A test apparatus and method for conducting a combustible liquid discharge test of an aircraft

Abstract

A test apparatus for conducting a combustible liquid discharge test of an aircraft, comprising: a liquid reservoir including a storage space for storing a test liquid, and including a reservoir outlet for exit of the test liquid; a liquid pump in fluid communication with the storage space for driving the test liquid to exit the liquid reservoir via the reservoir outlet; a discharge line in fluid communication with the reservoir outlet for flow of the discharged test liquid therethrough; and a spray head assembly connected to the other end of the discharge line opposite the end proximate the reservoir outlet for discharge of the discharged test liquid therefrom, further comprising: a discharge line liquid level sensing device disposed along the discharge line and configured to indicate whether the test liquid within the discharge line reaches a predetermined amount. Also related to a method of conducting a combustible liquid discharge test of an aircraft using the apparatus. With the test apparatus, the discharge time and discharge amount in the liquid discharge test flight can be precisely controlled, so as to improve the data accuracy and implementation reliability of the liquid discharge test flight.

Description

Technical Field

[0001] The present invention relates to the field of aircraft tests, and particularly to a test device and method for conducting combustible liquid discharge tests on aircraft. Background Art

[0002] Part 25 of the "Civil Aviation Regulations of the People's Republic of China" (CCAR) has clear requirements for the discharge of combustible liquids in the combustible liquid leakage areas of engines, APUs, and the fuselage. To meet the requirements for airworthiness certification, it is necessary to establish an aircraft combustible liquid discharge flight test facility to prove that the flammable liquids leaked from the engine compartment, APU compartment, and combustible liquid leakage areas of the aircraft fuselage can be safely discharged without accumulation during flight tests, and no other hazards will occur during the discharge.

[0003] The requirements for the discharge of combustible liquids include parameters such as the liquid flow rate and discharge time of the discharged liquid. To meet the requirements of airworthiness tests, a complete set of test devices is required to accurately control the drainage flow rate and time, and at the same time, to monitor the test area in real time.

[0004] The Chinese patent application CN 105599918 A of the Chinese Flight Test Establishment involves an aircraft combustible liquid discharge flight test facility, which includes three water tanks filled with different colored dyeing liquids respectively, and three sets of dyeing liquid systems supporting the three water tanks. The dyeing liquid system consists of a bottom valve, a water pump, a solenoid valve, a flow sensor, an overflow valve, a regulating valve, and a test control system. The test control system includes three sets of flow measurement display instruments, a liquid level sensor, and a liquid level measurement display instrument used in conjunction with the flow sensor, as well as a timer; the dyeing liquids in the water tanks respectively pass through the bottom valve, are pressurized by the water pump, the water supply pressure is adjusted by the overflow valve and the regulating valve, and then are injected into the aircraft injection area required for the test through the solenoid valve, the flow sensor, and the regulating valve.

[0005] This patent document mainly relates to the injection control system of colored water, mainly including a water pump, a water tank, a regulating valve, a valve, a pipeline, an electrical control system, and a flow measurement device, etc. It does not explain two core issues. One is the disposal mechanism for the pipeline delay time during the initial liquid discharge injection, and the other is that the fixed-position nozzles cannot meet the requirements of different injection areas in a single flight test.

[0006] Another Chinese patent application CN 106800096 A of the Chinese Flight Test Establishment involves a safe, reliable, and comprehensive flight state aircraft combustible liquid discharge test method. And it focuses on specific operation steps that meet the standards and are conducive to actual operation.

[0007] The patent document only provides a feasible test method, and it does not address the handling mechanism for pipeline delay time during the initial discharge injection, or the inability of a fixed-position nozzle to meet the needs of different injection areas in a single flight test.

[0008] Boeing's U.S. patent application US2015159909A1 discloses a liquid discharge method, system, and apparatus, which includes a discharge pipe connected to an air distribution system, a liquid collector connected to the discharge pipe and configured to receive liquid from the discharge pipe, and a suction system connected to the liquid collector.

[0009] This patent document focuses on the fact that the pressure in the liquid collector is lower than the pressure in the air distribution system, but does not address the handling mechanism for the pipeline delay time during the initial liquid discharge, or the fact that a fixed nozzle cannot meet the needs of different spray areas in a single flight test.

[0010] As can be seen from the above overview, the existing technology does not address two key issues: how to solve the impact of pipeline length on drainage time, and how to meet the need for drainage direction adjustment. Summary of the Invention

[0011] In view of the above-mentioned technical problems in the prior art, the present invention aims to provide a test apparatus for conducting flammable liquid discharge tests on aircraft, which supports flammable liquid discharge test flights. This test apparatus can achieve precise control of the discharge time and discharge volume during discharge test flights, thereby improving the data accuracy and implementation reliability of the discharge test flights.

[0012] Therefore, the present invention provides a test apparatus for conducting flammable liquid emission tests on aircraft.

[0013] include:

[0014] A liquid reservoir, the liquid reservoir including a storage space for storing test liquid to be discharged during the test, and the liquid reservoir including a reservoir outlet for the test liquid to leave the storage space;

[0015] A liquid pump, which is in fluid communication with the storage space, to drive the test liquid stored in the storage space out of the liquid reservoir through the reservoir outlet;

[0016] A discharge pipeline, which is in fluid communication with the outlet of the reservoir, allows the discharged test liquid to flow through it; and

[0017] A nozzle assembly is connected to the end of the discharge line opposite to the end near the reservoir outlet, so that the discharged test liquid can be discharged from it.

[0018] in,

[0019] The test apparatus also includes:

[0020] A discharge pipeline level sensing device is provided along the discharge pipeline and configured to indicate whether the test liquid in the discharge pipeline has reached a predetermined amount.

[0021] By installing a liquid level sensing device in the discharge pipeline, it is possible to sense and indicate whether the test liquid in the discharge pipeline has reached a predetermined value, so that test personnel or automatic test systems can accurately control the discharge time and discharge volume during the discharge test flight, thereby improving the data accuracy and implementation reliability of the discharge test flight.

[0022] According to a preferred but non-limiting embodiment of the experimental apparatus of the present invention, the discharge line level sensing device includes a collection funnel in fluid communication with the discharge line.

[0023] According to a preferred, but not limiting, embodiment of the experimental apparatus of the present invention, the experimental apparatus further includes:

[0024] A flow sensing device is provided along the discharge pipeline and configured to sense the flow rate of the test liquid flowing through the discharge pipeline.

[0025] in,

[0026] The discharge pipeline level sensing device is arranged between the liquid reservoir and the flow sensing device.

[0027] According to a preferred, but not limiting, embodiment of the experimental apparatus of the invention, the nozzle assembly is configured to adjust the direction of the test liquid injection relative to the discharge line.

[0028] According to a preferred, but not limiting, embodiment of the experimental apparatus of the present invention, the nozzle assembly comprises:

[0029] A base for fixed connection with the discharge pipeline;

[0030] A nozzle that can move relative to the base to change the spray direction;

[0031] The hose connecting the discharge line to the nozzle.

[0032] According to a preferred, but not limiting, embodiment of the experimental apparatus of the invention, the base includes a curved surface for the nozzle to move along its surface.

[0033] According to a preferred but non-limiting embodiment of the experimental apparatus of the present invention, the nozzle assembly further includes a drive device for driving the nozzle to move relative to the base.

[0034] Furthermore, the present invention also provides a method for conducting aircraft flammable liquid emission tests using the various testing devices described above.

[0035] Includes the following steps:

[0036] The step of filling the discharge line is as follows: the test liquid is pumped from the liquid reservoir to the discharge line by the liquid pump to fill the discharge line;

[0037] The step of sensing the liquid level in the discharge pipeline is as follows: the liquid level sensing device in the discharge pipeline is used to sense whether the test liquid in the discharge pipeline has reached a predetermined amount.

[0038] The procedure for initiating an aircraft flammable liquid discharge test is as follows: at least after detecting a signal from the discharge line level sensing device indicating that the test liquid in the discharge line has reached a predetermined amount, the test liquid is discharged to a predetermined location through the nozzle assembly.

[0039] More preferably, the present invention also provides a method for conducting aircraft flammable liquid emission tests using the above-described test apparatus including a flow sensing device.

[0040] Includes the following steps:

[0041] The step of filling the discharge line is as follows: the test liquid is pumped from the liquid reservoir to the discharge line by the liquid pump to fill the discharge line;

[0042] The step of sensing the liquid level in the discharge pipeline is as follows: the liquid level sensing device in the discharge pipeline is used to sense whether the test liquid in the discharge pipeline has reached a predetermined amount.

[0043] The procedure for initiating an aircraft flammable liquid discharge test is as follows: at least after detecting a signal from the discharge line level sensing device indicating that the test liquid in the discharge line has reached a predetermined amount, the test liquid is discharged to a predetermined location through the nozzle assembly, and the flow rate sensed by the flow sensing device is monitored in real time.

[0044] More preferably, the present invention also provides a method for conducting aircraft flammable liquid emission tests using the above-described test apparatus including a nozzle driving device.

[0045] Includes the following steps:

[0046] The step of filling the discharge line is as follows: the test liquid is pumped from the liquid reservoir to the discharge line by the liquid pump to fill the discharge line;

[0047] The step of sensing the liquid level in the discharge pipeline is as follows: the liquid level sensing device in the discharge pipeline is used to sense whether the test liquid in the discharge pipeline has reached a predetermined amount.

[0048] The procedure for initiating an aircraft flammable liquid discharge test is as follows: at least after detecting a signal from the discharge line level sensing device indicating whether the test liquid in the discharge line has reached a predetermined amount, the test liquid is discharged to a predetermined location through the nozzle assembly; and

[0049] The step of adjusting the spray direction of the nozzle assembly is to adjust the nozzle to the desired spray direction by actuating the drive device.

[0050] In summary, the technical advantages of the experimental apparatus and method of the present invention are at least as follows:

[0051] 1) By adding a liquid level sensing device such as a collection funnel to the front end of the flow sensing device such as a flow control valve, the liquid level sensing device in the discharge pipeline can be installed to detect when the liquid discharge function has reached the pre-position state. This allows the relevant pre-position state signal to be fed back to the display component and the pre-position state light to be lit. This enables precise control of the liquid discharge time and volume during the liquid discharge test flight, improves the data accuracy and implementation reliability of the liquid discharge test flight, solves the delay effect of the first spray caused by the long pipeline, and ensures that the spraying time of the colored water meets the test conditions.

[0052] 2) Through the design of the nozzle assembly, the nozzle angle is controlled and adjustable. The connection between the nozzle and the drain pipe is designed as a flexible hose. The spray angle is adjusted by the controlled command of the actuation mechanism, so as to meet the spraying needs of different areas at the same position and improve the efficiency of the test work. Attached Figure Description

[0053] This document includes accompanying drawings to provide a further understanding of various embodiments. The drawings are incorporated in and form part of this specification.

[0054] The accompanying drawings illustrate various embodiments described herein and, together with the textual description, serve to explain the principles and operation of the claimed subject matter.

[0055] With reference to the above objectives, the technical features of the present invention are clearly described below, and its advantages will be apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the invention by way of example, without limiting the scope of the invention.

[0056] In the attached image:

[0057] Figure 1 This is a schematic block diagram of a test apparatus for conducting flammable liquid emission tests on aircraft according to a preferred embodiment of the present invention.

[0058] Figure 2 This is a schematic diagram of the nozzle assembly in a test apparatus according to a preferred embodiment of the present invention.

[0059] List of reference numerals

[0060] 100 Liquid Storage Tank

[0061] 200 Liquid Pump

[0062] 300 emission pipeline

[0063] 400 nozzle assembly

[0064] 410 base

[0065] 411 Surface

[0066] 420 nozzle

[0067] 430 hose

[0068] 440 Matching Connector

[0069] 500 Discharge Pipeline Liquid Level Sensing Device

[0070] 600 Flow Sensing Device

[0071] 700 switching valve

[0072] 1000 Human-Machine Interface Module

[0073] 1100 Control Components

[0074] 1200 Display Components

[0075] 2000 Instruction Solving Module

[0076] 3000 Input / Output Acquisition Module

[0077] 4000 Tested Area

[0078] 5000 Video Surveillance Module Detailed Implementation

[0079] Embodiments of the invention will now be described in detail, examples of which are shown in the accompanying drawings and described below.

[0080] Although the invention will be described in conjunction with exemplary embodiments, it should be understood that this specification is not intended to limit the invention to the embodiments illustrated.

[0081] Conversely, the present invention is intended to cover not only these exemplary embodiments, but also various alternative forms, modifications, equivalent forms and other embodiments that may be included within the spirit and scope of the invention.

[0082] To facilitate explanation and precise definition of the technical solutions of the present invention, the terms "upper," "lower," "inner," and "outer" are used to describe these features with reference to the positions of features in the exemplary embodiments shown in the accompanying drawings.

[0083] Various preferred but non-limiting embodiments of the test apparatus and test method of the present invention will be described in detail below with reference to the accompanying drawings.

[0084] Figure 1 A schematic diagram of a preferred embodiment of a test apparatus for conducting flammable liquid emission tests on aircraft, according to the present invention, is shown.

[0085] like Figure 1 The experimental setup shown includes a liquid reservoir 100, a liquid pump 200, a discharge line 300, a nozzle assembly 400, and a discharge line level sensing device 500, for controlled spraying of test liquids such as coloring water. Furthermore, to further facilitate control of the experimental process, the setup may also include, for example, a human-machine interface module 1000 containing control components 1100 and / or display components 1200, a command processing module 2000, and an input / output acquisition module 3000. Figure 1 The diagram also schematically shows the tested area 4000 and the video monitoring module 5000.

[0086] The liquid reservoir 100 includes a storage space for storing the test liquid to be discharged during the test, and the liquid reservoir 100 includes a reservoir outlet for the test liquid to leave the storage space. The liquid reservoir 100 is, for example, in the form of a water tank. Figure 1 In the illustrative embodiment shown, corresponding to airworthiness certification requirements, the testing apparatus includes three independent liquid reservoirs 100, each for storing different colored waters used as different test liquids. These reservoirs may, for example, have functions such as aeration and level monitoring. The level monitoring signal is simultaneously fed back to the aforementioned display component 1200 for real-time monitoring by relevant operators, such as the commander participating in the test.

[0087] The liquid pump 200 is in fluid communication with the storage space so as to drive the test liquid stored in the storage space out of the liquid reservoir 100 through the reservoir outlet;

[0088] The discharge pipe 300 is in fluid communication with the reservoir outlet to allow the discharged test liquid to flow through. One end of the discharge pipe 300 is connected to the liquid reservoir 100, and the other end is connected to the nozzle assembly 400. For nozzles belonging to different test areas 4000, a switching valve 700 can be installed as needed to allow multiple test areas 4000 to share the common liquid reservoir 100. Figure 1 As shown in the image.

[0089] The nozzle assembly 400 is connected to the opposite end of the discharge line 300, which is near the reservoir outlet, so that the discharged test liquid can be discharged from it.

[0090] A discharge line level sensing device 500 is installed along the discharge line 300 and configured to indicate whether the test liquid in the discharge line 300 has reached a predetermined amount. The discharge line level sensing device 500 may preferably include a collection funnel in fluid communication with the discharge line 300. The collection funnel, as referred to herein, can be of various common types in the art, as long as it can indicate whether the liquid volume in the collection funnel has reached a threshold value, including but not limited to a tee fitting with a container at the lower end, which determines whether the liquid volume in the container has reached a threshold value by placing a photosensitive sensor in the detection section of the container and sensing changes in the optical refraction path.

[0091] Because the actual piping on the aircraft is quite long, there will be a significant delay effect during the first spray. In order to ensure that the spraying time of the colored water meets the test requirements, a liquid level sensing device 500 for the discharge pipeline is added as described above. When the colored water discharged into the discharge pipeline 300 reaches a certain amount, the discharge function reaches the pre-position state. The pre-position state signal can preferably be fed back to the display component and / or the pre-position state light can be lit.

[0092] In addition, Figure 1 In the preferred embodiment shown, the test apparatus may also preferably include a flow sensing device 600, which is arranged along the discharge line 300 and configured to sense the flow rate of the test liquid flowing through the discharge line 300. The flow sensing device 600 may include, but is not limited to, a flow control valve. The flow control valve can be used to control and detect whether the flow rate of the colored water at the corresponding discharge channel reaches the required setting. The monitoring signal is simultaneously fed back to the display component for real-time monitoring by the operator to verify compliance with the test conditions.

[0093] In the case of including the flow sensing device 600, the discharge line level sensing device 500 is arranged between the liquid reservoir 100 and the flow sensing device 600.

[0094] The nozzle assembly 400 is configured to adjust the direction of the test liquid spray relative to the discharge line 300. In a preferred embodiment, the nozzle assembly 400 may include: a base 410, a nozzle 420, a hose 430, and a drive mechanism for moving the nozzle 420 relative to the base 410. The base 410 is fixedly connected to the discharge line 300. The nozzle 420 is movable relative to the base 410 to change the spray direction. The hose 430 connects the discharge line 300 to the nozzle 420. Wherein, as Figure 2As shown, the hose 430 can be connected to the nozzle 420 via a mating connector. The base 410 includes a curved surface 411 for the nozzle 420 to move along its surface. By designing the connection between the nozzle 420 and the drain pipe 300 as a hose 430, the spraying requirements of different areas at the same location can be met, for example, by adjusting the spray angle through controlled rotation of the drive device. The drive device mentioned herein includes, but is not limited to, power sources such as motors that provide driving power, and multi-axis rotating structures for changing the spray direction of the nozzle 420. Those skilled in the art can select specific components of the drive device according to actual needs, which will not be elaborated here.

[0095] It should be noted that the actuation mechanism and movement mode of the nozzle assembly 400 are not limited to this. Rather, those skilled in the art can select other types of nozzle assemblies 400 according to actual needs, such as a movable plane along which the nozzle 420 moves, etc.

[0096] The aforementioned human-machine interface module 1000 is generally used for liquid discharge control operation and status display. The human-machine interface module 1000 can be positioned in the cockpit or passenger cabin control panel depending on the operator's identity. Those skilled in the art can design and construct the display and operation interface of the human-machine interface module 1000 according to actual needs, which will not be elaborated upon here.

[0097] The control component 1100 of the human-machine interface module 1000 can be used for the spraying control of the colorant, including spraying pre-positioning, spraying start and stop. The display component 1200 of the human-machine interface module 1000 can be used for displaying the spraying status of the colorant, including monitoring the liquid level status of the storage tank, monitoring the spraying flow rate status, and digitally displaying the draining time. Video monitoring is typically used for ground monitoring, but can also be implemented synchronously in the cabin by flight test engineers as needed.

[0098] The instruction processing module 2000 receives control instructions from the operator and processes them in two ways: first, it processes the instructions into the pressure required by the water pump; second, it processes the instructions into the opening state of the flow control valve, such as half-open or fully open.

[0099] The input / output acquisition module 3000 can acquire one or more of the following signals: liquid level signal from liquid storage tank 1000, liquid level signal from discharge pipeline level sensing device 500, flow signal from flow sensing device 600, and video monitoring signal from video monitoring module 5000. The acquired signals can be fed back to display component 1200 for display in an appropriate manner.

[0100] The tested area 4000 typically includes the aircraft engine mounting area, auxiliary power unit (APU) compartment area, landing gear compartment area, and aft equipment compartment area.

[0101] The video monitoring module 5000 records real-time video of the component under test and observes the liquid flow path during drainage.

[0102] The present invention also provides a method for conducting aircraft flammable liquid emission tests using the aforementioned test apparatus, the method comprising the following steps:

[0103] The procedure for filling the discharge line 300 is as follows: the test liquid is pumped from the liquid reservoir 100 to the discharge line 300 by the liquid pump 200 to fill the discharge line 300.

[0104] The steps for sensing the liquid level in the discharge pipeline 300 are as follows: The test liquid in the discharge pipeline 300 is sensed by the discharge pipeline liquid level sensing device 500 to determine whether the amount of liquid has reached the predetermined value.

[0105] The procedure for initiating an aircraft flammable liquid discharge test is as follows: at least after a signal indicating that the test liquid in the discharge line 300 has reached a predetermined amount is detected by the discharge line level sensing device 500, the test liquid is discharged to a predetermined location through the nozzle assembly 400.

[0106] The aforementioned step of initiating the aircraft flammable liquid discharge test may preferably include, when the test liquid is discharged to a predetermined location through the nozzle assembly 400, real-time monitoring of the flow rate sensed by the flow sensing device 600 is initiated.

[0107] Preferably, the test method may further include the step of adjusting the spray direction of the nozzle assembly 400 by adjusting the nozzle 420 to the desired spray direction by means of an actuation drive device.

[0108] The preferred embodiments of the present invention have been described in detail above, but it should be understood that, if necessary, aspects of the embodiments can be modified to utilize aspects, features, and concepts from various patents, applications, and publications to provide other embodiments.

[0109] In light of the detailed description above, these and other changes can be made to the embodiments described herein.

[0110] Generally, the terms used in the claims should not be considered as limited to the specific embodiments disclosed in the specification and claims, but should be understood to include all possible embodiments together with the full scope of equivalents enjoyed by these claims.

Claims

1. A test apparatus for conducting flammable liquid emission tests on aircraft. include: A liquid reservoir (100) includes a storage space for storing test liquid to be discharged during the test, and the liquid reservoir (100) includes a reservoir outlet for the test liquid to leave the storage space; A liquid pump (200) is in fluid communication with the storage space to drive the test liquid stored in the storage space out of the liquid reservoir (100) via the reservoir outlet; A discharge line (300) is in fluid communication with the outlet of the reservoir to allow the discharged test liquid to flow through it; and A nozzle assembly (400) is connected to the end of the discharge line (300) opposite to the end near the reservoir outlet, so that the discharged test liquid can be discharged from it. in, The test apparatus also includes: A discharge line liquid level sensing device (500) is provided along the discharge line (300) and configured to indicate whether the test liquid in the discharge line (300) has reached a predetermined amount.

2. The test apparatus according to claim 1, Its features are, The discharge pipeline level sensing device (500) includes a collection funnel in fluid communication with the discharge pipeline (300).

3. The test apparatus according to claim 1, Its features are, The test apparatus also includes: A flow sensing device (600) is provided along the discharge line (300) and configured to sense the flow rate of the test liquid flowing through the discharge line (300). in, The discharge pipeline level sensing device (500) is arranged between the liquid reservoir (100) and the flow sensing device (600).

4. The test apparatus according to claim 1, Its features are, The nozzle assembly (400) is configured to adjust the direction of the test liquid spray relative to the discharge line (300).

5. The testing apparatus according to claim 4, Its features are, The nozzle assembly (400) includes: A base (410) for fixed connection with the discharge pipeline (300); A nozzle (420) that can move relative to the base (410) to change the spray direction; The hose (430) connects the discharge line (300) to the nozzle (420).

6. The testing apparatus according to claim 5, Its features are, The base (410) includes a curved surface (411) for the nozzle to move along its surface.

7. The test apparatus according to claim 5, Its features are, The nozzle assembly (400) also includes a drive mechanism for driving the nozzle (420) to move relative to the base (410).

8. A method for conducting aircraft flammable liquid emission tests using the test apparatus according to any one of claims 1 to 7. Includes the following steps: The step of filling the discharge line (300) is as follows: the test liquid is discharged from the liquid reservoir (100) to the discharge line (300) by the liquid pump (200) to fill the discharge line (300); The step of sensing the liquid level in the discharge pipeline (300) is as follows: the test liquid in the discharge pipeline (300) is sensed by the liquid level sensing device (500) of the discharge pipeline to determine whether the liquid level has reached a predetermined value. The procedure for initiating an aircraft flammable liquid discharge test is as follows: at least after detecting a signal from the discharge line level sensing device (500) indicating that the test liquid in the discharge line (300) has reached a predetermined amount, the test liquid is discharged to a predetermined location through the nozzle assembly (400).

9. A method for conducting aircraft flammable liquid emission tests using the test apparatus according to claim 3. Includes the following steps: The step of filling the discharge line (300) is as follows: the test liquid is discharged from the liquid reservoir (100) to the discharge line (300) by the liquid pump (200) to fill the discharge line (300); The step of sensing the liquid level in the discharge pipeline (300) is as follows: the test liquid in the discharge pipeline (300) is sensed by the liquid level sensing device (500) of the discharge pipeline to determine whether the liquid level has reached a predetermined value. The steps for initiating an aircraft flammable liquid discharge test are as follows: at least after detecting a signal from the discharge line level sensing device (500) indicating that the test liquid in the discharge line (300) has reached a predetermined amount, the test liquid is discharged to a predetermined location through the nozzle assembly (400), and the flow rate sensed by the flow sensing device (600) is monitored in real time.

10. A method for conducting aircraft flammable liquid emission tests using the test apparatus according to claim 7. Includes the following steps: The step of filling the discharge line (300) is as follows: the test liquid is discharged from the liquid reservoir (100) to the discharge line (300) by the liquid pump (200) to fill the discharge line (300); The step of sensing the liquid level in the discharge pipeline (300) is as follows: the test liquid in the discharge pipeline (300) is sensed by the liquid level sensing device (500) of the discharge pipeline to determine whether the liquid level has reached a predetermined value. The steps for initiating an aircraft flammable liquid discharge test are as follows: at least after detecting a signal from the discharge line level sensing device (500) indicating whether the test liquid in the discharge line (300) has reached a predetermined amount, the test liquid is discharged to a predetermined location via the nozzle assembly (400); and The step of adjusting the spray direction of the nozzle assembly (400) is to adjust the nozzle (420) to the desired spray direction by actuating the drive device.

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