CN118439186A - Full-size ground test device for fuel system of aircraft with flying wing layout - Google Patents

Abstract

The invention discloses a full-size ground test device for an aircraft fuel system with an all-wing layout, which comprises an airborne fuel tank test simulation piece (comprising a wing test fuel tank and a fuselage test fuel tank), a flying height environment pressure simulation system, a bleed air pressure simulation system, an engine fuel consumption flow simulation system, a test measurement and control system, auxiliary power equipment and the like. The airborne fuel tank test simulation piece can truly restore the fuel liquid level change and the gas space pressure change condition in the fuel tank. The flying height environment pressure simulation system and the bleed air pressure simulation system simulate the changes of the environment pressure and the engine bleed air pressure under different flying heights respectively. The engine oil consumption flow simulation system can accurately simulate the actual oil consumption condition of the engine in each flight stage. The ground test device of the fuel system can simulate the working state and critical flight condition test of an aircraft, greatly reduce the test flight risk, and realize the system fault reproduction, analysis and improvement test.

Description

A full-scale ground test device for the fuel system of a flying wing aircraft

Technical Field

The invention belongs to the field of aerospace technology and relates to the testing and verification of an aircraft fuel system, in particular to a full-scale ground test device for a flying wing layout aircraft fuel system.

Background technique

The full-scale ground simulation test of the aircraft fuel system is an important and indispensable means to ensure the correctness and rationality of the fuel system design, to test the performance coordination of the system, and to ensure the flight safety and reliable operation of the aircraft. Through the full-scale test, it is possible to check whether the performance of each device in the fuel system meets the design requirements under normal working conditions and fault conditions, to test the functions and reliability of each finished accessory, and to test whether each finished accessory matches the system and whether the interface parameters are coordinated; based on the data obtained from the full-scale test, the aircraft fuel system can be optimized, providing a test basis for the safe first flight of the aircraft and a test basis for the finalization review of the aircraft fuel system.

The structure and equipment distribution of flying wing aircraft are very different from those of conventional aircraft, which puts higher requirements on the design of the fuel system and also brings many difficulties to the full-scale ground simulation test of the system. The ground test of the fuel system of flying wing aircraft must solve the following key technical problems to ensure the effectiveness and accuracy of the test:

(1) A true simulation of the consistency of the installed status of fuel system accessories. The wing/fuselage test tank is consistent with the external dimensions of the installed tank (Note: the ground test tank must withstand a large negative pressure) to ensure that the installation position of accessories such as the fuel pump, the changes in the fuel level and oil volume, and the changes in the gas space pressure in the tank are closer to reality. Only then can the fuel supply and delivery subsystem test simulation, ventilation subsystem test simulation, fuel filling and draining test simulation, fuel measurement and management test simulation, unavailable oil volume measurement, and unmeasurable oil volume measurement processes be quantified and accurate. Otherwise, it is impossible to conduct test simulations of the cross-linking working processes of each system;

(2) Realistic simulation of environmental pressure at flight altitude. During the aircraft's climb, cruise, and descent, the external atmospheric pressure changes accordingly. The ventilation accessories will perform ventilation work based on the difference between the pressure inside the wing/fuselage tank and the external environmental pressure to ensure that the difference between the internal and external pressures of the tank does not exceed the standard. Therefore, it is very necessary to build a vacuum system with a certain vacuum degree to simulate the changes in environmental pressure at the aircraft's flight altitude.

(3) Real simulation of the engine fuel flow rate. Under ground test conditions, there is no real engine load. Therefore, in order to simulate the continuous fuel supply state of the engine, it is necessary to build an engine fuel flow simulation device to check whether the fuel supply pressure meets the design requirements through flow control;

(4) Test process control and data acquisition. The full-scale fuel system test requires a large amount of data signals to be collected and recorded, and the relevant fuel pumps and valves need to be switched on and off. The construction of the corresponding test data measurement and control system is particularly necessary.

In summary, the ground test of the fuel system of a flying wing aircraft is faced with many technical challenges and difficulties. The solution of these problems is crucial to ensure the rationality of the fuel system design, the performance coordination of the inspection system, and the flight safety and working reliability of the aircraft. Therefore, it is an urgent technical problem to provide a ground test device for the fuel system of a flying wing aircraft to at least partially solve the above-mentioned technical problems.

Summary of the invention

(I) Purpose of the Invention

In view of the many difficulties and challenges in the ground simulation test of the fuel system of a flying wing layout aircraft, and in order to at least solve one or more of the technical problems such as the real simulation of the installed state, the ambient pressure at flight altitude, the engine fuel consumption flow rate and so on in the ground test of the fuel system, the present invention aims to provide a full-scale ground test device for the fuel system of a flying wing layout aircraft. By setting an onboard fuel tank test simulation part, a flight altitude ambient pressure simulation system, a bleed air pressure simulation system, an engine fuel consumption flow rate simulation system and the like, the real simulation of the installed state of the fuel system accessories, the real simulation of the change of the ambient pressure at flight altitude and the real simulation of the engine fuel consumption flow rate can be achieved, thereby providing a reliable test basis for the safe first flight of the aircraft and the finalization review of the fuel system, and can also realize the reproduction, analysis and improvement test of system faults, which is of great significance to the design and verification of the fuel system of the flying wing layout aircraft.

(II) Technical solution

In order to achieve the purpose of the invention and solve the technical problems, the present invention adopts the following technical solutions:

A full-scale ground test device for the fuel system of a flying wing aircraft, including an onboard fuel tank test simulation component, a flight altitude environmental pressure simulation system, a bleed air pressure simulation system and an engine fuel consumption flow simulation system, wherein:

The onboard fuel tank test simulation part includes a wing test fuel tank, a fuselage test fuel tank and fuel system accessories. The wing test fuel tank and the fuselage test fuel tank have the same dimensions as the actual onboard fuel tank, and the installation position of each fuel system accessory on the fuel tank is consistent with the actual installation state, so as to simulate the changes in the fuel level, fuel quantity and gas space pressure in the fuel tank under actual flight conditions;

The flight altitude environmental pressure simulation system comprises an environmental pressure simulation box and a vacuum pumping device. The environmental pressure simulation box is connected to the ventilation components of the wing and fuselage oil tanks, the ground atmospheric environment, and the vacuum pumping device through gas pipelines, and the internal pressure thereof is continuously changed according to the environmental pressure corresponding to the flight altitude profile by controlling the air intake rate and the air outlet rate, so as to provide a pressure reference for the ventilation of the wing and fuselage oil tanks.

The bleed air pressure simulation system comprises a bleed air pressure simulation box and a boost air pump. The bleed air pressure simulation box is connected to the wing and fuselage fuel tanks, the ground atmospheric environment, and the boost air pump through gas pipelines, and the internal pressure thereof is continuously changed according to the engine bleed air pressure corresponding to the test by controlling the air intake rate and the air outlet rate thereof.

The engine fuel consumption flow simulation system includes an oil storage tank, which is connected to the wing and fuselage fuel tanks through fuel pipelines and uses an on-board fuel supply pump as a power source. The engine fuel consumption flow simulation is achieved by controlling the fuel supply flow and the fuel supply pressure to continuously change according to a given profile.

(III) Technical Effect

It can be seen from the above technical solutions that the full-scale ground test device for the fuel system of a flying wing aircraft of the present invention has at least one or part of the following beneficial effects:

(1) The ground test device for the fuel system of a flying wing aircraft of the present invention can realize the real simulation of the consistency of the installation state of the accessories of the aircraft fuel system, the real simulation of the environmental pressure at the flight altitude and the fuel flow rate of the engine. By adopting the wing and fuselage test fuel tanks that are consistent with the external dimensions of the actual aircraft fuel tanks, it is ensured that the installation position of accessories such as the fuel pump on the fuel tank is consistent with the actual installation state, thereby accurately simulating the changes in the fuel level, fuel quantity and gas space pressure in the fuel tank under actual flight conditions. Through the flight altitude environmental pressure simulation system and the bleed air pressure simulation system, a real pressure environment reference is provided for the ventilation components of the wing and fuselage fuel tanks, simulating the changes in environmental pressure and engine bleed air pressure at different flight altitudes. The engine fuel flow simulation system can accurately simulate the actual fuel consumption changes of the engine in each flight stage. The simulation process can comprehensively evaluate the performance of the fuel system under different flight conditions, and the obtained test data has a high credibility, providing a test basis for the safe first flight of the aircraft and a test basis for the finalization review of the aircraft fuel system.

(2) The test device scheme based on the present invention can not only simulate normal flight conditions, but also simulate working conditions that are difficult to achieve during flight tests due to risks or other factors, such as the fuel consumption characteristics of engines of different models, thereby expanding the test coverage, effectively complementing the flight test, and improving the comprehensiveness and reliability of the fuel system test.

BRIEF DESCRIPTION OF THE DRAWINGS

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

FIG1 is a schematic diagram of a full-scale ground test device for a flying wing layout aircraft fuel system according to the present invention;

FIG2 is a schematic diagram of the layout of the aircraft fuel tank test simulation component of the present invention;

FIG3 is a schematic diagram of the layout of the flight altitude environmental pressure simulation system of the present invention;

FIG4 is a block diagram of the flight altitude ambient pressure control principle;

FIG5 is a schematic diagram of the layout of the bleed air pressure simulation system of the present invention;

FIG6 is a block diagram of the engine bleed air pressure control principle;

FIG7 is a schematic diagram of the layout of the engine fuel consumption flow simulation system of the present invention;

Figure 8 is a block diagram of the oil supply flow control principle.

Description of reference numerals:

Aircraft fuel tank test simulation part 10, wing test fuel tank 11, fuselage test fuel tank 12, ventilation pipeline 13, fuel pipeline 14, onboard safety valve 15, anti-vacuum valve 16, pressure reducer 17, onboard fuel supply pump 18, fuel consumption sensor 19, flight altitude environmental pressure simulation system 20, environmental pressure simulation box 21, vacuum exhaust equipment 22, air intake regulating valve 23, air outlet regulating valve 24, vacuum pressure sensor 25, bleed air pressure simulation system 30, bleed air pressure simulation box 31, booster air pump 32, air intake regulating valve 33, air outlet regulating valve 34, gas pressure sensor 35, engine fuel consumption flow simulation system 40, oil storage tank 41, fuel supply flow regulating valve 42, fuel flow meter 43, fuel pressure sensor 44.

Detailed ways

In order to better understand the present invention, the content of the present invention is further explained in conjunction with the embodiments below. In the accompanying drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limitations on the present invention. Based on the embodiments in the present invention, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present invention. The structure and technical solution of the present invention are further described in detail below in conjunction with the accompanying drawings, and an embodiment of the present invention is given.

In view of the many difficulties and challenges existing in the ground simulation test of the fuel system of a flying wing layout aircraft, and in order to at least solve one or more technical problems such as the real simulation of the installed state, the ambient pressure at the flight altitude, the engine fuel consumption flow rate and so on in the ground test of the fuel system, the present invention aims to provide a full-scale ground test device for the fuel system of a flying wing layout aircraft.

As a specific example, as shown in Figure 1, the full-scale ground test device for the fuel system of a flying wing layout aircraft of the present invention is composed of an onboard fuel tank test simulation part 10 (including a wing test fuel tank 11 and a fuselage test fuel tank 12), a flight altitude environmental pressure simulation system 20, a bleed air pressure simulation system 30, an engine fuel consumption flow simulation system 40, a test measurement and control system and an auxiliary power equipment.

2 is a schematic diagram of the layout of an onboard fuel tank test simulation component of the present invention. The onboard fuel tank test simulation component 10 of the present invention includes a wing test fuel tank 11, a fuselage test fuel tank 12 and fuel system accessories. The wing test fuel tank 11 and the fuselage test fuel tank 12 are consistent with the outer dimensions of an actual onboard fuel tank, and the installation position of each fuel system accessory on the fuel tank is consistent with the actual installation state, so as to simulate the changes in the fuel liquid level, fuel quantity and gas space pressure in the fuel tank under actual flight conditions.

In some preferred embodiments, in the onboard fuel tank test simulation part 10, the fuel system accessories include at least a ventilation line 13 and a fuel line 14 connected to the wing and fuselage fuel tanks, a ventilation component attached to the ventilation line, and a fuel supply component on the fuel line. The ventilation component includes at least an onboard safety valve 15, an anti-vacuum valve 16 and a pressure reducer 17. The fuel supply component includes at least an onboard fuel supply pump 18. The bleed air pressure simulation box 31 is connected to the onboard safety valve 15, the anti-vacuum valve 16 and the pressure reducer 17 through a gas pipeline to provide a pressure reference for the normal operation of the relevant ventilation components. The bleed air pressure simulation box 31 is connected to the pressure reducer 17 through a gas pipeline to simulate the changes in bleed air pressure at different flight altitudes. The fuel storage tank 41 is connected to the wing and fuselage fuel tanks through the fuel pipeline to achieve a true simulation of the engine fuel supply under different test conditions.

In addition, in a further preferred example, the fuel supply component also includes a fuel consumption sensor 19 and a pressure sensor 20. The fuel consumption sensor 19 is used to accurately measure the amount of fuel supplied from the wing and fuselage tanks to the fuel storage tank 41, thereby monitoring the entire fuel supply process, verifying the accuracy and reliability of each link of the fuel supply system, and providing data support for engine performance evaluation.

Through the above design, the airborne fuel tank test simulation part 10 of the present invention can truly simulate the external dimensions and working conditions of the actual installed fuel tank of the aircraft, ensuring that various parameters of the fuel system in the ground test are consistent with the actual flight conditions, thereby providing reliable test data for the design and optimization of the fuel system of the flying wing layout aircraft.

FIG3 is a schematic diagram of the layout of the flight altitude environmental pressure simulation system of the present invention. The flight altitude environmental pressure simulation system of the present invention is composed of a vacuum pumping device 22 (including a water ring vacuum pump, a vacuum pipeline, a vacuum pipeline valve, etc.), a vacuum pressure sensor 25, an air intake regulating valve 23, an air outlet regulating valve 24, a flight altitude pressure environment simulation box 21, etc. The environmental pressure simulation box 21 is connected to the ventilation components of the wing and fuselage fuel tanks, the ground atmospheric environment, and the vacuum pumping device 22 through gas pipelines, and by controlling its air intake rate and air outlet rate, the internal pressure thereof is continuously changed according to the environmental pressure corresponding to the flight altitude profile, providing a pressure reference for the ventilation of the wing and fuselage fuel tanks. Specifically, the vacuum exhaust equipment 22 is used to perform vacuum processing on the environmental pressure simulation box 21. The environmental pressure simulation box 21 is provided with a vacuum pressure sensor 25 connected with its internal space, and its air intake pipe is provided with an air intake regulating valve 23 and the air outlet pipe is provided with an air outlet regulating valve 24. The air intake regulating valve 23 and the air outlet regulating valve 24 are used to control the air intake rate and the air outlet rate of the environmental pressure simulation box 21 respectively, so that the internal pressure of the environmental pressure simulation box 21 can continuously change according to the environmental pressure corresponding to the flight altitude profile.

FIG4 is a block diagram of the flight altitude environmental pressure control principle. The flight altitude environmental pressure simulation system 20 of the present invention has the following environmental pressure control principle: as the flight altitude changes, the environmental pressure also gradually changes, and the pressure change trend curve is a given flight profile. According to the environmental pressure change curve, the control system uses pressure as the target control quantity, and after comparing it with the actual pressure feedback signal, the controller outputs the electric control valve opening control signal for the current deviation, and finally realizes the continuous and stable control of the pressure in the environmental box through the rapid, stable and accurate control of the intake and exhaust electric control valves.

Based on the above control principle, the flight altitude ambient pressure simulation system 20 can achieve continuous and stable control of the pressure in its ambient pressure simulation box according to the following sub-steps, for example:

SS21. Obtain preset flight altitude profile data, which reflects the changing trend of ambient pressure at different flight altitudes, and use the data as the target ambient pressure control amount of the ambient pressure simulation box;

SS22 real-time detection of the actual pressure value in the ambient pressure simulation box 21 and feed it back to the PID controller, the PID controller by comparing the actual pressure feedback value with the target ambient pressure value corresponding to the flight altitude, calculate the current pressure deviation;

SS23.PID controller calculates the expected opening values of the air inlet regulating valve 23 and the air outlet regulating valve 24 according to the current pressure deviation and outputs a control signal to adjust the opening of the air inlet regulating valve 23 and the air outlet regulating valve 24, thereby adjusting the air inlet and air outlet rates of the environmental pressure simulation box 21 to ensure continuous and stable changes in the internal pressure of the environmental pressure simulation box 21;

SS24. Repeat sub-steps SS21 to SS23 periodically to make the pressure in the environmental pressure simulation box 21 continuously track the changing flight altitude profile data, simulate the environmental pressure changes at different flight altitudes, and provide a pressure reference for the normal operation of the wing and fuselage tank ventilation components.

The flight altitude environmental pressure simulation system of the present invention can accurately simulate the impact of flight altitude changes on environmental pressure. By adjusting the air intake and outlet rates in the environmental pressure simulation box in real time, it ensures continuous and stable changes in the pressure inside the simulation box, and provides a reliable pressure reference for the normal operation of the fuel system ventilation component at different flight altitudes, thereby ensuring the authenticity and reliability of ground test data.

FIG5 is a schematic diagram of the layout of the bleed air pressure simulation system of the present invention. As shown in FIG5, the bleed air pressure simulation system of the present invention is composed of a boost air pump 32, a boost pipeline, a pressure sensor 35, an intake regulating valve 33, an outlet regulating valve 34, a bleed air pressure simulation box 31, etc. The bleed air pressure simulation box 31 is connected to the wing and fuselage fuel tanks, the ground atmospheric environment, and the boost air pump 32 through gas pipelines, and the internal pressure thereof is continuously changed according to the engine bleed air pressure corresponding to the test by controlling the intake rate and the outlet rate thereof. Specifically, the boost air pump 32 is used to perform a boost process on the bleed air pressure simulation box 31, and the bleed air pressure simulation box 31 is provided with a gas pressure sensor 35 connected with its internal space, and the intake boost pipeline thereof is provided with an intake regulating valve 33, and the outlet pipeline thereof is provided with an outlet regulating valve 34, and the intake and outlet rates of the bleed air pressure simulation box 31 are respectively controlled by the intake regulating valve 33 and the outlet regulating valve 34, so that the internal pressure thereof is continuously changed according to the engine bleed air pressure during the flight corresponding to the test.

FIG6 is a block diagram of the engine bleed air pressure control principle. The bleed air pressure simulation system 30 of the present invention has the following control principle: as the flight altitude and ambient pressure change, the engine bleed air pressure also gradually changes. According to the test requirements of the engine bleed air pressure at different flight altitudes, the control system uses pressure as the target control quantity. After comparing with the actual pressure feedback signal, the controller outputs the electric regulating valve opening control signal according to the current deviation. Through the rapid, stable and accurate control of the exhaust and intake electric regulating valves, the continuous and stable control of the pressure in the engine bleed air pressure simulation box is finally achieved.

Based on the engine bleed air pressure control principle, the bleed air pressure simulation system 30 can achieve continuous and stable control of the pressure in the controlled bleed air pressure simulation box 31 according to the following sub-steps:

SS31. Determine the target bleed air pressure value according to the given pressure change curve of the flight altitude profile and use it as the bleed air pressure control value;

SS32. The pressure sensor 35 detects the actual pressure value in the bleed air pressure simulation box 31 in real time and feeds it back to the PID controller;

SS33.PID controller compares the actual pressure feedback signal with the target bleed air pressure value at the corresponding moment and calculates the current pressure deviation;

The SS34.PID controller outputs a control signal according to the current pressure deviation, adjusts the opening of the air intake regulating valve 33 and the air outlet regulating valve 34, and adjusts the air intake and air outlet rates of the bleed air pressure simulation box 31 through rapid, stable and accurate control of the air intake regulating valve 33 and the air outlet regulating valve 34, so that the pressure in the bleed air pressure simulation box 31 gradually approaches the target bleed air pressure value, thereby achieving continuous and stable pressure control;

SS35. Periodically repeat sub-steps SS31 to SS34 so that the pressure in the bleed air pressure simulation box 31 continuously tracks the changing flight altitude profile, simulating the actual bleed air pressure changes at each stage of the engine.

The bleed air pressure simulation system of the present invention can accurately simulate the actual bleed air pressure changes of the engine under various flight conditions through various means such as boost air pump and regulating valve control, provide a highly reliable pressure environment for the test evaluation of bleed air related components in the fuel system such as the pressure reducer, and ensure the validity and reliability of ground test data.

FIG7 is a schematic diagram of the layout of the engine fuel consumption flow simulation system of the present invention. As shown in FIG7, the engine fuel consumption flow simulation system of the present invention uses the onboard fuel supply pump as the power source, and is mainly composed of a fuel pipeline, a fuel flow meter 43, a fuel pressure sensor 44, a fuel supply flow regulating valve 42, a pipeline valve, an oil storage tank 41, etc. The oil storage tank 41 is connected to the wing and fuselage fuel tanks through the fuel pipeline and uses the onboard fuel supply pump as the power source. By controlling the fuel supply flow and the fuel supply pressure to continuously change according to a given profile, the simulation of the engine fuel consumption flow is achieved. Specifically, the fuel pipeline is provided with a fuel flow regulating valve 42 with adjustable opening, a fuel flow meter 43, and a fuel pressure sensor 44. By continuously controlling the opening of the fuel flow regulating valve 42, the fuel flow of the engine fuel supply pipe can be continuously changed according to a preset flight operating condition profile to simulate the change in engine fuel consumption during actual flight. The fuel flow meter 43 monitors and feeds back the fuel flow in real time to evaluate the accuracy and dynamic response characteristics of the flow control. The fuel pressure sensor 44 monitors the fuel supply pressure in the fuel pipeline, and flow control is used to check whether the inlet fuel supply pressure meets the engine fuel supply pressure design requirements to ensure that the entire fuel supply system meets actual operating needs.

Figure 8 is a block diagram of the engine fuel flow control principle. The engine fuel flow control is used to accurately simulate the aircraft engine fuel flow, so as to check whether the performance of the aircraft fuel subsystem meets the engine operating conditions under this condition. The fuel flow control mainly uses computer systems, electric control valves, flow sensors and other main components to form a closed-loop control system for real-time flow control.

Based on the engine fuel flow control principle, the engine fuel flow simulation system 40 can achieve continuous control of its fuel flow according to the following sub-steps:

SS41. Obtain preset flight profile data, which reflects the target fuel flow rate corresponding to different flight stages, and use the data as the flow control amount;

SS42. The fuel flow meter 43 detects the actual value of the fuel flow rate in real time and feeds it back to the PID controller. By comparing it with the target fuel flow rate value at the corresponding moment, the current flow deviation value is calculated;

The SS43.PID controller calculates the expected opening value of the oil supply flow regulating valve 42 according to the current flow deviation value obtained, adjusts and controls the opening of the oil supply flow regulating valve 42, and adjusts the oil supply flow through the rapid, stable and accurate control of the oil supply flow regulating valve 42;

SS44. The fuel supply pressure is monitored in real time by the fuel pressure sensor 44. When the fuel supply pressure deviates from the design requirements of the engine fuel supply pressure, the fuel supply pressure is adjusted by increasing or decreasing the opening of the fuel supply flow regulating valve 42 to ensure that the engine working pressure requirements are met;

SS45. Repeat SS41 to SS44 periodically to allow the fuel supply flow to continuously track the changing flight profile, simulating the actual fuel consumption changes of the engine at each stage.

The engine fuel consumption flow simulation system of the present invention can accurately simulate the changes in the engine's fuel consumption under different flight conditions through multiple means such as computational control, electric regulating valves, and flow/pressure feedback, thereby providing reliable flow and pressure references for the normal operation of the fuel system under different flight conditions and ensuring that the fuel supply system meets actual operating requirements.

In a preferred embodiment of the present invention, the full-scale ground test device also includes a test measurement and control system. The test measurement and control system is mainly composed of a test unit, a control unit, an electrical unit, a central control console, etc., wherein the test unit is responsible for completing the physical signal acquisition of each test point, converting the physical signal into a digital quantity and uploading it to the central control console; the central control console sends the test start and stop instructions according to the test command requirements, and synchronously completes the data processing, acquisition and recording work; during the test, the control unit uses its own pressure or flow rate and other physical signal feedback as input, and completes the continuous and stable control simulation of the flight environment pressure and the engine fuel supply flow according to the flight profile instruction requirements; the electrical unit is responsible for simulating the onboard power supply status of the fuel system and the cross-linking status of the electrical cables, monitoring the main status parameters of the fuel system, and sending the relevant parameter information to the central control console to ensure the accuracy and reliability of the test process.

In the ground test device for the fuel system of a flying wing aircraft of the present invention, the pressure sensing ports of the onboard safety valve, vacuum prevention valve and pressure reducer are directly connected to the environmental pressure simulation box, and the water ring vacuum pump performs vacuum treatment on the environmental pressure simulation box. The air outlet rate and air intake rate in the environmental pressure simulation box are controlled by an electric regulating valve, so that the internal pressure of the environmental pressure simulation box can be continuously changed according to the environmental pressure corresponding to the flight altitude profile, and a pressure reference can be provided for the normal operation of the wing and fuselage ventilation components. In the process of simulating the flow rate of engine fuel consumption, an electric regulating valve is used as an opening regulating valve, and the test measurement and control system continuously controls the opening of the electric regulating valve to ensure that the flow rate of the fuel supply pipe changes continuously synchronously according to the given profile, and the fuel system is analyzed by the engine inlet pressure to see whether it meets the normal fuel supply pressure requirement. In the process of simulating the engine bleed air pressure, the fuselage pressure reducer is directly connected to the engine bleed air pressure simulation box, and the booster pump performs boost treatment on the engine bleed air pressure simulation box, and the air outlet rate and air intake rate in the engine bleed air pressure simulation box are controlled by the electric regulating valve, so that the internal pressure of the engine bleed air pressure simulation box can be continuously changed according to the engine bleed air pressure corresponding to the test.

Through the above embodiments, the purpose of the present invention is fully and effectively achieved. Those skilled in the art can understand that the present invention includes but is not limited to the contents described in the drawings and the above specific embodiments. Although the present invention has been described with respect to the most practical and preferred embodiments currently considered, it should be understood that the present invention is not limited to the disclosed embodiments, and any modification that does not deviate from the functional and structural principles of the present invention will be included in the scope of the claims.

Claims (10)

1. A full-scale ground test device for the fuel system of a flying wing aircraft, comprising an onboard fuel tank test simulation, a flight altitude environmental pressure simulation system, a bleed air pressure simulation system and an engine fuel consumption flow simulation system, characterized in that: The onboard fuel tank test simulation part includes a wing test fuel tank, a fuselage test fuel tank and fuel system accessories. The wing test fuel tank and the fuselage test fuel tank have the same external dimensions as the actual onboard fuel tank, and the installation position of each fuel system accessory on the fuel tank is consistent with the actual installation state; The flight altitude environmental pressure simulation system comprises an environmental pressure simulation box and a vacuum pumping device. The environmental pressure simulation box is connected to the ventilation components of the wing and fuselage oil tanks, the ground atmospheric environment, and the vacuum pumping device through gas pipelines, and the internal pressure thereof is continuously changed according to the environmental pressure corresponding to the flight altitude profile by controlling the air intake rate and the air outlet rate. The bleed air pressure simulation system comprises a bleed air pressure simulation box and a boost air pump. The bleed air pressure simulation box is connected to the wing and fuselage fuel tanks, the ground atmospheric environment, and the boost air pump through gas pipelines, and the internal pressure thereof is continuously changed according to the engine bleed air pressure corresponding to the test by controlling the air intake rate and the air outlet rate thereof. The engine fuel consumption flow simulation system includes an oil storage tank, which is connected to the wing and fuselage fuel tanks through fuel pipelines and uses an on-board fuel supply pump as a power source. The engine fuel consumption flow simulation is achieved by controlling the fuel supply flow and the fuel supply pressure to continuously change according to a given profile. 2. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 1 is characterized in that, in the onboard fuel tank test simulation part, the fuel system accessories at least include a ventilation pipe and a fuel pipe connected to the wing and fuselage fuel tanks, and a ventilation component attached to the ventilation pipe and a fuel supply component on the fuel pipe, the ventilation component at least includes an onboard safety valve, an anti-vacuum valve and a pressure reducer, the fuel supply component at least includes an onboard fuel supply pump, and the bleed air pressure simulation box is connected to the onboard safety valve, the anti-vacuum valve and the pressure reducer through a gas pipeline, the bleed air pressure simulation box is connected to the pressure reducer through a gas pipeline, and the oil storage tank is connected to the wing and fuselage fuel tanks through a fuel pipeline. 3. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 2 is characterized in that the fuel supply component also includes a fuel consumption sensor and a pressure sensor, and the fuel consumption sensor is used to accurately measure the amount of fuel supplied from the wing and fuselage tanks to the fuel storage tank. 4. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 1 is characterized in that, in the flight altitude environmental pressure simulation system, the environmental pressure simulation box is provided with a vacuum pressure sensor connected to its internal space, and its air intake pipe is provided with an air intake regulating valve and the air outlet pipe is provided with an air outlet regulating valve, and the air intake rate and the air outlet rate of the environmental pressure simulation box are respectively controlled by the air intake regulating valve and the air outlet regulating valve. 5. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 4 is characterized in that the flight altitude ambient pressure simulation system realizes continuous and stable control of the pressure in its ambient pressure simulation box according to the following sub-steps: SS21. Obtain preset flight altitude profile data, which reflects the changing trend of ambient pressure at different flight altitudes, and use the data as the target ambient pressure control amount of the ambient pressure simulation box; SS22. Detect the actual pressure value in the environmental pressure simulation box in real time and feed it back to the PID controller. The PID controller calculates the current pressure deviation by comparing the actual pressure feedback value with the target environmental pressure value corresponding to the flight altitude; SS23.PID controller calculates the expected opening values of the air inlet regulating valve and the air outlet regulating valve according to the current pressure deviation and outputs a control signal to adjust the opening of the air inlet regulating valve and the air outlet regulating valve, thereby adjusting the air inlet and air outlet rates of the environmental pressure simulation box to ensure continuous and stable changes in the internal pressure of the environmental pressure simulation box. SS24. Repeat sub-steps SS21 to SS23 periodically to make the pressure in the environmental pressure simulation box continuously track the changing flight altitude profile data, simulate the environmental pressure changes at different flight altitudes, and provide a pressure reference for the normal operation of the wing and fuselage tank ventilation components. 6. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 1 is characterized in that, in the bleed air pressure simulation system, the bleed air pressure simulation box is provided with a gas pressure sensor connected with its internal space, and its intake boost pipeline is provided with an intake regulating valve, and the outlet pipeline is provided with an outlet regulating valve, and the intake and outlet rates of the bleed air pressure simulation box are respectively controlled by the intake regulating valve and the outlet regulating valve, so that the internal pressure thereof is continuously changed according to the engine bleed air pressure during the flight corresponding to the test. 7. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 6, characterized in that the bleed air pressure simulation system realizes continuous and stable control of the pressure in the controlled bleed air pressure simulation box according to the following sub-steps: SS31. Determine the target bleed air pressure value according to the given pressure change curve of the flight altitude profile and use it as the bleed air pressure control value; SS32. The pressure sensor detects the actual pressure value in the bleed air pressure simulation box in real time and feeds it back to the PID controller; SS33.PID controller compares the actual pressure feedback signal with the target bleed air pressure value at the corresponding moment and calculates the current pressure deviation; The SS34.PID controller outputs a control signal according to the current pressure deviation to adjust the opening of the air intake regulating valve and the air outlet regulating valve. Through the rapid, stable and accurate control of the air intake regulating valve and the air outlet regulating valve, the air intake and air outlet rates of the bleed air pressure simulation box are adjusted, so that the pressure in the bleed air pressure simulation box gradually approaches the target bleed air pressure value, thus achieving continuous and stable pressure control; SS35. Periodically repeat sub-steps SS31 to SS34 so that the pressure in the bleed air pressure simulation box continuously tracks the changing flight altitude profile, simulating the actual bleed air pressure changes at each stage of the engine. 8. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 1 is characterized in that, in the engine fuel consumption flow simulation system, the fuel pipeline is provided with an opening-adjustable fuel flow regulating valve, a fuel flow meter, and a fuel pressure sensor, and the fuel supply flow of the engine fuel supply pipe is continuously changed according to a preset flight condition profile by continuously controlling the opening of the fuel supply flow regulating valve, the fuel supply flow is monitored and fed back in real time by the fuel flow meter, and the fuel supply pressure in the fuel pipeline is monitored by the fuel pressure sensor. 9. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 8, characterized in that the engine fuel consumption flow simulation system realizes continuous control of its fuel supply flow according to the following sub-steps: SS41. Obtain preset flight profile data, which reflects the target fuel flow rate corresponding to different flight stages, and use the data as the flow control amount; SS42. The fuel flow meter detects the actual value of the fuel flow in real time and feeds it back to the PID controller. By comparing it with the target fuel flow value at the corresponding moment, the current flow deviation value is calculated; The SS43.PID controller calculates the expected opening value of the oil supply flow control valve 42 according to the current flow deviation value obtained, adjusts and controls the opening of the oil supply flow control valve, and adjusts the oil supply flow through fast, stable and accurate control of the oil supply flow control valve; SS44. The fuel supply pressure is monitored in real time through the fuel pressure sensor. When the fuel supply pressure deviates from the design requirements of the engine fuel supply pressure, the fuel supply pressure is adjusted by increasing or decreasing the opening of the fuel supply flow regulating valve to ensure that the engine working pressure requirements are met; SS45. Repeat SS41 to SS44 periodically to allow the fuel supply flow to continuously track the changing flight profile, simulating the actual fuel consumption changes of the engine at each stage. 10. The full-scale ground test device for the fuel system of a flying wing aircraft according to claim 1 is characterized in that the test device also includes a test measurement and control system, including a test unit, a control unit, an electrical unit and a central control console, wherein the test unit is responsible for completing the physical signal acquisition of each test point, converting the physical signal into a digital quantity and uploading it to the central control console; the central control console sends the test start and stop instructions according to the test command requirements, and synchronously completes the data processing, acquisition and recording work; during the test, the control unit uses its own pressure or flow and other physical signal feedback as input, and completes the continuous and stable control simulation of the flight environment pressure and the engine fuel supply flow according to the flight profile instruction requirements; the electrical unit is responsible for simulating the onboard power supply status and electrical cable cross-linking status of the fuel system, monitoring the main status parameters of the fuel system, and sending the relevant parameter information to the central control console to ensure the accuracy and reliability of the test process.