Test simulation system and method for fuel delivery characteristics of refueling pod

Abstract

The invention belongs to the technical field of aircraft air refueling, and particularly relates to a refueling pod fuel delivery characteristic test simulation system and method. Comprising a ground controller, a refueling machine steel oil tank, an air refueling pump set, a fuel oil conveying pipeline, a refueling machine negative pressure oil tank, a flight environment pressure simulation tank, a refueling pod punching turbine pump, an electro-hydraulic proportional valve, a high-speed hydraulic motor, a refueling hose, a refueling and receiving assembly, a pressure adjusting valve, a receiving oil flow adjusting valve and a receiving oil flow sensor. The ground controller adjusts the rotating speed of the refueling pod stamping turbine pump directly connected with the hydraulic motor through the electro-hydraulic proportional valve according to the instruction requirement of the refueling pod pressure regulating controller, and the refueling pod pressure regulating process is simulated. The ground test controller changes the opening degree of the adjusting valve, changes of oil receiving flow are simulated, and verification of fuel oil conveying characteristics of the refueling pod under different oil receiving flows is achieved. The oil drain pump is arranged in the negative pressure oil tank of the oil receiving machine, and continuous simulation of the oil receiving process is achieved.

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 fuel delivery characteristics of a refueling pod. Background Art

[0002] In the prior art, aerial test flights are used to verify the functions of the refueling pod, such as towing, circling, refueling and detaching. However, under ground test conditions, due to the lack of aerodynamic conditions in the air, static docking is often used to focus on completing the verification of the fuel delivery function. According to a few public data, the factory test method of the refueling pod does not take into account the impact of the pod's high-altitude environment, and it is impossible to draw conclusions about the high-altitude fuel delivery characteristics of the refueling pod. Therefore, how to achieve experimental simulation of the fuel delivery characteristics of the refueling pod under ground conditions has become one of the key technical issues that need to be solved urgently. 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 the present 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 steel test tank;

[0007] After the steel test tank of the tanker is refueled, the pressure setting value is manually input to the ground controller, and 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 each chassis reaches the pressure setting value, the ground controller controls the refueling pump group to start and keep the refueling pump group in a zero flow state;

[0009] After the refueling pump group is started, the refueling valve is opened and the flow setting value is input to the ground controller; after receiving the flow setting 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 oil receiving 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, the next step is executed;

[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 resetting of the oil flow valve, and initial resetting of the control signal of the electro-hydraulic proportional valve.

[0013] Preferably, refueling the steel test oil tank of the fuel dispenser is specifically performed as follows: a ground controller sends a control instruction to a refueling regulating valve to control the refueling flow rate and add a certain amount of test oil into the steel fuel dispenser 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, which collects the oil flow of the refueling pump group test 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 setting 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 implementation method, 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 group, 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 refueling flow regulating valve and a receiving refueling flow sensor; the aerial refueling pump group and the fuel delivery pipeline are arranged on the steel fuel tank of the refueling machine, and the steel fuel tank of the refueling machine, the flight environment pressure simulation box, and the negative pressure fuel tank of the receiving aircraft are all equipped with two pressure regulating valves, the outlet of one of the pressure regulating valves is the test laboratory atmospheric environment, and the outlet of the other pressure regulating valve is 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 arranged 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 matched 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 interaction 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, and the internal shape and size of the tank are consistent with the actual fuel tank status of the aircraft.

[0022] Preferably, a space of a certain capacity is provided in the negative pressure fuel tank of the receiving aircraft, which can 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, and a vacuum suction method is adopted, whereby the ground controller controls the opening of a pressure regulating valve connected to the refueling pod to make the internal pressure consistent with the corresponding ambient pressure under the 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 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.

[0025] In the test simulation system and method of the fuel delivery characteristics of the refueling pod of the present application, the ground controller adjusts the speed of the refueling pod ramjet pump directly connected to the hydraulic motor through the electro-hydraulic proportional valve according to the instructions of the refueling pod pressure regulating controller, thereby realizing the simulation of the refueling pod pressure regulation process. The ground test controller changes the opening of the regulating valve to simulate the change of the oil receiving flow rate, thereby realizing the verification of the fuel delivery characteristics of the refueling pod under different oil receiving flow rates. The negative pressure tank of the receiving machine has a built-in oil drain pump to prevent the negative pressure tank from overflowing, thereby realizing the continuous simulation of the refueling process. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solution provided by the present application, the following is a brief introduction to the accompanying drawings. Obviously, the accompanying drawings described below are only some embodiments of the present 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 turbine pump of the refueling pod; 5. Electro-hydraulic proportional valve; 6. Ground controller; 7. Refueling hose; 8. Refueling and receiving components; 9. Refueling flow regulating valve; 10. Refueling flow sensor; 11. Flight environment pressure simulation box; 12. Negative pressure tank of the receiving aircraft. DETAILED DESCRIPTION

[0030] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. 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 creative work are within the scope of protection of the present invention.

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

[0032] Step S100, initialization of the ground controller. To ensure the safe operation of the test system, the initialization of the ground controller mainly 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.

[0033] Step S200, refueling the steel test tank of the tanker. After the ground controller is initialized, refueling is performed in the steel test tank of the tanker. Specifically, 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 tanker tank.

[0034] Step S300, pressure control. After the steel test tank of the fuel dispenser is refueled, the pressure setting value is manually input to the ground controller, and 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.

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

[0036] Step S400, start the refueling pump group. After each chassis reaches the pressure setting 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, which collects the oil flow of the refueling pump group test 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 group is started, the refueling valve is opened and the flow setting value is input to the ground controller; after receiving the flow setting value, the ground controller sends an opening adjustment instruction to the flow regulating valve so that the refueling flow of the flow regulating valve reaches the setting value, and then collects the refueling flow of the refueling pump group in real time and sends it to the ground controller.

[0039] Step S600, 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, the next step is executed; if not, the process returns to step S500, and 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.

[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 starting 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 the above design, the ground controller adjusts the speed of the refueling pod ramjet pump directly connected to the hydraulic motor through the electro-hydraulic proportional valve according to the instructions of the refueling pod pressure regulating controller, realizing the simulation of the refueling pod pressure regulation process. The ground test controller changes the opening of the regulating valve to simulate the change of the oil receiving flow rate, realizing the verification of the fuel delivery characteristics of the refueling pod under different oil receiving flow rates. The negative pressure tank of the receiving aircraft has a built-in oil drain pump to prevent the negative pressure tank from overflowing, realizing the continuous simulation of the refueling process.

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

[0043] As a specific implementation method, a specific example is used to illustrate:

[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 machine is 96kPa, the initial value of the pressure of the flight environment box is 96kPa, the initial value of the receiving oil flow sensor is 0, the initial opening of the pressure regulating valve is 0, and the opening of the receiving oil flow regulating valve is 0.

[0045] Step S200: The ground controller sends a refueling flow command of 1500 L / min to the refueling regulating valve, continuously fills 10 t of test oil into the steel refueling machine tank and automatically stops refueling.

[0046] Step S300, manually input the pressure setting value 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] 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 to the ground controller, and 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, enter 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 are repeated; otherwise, the test ends.

[0051] As a specific implementation, 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 , including: ground controller 6, steel tank of tanker 1, aerial refueling pump group and fuel delivery pipeline 2, negative pressure tank of receiving aircraft 12, flight environment pressure simulation box 11, ramjet pump 4 of refueling pod, electro-hydraulic proportional valve 5, high-speed hydraulic motor 3, refueling hose 7, refueling and receiving assembly 8, receiving flow regulating valve 9 and receiving flow sensor 10. The aerial refueling pump group and fuel delivery pipeline 2 are arranged on the steel tank of tanker 1, the steel tank of tanker 1, the flight environment pressure simulation box 11 and the negative pressure tank of receiving aircraft 12 are all closed tanks, and the steel tank of tanker 1, the flight environment pressure simulation box 11 and the negative pressure tank of receiving aircraft 12 are all equipped with two pressure regulating valves, the outlet of one pressure regulating valve is the laboratory atmosphere, and the outlet of the other pressure regulating valve is 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 arranged 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 matched 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 oil 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 interactive interface, which can manually input the settings of parameters such as test pressure and flow, and at the same time receive the pressure adjustment command of the refueling pod and send the adjustment command 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, and the internal shape and size of the tank are consistent with the actual tank state of the aircraft.

[0055] Preferably, the negative pressure 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 drain pump is installed inside the negative pressure tank 12 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, and a vacuum suction method is adopted, whereby the ground controller 6 controls the opening of a pressure regulating valve connected to the flight environment pressure simulation box 11 to control the internal pressure to be consistent with the corresponding ambient pressure under the 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 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 is added to the steel tank 1 of the tanker through the refueling regulating valve of the refueling port. The target pressure value in the steel tank 1 of the tanker, the target pressure value in the flight environment pressure simulation box 11, and the target pressure value in the negative pressure tank 12 of the receiving aircraft in this test are manually set to the ground controller 6. The vacuum system controls the pressure regulating valve to make the environmental pressure in these three containers the target value. After the refueling pump group is turned on, the fuel in the fuel delivery pipeline is in a static non-flowing state. When the refueling pod starts refueling, the receiving oil flow value is manually modified to the set value on the ground controller 6, and the receiving oil flow regulating valve 9 adjusts the receiving oil flow based on the feedback value of the receiving oil flow sensor 10. During this period, the refueling pod sends a pressure adjustment command to the ground controller 6 according to the test feedback value of the refueling pod pressure sensor. The ground controller 6 directly controls the opening of the electro-hydraulic proportional valve 5, and changes the speed of the refueling pod ramjet turbine by changing the speed of the hydraulic motor, thereby changing the receiving oil flow and pressure.

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

[0060] Through the above design, the gas phase environment pressure in the fuel tank of the refueling pod during aerial refueling and the working environment pressure of the refueling pressure sensor of the refueling pod during high-altitude flight are truly simulated. This test simulation system uses a ground controller to complete the test work, which has the significant advantages of high test authenticity and strong 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, and other structures can refer to the general design. In the absence of conflict, 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 protection scope 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 steel test tank; After the steel test tank of the tanker is refueled, the pressure setting value is manually input to the ground controller, and 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 each chassis reaches the pressure setting value, the ground controller controls the refueling pump group to start and keep the refueling pump group in a zero flow state; After the refueling pump group is started, the refueling valve is opened and the flow setting value is input to the ground controller; after receiving the flow setting 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 oil receiving 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, the next step is executed; 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 the sensor power-on self-test, the initial reset of the oil flow valve, and the 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 oil 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 negative pressure tank, the flight environment pressure simulation box and the tanker steel test tank.

5. The test simulation method of 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 oil flow of the refueling pump group test 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 receiving flow rate does not reach the set value, a new flow setting value is input to the ground controller until the oil receiving 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 refueling flow regulating valve (9) and a receiving refueling 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 the steel tank of the tanker (1), the flight environment pressure simulation box (11) and the negative pressure tank of the receiving aircraft (12) are all equipped with two pressure regulating valves, wherein the outlet of one of the pressure regulating valves 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 fuel receiving flow regulating valve (9) and a fuel receiving 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 fuel receiving flow regulating valve (9); the fuel receiving flow regulating valve (9) and the fuel receiving 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 negative pressure oil tank (12) of a receiving aircraft is connected to the fuel receiving 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 test simulation system for fuel delivery characteristics 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 interior of the fuel tank are consistent with the actual fuel tank state 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 oil 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 inside the negative pressure oil tank to timely discharge the accumulated fuel inside the negative pressure oil tank.

12. The test simulation system for fuel delivery characteristics 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 flight environment pressure simulation box (11) to make the internal pressure consistent with the corresponding environment pressure under the actual flight altitude condition by using a vacuum suction method.

13. The test simulation system for fuel delivery characteristics 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 each equipped with two pressure regulating valves, and the outlet of one of the pressure regulating valves is the test laboratory atmosphere, and the outlet of the other pressure regulating valve is a vacuum suction pipeline.

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