A test simulation system and method for fuel delivery characteristics of a refueling pod

Abstract

The application belongs to the technical field of aircraft in-flight refueling, and particularly relates to a test simulation system and method for fuel delivery characteristics of a refueling pod, comprising: a ground controller, a steel fuel tank of a refueling aircraft, an in-flight refueling pump set, a fuel delivery pipeline, a negative pressure fuel tank of a receiver aircraft, a flight environment pressure simulation box, a ram turbine pump of the refueling pod, an electro-hydraulic proportional valve, a high-speed hydraulic motor, a refueling hose, a refueling and receiving assembly, a pressure regulating valve, a receiving flow regulating valve and a receiving flow sensor. The ground controller adjusts the rotating speed of the ram turbine pump of the refueling pod directly connected with the hydraulic motor through the electro-hydraulic proportional valve according to the command of a pressure regulating controller of the refueling pod, so that the pressure regulating process simulation of the refueling pod is realized. The ground test controller changes the opening degree of the regulating valve to simulate the change of the receiving flow, so that the verification of the fuel delivery characteristics of the refueling pod under different receiving flows is realized. The negative pressure fuel tank of the receiver aircraft is provided with an oil discharge pump, so that the continuous simulation of the receiving process is realized.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft aerial refueling, and in particular relates to a test simulation system and method for the fuel delivery characteristics of a refueling pod. Background Art

[0002] Prior art uses aerial test flights to verify the refueling pod's towing, retraction, refueling, and detachment functions. However, ground testing, lacking the aerodynamic conditions of the air, often relies on static docking, focusing on verifying the fuel transfer function. According to limited public information, factory test methods for refueling pods fail to consider the impact of the high-altitude environment, making it impossible to draw conclusions about the refueling pod's high-altitude fuel transfer characteristics. Therefore, achieving experimental simulation of the refueling pod's fuel transfer characteristics under ground conditions has become a key technical issue that urgently needs to be addressed. Summary of the Invention

[0003] The purpose of this application is to provide a test simulation system and method for the fuel delivery characteristics of a refueling pod, so as to solve the problem that the factory test method of the refueling pod in the prior art does not take into account the impact of the pod's high-altitude environment.

[0004] The technical solution of this application is: a test simulation method for fuel delivery characteristics of a refueling pod, comprising:

[0005] Ground controller initialization;

[0006] After the ground controller initialization is complete, refuel the tanker's steel test tank;

[0007] After the steel test tank of the fuel dispenser is refueled, the pressure setting value is manually input to the ground controller. The ground controller sends an opening adjustment instruction to the vacuum regulating valve to control the opening of the lower chassis so that the pressure inside each chassis reaches the set value.

[0008] After the pressure in each chassis reaches the set value, the ground controller controls the fuel pump group to start and keep the fuel pump group in a zero flow state;

[0009] After the refueling pump group is started, the refueling valve is opened and the flow set value is input to the ground controller; after receiving the flow set value, the ground controller sends an opening adjustment instruction to the flow control valve so that the refueling flow of the flow control valve reaches the set value, and then collects the refueling flow of the refueling pump group in real time and sends it to the ground controller;

[0010] The ground controller obtains the oil flow rate in the refueling pump group and determines whether the oil flow rate reaches the set value. If so, it executes the next step;

[0011] Obtain the aircraft's flight altitude during the air test and compare it with the set value to determine whether it meets the set altitude value. If so, the test ends.

[0012] Preferably, the ground controller initialization includes power-on self-test of the sensor, initial reset of the oil flow valve, and initial reset of the control signal of the electro-hydraulic proportional valve.

[0013] Preferably, refueling the steel test oil tank of the refueling machine is specifically as follows: the ground controller sends a control instruction to the refueling regulating valve to control the refueling flow rate and add a certain amount of test oil into the steel refueling machine tank.

[0014] Preferably, the lower-level chassis includes a negative pressure fuel tank of the receiving aircraft, a flight environment pressure simulation box and a steel test fuel tank of the tanker.

[0015] Preferably, an oil flow sensor is provided in the refueling pump group. The oil flow sensor collects the test oil flow of the refueling pump group and transmits it to the ground controller. When the ground controller determines that the signal collected by the oil flow sensor is 0, the refueling pump group is started.

[0016] Preferably, when the oil receiving flow rate does not reach the set value, a new flow rate set value is input to the ground controller until the oil receiving flow rate in the refueling pump group reaches the set value.

[0017] Preferably, when the aircraft flight altitude does not meet the altitude setting value, the pressure setting value is modified, the refueling pump group is repeatedly opened according to the new pressure setting value and the oil flow control of the refueling pump group is re-performed until the altitude setting value is reached.

[0018] As a specific embodiment, a test simulation system for fuel delivery characteristics of a refueling pod includes: a ground controller, a steel fuel tank of a refueling machine, an aerial refueling pump assembly, a fuel delivery pipeline, a negative pressure fuel tank of a receiving aircraft, a flight environment pressure simulation box, a refueling pod ramjet pump, an electro-hydraulic proportional valve, a high-speed hydraulic motor, a refueling hose, a refueling and receiving assembly, a pressure regulating valve, a receiving flow regulating valve, and a receiving flow sensor; the aerial refueling pump assembly and fuel delivery pipeline are installed on the steel fuel tank of the refueling machine, and two pressure regulating valves are installed on the steel fuel tank of the refueling machine, the flight environment pressure simulation box, and the negative pressure fuel tank of the receiving aircraft, one of the pressure regulating valves having an outlet to the test laboratory atmosphere, and the other pressure regulating valve having an outlet to a vacuum suction pipeline;

[0019] The refueling pod ramjet pump is connected to the aerial refueling pump group and one end of the fuel delivery pipeline. The ground controller is located on the ground and is electrically connected to the electro-hydraulic proportional valve, the refueling pod ramjet pump, the oil receiving flow regulating valve and the oil receiving flow sensor. The high-speed hydraulic motor is connected between the electro-hydraulic proportional valve and the refueling pod ramjet pump to provide power to the refueling pod ramjet pump; the refueling hose and the refueling and receiving assembly are connected in series, and one end is connected to the refueling pod ramjet pump and the other end is connected to the oil receiving flow regulating valve; the oil receiving flow regulating valve and the oil receiving flow sensor are connected in series, the flight environment pressure simulation box is connected to the refueling pod ramjet pump, and the negative pressure fuel tank of the receiving aircraft is connected to the oil receiving flow regulating valve.

[0020] Preferably, a human-machine interface is provided on the ground controller, which can manually input the settings of the test pressure and flow parameters, and simultaneously receive the pressure adjustment instructions of the refueling pod and send adjustment instructions to the electro-hydraulic proportional valve at the front end of the hydraulic motor.

[0021] Preferably, a certain amount of test oil is stored in the steel fuel tank of the tanker, and an aerial refueling pump group and a fuel delivery pipeline are installed inside. The internal shape and size of the tank are consistent with the actual fuel tank state of the aircraft.

[0022] Preferably, a space of a certain capacity is provided in the negative pressure fuel tank of the receiving aircraft to temporarily store the fuel accumulated during the aerial refueling, and an oil drain pump is installed inside the negative pressure fuel tank to drain the accumulated fuel in time.

[0023] Preferably, a refueling pod pressure sensor is installed inside the flight environment pressure simulation box. Using a vacuum suction method, the ground controller controls the opening of a pressure regulating valve connected to the refueling pod to ensure that the internal pressure is consistent with the corresponding ambient pressure under actual flight altitude conditions.

[0024] Preferably, the tanker steel tank, the flight environment pressure simulation box and the receiving aircraft negative pressure tank are closed containers and are each equipped with two pressure regulating valves, and the outlet of one of the pressure regulating valves is the laboratory atmospheric environment, and the outlet of the other pressure regulating valve is the vacuum suction pipeline.

[0025] The present application describes a system and method for testing and simulating the fuel delivery characteristics of a refueling pod. A ground controller, based on instructions from the refueling pod pressure regulator controller, regulates the speed of the refueling pod's ramjet pump, directly connected to the hydraulic motor, via an electro-hydraulic proportional valve, thereby simulating the refueling pod's pressure regulation process. The ground test controller varies the opening of the regulating valve to simulate changes in the receiving fuel flow rate, verifying the refueling pod's fuel delivery characteristics under varying fuel flow rates. The receiving aircraft's negative pressure tank includes a built-in oil drain pump to prevent fuel overflow, enabling continuous simulation of the refueling process. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions provided by this application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of this application.

[0027] Figure 1 This is a schematic diagram of the overall process of this application;

[0028] Figure 2 This is the overall system structure diagram of this application.

[0029] In the figure, 1. Steel fuel tank of the tanker; 2. Aerial refueling pump group and fuel delivery pipeline; 3. High-speed hydraulic motor; 4. Ramjet pump of the refueling pod; 5. Electro-hydraulic proportional valve; 6. Ground controller; 7. Refueling hose; 8. Fueling and receiving components; 9. Fuel receiving flow regulating valve; 10. Fuel receiving flow sensor; 11. Flight environment pressure simulation box; 12. Negative pressure tank of the receiving aircraft. DETAILED DESCRIPTION

[0030] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0031] A test simulation method for fuel delivery characteristics of a refueling pod, such as Figure 1 , including the following steps:

[0032] Step S100: Initializing the ground controller. To ensure the safe operation of the test system, the ground controller initialization mainly includes sensor power-on self-test, initial reset of the oil flow valve, and initial reset of the electro-hydraulic proportional valve control signal.

[0033] Step S200: Filling the steel test tank of the fuel dispenser. After the ground controller is initialized, the steel test tank of the fuel dispenser is filled with fuel. Specifically, the ground controller sends a control command to the fuel regulating valve to control the fuel flow and add a certain amount of test oil to the steel fuel dispenser tank.

[0034] Step S300: Pressure Control. After refueling the steel test tank, manually input the pressure setting value into the ground controller. The ground controller sends an opening adjustment command to the vacuum control valve, controlling the opening of the lower-level chassis until the pressure inside each chassis reaches the set value.

[0035] The lower-level chassis includes the receiving aircraft's negative pressure fuel tank, the flight environment pressure simulation box and the tanker's steel test fuel tank.

[0036] Step S400: Start the refueling pump group. After the pressure in each chassis reaches the set value, the ground controller controls the refueling pump group to start and keep the refueling pump group in a zero flow state.

[0037] Preferably, an oil flow sensor is provided in the refueling pump group. The oil flow sensor collects the test oil flow of the refueling pump group and transmits it to the ground controller. When the ground controller determines that the signal collected by the oil flow sensor is 0, the refueling pump group is started.

[0038] Step S500: Oil flow control. After the refueling pump assembly is started, the refueling valve is opened and the flow setpoint is input to the ground controller. After receiving the flow setpoint, the ground controller sends an opening adjustment command to the flow control valve to adjust the refueling flow rate to the setpoint. The ground controller then collects the refueling pump assembly's oil flow rate in real time and sends it to the ground controller.

[0039] In step S600, the ground controller obtains the oil flow rate in the refueling pump group and determines whether the oil flow rate has reached the set value. If so, the next step is executed; if not, the process returns to step S500 and inputs a new flow rate set value to the ground controller until the oil flow rate in the refueling pump group reaches the set value.

[0040] Step S700, obtain the flight altitude of the aircraft during the aerial test flight, compare it with the set value, and determine whether the altitude setting value is met. If so, the test ends and returns to step S300, repeating steps S400 to S500, modifying the pressure setting value, and repeatedly turning on the refueling pump group according to the new pressure setting value and re-controlling the oil flow of the refueling pump group until the altitude setting value is reached.

[0041] Through this design, the ground controller simulated the refueling pod's pressure regulation process by adjusting the speed of the refueling pod's ramjet pump, directly connected to the hydraulic motor, via an electro-hydraulic proportional valve based on instructions from the refueling pod's pressure regulator controller. The ground test controller varied the opening of the regulating valve to simulate changes in the refueling flow rate, verifying the refueling pod's fuel delivery characteristics under varying refueling flow rates. The receiving aircraft's negative pressure tank included a built-in drain pump to prevent overflow, enabling continuous simulation of the refueling process.

[0042] Among them, the refueling pod's built-in refueling pressure sensor was modified on the ground and placed in the flight environment pressure simulation box.

[0043] As a specific implementation method, the following is described with a specific example:

[0044] Step S100, the sensor is powered on for self-test. The initial value of the tank pressure sensor of the refueling machine is 96kPa, the initial value of the tank pressure of the receiving aircraft is 96kPa, the initial value of the pressure in the flight environment chamber is 96kPa, the initial value of the receiving fuel flow sensor is 0, the initial opening of the pressure regulating valve is 0, and the opening of the receiving fuel flow regulating valve is 0.

[0045] In step S200, the ground controller sends a refueling flow command of 1500 L / min to the refueling regulating valve, continuously injects 10 tons of test oil into the steel refueling machine tank and automatically stops refueling.

[0046] Step S300, manually input the pressure setting values ​​to the ground controller: the pressure setting value of the negative pressure tank of the receiving aircraft is 50kPa, the pressure setting value of the flight environment pressure simulation box is 50kPa, and the pressure setting value of the steel test tank of the tanker is 73kPa.

[0047] In step S400, the ground controller controls the refueling pump group to be powered on and operated.

[0048] Step S500: manually input the refueling flow setting value 1000L / min into the ground controller. The controller adjusts the refueling flow regulating valve in real time based on the refueling flow feedback value so that the refueling flow reaches the set value.

[0049] Step S600: If the oil receiving flow rate needs to be changed, return to step S500 to complete the modification of the oil receiving flow rate value; otherwise, proceed to step S700;

[0050] Step S700: If the flight altitude needs to be changed, step S300 needs to be repeated to complete the modification of the ambient pressure value, and steps S400 to S500 need to be repeated; otherwise, the test ends.

[0051] As a specific embodiment, a ground simulation system for the aerial refueling process of a refueling pod is also provided, which adopts the above design, such as Figure 2 The system includes: a ground controller 6, a tanker steel tank 1, an aerial refueling pump assembly and fuel delivery pipeline 2, a receiving aircraft negative pressure tank 12, a flight environment pressure simulation chamber 11, a refueling pod ramjet pump 4, an electro-hydraulic proportional valve 5, a high-speed hydraulic motor 3, a refueling hose 7, a refueling and receiving assembly 8, a receiving fuel flow regulating valve 9, and a receiving fuel flow sensor 10. The aerial refueling pump assembly and fuel delivery pipeline 2 are installed on the tanker steel tank 1. The tanker steel tank 1, the flight environment pressure simulation chamber 11, and the receiving aircraft negative pressure tank 12 are all closed tanks. Each of these tanks is equipped with two pressure regulating valves, one of which is connected to the laboratory atmosphere, and the other to the vacuum suction pipeline.

[0052] The refueling pod ramjet pump 4 is connected to the aerial refueling pump group and one end of the fuel delivery pipeline 2. The ground controller 6 is located on the ground and is electrically connected to the electro-hydraulic proportional valve 5, the refueling pod ramjet pump 4, the oil receiving flow regulating valve 9 and the oil receiving flow sensor 10. The high-speed hydraulic motor 3 is connected between the electro-hydraulic proportional valve 5 and the refueling pod ramjet pump 4 to provide power to the refueling pod ramjet pump 4; the refueling hose 7 and the refueling and receiving assembly 8 are coordinated in series, and one end is connected to the refueling pod ramjet pump 4 and the other end is connected to the oil receiving flow regulating valve 9; the oil receiving flow regulating valve 9 and the oil receiving flow sensor 10 are connected in series; the flight environment pressure simulation box 11 is connected to the refueling pod ramjet pump 4, and the negative pressure fuel tank 12 of the receiving aircraft is connected to the oil receiving flow regulating valve 9.

[0053] Preferably, the ground controller 6 is provided with a human-machine interface, which can manually input the settings of parameters such as test pressure and flow, and at the same time receive the pressure adjustment instructions of the refueling pod and send adjustment instructions to the electro-hydraulic proportional valve 5 at the front end of the hydraulic motor;

[0054] Preferably, a certain amount of test oil is stored in the steel tank 1 of the tanker, and an aerial refueling pump group and a fuel delivery pipeline are installed inside. The internal shape and size of the tank are consistent with the actual tank state of the aircraft.

[0055] Preferably, a space of a certain capacity is provided in the negative pressure fuel tank 12 of the receiving aircraft, which can temporarily store the fuel accumulated during the aerial refueling, and an oil drain pump is installed inside it to drain the accumulated fuel in time to maintain the long-term operation of the test process.

[0056] Preferably, a refueling pod pressure sensor is installed inside the flight environment pressure simulation box 11. Using a vacuum suction method, the ground controller 6 controls the opening of a pressure regulating valve connected to the box to control the internal pressure to be consistent with the corresponding ambient pressure under actual flight altitude conditions.

[0057] Preferably, the tanker steel tank 1, the flight environment pressure simulation box 11 and the receiving aircraft negative pressure tank 12 are closed containers and are each equipped with two pressure regulating valves, and the outlet of one of the pressure regulating valves is the laboratory atmospheric environment, and the outlet of the other pressure regulating valve is a vacuum suction pipeline.

[0058] Before the test, a certain amount of test fuel was added to the tanker's steel tank 1 through the refueling control valve at the refueling port. The target pressures for the refueler's steel tank 1, the flight environment pressure simulation chamber 11, and the receiving aircraft's negative pressure tank 12 were manually set at the ground controller 6. The vacuum system controlled the pressure control valves to maintain the ambient pressures within these three containers at the target values. After the refueling pump assembly was activated, the fuel in the fuel delivery pipeline was in a static, non-flowing state. When the refueling pod began refueling, the receiving flow rate was manually set to the set value at the ground controller 6. The receiving flow control valve 9 regulated the receiving flow rate based on the feedback from the receiving flow sensor 10. During this time, the refueling pod sent pressure adjustment commands to the ground controller 6 based on the test feedback from the refueling pod pressure sensor. The ground controller 6 directly controlled the opening of the electro-hydraulic proportional valve 5, varying the hydraulic motor speed to change the ramjet turbine speed, thereby varying the receiving flow rate and pressure.

[0059] The fuel flowing out of the outlet of the refueling and receiving assembly 8 flows into the negative pressure fuel tank 12 of the receiving aircraft, and the fuel in the tank is simultaneously emptied by the oil discharge pump during the test, thereby maintaining a long-term aerial refueling test of the refueling pod.

[0060] This design realistically simulates the ambient pressure inside the fuel tank of the refueling and receiving aircraft during aerial refueling, as well as the operating pressure of the refueling pressure sensor during high-altitude flight. This test simulation system utilizes a ground controller to conduct testing, offering significant advantages such as high test realism and a high degree of automation.

[0061] Finally, it should be noted that the drawings of the embodiments disclosed in the present invention only involve structures related to the embodiments disclosed in the present invention. Other structures can refer to common designs. In the absence of conflicts, the same embodiment and different embodiments of the present invention can be combined with each other.

[0062] Finally: The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A test simulation method for fuel delivery characteristics of a refueling pod, characterized in that: include: Ground controller initialization; After the ground controller initialization is complete, refuel the tanker's steel test tank; After the steel test tank of the fuel dispenser is refueled, the pressure setting value is manually input to the ground controller. The ground controller sends an opening adjustment instruction to the vacuum regulating valve to control the opening of the lower chassis so that the pressure inside each chassis reaches the set value. After the pressure in each chassis reaches the set value, the ground controller controls the fuel pump group to start and keep the fuel pump group in a zero flow state; After the refueling pump group is started, the refueling valve is opened and the flow set value is input to the ground controller; after receiving the flow set value, the ground controller sends an opening adjustment instruction to the flow control valve so that the refueling flow of the flow control valve reaches the set value, and then collects the refueling flow of the refueling pump group in real time and sends it to the ground controller; The ground controller obtains the oil flow rate in the refueling pump group and determines whether the oil flow rate reaches the set value. If so, it executes the next step; Obtain the aircraft's flight altitude during the air test and compare it with the set value to determine whether it meets the set altitude value. If so, the test ends.

2. The test simulation method for fuel delivery characteristics of a refueling pod according to claim 1, characterized in that: The ground controller initialization includes sensor power-on self-test, initial reset of the oil flow valve, and initial reset of the electro-hydraulic proportional valve control signal.

3. The test simulation method for fuel delivery characteristics of a refueling pod according to claim 1, characterized in that: The specific steps of refueling the steel test fuel tank of the refueling machine are as follows: the ground controller sends a control instruction to the refueling regulating valve to control the refueling flow and add a certain amount of test oil into the steel refueling machine tank.

4. The test simulation method for fuel delivery characteristics of a refueling pod according to claim 1, characterized in that: The lower-level chassis includes the receiving aircraft's negative pressure fuel tank, the flight environment pressure simulation box and the tanker's steel test fuel tank.

5. The test simulation method for fuel delivery characteristics of a refueling pod according to claim 1, characterized in that: An oil flow sensor is installed in the refueling pump group. The oil flow sensor collects the test oil flow of the refueling pump group and transmits it to the ground controller. When the ground controller determines that the signal collected by the oil flow sensor is 0, the refueling pump group is started.

6. The test simulation method for fuel delivery characteristics of a refueling pod according to claim 1, characterized in that: When the oil flow rate does not reach the set value, a new flow rate set value is input to the ground controller until the oil flow rate in the refueling pump group reaches the set value.

7. The test simulation method for fuel delivery characteristics of a refueling pod according to claim 1, characterized in that: When the aircraft's flight altitude does not meet the altitude setting value, the pressure setting value is modified, and the refueling pump group is repeatedly opened and the oil flow control of the refueling pump group is re-performed according to the new pressure setting value until the altitude setting value is reached.

8. A test simulation system for fuel delivery characteristics of a refueling pod, using the method according to any one of claims 1 to 7, characterized in that: include: A ground controller (6), a steel tank of a tanker (1), an aerial refueling pump group, a fuel delivery pipeline, a negative pressure tank of a receiving aircraft (12), a flight environment pressure simulation box (11), a refueling pod ramjet pump (4), an electro-hydraulic proportional valve (5), a high-speed hydraulic motor (3), a refueling hose (7), a refueling and receiving assembly (8), a pressure regulating valve, a receiving flow regulating valve (9) and a receiving flow sensor (10); the aerial refueling pump group and the fuel delivery pipeline (2) are arranged on the steel tank of the tanker (1), and two pressure regulating valves are installed on the steel tank of the tanker (1), the flight environment pressure simulation box (11) and the negative pressure tank of the receiving aircraft (12), wherein the outlet of one pressure regulating valve is the test laboratory atmosphere, and the outlet of the other pressure regulating valve is the vacuum suction pipeline; The refueling pod ramjet pump (4) is connected to an aerial refueling pump group and one end of a fuel delivery pipeline (2); a ground controller (6) is arranged on the ground and is electrically connected to an electro-hydraulic proportional valve (5), the refueling pod ramjet pump (4), a receiving oil flow regulating valve (9) and a receiving oil flow sensor (10); a high-speed hydraulic motor (3) is connected between the electro-hydraulic proportional valve (5) and the refueling pod ramjet pump (4) and is used to provide power to the refueling pod ramjet pump (4); a refueling hose (7) and a refueling and receiving assembly (8) are connected in series, and one end is connected to the refueling pod ramjet pump (4) and the other end is connected to the receiving oil flow regulating valve (9); the receiving oil flow regulating valve (9) and the receiving oil flow sensor (10) are connected in series; a flight environment pressure simulation box (11) is connected to the refueling pod ramjet pump (4); and a receiving aircraft negative pressure fuel tank (12) is connected to the receiving oil flow regulating valve (9).

9. The test simulation system for fuel delivery characteristics of a refueling pod according to claim 8, characterized in that: The ground controller (6) is provided with a human-machine interactive interface, which can manually input the settings of the test pressure and flow parameters, and simultaneously receive the pressure adjustment instructions of the refueling pod and send adjustment instructions to the electro-hydraulic proportional valve (5) at the front end of the hydraulic motor.

10. The fuel delivery characteristics test simulation system of a refueling pod according to claim 8, characterized in that: A certain amount of test oil is stored in the steel fuel tank (1) of the tanker, and an aerial refueling pump group and a fuel delivery pipeline are installed inside. The shape and size of the internal fuel tank are consistent with the state of the actual fuel tank of the aircraft.

11. The test simulation system for fuel delivery characteristics of a refueling pod according to claim 8, characterized in that: The negative pressure fuel tank (12) of the receiving aircraft is provided with a space of a certain capacity, which can temporarily store the fuel accumulated during the aerial refueling, and an oil discharge pump is installed therein for timely emptying the fuel accumulated therein.

12. The fuel delivery characteristics test simulation system of a refueling pod according to claim 8, characterized in that: A refueling pod pressure sensor is installed inside the flight environment pressure simulation box (11). The ground controller (6) controls the opening of a pressure regulating valve connected to the refueling pod pressure sensor by using a vacuum suction method to control the internal pressure to be consistent with the corresponding environmental pressure under the actual flight altitude conditions.

13. The fuel delivery characteristics test simulation system of a refueling pod according to claim 8, characterized in that: The tanker steel tank (1), the flight environment pressure simulation box (11) and the receiving aircraft negative pressure tank (12) are closed containers and are each equipped with two pressure regulating valves, and the outlet of one of the pressure regulating valves is the laboratory atmosphere, and the outlet of the other pressure regulating valve is a vacuum suction pipeline.

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