mechanism, a clamping mechanism, a control module and a driving module;
the carrying mechanism comprises a lifting frame (2) arranged at the center below an operating platform (1), a feeding hole (3) corresponding to the top of the lifting frame (2) is formed in the center of the top of the operating platform (1), a lifting plate (4) is connected to the inner wall of the lifting frame (2) in a sliding mode along the vertical direction, an oil pump platform (5) is rotatably connected to the top of the lifting plate (4), and three groups of lifting grooves (6) are formed in the top of the oil pump platform (5);
the clamping mechanism comprises two guide rails (7) which are symmetrically arranged on the front side and the rear side of the top of the operation table (1), sliding mechanisms (8) which are distributed on two sides of the feeding port (3) are connected to the guide rails (7) in a sliding mode along the extending direction of the guide rails (7), transverse cylinders (9) are symmetrically arranged on two sides of the top of the operation table (1), cylinder shafts (10) of the two transverse cylinders (9) are fixedly connected with the two sliding mechanisms (8) respectively, the top of the sliding mechanism (8) on the left side is fixedly connected with a lifting clamp tool (11), and the top of the sliding mechanism (8) on the right side is fixedly connected with a rotating clamp tool (12);
the control module comprises an electric appliance cabinet (13) arranged in the operation table (1), and a display (14) and an alarm (15) which are arranged on one side of the top of the operation table (1), wherein a PLC (programmable logic controller) is arranged in the electric appliance cabinet (13);
the driving module comprises an air pump (16) used for driving the transverse air cylinder (9), and the air pump (16) is arranged inside the operating platform (1).
2. An aircraft fuel system test rig according to claim 1, wherein: the front end of the lifting frame (2) is provided with an inclined sliding table (17) which is attached to the upper surface of the oil pump table (5).
3. An aircraft fuel system test rig according to claim 1, wherein: sliding openings (18) are formed in the two sides of the lifting frame (2), a lifting support (19) fixedly connected with the lifting plate (4) is connected to the inner wall of each sliding opening (18) in a sliding mode, the bottom of the lifting frame (2) is provided with a first motor (20), the bottom of the lifting frame (2) is also rotationally connected with a rotating shaft (21), the first motor (20) is meshed with the rotating shaft (21) through a gear, two ends of the rotating shaft (21) penetrate through the lifting frame (2) and are fixedly connected with first bevel gears (22) positioned on two sides of the lifting frame (2), the two sides of the lifting frame (2) are also rotatably connected with screw rods (23), the screw rods (23) penetrate through the lifting support (19) and are in threaded connection with the lifting support (19), and a second bevel gear (25) in meshed connection with the first bevel gear (22) is fixedly connected to the surface of the screw rod (23).
4. An aircraft fuel system test rig according to claim 1, wherein: the top of the lifting plate (4) is rotatably connected with a rotary cylinder (24), the oil pump platform (5) is rotatably arranged on the lifting plate (4) through the rotary cylinder (24), and the angle rotation range of the rotary cylinder (24) is 0-90 degrees.
5. An aircraft fuel system test rig according to claim 1, wherein: slide mechanism (8) are including blocking on guide rail (7) and along the slider (801) of guide rail (7) extending direction gliding, the top fixedly connected with mounting panel (802) of slider (801).
6. An aircraft fuel system test rig according to claim 1, wherein: lifting clamp frock (11) are including fixed connection at the left Y axle moving platform (1101) at slide mechanism (8) top, one side fixedly connected with bearing frame (1102) of Y axle moving platform (1101), one side of bearing frame (1102) is rotated and is connected with cardboard (1103), one side lower extreme fixedly connected with and the ram (1104) of raising groove (6) assorted of cardboard (1103), one side upper end fixed mounting of cardboard (1103) has vertical cylinder (1105), the bottom fixedly connected with depression bar (1106) of vertical cylinder (1105).
7. An aircraft fuel system detection test rig according to claim 6, wherein: an oil pump pressure sensing area (1107) is arranged on one side of the clamping plate (1103), and a pressure sensor is arranged inside the oil pump pressure sensing area (1107).
8. An aircraft fuel system test rig according to claim 1, wherein: the rotary clamp tool (12) comprises two fixing plates (1201) fixed to the top of the sliding mechanism (8) on the right side, a second motor (1202) is fixedly connected to one side of the fixing plate (1201) on the right side, an output shaft of the second motor (1202) penetrates through the fixing plate (1201) on the right side and is fixedly connected with a driving wheel (1209), the other side of the fixing plate (1201) on the right side is rotatably connected with a driven wheel (1203), a belt is in transmission connection with the surfaces of the driven wheel (1203) and the driving wheel (1209), a rotating shaft (1204) is fixedly connected to one ends of the driving wheel (1209) and the driven wheel (1203), and one end of the rotating shaft (1204) penetrates through the fixing plate (1201) on the left side and is fixedly connected with a three-head clamp.
9. An aircraft fuel system test rig according to claim 8, wherein: the three-head clamp comprises a clamp seat (1205), a spring seat (1206) is arranged on one side of the clamp seat (1205), a chuck (1207) is fixedly connected to one side of the spring seat (1206), the chuck (1207) is close to a limit shaft (1208) fixedly connected to the center of one side of the clamp seat (1205), and one end of the limit shaft (1208) is in clearance fit with the center of the clamp seat (1205) and is rotatably connected with the clamp seat (1205).
10. An aircraft fuel system detection test rig according to claim 6, wherein: the opposite sides of the cantilever lever (1104) and the pressure lever (1106) are both arranged in an arc shape, and the opposite sides of the cantilever lever (1104) and the pressure lever (1106) are both provided with rubber pads.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202011017335.6A CN112208788B (en) | 2020-09-24 | 2020-09-24 | Aircraft fuel system detection test bench |
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|---|---|---|---|
| CN202011017335.6A CN112208788B (en) | 2020-09-24 | 2020-09-24 | Aircraft fuel system detection test bench |
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| CN112208788A CN112208788A (en) | 2021-01-12 |
| CN112208788B true CN112208788B (en) | 2022-04-05 |
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| CN116252963B (en) * | 2023-03-15 | 2024-02-09 | 北京科荣达航空科技股份有限公司 | Aircraft fuel system detects test bench |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104100512A (en) * | 2013-04-03 | 2014-10-15 | 上海航新航宇机械技术有限公司 | Fuel pump test bed |
| CN109958612A (en) * | 2019-03-29 | 2019-07-02 | 宁波星箭航天机械有限公司 | Airplane hydraulic pressure oil pump ground drives testing equipment |
| CN210099719U (en) * | 2019-04-30 | 2020-02-21 | 江苏湖润泵业科技有限公司 | Automatic unloading and recycling device for oil pump workpiece carrying disc |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9108730B2 (en) * | 2011-10-11 | 2015-08-18 | Victor A. Grossman | Rapid store load system for aircraft and method of operation thereof |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104100512A (en) * | 2013-04-03 | 2014-10-15 | 上海航新航宇机械技术有限公司 | Fuel pump test bed |
| CN109958612A (en) * | 2019-03-29 | 2019-07-02 | 宁波星箭航天机械有限公司 | Airplane hydraulic pressure oil pump ground drives testing equipment |
| CN210099719U (en) * | 2019-04-30 | 2020-02-21 | 江苏湖润泵业科技有限公司 | Automatic unloading and recycling device for oil pump workpiece carrying disc |
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