System simulation method for air refueling process of fuel system

Abstract

The invention provides a system simulation method for an air refueling process of a fuel system. The method comprises the following steps: constructing a working logic and a fuel distribution scheme of the fuel system during air refueling; a fuel oil system simulation model, a refueling simulation module and a logic control module are respectively built by using AMEsim software, and an air refueling simulation model is formed through combination; setting flight profile parameters based on the fuel system simulation model; refueling parameters in a refueling simulation module are set according to the fuel oil distribution scheme and preset refueling conditions; setting a trigger event of the logic control module according to the working logic of the fuel system and the flight profile parameters; simulating to obtain the flow velocity of each refueling pipeline, the mass center change condition of each fuel tank and the total refueling time; and iteratively adjusting the fuel oil distribution scheme according to the simulated flow velocity of each refueling pipeline, the mass center change condition of each fuel tank and the total refueling time. According to the technical scheme, the technical problems that in the prior art, air refueling is carried out through tests, the design period is long, and cost is high are solved.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft fuel systems, and in particular to a system simulation method for an aerial refueling process of a fuel system. Background Art

[0002] Aerial refueling technology can make up for the lack of fuel in an aircraft, increase its combat radius and range, and ensure that the aircraft has the ability to perform long-range missions. According to literature statistics, after one aerial refueling, the combat radius of a bomber can increase by 25-30%, the combat radius of a fighter can increase by 30-40%, and the range of a transport aircraft can double. As the speed of the aircraft continues to increase, the location and shape of the fuel tank and other parameters are affected by the appearance of the aircraft and are more dispersed and flat in shape. In addition, the flow rate of aerial refueling continues to increase. During aerial refueling, it is necessary to finely control the opening and closing timing of the refueling valve and the center of gravity to ensure the safe docking of the tanker and the receiving aircraft.

[0003] According to the Aircraft Design Manual, the receiving aircraft should refuel from 10% of the aircraft's maximum fuel capacity to the aircraft's normal maximum fuel capacity within the specified refueling time. The aerial refueling process is vulnerable to interference and attack by enemy aircraft, so shortening the aerial refueling time is very important to ensure flight safety and enhance the combat effectiveness of fighter aircraft.

[0004] Issues such as aircraft center of gravity control, fuel tank filling timing, and aerial refueling time are issues that must be considered and designed in advance when designing the aerial refueling plan of the fuel system. This process involves multiple pathways such as the gas circuit, oil circuit, control circuit, and multiple factors such as gas and heat. Currently, this design is completed solely through experiments, which takes a long cycle and is costly. Summary of the invention

[0005] The present invention provides a system simulation method for the aerial refueling process of a fuel system, which can solve the technical problems of long design cycle and high cost of aerial refueling through experiments in the prior art.

[0006] According to one aspect of the present invention, a system simulation method for an aerial refueling process of a fuel system is provided, the method comprising:

[0007] S1, build the working logic and fuel distribution plan of the fuel system during aerial refueling;

[0008] S2, using AMEsim software to build a fuel system simulation model, a refueling simulation module and a logic control module respectively, and the fuel system simulation model, the refueling simulation module and the logic control module are combined to form an aerial refueling simulation model;

[0009] S3, setting flight profile parameters based on the fuel system simulation model;

[0010] S4, setting refueling parameters in the refueling simulation module according to the fuel distribution plan and preset refueling conditions, wherein the preset refueling conditions include an aerial refueling fuel temperature and an aerial refueling fuel pressure;

[0011] S5, setting a trigger event of the logic control module according to the working logic of the fuel system and the flight profile parameters;

[0012] S6, setting the simulation end time, output interval and simulation mode of the aerial refueling simulation model and then performing simulation to obtain the flow rate of each refueling pipeline, the change of the center of mass of each fuel tank and the total refueling time;

[0013] S7, judging whether the flow rate of each refueling pipeline, the change of the center of mass of each fuel tank and the total refueling time obtained by simulation meet the requirements, if not, turning to S8, if yes, turning to S9;

[0014] S8, adjusting the fuel distribution plan, and adjusting the refueling parameters in the refueling simulation module accordingly based on the adjusted fuel distribution plan, and returning to S6;

[0015] S9, ends the simulation and outputs the current fuel distribution plan as the final result.

[0016] Furthermore, the fuel system working logic and fuel distribution scheme for aerial refueling include:

[0017] According to the fuel system inerting and pressurizing system, refueling exhaust requirements, and the coordination between the fuel level signal and the fuel quantity sensor, the working logic of the fuel system during aerial refueling is constructed;

[0018] The fuel distribution plan for aerial refueling is constructed based on the aircraft's refueling speed, the volume of each fuel tank, and the aircraft's center of gravity control requirements.

[0019] Furthermore, building a fuel system simulation model using AMEsim software includes: using ACFTANK01, ACF2THHVOR001, ACF2PNVOR001, ACFATTISIMP001, ACFGEOMSENSOR001, ACFFHS002, PNVS001, PNV0001, TFVORFO and TFMPTO submodules in AMEsim software to build a fuel system simulation model.

[0020] Furthermore, using AMEsim software to build a refueling simulation module includes: using the PNL0001 sub-module in the AMEsim software to build each refueling pipeline in the refueling simulation module, using the ACFTNK2FIVORPN001 sub-module in the AMEsim software to build each refueling control valve in the refueling simulation module, using the ACFFIPTS001 sub-module in the AMEsim software to set the aerial refueling fuel temperature and aerial refueling fuel pressure in the refueling simulation module, and using the PNVS001 sub-module and PNCV010 sub-module in the AMEsim software to build the refueling exhaust components in the refueling simulation module.

[0021] Further, setting the refueling parameters in the refueling simulation module according to the fuel distribution plan includes: setting the diameter of each refueling pipeline and the aperture of each refueling control valve in the refueling simulation module according to the fuel distribution plan.

[0022] Furthermore, the logic control module constructed using AMEsim software includes:

[0023] The output value of the fuel level sensor simulation submodule ACFFHS002 is judged to be in a large or small relationship with the specific liquid level, and the judgment result is used as the signal of the oil level signaler in the logic control module;

[0024] Use the dynamic_acf_gauge submodule in AMEsim software to build the oil level sensor in the logic control module and output the multi-point oil immersion height;

[0025] The FXYZ submodule in AMEsim software is used to build the oil level angle calculation submodule in the logic control module, and the fuel oil level angle is calculated according to the flight profile parameters;

[0026] The NDFXAO submodule in AMEsim software is used to build the fuel volume interpolation submodule in the logic control module, and the fuel volume is determined by interpolation based on the multi-point oil immersion height and oil surface angle;

[0027] Use the Statechart submodule in the AMEsim software to build the refueling control valve control submodule in the logic control module. Use the signal of the oil level signalizer and the calculated fuel volume as the input of the refueling control valve control submodule, and output the opening and closing parameters of each refueling control valve simulation submodule.

[0028] Further, setting the triggering event of the logic control module according to the working logic of the fuel system and the flight profile parameters includes: setting the Events in the Statechart submodule according to the working logic of the fuel system and the flight profile parameters.

[0029] Furthermore, the total refueling time is the time consumed to fill up all the fuel tanks.

[0030] Further, judging whether the change of the center of mass of each fuel tank obtained by simulation meets the requirements includes: calculating the change of the center of mass of the entire aircraft according to the change of the center of mass of each fuel tank, judging whether the change of the center of mass of the entire aircraft meets the requirements, if so, judging that the change of the center of mass of each fuel tank obtained by simulation meets the requirements, if not, judging that the change of the center of mass of each fuel tank obtained by simulation does not meet the requirements.

[0031] The technical solution of the present invention is applied to provide a system simulation method for the aerial refueling process of a fuel system. The method constructs the working logic and fuel distribution scheme of the fuel system during aerial refueling, uses AMEsim software to respectively build a fuel system simulation model, a refueling simulation module and a logic control module, and together constitutes an aerial refueling simulation model. The flight profile parameters are set based on the aerial refueling simulation model, and the refueling parameters of the refueling simulation module and the triggering events of the logic control module are respectively configured to achieve effective simulation of the working process of the fuel system during aerial refueling of high-speed aircraft. Based on this method, under the condition of a given aerial refueling scheme, the law of the change of the center of gravity of the aircraft, the law of the refueling of each fuel tank and the total time of aerial refueling can be analyzed and evaluated, and the scheme can be quickly verified and iterated, providing an effective basis for the design of the fuel system of aerial refueling. The method can simulate the aerial refueling process under different flight profiles and different refueling strategies of high-speed aircraft, and has strong versatility; through the logic control module, comprehensive judgment control can be achieved, and key parameters such as the aerial refueling time and the law of the change of the center of mass can be quickly obtained, so as to accelerate the convergence and iteration of the scheme and reduce the cost of doing experiments. In addition, the simulation method provided by the present invention can be used as a benchmark method, and later users can perform secondary development on it according to their needs (such as considering the thermal environment). BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The included drawings are used to provide a further understanding of the embodiments of the present invention, which constitute a part of the specification, are used to illustrate the embodiments of the present invention, and together with the text description, explain the principles of the present invention. Obviously, the drawings in the following description are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0033] Figure 1 A fuel system AMEsim simulation model diagram of a fuel system aerial refueling process provided according to a specific embodiment of the present invention is shown;

[0034] Figure 2 The simulation calculation result of the aircraft fuel tank mass provided by the specific embodiment of the present invention is shown;

[0035] Figure 3The figure shows the simulation calculation result of the center of mass of the aircraft fuel tank provided according to the specific embodiment of the present invention. DETAILED DESCRIPTION

[0036] It should be noted that, in the absence of conflict, the embodiments in this application and the features in the embodiments can be combined with each other. The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings 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. The following description of at least one exemplary embodiment is actually only illustrative and is by no means intended to limit the present invention and its application or use. Based on the embodiments in 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.

[0037] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0038] Unless otherwise specifically stated, the relative arrangement of the parts and steps described in these embodiments, numerical expressions and numerical values ​​do not limit the scope of the present invention. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to ordinary technicians in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be regarded as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0039] According to a specific embodiment of the present invention, a system simulation method for an aerial refueling process of a fuel system is provided, the method comprising:

[0040] S1, build the working logic and fuel distribution plan of the fuel system during aerial refueling;

[0041] S2, using AMEsim software to build a fuel system simulation model, a refueling simulation module and a logic control module respectively, and the fuel system simulation model, the refueling simulation module and the logic control module are combined to form an aerial refueling simulation model;

[0042] S3, setting flight profile parameters based on the fuel system simulation model;

[0043] S4, setting refueling parameters in the refueling simulation module according to the fuel distribution plan and preset refueling conditions, wherein the preset refueling conditions include an aerial refueling fuel temperature and an aerial refueling fuel pressure;

[0044] S5, setting a trigger event of the logic control module according to the working logic of the fuel system and the flight profile parameters;

[0045] S6, setting the simulation end time, output interval and simulation mode of the aerial refueling simulation model and then performing simulation to obtain the flow rate of each refueling pipeline, the change of the center of mass of each fuel tank and the total refueling time;

[0046] S7, judging whether the flow rate of each refueling pipeline, the change of the center of mass of each fuel tank and the total refueling time obtained by simulation meet the requirements, if not, turning to S8, if yes, turning to S9;

[0047] S8, adjusting the fuel distribution plan, and adjusting the refueling parameters in the refueling simulation module accordingly based on the adjusted fuel distribution plan, and returning to S6;

[0048] S9, ends the simulation and outputs the current fuel distribution plan as the final result.

[0049] By applying this configuration mode, a system simulation method for the aerial refueling process of a fuel system is provided. The method constructs the working logic and fuel distribution scheme of the fuel system during aerial refueling, and uses AMEsim software to respectively build a fuel system simulation model, a refueling simulation module and a logic control module, which together constitute an aerial refueling simulation model. The flight profile parameters are set based on the aerial refueling simulation model, and the refueling parameters of the refueling simulation module and the triggering events of the logic control module are respectively configured to achieve effective simulation of the working process of the fuel system during aerial refueling of high-speed aircraft. Based on this method, under the condition of a given aerial refueling scheme, the law of the change of the center of gravity of the aircraft, the law of the refueling of each fuel tank and the total time of aerial refueling can be analyzed and evaluated, and the scheme can be quickly verified and iterated, providing an effective basis for the design of the fuel system of aerial refueling. The method can simulate the aerial refueling process under different flight profiles and different refueling strategies of high-speed aircraft, and has strong versatility; through the logic control module, comprehensive judgment control can be achieved, and key parameters such as the aerial refueling time and the law of the change of the center of mass can be quickly obtained, so as to accelerate the convergence and iteration of the scheme and reduce the cost of doing experiments. In addition, the simulation method provided by the present invention can be used as a benchmark method, and users can perform secondary development on it according to their needs (such as considering the thermal environment) in the later stage. Compared with the prior art, the technical solution of the present invention can solve the technical problems of long design cycle and high cost of aerial refueling through experiments in the prior art.

[0050] Furthermore, in an embodiment of the present invention, the fuel system working logic and fuel distribution scheme during aerial refueling are constructed including:

[0051] According to the fuel system inerting and pressurizing system, refueling exhaust requirements, and the coordination between the fuel level signal and the fuel quantity sensor, the working logic of the fuel system during aerial refueling is constructed;

[0052] The fuel distribution plan for aerial refueling is constructed based on the aircraft's refueling speed, the volume of each fuel tank, and the aircraft's center of gravity control requirements. Specifically, the fuel distribution plan includes the diameter of each refueling pipeline, the aperture of each refueling control valve, and the refueling control strategy.

[0053] like Figure 1 As shown, in the embodiment of the present invention, using AMEsim software to build a fuel system simulation model includes: using ACFTANK01, ACF2THHVOR001, ACF2PNVOR001, ACFATTISIMP001, ACFGEOMSENSOR001, ACFFHS002, PNVS001, PNV0001, TFVORFO and TFMPTO submodules in the AMEsim software to build a fuel system simulation model.

[0054] Further, in an embodiment of the present invention, using AMEsim software to build a refueling simulation module includes: using the PNL0001 sub-module in the AMEsim software to build each refueling pipeline in the refueling simulation module, using the ACFTNK2FIVORPN001 sub-module in the AMEsim software to build each refueling control valve in the refueling simulation module, using the ACFFIPTS001 sub-module in the AMEsim software to set the aerial refueling fuel temperature and aerial refueling fuel pressure in the refueling simulation module, and using the PNVS001 sub-module and PNCV010 sub-module in the AMEsim software to build the refueling exhaust components in the refueling simulation module.

[0055] Using AMEsim software to build a logic control module includes: judging the size relationship between the output value of the fuel height sensor simulation submodule ACFFHS002 and the specific liquid level, and using the judgment result as the signal of the oil level signaler in the logic control module; using the dynamic_acf_gauge submodule in the AMEsim software to build the oil volume sensor in the logic control module, and output the multi-point oil immersion height; using the FXYZ submodule in the AMEsim software to build the oil level angle calculation submodule in the logic control module, and calculate the fuel oil level angle according to the flight profile parameters; using the NDFXAO submodule in the AMEsim software to build the fuel volume interpolation submodule in the logic control module, and determine the fuel volume according to the multi-point oil immersion height and the oil level angle interpolation; using the Statechart submodule in the AMEsim software to build the refueling control valve control submodule in the logic control module, using the signal of the oil level signaler and the calculated fuel volume as the input of the refueling control valve control submodule, and outputting the opening and closing parameters of each refueling control valve simulation submodule.

[0056] In this way, a method for building a sub-simulation model of the aerial refueling process of the fuel system is given in detail, and a fuel level signal and fuel quantity sensor model corresponding to the actual situation is established. The Statechart module is used to realize the comprehensive judgment and control of the fuel full timing and the comprehensive integrated analysis of the functional performance of the fuel system. It can quickly obtain key parameters such as the aerial refueling time and the law of center of mass change, accelerate the convergence and iteration of the solution, and reduce the cost of conducting experiments.

[0057] Based on the above embodiments, in the embodiments of the present invention, setting the refueling parameters in the refueling simulation module according to the fuel distribution plan includes: setting the diameter of each refueling pipeline and the aperture of each refueling control valve in the refueling simulation module according to the fuel distribution plan. Setting the triggering events of the logic control module according to the working logic of the fuel system and the flight profile parameters includes: setting the Events in the Statechart submodule according to the working logic of the fuel system and the flight profile parameters. In this way, the process control of aerial refueling can be achieved. By setting the refueling pipe diameter parameters and the refueling strategy, the design pain points can be found, and the measurement and comprehensive judgment of the time when the fuel tank is full of fuel can be made.

[0058] In addition, in the embodiment of the present invention, the total refueling time is the time consumed for filling up all the fuel tanks. Judging whether the changes in the center of mass of each fuel tank obtained by simulation meet the requirements includes: calculating the changes in the center of mass of the entire aircraft according to the changes in the center of mass of each fuel tank, judging whether the changes in the center of mass of the entire aircraft meet the requirements, if yes, judging that the changes in the center of mass of each fuel tank obtained by simulation meet the requirements, if not, judging that the changes in the center of mass of each fuel tank obtained by simulation do not meet the requirements.

[0059] In order to facilitate a clearer understanding of the system simulation method for the aerial refueling process of the fuel system provided by the present invention, the above-mentioned processes will be described in detail below using practical application examples. Relevant technical personnel in the field should know that this example is only to facilitate a clearer understanding of the system simulation method for the aerial refueling process of the fuel system provided by the present invention, and does not impose any technical limitation on it.

[0060] The system simulation method for the aerial refueling process of the fuel system provided by the present invention specifically comprises the following steps:

[0061] Step 1: Construct the fuel system working logic and fuel distribution plan during aerial refueling.

[0062] The fuel distribution plan for aerial refueling of the aircraft (including the diameter of each refueling pipeline, the aperture of each refueling control valve and the refueling control strategy) is determined according to the refueling speed, the volume of each fuel tank and the requirements of the aircraft's center of gravity control to ensure that the aircraft is always refueled at the maximum refueling rate. In addition, considering the needs of the original fuel system's inerting and pressurization system, refueling exhaust, and the coordination of the two sensors, the oil level signalizer and the oil quantity sensor, the working logic of the fuel system during refueling is constructed to form a preliminary plan for aerial refueling of the fuel system.

[0063] Step 2: Build a fuel system simulation model in AMEsim.

[0064] A simulation model of the fuel system is built using sub-modules such as ACFTANK01, ACF2THHVOR001, ACF2PNVOR001, ACFATTISIMP001, ACFGEOMSENSOR001, ACFFHS002, PNVS001, PNV0001, TFVORFO, and TFMPTO. Considering the influence of flight conditions, the simulation model of the fuel system is realized to realize functions such as fuel tank supply and delivery, inerting and pressurization, fuel center of mass calculation, and oil immersion height measurement.

[0065] Step 3: Build the refueling simulation module.

[0066] Use the PNL0001 submodule to build each refueling pipeline, determine the diameter of the oil pipe leading to each fuel tank according to the aerial refueling fuel distribution plan, use the ACFTNK2FIVORPN001 submodule to implement the functions of each refueling control valve, use the PNVS001 submodule and PNCV010 submodule to implement the refueling and refueling exhaust functions, and use the ACFFIPTS001 submodule to set the aerial refueling fuel temperature and aerial refueling fuel pressure.

[0067] Step 4: Build the logic control module.

[0068] The fuel height sensor is combined with the specific liquid level judgment to form a fuel level signaler; the multi-point oil immersion height output by the dynamic_acf_gauge model is used to form a fuel volume sensor, and the current flight status is used as the input of the FXYZ sub-module to calculate the fuel oil level angle. After determining the oil immersion height and oil level angle, the fuel volume is determined by interpolation through the NDFXAO sub-module; using the Statechart function, the fuel level signaler signal and the calculated fuel volume are set as logical inputs, and the output parameters such as the opening and closing of the refueling control valve are set according to the control logic, and the input and output parameters of the Statechart are linked to the Port tag of the dynamic_transmitter and dynamic_receiver parameters in the model.

[0069] Step 5: Complete the parameter settings of the entire system.

[0070] Set the flight profile, aerial refueling fuel temperature and pressure, as well as the diameter of each pipeline, the aperture of the refueling control valve, and other parameters. Set the Events in the Statechart according to the flight profile and work logic, including the start time of aerial refueling and the logical control of the refueling control valve, to achieve process control.

[0071] Step 6: Perform system simulation.

[0072] Set the simulation end time, output interval, simulation mode and other parameters, start the simulation, and obtain the flow rate of each refueling pipeline, the change of the center of mass of each fuel tank and the total refueling time.

[0073] Step 7: Iterative calculation.

[0074] According to the simulation calculation results, firstly, the parameters such as the diameter of the main refueling pipe and the aperture of the refueling control valve of the large fuel tank are adjusted to make the total refueling time meet the requirements; secondly, the refueling control strategy is adjusted by observing the change of the center of mass; finally, the diameter of each branch pipe and the aperture of the refueling control valve are finely adjusted to meet the pipeline flow rate not exceeding 9m / s and the center of mass control requirements.

[0075] Among them, the opening and closing of the refueling control valve of each fuel tank is determined by the measurement and integrated control module of the fuel level signal and the fuel quantity sensor, and the time consumed after all the fuel tanks are filled is the total time of aerial refueling, which can be used to evaluate the system solution. Through system simulation, the center of mass change of each fuel tank is calculated according to the center of mass calculation formula to verify whether it meets the requirements.

[0076] In summary, the present invention provides a system simulation method for the aerial refueling process of a fuel system. The method constructs the working logic and fuel distribution scheme of the fuel system during aerial refueling, uses AMEsim software to respectively build a fuel system simulation model, a refueling simulation module and a logic control module, and together constitutes an aerial refueling simulation model. The flight profile parameters are set based on the aerial refueling simulation model, and the refueling parameters of the refueling simulation module and the triggering events of the logic control module are respectively configured to achieve effective simulation of the working process of the fuel system during aerial refueling of high-speed aircraft. Based on this method, under the condition of a given aerial refueling scheme, the law of the change of the center of gravity of the aircraft, the law of the refueling of each fuel tank and the total time of aerial refueling can be analyzed and evaluated, and the scheme can be quickly verified and iterated, providing an effective basis for the design of the fuel system of aerial refueling. The method can simulate the aerial refueling process under different flight profiles and different refueling strategies of high-speed aircraft, and has strong versatility; through the logic control module, comprehensive judgment control can be achieved, and key parameters such as the aerial refueling time and the law of the change of the center of mass can be quickly obtained, so as to accelerate the convergence and iteration of the scheme and reduce the cost of doing experiments. In addition, the simulation method provided by the present invention can be used as a benchmark method, and later users can perform secondary development on it according to their needs (such as considering the thermal environment). Compared with the prior art, the technical solution of the present invention can solve the technical problems of long design cycle and high cost of aerial refueling through experiments in the prior art.

[0077] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used here to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" can include both "above" and "below". The device can also be positioned in other different ways (rotated 90 degrees or in other orientations), and the spatially relative descriptions used here are interpreted accordingly.

[0078] In addition, it should be noted that the use of terms such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above terms have no special meaning and therefore cannot be understood as limiting the scope of protection of the present invention.

[0079] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A system simulation method for the aerial refueling process of a fuel system, characterized in that: The method comprises: S1, build the working logic and fuel distribution plan of the fuel system during aerial refueling; S2, using AMEsim software to respectively build a fuel system simulation model, a refueling simulation module and a logic control module, wherein the fuel system simulation model, the refueling simulation module and the logic control module are combined to form an aerial refueling simulation model; S3, setting flight profile parameters based on the fuel system simulation model; S4, setting the refueling parameters in the refueling simulation module according to the fuel distribution plan and the preset refueling conditions, wherein the preset refueling conditions include the aerial refueling fuel temperature and the aerial refueling fuel pressure; S5, setting a trigger event of the logic control module according to the fuel system working logic and the flight profile parameters; S6, setting the simulation end time, output interval and simulation mode of the aerial refueling simulation model and then performing simulation to obtain the flow rate of each refueling pipeline, the change of the center of mass of each fuel tank and the total refueling time; S7, judging whether the flow rate of each refueling pipeline, the change of the center of mass of each fuel tank and the total refueling time obtained by simulation meet the requirements, if not, turning to S8, if yes, turning to S9; S8, adjusting the fuel distribution plan, and adjusting the refueling parameters in the refueling simulation module accordingly based on the adjusted fuel distribution plan, and returning to S6; S9, ends the simulation and outputs the current fuel distribution plan as the final result.

2. The method according to claim 1, characterized in that The fuel system working logic and fuel distribution plan for aerial refueling include: According to the fuel system inerting and pressurizing system, refueling exhaust requirements, and the coordination between the fuel level signal and the fuel quantity sensor, the working logic of the fuel system during aerial refueling is constructed; The fuel distribution plan for aerial refueling is constructed based on the aircraft's refueling speed, the volume of each fuel tank, and the aircraft's center of gravity control requirements.

3. The method according to claim 2, characterized in that Building a fuel system simulation model using AMEsim software includes: using ACFTANK01, ACF2THHVOR001, ACF2PNVOR001, ACFATTISIMP001, ACFGEOMSENSOR001, ACFFHS002, PNVS001, PNV0001, TFVORFO and TFMPTO sub-modules in AMEsim software to build a fuel system simulation model.

4. The method according to claim 2, characterized in that: Using AMEsim software to build a refueling simulation module includes: using the PNL0001 sub-module in the AMEsim software to build the refueling pipelines in the refueling simulation module, using the ACFTNK2FIVORPN001 sub-module in the AMEsim software to build the refueling control valves in the refueling simulation module, using the ACFFIPTS001 sub-module in the AMEsim software to set the aerial refueling fuel temperature and aerial refueling fuel pressure in the refueling simulation module, and using the PNVS001 sub-module and PNCV010 sub-module in the AMEsim software to build the refueling exhaust components in the refueling simulation module.

5. The method according to claim 4, characterized in that Setting the refueling parameters in the refueling simulation module according to the fuel distribution scheme includes: setting the diameter of each refueling pipeline and the aperture of each refueling control valve in the refueling simulation module according to the fuel distribution scheme.

6. The method according to claim 3, characterized in that Using AMEsim software to build a logic control module includes: The output value of the fuel level sensor simulation submodule ACFFHS002 is judged to be in a large or small relationship with the specific liquid level, and the judgment result is used as the signal of the oil level signaler in the logic control module; Use the dynamic_acf_gauge submodule in AMEsim software to build the oil level sensor in the logic control module and output the multi-point oil immersion height; The FXYZ submodule in AMEsim software is used to build the oil level angle calculation submodule in the logic control module, and the fuel oil level angle is calculated according to the flight profile parameters; The NDFXAO submodule in AMEsim software is used to build the fuel volume interpolation submodule in the logic control module, and the fuel volume is determined by interpolation based on the multi-point oil immersion height and oil surface angle; Use the Statechart submodule in the AMEsim software to build the refueling control valve control submodule in the logic control module. Use the signal of the oil level signalizer and the calculated fuel volume as the input of the refueling control valve control submodule, and output the opening and closing parameters of each refueling control valve simulation submodule.

7. The method according to claim 6, characterized in that Setting the triggering event of the logic control module according to the working logic of the fuel system and the flight profile parameters includes: setting Events in the Statechart submodule according to the working logic of the fuel system and the flight profile parameters.

8. The method according to any one of claims 1 to 7, characterized in that The total refueling time is the time consumed to fill up all the fuel tanks.

9. The method according to any one of claims 1 to 7, characterized in that Judging whether the changes in the center of mass of each fuel tank obtained by simulation meet the requirements includes: calculating the changes in the center of mass of the entire aircraft according to the changes in the center of mass of each fuel tank, and judging whether the changes in the center of mass of the entire aircraft meet the requirements; if so, judging that the changes in the center of mass of each fuel tank obtained by simulation meet the requirements; if not, judging that the changes in the center of mass of each fuel tank obtained by simulation do not meet the requirements.

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