CN219382814U - High-altitude acceleration inspection instrument - Google Patents

Abstract

The utility model discloses a high-altitude acceleration tester, which comprises a tester body, a pipeline room, an upper cover, a handle, a display, a vacuumizing pipe, a partition board, an auxiliary oil way process cover, a first pressure sensor, a pushing handle, a device room, a controller, universal wheels, a vacuumizing machine, a servo electromagnetic valve, a nozzle and a second pressure sensor, wherein the interior of the tester body is arranged between the pipeline room and the device room through the partition board, the pipeline room is positioned above the device room, the upper cover is arranged between the pipeline room, the handle is arranged on the upper cover, the display is arranged on the front surface of the pipeline room, the pushing handle is arranged on the side edge of the tester body, the universal wheels are arranged at the lower part of the tester body, the controller and the vacuumizing machine are arranged at the lower part of the device room, and the vacuumizing pipe and the auxiliary oil way process cover are arranged in the pipeline room. The high-altitude acceleration tester is simple and compact in structure and convenient to operate, can automatically test the high-altitude acceleration of the aircraft engine, and better improves the high-altitude acceleration precision of the aircraft engine.

Description

High-altitude acceleration inspection instrument

Technical Field

The utility model relates to the technical field of airplane test flight test, in particular to a high-altitude acceleration detector.

Background

The high-altitude acceleration is one of important indexes for measuring the performance of an aircraft, and when the aircraft is used for replacing an engine or performing high-altitude acceleration flight verification, the high-altitude acceleration performance of the aircraft engine needs to be simulated, checked and detected on the ground, so that the aircraft engine is ensured to be safely used in the flight range, and the measurement requirement of the high-altitude acceleration performance index of the aircraft is met. The high-altitude acceleration performance of the aircraft is checked by using a vacuum pump to vacuumize a main pump high-altitude diaphragm capsule of the aircraft engine, adjusting the pressure of the vacuum pump to the pressure specified by vacuumizing the main pump high-altitude diaphragm capsule of the aircraft engine by adjusting an air extraction switch, and simultaneously checking the fuel pressure change condition of an auxiliary oil way of the aircraft engine, thereby achieving the purpose of checking the high-altitude acceleration time of the aircraft engine. At present, in a conventional aircraft engine high-altitude acceleration tester, the pressure of a vacuum pump pressure gauge and the pressure change of an auxiliary oil way of an aircraft engine are manually observed to reach a preset pressure time in the process of vacuumizing the aircraft engine through the vacuum pump, although the function test on the high-altitude acceleration of the aircraft engine can be completed. However, because the vacuumizing pressure is adjusted by manual observation, the overlarge vacuumizing pressure of the vacuumizing pump often appears, and the high-altitude diaphragm capsule of the aircraft engine is damaged, so that economic loss is caused, and meanwhile, the test flight work task of the aircraft test is influenced. In addition, errors often occur due to the fact that the pressure change time condition of the auxiliary oil way of the aircraft engine in the vacuumizing process is interpreted manually, and the high-altitude acceleration function checking effect of the aircraft engine is affected. In addition, the structure is very complex, and the operation is inconvenient, so that the high-altitude acceleration inspection efficiency of the aircraft engine is low.

Disclosure of Invention

The utility model mainly aims to solve the defects and provides the high-altitude acceleration tester which can reliably test the high-altitude acceleration of the aircraft engine and improve the accuracy and efficiency of the high-altitude acceleration test of the aircraft engine.

The utility model provides an high altitude acceleration inspection machine, including the inspection machine body, between the pipeline, the upper cover, the handle, a display, the evacuation tube, the baffle, vice oil circuit technology flap, first pressure sensor, the pushing hands, between the equipment, a controller, the universal wheel, the evacuation machine, servo solenoid valve, connect mouth and pressure sensor two, the inspection machine body is inside to be set up between pipeline and between the equipment through the baffle, be located between the equipment top between the pipeline, set up by the upper cover on the pipeline, be provided with the handle on the upper cover, the display sets up on the front between the pipeline, the pushing hands sets up on inspection machine body side, the universal wheel sets up in inspection machine body lower part, controller and evacuation machine set up in the lower part in between the equipment, evacuation tube and vice oil circuit technology flap are placed in the pipeline, be provided with pressure sensor one on the vice oil circuit technology flap, evacuation tube one end is connected its other end and is provided with connect mouth with, servo solenoid valve and pressure sensor two sets up in the evacuation tube, the display, first pressure sensor, the evacuation machine, servo solenoid valve and pressure sensor two are through cable electric connection with the controller.

Further, the high-altitude acceleration tester also comprises a temperature sensor, an air outlet and a fan, wherein the temperature sensor is arranged on the inner wall of the equipment room, the fan is arranged in the equipment room, the air outlet is arranged on the front surface of the equipment room, and the temperature sensor and the fan are electrically connected with the controller through cables.

Further, the high-altitude acceleration tester also comprises a flow sensor, wherein the flow sensor is arranged in the vacuumizing tube and is electrically connected with the controller through a cable.

Further, the controller of the high-altitude acceleration tester is a singlechip processor, an MCU processor or a PLC processor.

Compared with the prior art, the utility model has the following beneficial technical effects: the high-altitude acceleration tester is simple and compact in structure and convenient to operate, can automatically test the high-altitude acceleration of the aircraft engine, better improves the high-altitude acceleration precision of the aircraft engine, ensures the safety of test work, improves the efficiency of high-altitude acceleration test of the aircraft engine, ensures the test flight work task of the aircraft test, and is suitable for popularization and use.

Drawings

Fig. 1 is a schematic structural view of the present utility model.

Fig. 2 is a logic diagram of the present utility model.

In the figure, 1, an inspection tester body; 2. the pipelines are connected; 3. an upper cover; 4. a handle; 5. a display; 6. vacuumizing the tube; 7. a partition plate; 8. a process port cover of the auxiliary oil way; 9. a first pressure sensor; 10. pushing hands; 11. a temperature sensor; 12. the equipment room; 13. a controller; 14. an air outlet; 15. a fan; 16. a universal wheel; 17. a vacuum extractor; 18. a flow sensor; 19. a servo solenoid valve; 20. a nozzle; 21. and a second pressure sensor.

Detailed Description

The principles and features of the present utility model are described below with reference to the drawings, the examples being provided for illustration only and not for limitation of the scope of the utility model.

The high-altitude acceleration inspection instrument comprises an inspection instrument body 1, a pipeline room 2, an upper cover 3, a handle 4, a display 5, a vacuumizing tube 6, a partition 7, an auxiliary oil way process cover 8, a first pressure sensor 9, a pushing handle 10, a room 12, a controller 13, a universal wheel 16, a vacuumizing machine 17, a servo electromagnetic valve 19, a first connector 20 and a second pressure sensor 21, wherein the interior of the inspection instrument body 1 is arranged into the pipeline room 2 and the room 12 through the partition 7, the pipeline room 2 is positioned above the room 12, the upper cover 3 is arranged on the pipeline room 2, the handle 4 is arranged on the upper cover 3, the display 5 is arranged on the front surface of the pipeline room 2, the pushing handle 10 is arranged on the side edge of the inspection instrument body 1, the universal wheel 16 is arranged on the lower part of the inspection instrument body 1, the controller 13 and the vacuumizing machine 17 are arranged on the lower part in the room 12, the vacuumizing tube 6 and the auxiliary oil way process cover 8 are arranged in the pipeline room 2, the first pressure sensor 9 is arranged on the auxiliary oil way process cover 8, one end of the vacuumizing tube 6 is connected with the vacuumizing machine 17, the other end of the vacuumizing machine 20 is arranged, the servo electromagnetic valve 19 and the second connector 21 is arranged in the vacuum machine 17, the other end of the vacuum sensor is connected with the vacuumizing machine 21, the first pressure sensor is arranged on the front surface of the vacuum machine 9, the vacuum machine 13, and the vacuum sensor is electrically connected with the second pressure sensor 13 through the vacuum electromagnetic valve 17 and the pressure sensor 13.

To enable a good environment between the devices 12, normal use of the relevant devices is ensured. The high-altitude acceleration tester further comprises a temperature sensor 11, an air outlet 14 and a fan 15, wherein the temperature sensor 11 is arranged on the inner wall of the equipment room 12, the fan 15 is arranged in the equipment room 12, the air outlet 14 is arranged on the front surface of the equipment room 12, and the temperature sensor 11 and the fan 15 are electrically connected with the controller 13 through cables.

In order to enable real-time monitoring of the vacuum pumping quantity, the high-altitude acceleration tester further comprises a flow sensor 18, wherein the flow sensor 18 is arranged in the vacuum pumping tube 6, and the flow sensor 18 is electrically connected with the controller 13 through a cable.

To enable different types of processors to be satisfied, its applicability is improved. The controller 13 of the high-altitude acceleration tester is a single-chip processor, an MCU processor or a PLC processor.

The working principle of the utility model is as follows: the nozzle 20 on the vacuumizing tube 6 is connected to a main pump high-altitude diaphragm capsule of the engine, the auxiliary oil way process port cover 8 is arranged on an auxiliary oil way of the engine, the vacuumizing machine 17 is controlled by the controller 13 to work so as to vacuumize the main pump high-altitude diaphragm capsule of the engine, the first pressure sensor 9 monitors the vacuumizing pressure condition in real time and feeds back to the controller 13, the second pressure sensor 21 monitors the auxiliary oil way pressure condition of the engine in real time and feeds back to the controller 13, and the controller 13 judges vacuumizing time and auxiliary oil way pressure rising time so as to achieve the purpose of checking the high-altitude acceleration of the aircraft engine.

The utility model aims to integrate the universal devices into a whole for checking the high-altitude acceleration of an aircraft engine.

The foregoing description of the preferred embodiments of the utility model is not intended to limit the utility model to the precise form disclosed, and any such modifications, equivalents, and alternatives falling within the spirit and scope of the utility model are intended to be included within the scope of the utility model.

Claims (4)

1. An overhead acceleration tester, characterized in that: the high-altitude acceleration tester comprises a tester body (1), a pipeline room (2), an upper cover (3), a handle (4), a display (5), a vacuumizing tube (6), a partition plate (7), an auxiliary oil way process cover (8), a first pressure sensor (9), a pushing handle (10), a device room (12), a controller (13), a universal wheel (16), a vacuumizing machine (17), a servo electromagnetic valve (19), a connector (20) and a second pressure sensor (21), wherein the interior of the tester body (1) is arranged into the pipeline room (2) and the pipeline room (12) through the partition plate (7), the pipeline room (2) is positioned above the device room (12), the upper cover (3) is arranged on the pipeline room (2), the handle (4) is arranged on the upper cover (3), the display (5) is arranged on the front surface of the pipeline room (2), the pushing handle (10) is arranged on the side of the tester body (1), the universal wheel (16) is arranged at the lower part of the tester body (1), the controller (13) and the vacuumizing machine (17) are arranged in the vacuum pipe room (8) and the auxiliary oil way cover (6) is arranged in the device room (12), be provided with pressure sensor one (9) on auxiliary oil circuit technology flap (8), vacuum tube (6) one end is connected its other end with evacuating machine (17) and is provided with connect mouth (20), servo solenoid valve (19) and pressure sensor two (21) set up in vacuum tube (6), display (5), pressure sensor one (9), evacuating machine (17), servo solenoid valve (19) and pressure sensor two (21) pass through cable and controller (13) electric connection.

2. The high altitude acceleration tester according to claim 1, wherein: the high-altitude acceleration tester also comprises a temperature sensor (11), an air outlet (14) and a fan (15), wherein the temperature sensor (11) is arranged on the inner wall of the equipment room (12), the fan (15) is arranged in the equipment room (12), the air outlet (14) is arranged on the front surface of the equipment room (12), and the temperature sensor (11) and the fan (15) are electrically connected with the controller (13) through cables.

3. The high altitude acceleration tester according to claim 1 or 2, wherein: the high-altitude acceleration tester also comprises a flow sensor (18), wherein the flow sensor (18) is arranged in the vacuumizing tube (6), and the flow sensor (18) is electrically connected with the controller (13) through a cable.

4. A high altitude acceleration tester according to claim 3, wherein: the controller (13) is a singlechip processor, an MCU processor or a PLC processor.