Practical training device for detection test of airplane total static pressure system

Abstract

The utility model provides an aircraft total static pressure system detection test training device, which belongs to the technical field of aircraft training, and comprises two groups of gas path detection systems, each gas path detection system comprises a first gas supply pipe, the end part of each gas supply pipe is connected with a driving pump, the driving pump is connected with a motor, and the first gas supply pipe is also provided with a communication switch; the four-way connector is connected to the other end of the first gas feeding pipe and used for gas steering transmission; the second air supply pipe is connected to the four-way connector, the other end of the second air supply pipe is connected with a pressure gauge, and the pressure gauge is used for detecting and digitally displaying static pressure or dynamic pressure in the pipeline; the third air supply pipe is connected to the four-way connector, and an air release switch is further arranged on the third air supply pipe; the fourth air supply pipe is connected to the four-way connector, the fourth air supply pipe is connected with an airspeed pipe connector, the airspeed pipe connector is connected with an airspeed system, and the airspeed system comprises a lifting speedometer; according to the utility model, the practical operation effect of trainees can be achieved through the practical training device without operation on an airplane.

Description

Technical Field

[0001] This utility model relates to the field of aircraft training equipment technology, specifically to an aircraft hydrostatic system testing and training device. Background Technology

[0002] The total static pressure system (TPSPS) of an aircraft is a crucial component of aviation equipment. Its main function is to collect total pressure and static pressure signals from the atmosphere and transmit these signals to key equipment and systems such as air data instruments, flight control systems, and air data computers. The sealing and unobstructed flow of the TPSPS directly affect the aircraft's flight performance and safety. Therefore, regularly testing and inspecting the TPSPS to ensure its stable and reliable performance is an important part of aircraft maintenance.

[0003] The testing, inspection, and maintenance of total static pressure systems are not only crucial for ensuring flight safety but also essential professional skills for aircraft maintenance personnel. Every year, a large number of new maintenance personnel need to master the basic principles, operating methods, testing procedures, and maintenance techniques of total static pressure systems through systematic learning and practice. However, the locations of the relevant components of the total static pressure system on aircraft are concealed, making them difficult to observe and operate, which poses a significant challenge to the learning of new maintenance personnel. Furthermore, the heavy workload of military training missions limits the availability of sufficient aircraft for new maintenance personnel to learn and practice on, further exacerbating the shortage of training resources. Utility Model Content

[0004] In view of this, the present invention provides a training device for testing and experimenting with an aircraft hydrostatic system. The present invention allows trainees to achieve the effect of hands-on practice without having to operate the equipment on an aircraft.

[0005] To solve the above-mentioned technical problems, this utility model provides an aircraft full static pressure system testing and training device, including two sets of air path testing systems. Each air path testing system includes a first air supply pipe, the end of which is connected to a drive pump. The drive pump is connected to a motor, and the motor can drive the drive pump to work. A connection switch is also provided on the first air supply pipe. The drive pump is used to create a positive pressure environment on the first air supply pipe of one set of air path testing systems and to create a static pressure environment on the first air supply pipe of the other set of air path testing systems.

[0006] The four-way connector is connected to the other end of the first gas supply pipe and is used to redirect the gas flow.

[0007] The second air supply pipe is connected to a four-way connector, and a pressure gauge is connected to the other end. The pressure gauge is used to detect and display the static or dynamic pressure in the pipe.

[0008] The third air supply pipe is connected to the four-way connector and is equipped with a vent switch, which can control the opening and closing of the third air supply pipe.

[0009] The fourth air supply pipe is connected to the four-way connector. The airflow between the first air supply pipe and the fourth air supply pipe can flow between them. The fourth air supply pipe is connected to an airspeed pipe interface, which is connected to the airspeed system. The airspeed system includes a speedometer, which can detect pressure changes in the pipe.

[0010] The third air supply pipe is also connected to an exhaust pipe, which is used to discharge the gas to the external environment.

[0011] The fourth air supply pipe is connected to an air speed tube via an interface nozzle. The interface nozzle allows for a detachable connection between the air speed tube and the fourth air supply pipe. The air speed tube interface is located on the air speed tube, making it easy to remove the air speed tube interface and the air speed tube for storage.

[0012] It also includes a timer, which is used to accurately measure the parameters being measured, and the timer makes it easy to understand the rate of increase of positive or negative pressure.

[0013] It also includes a cooling fan installed inside the device, which is used to dissipate heat from the internal circuit components.

[0014] It also includes an airspeed tube heater installed inside the device, which is used to heat the airspeed tube, thereby simulating the operation of the airspeed tube heater in a high-altitude environment.

[0015] The drive pump and / or pitot tube heater are connected to indicator lights, which provide a clear indication of whether the drive pump and / or pitot tube heater are operating.

[0016] The training equipment includes a storage cabinet, which is used to store the components to be tested and the instruction manuals and accessories. The storage cabinet facilitates the storage and placement of accessories or miscellaneous items.

[0017] The training device also includes multiple casters at the bottom, which enable the device to move.

[0018] In summary, compared with the prior art, this application includes at least one of the following beneficial technical effects:

[0019] 1. Highly Practical: This training device provides maintenance personnel with a practical platform that closely resembles the actual working environment by simulating the full hydrostatic system of an aircraft. Maintenance personnel can conduct systematic learning and practice on this device without operating on a real aircraft, thereby reducing training costs and improving training efficiency.

[0020] 2. Comprehensive Functions: The training device includes two sets of air path detection systems, capable of creating positive pressure and static pressure environments respectively to meet the needs of different testing experiments. Simultaneously, the device is also equipped with components such as pressure gauges, vent switches, exhaust pipes, and airspeed pipes, enabling comprehensive testing of the sealing and unobstructed flow of the full static pressure system, ensuring stable and reliable system performance.

[0021] 3. Intelligent Design: The training device incorporates intelligent designs such as a timer, cooling fan, airspeed tube heater, and indicator lights. The timer accurately records the time, helping maintenance personnel understand the rate of positive or negative pressure rise; the cooling fan dissipates heat from the internal circuit components, ensuring stable operation of the device over long periods; the airspeed tube heater simulates operation in a high-altitude environment, improving the realism and accuracy of the training; and the indicator lights visually display the working status of the drive pump and airspeed tube heater, facilitating timely problem detection and handling by maintenance personnel.

[0022] 4. High Convenience: The training device uses a detachable pitot tube and pitot tube interface, which is easy to disassemble and store, improving ease of use. In addition, multiple casters are installed at the bottom of the device for easy movement and transport, meeting the needs of different scenarios.

[0023] 5. Wide Applicability: This training device is not only suitable for training and learning new maintenance personnel, but can also serve as a tool for professional technicians in the aviation maintenance field to improve their skills and undergo assessments. Through this device, maintenance personnel can gain a deeper understanding of the basic principles, operating methods, testing procedures, and maintenance techniques of the total hydrostatic system, providing strong support for aircraft flight safety and performance stability. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the gas path principle of this utility model;

[0025] Figure 2 This is a schematic diagram of the circuit principle of this utility model.

[0026] Explanation of reference numerals in the attached figures:

[0027] 1. Drive pump; 2. First air supply pipe; 3. Connecting switch; 4. Four-way connector; 5. Second air supply pipe; 6. Pressure gauge; 7. Third air supply pipe; 8. Vent switch; 9. Fourth air supply pipe; 10. Speed ​​gauge; 11. Exhaust pipe; 12. Air speed pipe; 13. Connecting nozzle. Detailed Implementation

[0028] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the following will be described in conjunction with the accompanying drawings of the embodiments of this utility model. Figure 1-2The technical solutions of the embodiments of this utility model are clearly and completely described herein. Obviously, the described embodiments are only some, not all, of the embodiments of this utility model. All other embodiments obtained by those skilled in the art based on the described embodiments of this utility model are within the protection scope of this utility model.

[0029] This embodiment provides a testing and training device for an aircraft's full static pressure system, such as... Figure 1-2 As shown: It includes two sets of gas path detection systems, which are used to detect positive and negative pressure respectively.

[0030] The positive pressure air path detection system includes a positive pressure drive pump 1 connected to a motor. The positive pressure drive pump 1 is connected to a first air delivery pipe 2. When the positive pressure drive pump 1 is working, it can deliver airflow into the first air delivery pipe 2, thereby creating a positive pressure environment in the pipe. The first air delivery pipe 2 is also equipped with a connection switch 3 for controlling the opening and closing of the pipe. The end of the first air delivery pipe 2 away from the positive pressure drive pump 1 is also connected to a four-way connector 4. The four-way connector 4 is used to redirect the airflow. The four-way connector 4 is also connected to a second air delivery pipe 5, a third air delivery pipe 7, and a fourth air delivery pipe 9. The third air delivery pipe 7 is equipped with a vent switch 8 for controlling the opening and closing of the pipe. The fourth air delivery pipe 9 is connected to an air speed mechanism. The air speed mechanism is equipped with a speed gauge 10, which can sense the air pressure in the air speed mechanism and display it digitally. The second air delivery pipe 5 is equipped with a pressure gauge 6, which can detect the air pressure in the pipe.

[0031] During positive pressure testing, check if the connecting switch 3 and the venting switch 8 are in the designated positions. Then, control the dynamic pressure drive pump 1 to work. When the dynamic pressure drive pump 1 is activated, you can hear the sound of it working. The dynamic pressure drive pump 1 will slowly pressurize the first air supply pipe 2. At this time, open the connecting switch 3, and the pipe will be gradually pressurized. When the airspeed indicator 10 in the airspeed mechanism reaches an indicated airspeed of 1500 km / h, quickly close the dynamic pressure connecting switch 3. When the indicated airspeed value of the airspeed system immediately stops rising, it indicates that the total pressure line of the airspeed system is unobstructed. Then, turn off the dynamic pressure pump switch and wait for 5 minutes. When the airspeed value indicated by the airspeed indicator 10 on the airspeed system drops by no more than 19 km / h, it indicates that the total pressure line of the airspeed system is well sealed. Finally, slowly open the dynamic pressure venting switch 8, and the airflow in the pipeline can be discharged through the third air supply pipe 7. That is, slowly venting the air will cause the airspeed indicator 10 of the airspeed system to return to zero (the values ​​of the airspeed indicator 10 and the pressure gauge 6 correspond to each other. When the values ​​of the airspeed indicator 10 and the pressure gauge 6 are different from the preset values, it means that one of the airspeed indicator 10 or the pressure gauge 6 is damaged and can no longer be used normally and needs to be replaced).

[0032] The air path detection system for static pressure includes a static pressure drive pump 1 connected to a motor. The static pressure drive pump 1 is connected to a first air delivery pipe 2. When the static pressure drive pump 1 is working, it can draw out the airflow in the first air delivery pipe 2 to create a static pressure environment in the pipe. The first air delivery pipe 2 is also equipped with a connection switch 3 for controlling the opening and closing of the pipe. The end of the first air delivery pipe 2 away from the static pressure drive pump 1 is also connected to a four-way connector 4. The four-way connector 4 is used to redirect and transmit the airflow. The four-way connector 4 is also connected to a second air delivery pipe 5, a third air delivery pipe 7, and a fourth air delivery pipe 9. The third air delivery pipe 7 is equipped with a venting switch 8 for controlling the opening and closing of the pipe. The fourth air delivery pipe 9 is connected to an air speed mechanism. The air speed mechanism is equipped with a speed gauge 10, which can sense the air pressure in the air speed mechanism and display it digitally. The second air delivery pipe 5 is equipped with a pressure gauge 6, which can detect the air pressure in the pipe.

[0033] During static pressure testing, check that the connecting switch 3 and the venting switch 8 are in the designated positions. Then, control the static pressure drive pump 1 to operate. The static pressure drive pump 1 will be audible when it operates. It slowly draws air from the piping system through the first air supply pipe 2 to create a static pressure environment. When the vertical speedometer 10 reaches an altitude of 12,000 meters, quickly close the static pressure connecting switch 3. At this point, the altitude reading on the vertical speedometer 10 should immediately stop rising, indicating good static pressure piping patency in the airspeed system. Turn off the static pressure drive pump 1 switch and start timing for 5 minutes. If the airspeed system's altitude reading drops by no more than 19 km / h, the static pressure piping of the airspeed system is well-sealed. Finally, slowly open the static pressure venting switch 8 to equalize the pressure, slowly releasing air until the airspeed system's altitude reading returns to zero.

[0034] Furthermore, the third air supply pipe 7 is also connected to an exhaust pipe 11, that is, when equalizing the pressure of the pipeline system, the airflow inside the pipeline system will be discharged to the external environment or the airflow in the external environment will enter the third air supply pipe 7 through the exhaust pipe 11.

[0035] Furthermore, the fourth air supply pipe 9 is equipped with an airspeed tube 12 at its end. The airspeed tube 12 has an airspeed tube 12 interface, and the airspeed system is connected to the airspeed tube 12 interface. That is, by setting the airspeed tube 12, the training experience of students can be enhanced and the simulation effect can be improved.

[0036] Furthermore, the airspeed tube 12 is connected to the interface nozzle 13. The interface nozzle 13 makes the airspeed tube 12 and the fourth air supply tube 9 detachable, so that the airspeed tube 12 can be easily removed for storage or maintenance.

[0037] Furthermore, the training device is also equipped with a timer, which allows trainees to keep track of time (the aforementioned timer is 5 minutes).

[0038] Furthermore, the training device also includes an airspeed tube 12 heater installed inside the device. The airspeed tube 12 heater is used to heat the airspeed tube 12. That is, the airspeed tube 12 needs to be heated when the aircraft is flying at high altitude to avoid the low temperature from affecting the detection or circuit system. The airspeed tube 12 heater can be set as an electric heating wire structure.

[0039] Furthermore, the dynamic pressure drive pump 1, the static pressure drive pump 1, and the air speed tube 12 heater are all connected to indicator lights. The indicator lights allow for a direct observation of whether the dynamic pressure drive pump 1, the static pressure drive pump 1, and the air speed tube 12 heater are working properly. If the indicator lights do not display normally, it means that the dynamic pressure drive pump 1, the static pressure drive pump 1, or the air speed tube 12 heater needs maintenance.

[0040] Furthermore, the training device also includes a cooling fan installed inside the device. The cooling fan is used to dissipate heat from the internal circuit components, thereby preventing the circuit system from collapsing or burning out due to high temperature.

[0041] The training device also includes a storage cabinet, which is used to store the components to be tested and the instruction manuals and accessories, thus enabling the storage of some miscellaneous items and accessories.

[0042] The training device is also equipped with an operation panel, which is used to control the static pressure drive pump 1, dynamic pressure drive pump 1, air speed tube 12 heater, and timer switch. The pressure gauge 6 is also located on the control panel for easy operation by the trainees.

[0043] The training device also includes multiple casters at the bottom, which enable the device to move.

[0044] Corresponding to the two sets of gas path detection systems mentioned above, the training device is also equipped with a power supply system, such as... Figure 2 As shown: The power supply system includes a power supply unit, which is connected to the static pressure pump motor and the dynamic pressure pump motor via a fuse and a power switch. A voltmeter is also connected in parallel between the dynamic pressure pump motors to monitor the 24V DC power supplied by the power supply unit. Then, the positive pressure drive pump 1 motor and the static pressure drive pump 1 motor are controlled to work through two pressure switches respectively. At the same time, each of the two motors is connected in parallel with an indicator light. When the air pump motor is powered on, the corresponding indicator light lights up to indicate to the operator that the corresponding drive pump 1 is in working condition.

[0045] The power supply line of the power supply unit is also connected to the airspeed tube 12 heater via a fuse and a pressure switch. An indicator light is also connected in parallel to the airspeed tube 12 heater. When the indicator light is on, it indicates to the operator that the airspeed tube 12 heater is heating the airspeed tube 12.

[0046] The power supply unit's power transmission line is also connected to a timer and a USB interface via a DC-DC converter. The DC-DC converter converts the 24V DC power to 5V to power the minute and second timer on the operation panel and the USB 5V interface.

[0047] The power supply unit's power transmission line is also connected to a cooling fan, which can dissipate heat from the inside of the training device.

[0048] The power supply unit's transmission line is also connected to a voltmeter, which is used to monitor the voltage supplied by the power supply unit.

[0049] In this embodiment, there are two power supply units;

[0050] Firstly, it is connected to the mains power supply, and the current from the mains power supply is sent to the power supply line after passing through a switching power supply.

[0051] Secondly, it includes a battery pack installed inside the training device. The current delivered by the battery pack is converted to 24V DC by a DC-DC converter and then sent to the power supply line.

[0052] Furthermore, the battery pack can be recharged via a charger.

[0053] The two power supply units can be switched as needed via a switch. Furthermore, it should be noted that, in the description of this utility model, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0054] The above description is the preferred embodiment of this utility model. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of this utility model, and these improvements and modifications should also be considered within the protection scope of this utility model.

Claims

1. A testing and training device for an aircraft's total static pressure system, characterized in that: It includes two sets of gas path detection systems, wherein the gas path detection system includes; The first air supply pipe (2) is connected to a drive pump (1) at its end. The drive pump (1) is connected to a motor, and the first air supply pipe (2) is also equipped with a connection switch (3). The drive pump (1) is used to create a positive pressure environment on the first air supply pipe (2) of one set of air circuit detection systems and to create a static pressure environment on the first air supply pipe (2) of another set of air circuit detection systems. The four-way connector (4) is connected to the other end of the first gas supply pipe (2) for diverting gas transmission. The second air supply pipe (5) is connected to the four-way connector (4) and the other end is connected to a pressure gauge (6). The pressure gauge (6) is used to detect and display the static or dynamic pressure in the pipe. The third air supply pipe (7) is connected to the four-way connector (4) and the third air supply pipe (7) is also equipped with a venting switch (8); The fourth air supply pipe (9) is connected to the four-way connector (4). The fourth air supply pipe (9) is connected to the airspeed pipe interface, which is connected to the airspeed system, which includes a vertical speed gauge (10).

2. The aircraft full static pressure system testing and training device as described in claim 1, characterized in that: The third gas supply pipe (7) is also connected to an exhaust pipe (11) at its end, which is used to discharge gas to the external environment.

3. The aircraft full static pressure system testing and training device as described in claim 1, characterized in that: The fourth air supply pipe (9) is connected to the air speed pipe (12) at its end via an interface nozzle (13). The air speed pipe (12) and the fourth air supply pipe (9) are detachably connected via the interface nozzle (13). The air speed pipe interface is located on the air speed pipe (12).

4. The aircraft full static pressure system testing and training device as described in claim 1, characterized in that: It also includes a timer, which is used to accurately time the measured parameter.

5. The aircraft full static pressure system testing and training device as described in claim 4, characterized in that: It also includes a cooling fan installed inside the device, which is used to dissipate heat from the internal circuit components.

6. The aircraft full static pressure system testing and training device as described in claim 4, characterized in that: It also includes an airspeed tube heater disposed inside the device, which is used to heat the airspeed tube.

7. The aircraft full static pressure system testing and training device as described in claim 4, characterized in that: The drive pump (1) and / or air tube heater are connected to indicator lights.

8. The aircraft full static pressure system testing and training device as described in claim 1, characterized in that: The training device includes a storage cabinet, which is used to store the components to be tested and the instruction manuals and accessories.

9. The aircraft full static pressure system testing and training device as described in claim 4, characterized in that: The training device also includes multiple casters at the bottom.

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