Multifunctional atmosphere data system testing device

Abstract

The utility model provides a multifunctional atmosphere data system testing device. The device comprises a bus monitor and a test adapter. The bus monitor comprises a computer unit, an ARINC 429 bus, a CSDB bus and a Manchester bus. The test adapter comprises a signal conditioning distribution unit, a front panel control and a rear panel control. According to the utility model, a test product and temperature corresponding to a test item are selected through the front panel control, the signal conditioning distribution unit sends a corresponding test demand signal to the test product, and three types of buses are respectively communicated with airborne equipment of an airplane, an airplane control computer and an atmosphere indicating instrument and collect test feedback signals. The test feedback signal is processed based on the computer unit, the test result is obtained, the dual-system calibration requirement, the system test requirement and the single-piece test requirement are met at the same time, dual-system calibration test, system test and single-piece test can be achieved through one device, and the test efficiency is improved.

Description

Technical Field

[0001] The utility model relates to the field of aviation technology, in particular to a multifunctional atmospheric data system testing device. Background Art

[0002] The atmospheric data system is composed of sensors, atmospheric data computers, and indicating instruments. The sensors collect the atmospheric environment data of the aircraft and send them to the atmospheric data computer. After processing by the atmospheric data computer, the atmospheric data computer outputs parameter signals such as pressure altitude, altitude change rate, indicated airspeed, etc. to the corresponding indicating instruments for the pilot to determine the flight status. At the same time, the data is sent to other airborne systems such as automatic flight control and flight management as a source of working data.

[0003] The atmospheric data system generally adopts a combination of digital indication and mechanical instruments. The digital indication is transmitted through the bus for efficient data transmission. The indicating instrument provides the pilot with the status change trend while indicating the data. Transport aircraft are equipped with at least two complete atmospheric data systems to back up each other and provide indications to the pilot and co-pilot respectively. In view of the importance of the atmospheric data system on the aircraft, each aircraft needs to conduct inspection and calibration and system testing of the atmospheric data computer every 3 to 4 years on average. Inspection and calibration is used to detect the working performance of the atmospheric data computer and the consistency of multiple systems. System testing is used to detect the matching of various components of the system, and at the same time check the accuracy of the bus data and the reliability of the indicating instruments.

[0004] Currently, a successive test method is usually adopted to carry out inspection, calibration and system testing of multiple systems, which is inefficient. Utility Model Content

[0005] In view of this, it is necessary to provide a multifunctional atmospheric data system test device to solve the existing technical problem of low efficiency in detection, calibration and system testing of multiple systems.

[0006] In order to solve the above problems, the utility model provides a multifunctional air data system test device, including a bus monitor and a test adapter; the bus monitor includes a computer unit, an ARINC 429 bus, a CSDB bus and a Manchester bus, and the test adapter includes a signal conditioning distribution unit, a front panel control and a rear panel control;

[0007] wherein the bus monitor is connected to the test adapter via a bus test interface, and the test adapter is respectively connected to the first air data computer, the second air data computer and the aircraft indicating instrument via the rear panel controls;

[0008] Among them, the test product and temperature corresponding to the test item are selected through the front panel control, the signal conditioning distribution unit sends the corresponding test requirement signal to the test product, communicates with the aircraft's onboard equipment, aircraft control computer and atmospheric indicating instrument through the ARINC 429 bus, the CSDB bus and the Manchester bus respectively, and collects test feedback signals, and processes the test feedback signals based on the computer unit to obtain test results, thereby meeting the dual-system calibration requirements, system test requirements and single-piece test requirements.

[0009] Optionally, the bus monitor further includes a bus power processing unit consisting of a power adapter, a DC power module and a lithium battery pack;

[0010] The power adapter is connected to an external AC power supply and a DC power module respectively, and the DC power module is connected to the computer unit, the ARINC 429 bus, the CSDB bus, the Manchester bus and the lithium battery pack respectively.

[0011] Optionally, the bus monitor further includes a bus power input interface connected to the external AC power supply, and a USB interface and an RS232 interface for data transmission.

[0012] Optionally, the test adapter also includes a test power supply;

[0013] The test power supply is composed of a plurality of voltage conversion chips, switches and indicator lights. The test power supply is respectively connected to the external AC power supply and the test product to provide the voltage required by the test product.

[0014] Optionally, the front panel controls include a monitoring area and a selection area;

[0015] The test product and the temperature corresponding to the test product are selected by the rotary button in the selection area, and the status of the test product is displayed by the light in the monitoring area.

[0016] Optionally, the selection area includes a system selection area, a temperature selection area and a single-piece test selection area.

[0017] Optionally, the monitoring area includes a power supply monitoring area, a first system test monitoring area, a second system test monitoring area, an air pressure altitude test monitoring area, an altitude preselection test monitoring area, a temperature indication test monitoring area and an airspeed indication test monitoring area.

[0018] Optionally, the rear panel controls include a product connection area, a bus transmission area, and a power input area;

[0019] Among them, the product connection area is provided with a first atmospheric data computer interface, a second atmospheric data computer interface, a barometric altimeter interface, an altitude preselector interface, a temperature indicator interface and an airspeed indicator interface, the power input area is provided with a power plug and an external power interface, and the bus transmission area is provided with a first cross-linking interface, a second cross-linking interface and a bus test interface.

[0020] Optionally, the air pressure altitude test monitoring area, altitude preselection test monitoring area, temperature indication test monitoring area and airspeed indication test monitoring area are all provided with corresponding nighttime lighting power switches.

[0021] Optionally, the test adapter further includes a test box and a test bracket;

[0022] The conditioning and distribution unit, the front panel controls, the rear panel controls and the test power supply are installed inside the test box, and the test bracket is used for fixedly installing the first atmospheric data computer and the second atmospheric data computer.

[0023] The utility model has the following beneficial effects: the multifunctional atmospheric data system test device provided by the utility model comprises a bus monitor and a test adapter; the bus monitor comprises a computer unit, an ARINC 429 bus, a CSDB bus and a Manchester bus; the test adapter comprises a signal conditioning distribution unit, a front panel control and a rear panel control; the bus monitor is connected to the test adapter through a bus test interface; the test adapter is respectively connected to a first atmospheric data computer, a second atmospheric data computer and an aircraft indicating instrument through the rear panel control; the utility model selects a test product and a temperature corresponding to a test item through the front panel control; the signal conditioning distribution unit sends a corresponding test requirement signal to the test product; the test product communicates with an onboard device of an aircraft, an aircraft control computer and an atmospheric indicating instrument through the ARINC 429 bus, the CSDB bus and the Manchester bus respectively and collects a test feedback signal; the test feedback signal is processed based on the computer unit to obtain a test result; the dual-system calibration requirement, the system test requirement and the single-piece test requirement are met at the same time; the dual-system calibration test, the system test and the single-piece test can be realized by using one device, and the test efficiency is improved. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the embodiments of the utility model or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on the structures shown in these drawings without paying creative work.

[0025] Figure 1 A structural schematic diagram of an embodiment of a multifunctional air data system testing device provided by the utility model;

[0026] Figure 2 A schematic diagram of a signal conditioning distribution unit of an embodiment of a multifunctional air data system test device provided by the utility model;

[0027] Figure 3 An air data computer wiring diagram of an embodiment of a multifunctional air data system test device provided by the utility model;

[0028] Figure 4 An aircraft indicating instrument wiring diagram of an embodiment of a multi-function air data system test device provided by the utility model;

[0029] Figure 5 A test power supply schematic diagram of an embodiment of a multifunctional air data system test device provided by the utility model;

[0030] Figure 6 A front panel control diagram of an embodiment of a multi-function air data system test device provided by the utility model;

[0031] Figure 7 This is a diagram of the front and rear panel controls of an embodiment of a multi-function air data system test device provided by the utility model. DETAILED DESCRIPTION

[0032] It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0033] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0034] It should be noted that all directional indications in the embodiments of the present invention (such as up, down, left, right, front, back...) are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0035] In addition, the descriptions of "first", "second", etc. in the present utility model are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In addition, the technical solutions between the various embodiments can be combined with each other, but they must be based on the ability of ordinary technicians in the field to implement them. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the scope of protection required by the present utility model.

[0036] The embodiments of the utility model provide a detection device and system for an aircraft turbine generator, which are described below respectively.

[0037] Figure 1 The structure diagram of an embodiment of a multi-functional air data system test device provided by the utility model is as follows: Figure 1 As shown, the multifunctional air data system test device includes a bus monitor and a test adapter; the bus monitor includes a computer unit, an ARINC 429 bus, a CSDB bus and a Manchester bus, and the test adapter includes a signal conditioning distribution unit, a front panel control and a rear panel control;

[0038] The bus monitor is connected to the test adapter via the bus test interface, and the test adapter is connected to the first air data computer, the second air data computer and the aircraft indicating instrument respectively via the rear panel control;

[0039] Among them, the test product and temperature corresponding to the test item are selected through the front panel controls, and the corresponding test requirement signal is sent to the test product through the signal conditioning distribution unit. The ARINC 429 bus, CSDB bus and Manchester bus are used to communicate with the aircraft's onboard equipment, aircraft control computer and atmospheric indicating instrument respectively, and the test feedback signal is collected. The test feedback signal is processed based on the computer unit to obtain the test result, which meets the dual-system calibration requirements, system test requirements and single-piece test requirements.

[0040] It should be noted that in the embodiment of the utility model, the bus monitor communicates with airborne equipment such as the attitude computer, the navigation computer, and the flight parameter recorder through the ARINC 429 bus, communicates with the flight control computer through the CSDB bus, and communicates with the atmospheric indicating instrument inside the atmospheric data system through the Manchester bus. In order to meet the monitoring function of the two sets of atmospheric data systems, the bus of the utility model is equipped with two detection channels. To facilitate on-site testing and data analysis, the circuits of the three types of buses are designed inside the bus monitor. The computer unit mainly provides a hardware basic platform and a human-computer interaction interface for the device, and is composed of an industrial control mainboard, a display component, a keyboard component, a touchpad component, an indicator light component, etc. The mainboard of the computer unit has at least 1 RS232 external interface, 2 USB2.0 serial external interfaces, 1 RS232 internal interface, 2 USB2.0 serial internal interfaces and 1 32-bit PCI (Peripheral Component Interconnect, peripheral component interconnection standard) expansion slot, ARINC The 429 bus uses a commercial PCI bus card and is connected to the motherboard's 1-way PCI expansion slot via a flexible cable, providing at least 2 ARINC 429 transceiver channels. The CSDB bus converts the motherboard's 2-way built-in USB interface into a CSDB bus interface connected to the test product, providing 2 CSDB transceiver channels. The Manchester bus converts the motherboard's 1-way built-in RS232 interface into a Manchester bus with 2-way receiving and 1-way sending functions. Figure 2 This is a schematic diagram of a signal conditioning distribution unit of an embodiment of a multifunctional air data system test device provided by the utility model. The specific structure of the signal conditioning distribution unit can be referred to Figure 2 , Figure 3 An air data computer wiring diagram of an embodiment of a multi-function air data system test device provided by the utility model; Figure 4 The aircraft indicating instrument wiring diagram of the embodiment of the multi-function air data system test device provided by the utility model can be implemented according to Figure 3 and Figure 4 The aircraft indicating instruments and the air data computer are connected to the device for testing.

[0041] Compared with the prior art, the utility model provides a multifunctional atmospheric data system test device, which includes a bus monitor and a test adapter; the bus monitor includes a computer unit, an ARINC 429 bus, a CSDB bus and a Manchester bus; the test adapter includes a signal conditioning distribution unit, a front panel control and a rear panel control; the bus monitor is connected to the test adapter through a bus test interface; the test adapter is respectively connected to a first atmospheric data computer, a second atmospheric data computer and an aircraft indicating instrument through the rear panel control; the utility model selects a test product and a temperature corresponding to a test item through the front panel control, uses a signal conditioning distribution unit to send a corresponding test requirement signal to the test product, communicates with an onboard device of an aircraft, an aircraft control computer and an atmospheric indicating instrument through the ARINC429 bus, the CSDB bus and the Manchester bus respectively and collects a test feedback signal, processes the test feedback signal based on the computer unit, obtains a test result, and satisfies the dual-system calibration requirements, the system test requirements and the single-piece test requirements at the same time; one device can be used to realize the dual-system calibration test, the system test and the single-piece test, thereby improving the test efficiency.

[0042] In some embodiments of the utility model, the bus monitor further includes a bus power processing unit composed of a power adapter, a DC power module and a lithium battery pack;

[0043] The power adapter is connected to an external AC power source and a DC power module respectively, and the DC power module is connected to a computer unit, an ARINC 429 bus, a CSDB bus, a Manchester bus and a lithium battery pack respectively.

[0044] It can be understood that in the embodiment of the utility model, the power processing unit mainly includes a power adapter, a DC-ATX power module, and a lithium battery pack. The power adapter converts the 220V AC power supply into a 12V DC power supply, enters the bus monitor through the power input interface, and provides an external power supply for the device. The 12V DC power supply is converted through the DC-ATX power module to provide the computer unit and the bus with the ±12V, +5V, and +3.3V power supplies required for work. The other path is converted through the charging and discharging plate of the lithium battery pack to charge the lithium battery pack. At the same time, the lithium battery pack provides a backup power supply channel for the DC-ATX power module.

[0045] In some embodiments of the present invention, the bus monitor further includes a bus power input interface for accessing an external AC power supply, and a USB interface and an RS232 interface for data transmission.

[0046] Reference Figure 5 , Figure 5A test power supply schematic diagram of an embodiment of a multifunctional air data system test device provided by the utility model. In some embodiments of the utility model, the test adapter further includes a test power supply;

[0047] Among them, the test power supply is composed of multiple voltage conversion chips, switches and indicator lights. The test power supply is connected to the external AC power supply and the test product respectively to provide the voltage required by the test product.

[0048] refer to Figure 6 , Figure 6 A diagram of a front panel control of an embodiment of a multifunctional air data system test device provided by the utility model. In some embodiments of the utility model, the front panel control includes a monitoring area and a selection area;

[0049] Among them, the test product and the temperature corresponding to the test product are selected by the rotary button in the selection area, and the status of the test product is displayed by the light in the monitoring area; the selection area includes a system selection area, a temperature selection area and a single-piece test selection area; the monitoring area includes a power supply monitoring area, a first system test monitoring area, a second system test monitoring area, an air pressure altitude test monitoring area, an altitude preselection test monitoring area, a temperature indication test monitoring area and an airspeed indication test monitoring area.

[0050] It can be understood that in the embodiment of the present utility model, Figure 2 The ACD1 test monitoring area is the first system test monitoring area, the ADC2 test monitoring area is the second system test monitoring area, the ALL test monitoring area is the pressure altitude test monitoring area, the PRE test monitoring area is the altitude preselection test monitoring area, the TAI test monitoring area is the temperature indication test monitoring area, and the ASI test monitoring area is the airspeed indication test monitoring area; the power monitoring area is used to complete the monitoring of the power supply of the device and the test product, and provide a current and voltage measurement interface to measure the current and voltage; the first system test monitoring area, the second system test monitoring area, the pressure altitude test monitoring area, the altitude preselection test monitoring area, the temperature indication test monitoring area and the airspeed indication test monitoring area are used to display the status of each test product through light signals when performing their respective corresponding tests, so as to achieve the purpose of monitoring the test product; the system selection area is used to select the first or second system when connecting to two sets of atmospheric data systems for system testing; the temperature selection area is used to simulate the signal output by the aircraft total temperature sensor; the single-piece test selection area is used to adjust the signal distribution inside the test adapter according to the test object when performing a single-piece test.

[0051] refer to Figure 7 , Figure 7 A diagram of the front and rear panel controls of an embodiment of a multifunctional air data system test device provided by the utility model. In some embodiments of the utility model, the rear panel controls include a product connection area, a bus transmission area, and a power input area;

[0052] Among them, the product connection area is equipped with the first atmospheric data computer interface ( Figure 3 ADC1 air data computer in), second air data computer interface ( Figure 3 The bus transmission area is provided with a first cross-linking interface (ADC1 cross-linking interface), a second cross-linking interface (ADC2 cross-linking interface) and a bus test interface.

[0053] It can be understood that in the embodiment of the utility model, the power input area is used to connect to an external AC power supply and is provided with overcurrent protection. The various product interfaces in the product connection area are connected to corresponding test products and are used to transmit electrical signals when performing system testing or single-piece testing. The first cross-linking interface and the second cross-linking interface are function expansion interfaces, which are used to perform cross-linking tests with other airborne systems such as flight control systems and anti-collision systems when necessary.

[0054] In some embodiments of the utility model, the air pressure altitude test monitoring area, the altitude preselection test monitoring area, the temperature indication test monitoring area and the airspeed indication test monitoring area are all provided with corresponding nighttime lighting power switches.

[0055] In the specific implementation, after completing the electrical connection between the test product and the device, start the bus monitor power supply to enter the test interface and turn on the power switch of the test adapter, and the device enters the test state; the "Channel 1", "Channel 2", and "Battery" switches on the test adapter simulate the main bus, spare bus, and battery on the machine to power the product, respectively, and the signal conditioning and distribution unit provides a total temperature simulation signal for the system under test. The external universal atmospheric comprehensive measuring instrument provides static pressure and total pressure. At this time, the atmospheric data computer starts to collect the atmospheric simulation data input by the bus monitor and outputs feedback information to the bus monitor through three types of buses. The line monitor determines the performance of the system under test by comparing the input value and the bus reading value, including 3 ARINC429 buses, 2 CSDB buses and 4 Manchester buses; the temperature selection zone switch of the test adapter controls the signal conditioning distribution circuit to provide 9 preset parameters in the range of -40℃ to 40℃ with a step of 10℃, and outputs the total temperature analog signal to the system under test; when the switch in the system selection zone is set to ADC1, the data collected by the first atmospheric data computer is sent to the pressure altimeter, altitude preselector, temperature indicator and airspeed indicator under test through the Manchester bus, After being internally decoded by each indicating instrument, it is displayed on its instrument panel. Similarly, when the switch is set to ADC2, the data collected by the second atmospheric data computer is sent to each indicating instrument for display; when the switch in the system selection area is set to OFF, the Manchester bus detection source of the bus monitor is set through the switch in the single test selection area. When single products such as the pressure altimeter, altitude preselector, temperature indicator and airspeed indicator are selected for testing, the Manchester bus sending channel of the bus monitor is connected to the receiving channel of the corresponding product, and the data set by the test software is sent to the instrument under test. The Manchester bus receiving channel of the bus monitor receives the feedback value of each instrument or monitors the sending data; the first system test monitoring area and the second system test monitoring area on the test adapter panel are provided with a control switch to provide the product under test with discrete signals of external states such as landing gear lowering and overspeeding, and the pressure altitude test monitoring area, the altitude preselection test monitoring area, the temperature indication test monitoring area and the airspeed indication test monitoring area are provided with a lighting switch to provide each instrument with a nighttime lighting power supply of different amplitudes. The monitoring area is provided with an indicator light to indicate the status signal output by the test product, and a test hole and an inspection plug are provided to provide a signal detection interface.

[0056] It can be understood that in the specific implementation of the present invention, when the dual-machine calibration is performed on the performance of the dual-machine atmospheric data computers, the object to be tested is only two atmospheric data computers. According to the technical requirements of the product to be tested, the universal atmospheric comprehensive measuring instrument is controlled to input the standard static pressure and total pressure and set the total temperature parameters. The performance and consistency of the two ADCs are determined by reading the engineering values ​​decoded by the three buses ARINC429, CSDB, and Manchester on the test software and comparing them with the input parameters; when performing a system test, the object to be tested includes one of the first atmospheric data computer or the second atmospheric data computer, and also includes a pressure altimeter, an altitude preselector, a temperature indicator, and an airspeed indicator. After setting the test environment, the data source of the indicating instrument is set through the system selection area switch of the test adapter, and the system state is determined by comparing the bus data read by the test software, the indication values ​​of each indicating instrument, and the input parameters; when performing a single-piece test, the test object is set with the single-piece test selection area switch of the test adapter. At this time, the internal signal distribution unit of the adapter switches the bus to the corresponding channel, and the bus monitor sends the simulated atmospheric data through the Manchester bus. The performance of the test piece to be tested is determined by comparing the bus setting value and the instrument indication value.

[0057] In some embodiments of the present utility model, the test adapter further comprises a test box and a test bracket;

[0058] The conditioning and distribution unit, the front panel controls, the rear panel controls and the test power supply are installed inside the test box, and the test bracket is used for fixing the first air data computer and the second air data computer.

[0059] It can be understood that in the embodiment of the utility model, the test box adopts a 6U standard chassis with an overall size of 482.5mm (width) × 267mm (height) × 576mm (depth), and two test brackets are fixedly installed on the top of the test adapter, and the two brackets are independent components, which are used to fix the first atmospheric data computer and the second atmospheric data computer to complete the electrical connection between the test product and the test adapter. Each bracket is fixed to the top of the test adapter with 4 M6 screws, and a plug-in connector connected to the atmospheric data computer is fixed at the rear of the bracket. The cable is connected to the product connection area of ​​the rear panel control through a 106-pin rectangular connector.

[0060] The above description is only a preferred specific implementation manner of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by any technician familiar with the technical field within the technical scope disclosed in the present invention should be included in the protection scope of the present invention.

Claims

1. A multifunctional air data system test device, characterized in that: It includes a bus monitor and a test adapter; the bus monitor includes a computer unit, an ARINC 429 bus, a CSDB bus and a Manchester bus, and the test adapter includes a signal conditioning distribution unit, a front panel control and a rear panel control; wherein the bus monitor is connected to the test adapter via a bus test interface, and the test adapter is respectively connected to the first air data computer, the second air data computer and the aircraft indicating instrument via the rear panel controls; The front panel control selects the test product and temperature corresponding to the test item, the signal conditioning distribution unit sends the corresponding test requirement signal to the test product, the ARINC 429 bus, the CSDB bus and the Manchester bus communicate with the aircraft's onboard equipment, the aircraft control computer and the atmospheric indicating instrument respectively and collect test feedback signals, and the computer unit processes the test feedback signals to obtain test results.

2. The multifunctional air data system test device according to claim 1, characterized in that: The bus monitor also includes a bus power processing unit consisting of a power adapter, a DC power module and a lithium battery pack; The power adapter is connected to an external AC power supply and a DC power module respectively, and the DC power module is connected to the computer unit, the ARINC 429 bus, the CSDB bus, the Manchester bus and the lithium battery pack respectively.

3. The multifunctional air data system test device according to claim 2, characterized in that: The bus monitor also includes a bus power input interface connected to the external AC power supply, and a USB interface and an RS232 interface for data transmission.

4. The multifunctional air data system test device according to claim 3, characterized in that: The test adapter also includes a test power supply; The test power supply is composed of a plurality of voltage conversion chips, switches and indicator lights. The test power supply is respectively connected to the external AC power supply and the test product to provide the voltage required by the test product.

5. The multifunctional air data system test device according to claim 4, characterized in that: The front panel controls include a monitoring area and a selection area; The test product and the temperature corresponding to the test product are selected by the rotary button in the selection area, and the status of the test product is displayed by the light in the monitoring area.

6. The multifunctional air data system test device according to claim 5, characterized in that: The selection area includes a system selection area, a temperature selection area and a single-piece test selection area.

7. The multifunctional air data system test device according to claim 6, characterized in that: The monitoring area includes a power supply monitoring area, a first system test monitoring area, a second system test monitoring area, an air pressure altitude test monitoring area, an altitude preselection test monitoring area, a temperature indication test monitoring area and an airspeed indication test monitoring area.

8. The multifunctional air data system test device according to claim 7, characterized in that: The rear panel controls include a product connection area, a bus transmission area, and a power input area; Among them, the product connection area is provided with a first atmospheric data computer interface, a second atmospheric data computer interface, a barometric altimeter interface, an altitude preselector interface, a temperature indicator interface and an airspeed indicator interface, the power input area is provided with a power plug and an external power interface, and the bus transmission area is provided with a first cross-linking interface, a second cross-linking interface and a bus test interface.

9. The multifunctional air data system test device according to claim 8, characterized in that: The air pressure altitude test monitoring area, the altitude preselection test monitoring area, the temperature indication test monitoring area and the airspeed indication test monitoring area are all provided with corresponding nighttime lighting power switches.

10. The multifunctional air data system test device according to claim 9, characterized in that: The test adapter also includes a test box and a test bracket; The conditioning and distribution unit, the front panel controls, the rear panel controls and the test power supply are installed inside the test box, and the test bracket is used for fixedly installing the first atmospheric data computer and the second atmospheric data computer.

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