WO2021088097A1 - 一种浮空器结冰特性数值仿真与试验验证系统 - Google Patents

一种浮空器结冰特性数值仿真与试验验证系统 Download PDF

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WO2021088097A1
WO2021088097A1 PCT/CN2019/117245 CN2019117245W WO2021088097A1 WO 2021088097 A1 WO2021088097 A1 WO 2021088097A1 CN 2019117245 W CN2019117245 W CN 2019117245W WO 2021088097 A1 WO2021088097 A1 WO 2021088097A1
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aerostat
icing
module
test
numerical simulation
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English (en)
French (fr)
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刘强
杨燕初
崔燕香
才晶晶
祝榕辰
赵凯彬
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Aerospcace Information Research Institute Chinese Academy Of Science
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Aerospcace Information Research Institute Chinese Academy Of Science
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Priority to EP19934358.3A priority Critical patent/EP3845465B1/en
Priority to US17/256,651 priority patent/US11161629B2/en
Publication of WO2021088097A1 publication Critical patent/WO2021088097A1/zh
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/23—Design optimisation, verification or simulation using finite element methods [FEM] or finite difference methods [FDM]
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/20—Design optimisation, verification or simulation
    • G06F30/28—Design optimisation, verification or simulation using fluid dynamics, e.g. using Navier-Stokes equations or computational fluid dynamics [CFD]
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/02—Non-rigid airships
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64B—LIGHTER-THAN AIR AIRCRAFT
    • B64B1/00—Lighter-than-air aircraft
    • B64B1/40—Balloons
    • G—PHYSICS
    • G06—COMPUTING OR CALCULATING; COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/10—Numerical modelling

Definitions

  • the invention belongs to the technical field of high-altitude balloon thermal control, and in particular relates to a numerical simulation and test verification system for aerostat icing characteristics.
  • the interior of the aerostat is filled with a floating gas whose density is lower than that of the air to obtain buoyancy, so as to realize the lift-off and high-altitude resident flight of the aerostat.
  • a floating gas whose density is lower than that of the air to obtain buoyancy, so as to realize the lift-off and high-altitude resident flight of the aerostat.
  • the purpose of the present invention is to overcome the defects of the prior art and provide a numerical simulation and experimental verification system capable of comprehensively testing and estimating the icing characteristics of the aerostat.
  • the technical scheme of the present invention is: a numerical simulation and test verification system for aerostat icing characteristics, including:
  • An aerostat icing characteristic test system where the aerostat icing characteristic test system is used to obtain the aerostat icing characteristic data through a physical simulation test;
  • the aerostat icing data obtained through numerical simulation and the aerostat icing characteristic data obtained through physical simulation experiments are mutually verified and mutually improved, so as to provide a numerical simulation basis for in-depth research and accurate analysis of the aerostat icing characteristics And the basis for experimental verification.
  • the aerostat icing characteristic test system includes: aerostat, an icing characteristic test object; a water drop ejector, used to simulate rainfall conditions; an environmental data collection module, used to measure environmental data; aerostat pressure Differential data acquisition module, used to measure the pressure difference between the inside and outside of the aerostat; pull test module, used to measure the buoyancy of the aerostat; data storage and processing module, used to store and process the data transmitted from each module; test status record The module is used to record the changes in the icing characteristics of the aerostat during the test; the low-temperature environment laboratory is used to provide an indoor temperature of 0-20°C; wherein the water droplet ejector is arranged above the aerostat
  • the environmental data acquisition module, the aerostat pressure difference data acquisition module, and the tensile test module are connected to the data storage and processing module, and the tensile test module is connected to the tethering rope of the aerostat.
  • the aerostat includes an airship, a captive balloon, a zero-pressure balloon or an over-pressure balloon.
  • the aerostat icing characteristic calculation model includes: aerostat temperature field-flow field characteristic calculation module, aerostat supercooled water drop impact characteristic calculation module, and aerostat surface ice growth calculation module.
  • the modeling of the aerostat icing characteristic calculation model includes: calculating the aerostat flight parameters and design parameters according to the requirements of the aerostat flight mission; calculating the aerostat atmospheric and thermal environment parameters; based on the aerostat Geometric characteristics and heat transfer mode, the establishment of aerostat temperature field-flow field characteristics calculation module.
  • the modeling of the aerostat icing characteristic calculation model includes: using the aerostat temperature field-flow field characteristic calculation module to establish the aerostat supercooled droplet impact characteristic calculation module.
  • the modeling of the aerostat icing characteristic calculation model includes: using the aerostat temperature field-flow field characteristic calculation module and the aerostat supercooled droplet impact characteristic module to establish the aerostat surface ice growth calculation module.
  • the icing characteristic data of the aerostat includes icing thickness and icing distribution on the surface of the aerostat.
  • test conditions of the aerostat icing characteristic test system are the same as the boundary conditions of the aerostat icing characteristic calculation model.
  • the invention has the following beneficial effects: the aerostat icing characteristic data is obtained by means of numerical simulation and physical simulation test, and the calculation result obtained by numerical simulation and the test result of physical simulation test are mutually confirmed and perfected, thereby in-depth study And accurately analyze the icing characteristics of the aerostat.
  • Figure 1 is a schematic diagram of the composition of the aerostat icing characteristic calculation model.
  • Figure 2 is a schematic flow chart of the method for calculating the icing characteristics of the aerostat.
  • Figure 3 is a schematic diagram of the structure of the boat-shaped aerostat icing characteristics test system.
  • Figure 4 is a schematic diagram of the structure of the icing characteristic test system for a spherical aerostat.
  • the above drawings include the following reference signs: 1. Aerostat; 2. Water drop ejector; 3. Environmental data acquisition module; 4. Aerostat pressure difference data acquisition module; 5. Tension test module; 6. Data Storage and processing module; 7. Test status recording module; 8. Low temperature environment laboratory.
  • a numerical simulation and test verification system for aerostat icing characteristics including aerostat icing characteristic calculation model and aerostat icing characteristic test system.
  • the aerostat icing characteristic calculation model is used for numerical simulation.
  • Obtain the aerostat icing data the aerostat icing characteristic test system is used to obtain the aerostat icing characteristic data through the physical simulation test, and the calculation results obtained by the numerical simulation and the test results of the physical simulation test are mutually confirmed and perfected, thereby In-depth study and analysis of the icing characteristics of the aerostat.
  • the icing process on the surface of the aerostat can be divided into three steps: (1) supercooled water droplets flow in the flow field around the aerostat and hit the windward surface of the aerostat; (2) supercooling that hits the windward surface of the aerostat A part of the water droplets are attached to the surface of the aerostat to form a water film flowing, and a part is bounced and splashed away from the surface of the aerostat; (3) The water film attached to the surface of the aerostat freezes after heat exchange.
  • the aerostat icing characteristic calculation model includes three calculation modules, namely the aerostat temperature field-flow field characteristic calculation module, the aerostat supercooled droplet impact characteristic calculation module and the aerostat surface
  • the ice-type growth calculation module the relationship between the modules is shown in Figure 1.
  • the flight parameters of the aerostat include the flight time of the aerostat, the longitude of the aerostat's flight location, the latitude of the aerostat's flight location, the altitude of the aerostat and the airspeed of the aerostat;
  • the design parameters of the aerostat include the volume of the aerostat, the length of the aerostat, the maximum diameter of the aerostat, the surface area of the aerostat and the solar cell area.
  • the atmospheric environment parameters of the aerostat include the atmospheric temperature, atmospheric pressure and atmospheric density at the altitude of the aerostat;
  • the thermal environment parameters of the aerostat include the radiant heat environment parameters and convective heat exchange environment parameters of the aerostat.
  • the radiant heat environment parameters of the aerostat include direct solar radiant heat flow, atmospheric scattering solar radiant heat flow, and ground reflection solar radiant heat flow , Long-wave radiant heat flow in the atmosphere and long-wave radiant heat flow on the ground.
  • CATIA software to create a three-dimensional model of the aerostat, import the three-dimensional model into CFD/ICEM software to create a calculation domain, generate an unstructured grid to discretize the calculation domain, and complete the modeling of a finite element model of the aerostat.
  • the aerostat's radiant heat environment parameters and convective heat transfer environment parameters are used as boundary conditions and loaded on the aerostat's finite element model.
  • the temperature field The coupling characteristics of the flow field are solved by the pressure-based semi-implicit separation solution method (SIMPLE), and the convection term and diffusion term are discretized by the second-order discrete format, so as to complete the establishment of the aerostat temperature field-flow field characteristic calculation module.
  • the reasonable settings include:
  • the shape of supercooled water droplets is spherical
  • the turbulence of the flow field of the aerostat has no effect on the flow field of the supercooled water droplets.
  • S500 Use the aerostat temperature field-flow field characteristic calculation module and the aerostat supercooled droplet impact characteristic module to establish the aerostat surface ice growth calculation module, thereby completing the modeling of the aerostat icing characteristic calculation model.
  • the field-flow field calculation module obtains the surface temperature, frictional resistance and heat flow data of the aerostat, and uses the supercooled droplet impact calculation module to obtain the supercooled droplet collection coefficient on the surface of the aerostat, and establishes the quality of the surface ice growth of the aerostat And the energy conservation equation to complete the establishment of the calculation module for ice growth on the surface of the aerostat;
  • the equations of all the micro-elements in the calculation module can be solved simultaneously, and the aerostat icing characteristic data and the aerostat icing characteristic data can be calculated. Including the icing thickness and icing distribution on the surface of the aerostat, it provides a basis for numerical calculations for the aerostat test.
  • Aerostat icing characteristic test system including aerostat 1, water drop ejector 2, environmental data acquisition module 3, aerostat pressure difference data acquisition module 4, tensile test module 5, data storage and processing module 6, test status Recording module 7, 8 modules of low temperature environment laboratory.
  • the environmental data acquisition module 3, the aerostat pressure difference data acquisition module 4, the tensile test module 5 are connected to the data storage and processing module 7, and the tensile test module 5 is connected to the tether of the aerostat for measuring the aerostat
  • the buoyancy of the aerostat is equal to the buoyancy of the aerostat minus the gravity of the aerostat.
  • the aerostat 1 is an icing characteristic test object, including aerostats such as airships, tethered balloons, zero-pressure balloons or over-pressure balloons.
  • the droplet ejector 2 is set above the aerostat 1.
  • the droplet ejector 2 is composed of a main pipe and a series of nozzles for simulating rainfall.
  • the nozzles spray a mixed fluid of air and water droplets.
  • the mixing can be adjusted by adjusting the nozzles.
  • the spray water content refers to the mass of water droplets per cubic meter of air.
  • the environmental data acquisition module 3 is composed of environmental atmospheric temperature, environmental atmospheric pressure, environmental atmospheric humidity, environmental wind speed and wind direction testing instruments, used to measure environmental atmospheric temperature data, environmental atmospheric pressure data, environmental atmospheric humidity data, and environmental wind speed and direction data.
  • the aerostat pressure difference data acquisition module 4 includes a pressure difference sensor for measuring the pressure difference between the inside and outside of the aerostat.
  • the tensile test module 5 including a tensiometer, is used to measure the buoyancy data of the aerostat.
  • the data storage and processing module 6 is mainly composed of computer hardware and data processing software, and is used to store and process the data transmitted from each module.
  • the test state recording module 7 is composed of two cameras and is used to record the changes in the icing characteristics of the aerostat during the test.
  • Low temperature environment laboratory 8 used to provide indoor temperature of 0-20 °C.
  • the aerostat icing characteristic test can be carried out, including the following steps:
  • Step S1 connect the data acquisition instrument to the data storage and processing module, and debug the running state.
  • Step S101 Connect the environmental data acquisition module, aerostat pressure difference data acquisition module, and tensile test module to the data storage and processing module, turn on the environmental data acquisition module, aerostat pressure difference data acquisition module, and tensile test module to ensure the environment
  • the data acquisition module and the tensile test module function normally, and the collected data is accurate;
  • Step S102 Debug the test state recording module to ensure that the test state recording module functions normally
  • Step S2 prepare a low-temperature environment laboratory.
  • Step S201 Turn on the low-temperature environment laboratory to ensure that the low-temperature environment laboratory functions normally and the room temperature can be adjusted;
  • step S202 the room temperature is adjusted according to the test requirements.
  • Step S3 debugging the water drop ejector.
  • Step S301 Turn on the water drop ejector to ensure that the water drop ejector functions normally, and the diameter, spray water content, and flow rate of the water droplets sprayed can be adjusted;
  • Step S302 Adjust the sprayed water droplet diameter, sprayed water content and flow rate according to the test requirements.
  • Step S4 install the data acquisition module on the aerostat, and debug the aerostat.
  • Step S401 installing an aerostat pressure difference data acquisition module on the aerostat, and the aerostat pressure difference data acquisition module is connected to the data acquisition and processing module;
  • Step S402 Fill the aerostat with helium, move the aerostat under the droplet ejector, connect the aerostat to the tensile test module and then fix it on the ground;
  • Step S5 Test the icing characteristics of the aerostat.
  • the test conditions of the aerostat icing characteristic test are the same as the boundary conditions of the aerostat icing characteristic calculation model.
  • the icing characteristics of the aerostat surface are affected by six factors such as ambient temperature, aerostat pressure difference, droplet diameter, spray water content, flow rate and freezing time.
  • This test method adopts a single variable method to quantitatively test each type. The influence of factors on the icing characteristics of the aerostat, set the reference values of the ambient temperature, aerostat pressure difference, droplet diameter, spray water content, flow rate and icing duration, and keep the five variables unchanged and keep the reference values.
  • the sixth variable is changed separately, and the changed value floats up and down around the reference value.
  • Step S510 under the same ambient temperature, aerostat pressure difference, droplet diameter, spray water content, and flow rate conditions, that is, when the ambient temperature, aerostat pressure difference, droplet diameter, spray water content, and flow rate are the reference values, the test is different Changes in the icing characteristics of the aerostat under the condition of icing time.
  • Step S511 open the environmental laboratory, adjust the indoor temperature to the ambient temperature required for the test, set the aerostat pressure difference as a reference value, and test the buoyancy of the aerostat when there is no icing;
  • Step S512 keeping the water droplet diameter, spray water content, flow rate and aerostat pressure difference as reference values, and testing the change of the aerostat's buoyancy force with icing time;
  • Step S513 Subtract the aerostat buoyancy data measured by 511 from the aerostat buoyancy data measured by 512 to obtain different results under certain conditions of ambient temperature, droplet diameter, spray water content, flow rate, and aerostat pressure difference. The icing quality on the surface of the aerostat under the condition of ice time;
  • Step S520 repeat step 510, fix the other five parameters, change the variables to ambient temperature, aerostat pressure difference, droplet diameter, spray water content, and flow rate in turn, and measure the icing characteristics of the aerostat surface under the influence of each factor .
  • Step S5 also includes during the test, using the test state recording module to record changes in the icing state of the aerostat during the test.
  • Step S6 After the test is completed, the test data is processed and analyzed, so as to mutually verify and mutually improve the calculation result of the aerostat icing characteristic calculation model.

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Abstract

一种浮空器结冰特性的数值仿真与试验验证系统，包括浮空器结冰特性计算模型和浮空器结冰特性试验系统，其中浮空器结冰特性计算模型用于通过数值仿真的方式获得浮空器结冰数据，浮空器结冰特性试验系统用于通过物理模拟试验获得浮空器结冰特性数据，数值仿真得到的计算结果和物理模拟试验的试验结果相互印证和完善，从而深入研究和分析浮空器的结冰特性。

Description

一种浮空器结冰特性数值仿真与试验验证系统 技术领域
本发明属于高空气球热控制技术领域，尤其涉及一种浮空器结冰特性数值仿真与试验验证系统。
背景技术
浮空器的内部填充密度低于空气的浮升气体从而获得浮升力，实现浮空器的升空和高空驻留飞行，在升空和高空飞行时，浮空器经过云层且温度较低时，外壳表面会结冰，而浮空器结冰后对浮空器飞行特性影响较大，目前还没有一个能够全面地测试和估算浮空器结冰特性的数值仿真与试验验证系统。
发明内容
本发明的目的在于克服现有技术的缺陷，提供一种能够全面地测试和估算浮空器结冰特性的数值仿真与试验验证系统。
本发明的技术方案是：一种浮空器结冰特性的数值仿真与试验验证系统，包括：
浮空器结冰特性计算模型，所述浮空器结冰特性计算模型用于通过数值仿真的方式获得浮空器结冰数据；
浮空器结冰特性试验系统，所述浮空器结冰特性试验系统用于通过物理模拟试验获得浮空器结冰特性数据；
通过数值仿真的方式获得浮空器结冰数据和通过物理模拟试验获得浮空器结冰特性数据相互验证，相互完善，从而为深入研究和准确分析浮空器的结冰特性提供数值仿真的依据和试验验证的依据。
进一步地，所述浮空器结冰特性试验系统包括：浮空器，结冰特性试验对象；水滴喷射器，用于模拟降雨状态；环境数据采集模块，用来测量环境数据；浮空器压差数据采集模块，用于测量浮空器内外压差；拉力测试模块，用于测量浮空器的浮升力；数据存储和处理模块，用于存储和处理各个模块传输来的数据；试验状态记录模块，用于记录试验过程中浮空器结冰特性的变化情况；低温环境实验室，用于提供0-20℃的室内温度；其中，所述水滴喷射器设置在所述浮空器的上方，所述环境数据采集模块、浮空器压差数据采集模块、拉力测试模块与所述数据存储和处理模块相连，所述拉力测试模块与所述浮空器的系留绳相连。
进一步地，所述浮空器包括飞艇、系留气球、零压气球或超压气球。
进一步地，所述浮空器结冰特性计算模型包括：浮空器温度场-流场特性计算模块，浮空器过冷水滴撞击特性计算模块，浮空器表面冰型生长计算模块。
进一步地，浮空器结冰特性计算模型的建模包括：根据浮空器飞行任务需求，计算浮空器飞行参数及设计参数；计算浮空器大气环境参数和热环境参数；基于浮空器几何特征及传热模式，建立浮空器温度场-流场特性计算模块。
进一步地，浮空器结冰特性计算模型的建模包括：利用浮空器温度场-流场特性计算模块，建立浮空器过冷水滴撞击特性计算模块。、
进一步地，浮空器结冰特性计算模型的建模包括：利用浮空器温度场-流场特性计算模块、浮空器过冷水滴撞击特性模块，建立浮空器表面冰型生长计算模块。
进一步地，所述浮空器结冰特性数据包括浮空器表面的结冰厚度和结冰分布。
进一步地，浮空器结冰特性试验系统的试验工况与浮空器结冰特性计算模型的边界条件相同。
本发明具有以下有益效果：通过数值仿真的方式获和物理模拟试验两种方式获得浮空器结冰特性数据，数值仿真得到的计算结果和物理模拟试验的试验结果相互印证和完善，从而深入研究和准确分析浮空器的结冰特性。
附图说明
图1是浮空器结冰特性计算模型的组成示意图。
图2是浮空器结冰特性计算方法的流程示意图。
图3是艇形浮空器结冰特性试验系统结构示意图。
图4是球形浮空器结冰特性试验系统结构示意图。
其中，上述附图包括以下附图标记：1、浮空器；2、水滴喷射器；3、环境数据采集模块；4、浮空器压差数据采集模块；5、拉力测试模块；6、数据存储和处理模块；7、试验状态记录模块；8、低温环境实验室。
具体实施方式
下面将结合附图对本发明的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
一种浮空器结冰特性的数值仿真与试验验证系统，包括浮空器结冰特性计算模型和浮空器结冰特性试验系统，浮空器结冰特性计算模型用于通过数值仿真的方式获得浮空器结冰数据，浮空器结冰特性试验系统用于通过物理模拟试验获得浮空器结冰特性数据，数值仿真得到的计算结果和物理模拟试验的试验结果相互印证和完善，从而深入研究和分析浮空器的结冰特性。
浮空器表面结冰过程可以划分为三个步骤：(1)过冷水滴在浮空器周边流场中流动而撞击浮空器迎风面；(2)撞击到浮空器迎风面的过冷水滴有一部分贴附在浮空器表面形成水膜流动，有一部分被反弹飞溅离开浮空器表面；(3)贴附在浮空器表面的水膜经过换热后结冰。
根据以上三个步骤，将浮空器结冰特性计算模型包括三个计算模块，分别是浮空器温度场-流场特性计算模块，浮空器过冷水滴撞击特性计算模块以及浮空器表面冰型生长计算模块，各模块之间的关系如图1所示。
浮空器结冰特性计算模型的建模方法，包括以下步骤：
S100，根据浮空器飞行任务需求，计算浮空器飞行参数及设计参数；
浮空器的飞行参数包括浮空器的飞行时间、浮空器的飞行地点经度、浮空器的飞行地点纬度、浮空器的飞行海拔高度和浮空器的飞行空速；
浮空器的设计参数包括浮空器的体积、浮空器的长度、浮空器的最大直径、浮空器的表面积和太阳能电池面积。
S200，计算浮空器大气环境参数和热环境参数；
浮空器的大气环境参数包括浮空器的飞行海拔高度处的大气温度、大气压力和大气密度；
浮空器的热环境参数包括浮空器的辐射热环境参数和对流换热环境参数，所述浮空器的辐射热环境参数包括太阳直接辐射热流、大气散射太阳辐射热流、地面反射太阳辐射热流、大气长波辐射热流和地面长波辐射热流。
S300，基于浮空器几何特征及传热模式，建立浮空器温度场-流场特性计算模块；
利用CATIA软件创建浮空器的三维模型，将所述三维模型导入CFD/ICEM软件创建计算域，生成非结构网格以离散计算域，完成浮空器有限元模型的建模。
在CFD/Fluent软件中，基于三维纳维-斯托克斯方程，将浮空器的辐射热环境参数和对流换热环境参数作为边界条件，加载在浮空器的有限元模型上，温度场-流场的耦合特性利用基于压力的半隐式分离求解法(SIMPLE)解算，利用二阶离散格式离散对流项和扩散项，从而完成浮空器温度场-流场特性计算模块的建立。
S400，利用浮空器温度场-流场特性计算模块，建立浮空器过冷水滴撞击特性计算模块；
将CFD/FLUENT中的浮空器有限元模型和外流场数据的计算结果导入FENSAP-ICE软件，在FENSAP-ICE软件中，基于欧拉两相流理论，以及一些合理的设定，建立过冷水滴流动质量和动量守恒方程，从而完成浮空器过冷水滴撞击特性计算模块的建立；
所述合理的设定包括：
过冷水滴形状为球形；
过冷水滴在浮空器的周边流场中流动时，在撞击或流过浮空器的表面之前，不发生变形，不与环境换热；
浮空器的流场的湍动对过冷水滴流场无影响。
S500，利用浮空器温度场-流场特性计算模块、浮空器过冷水滴撞击特性模块，建立浮空器表面冰型生长计算模块，从而完成浮空器结冰特性计算模型的建模。
将CFD/FLUENT中的浮空器有限元模型和外流场数据的计算结果导入FENSAP-ICE软件，以及过冷水滴撞击计算模块的计算结果，在FENSAP-ICE软件中，利用浮空器的温度场-流场计算模块得到浮空器的表面温度、摩擦阻力和热流数据，利用过冷水滴撞击计算模块得到浮空器的表面过冷水滴收集系数，建立浮空器的表面冰型生长的质量和能量守恒方程，从而完成浮空器表面冰型生长计算模块的建立；
通过浮空器结冰特性计算模型，根据浮空器材料热特性参数，联立求解计算模块内所有微元的方程组，可计算出浮空器结冰特性数据，浮空器结冰特性数据包括浮空器表面的结冰 厚度和结冰分布，为浮空器试验提供数值计算的依据。
浮空器结冰特性试验系统，包括浮空器1，水滴喷射器2，环境数据采集模块3，浮空器压差数据采集模块4，拉力测试模块5，数据存储和处理模块6，试验状态记录模块7、低温环境实验室8八个模块。
环境数据采集模块3、浮空器压差数据采集模块4、拉力测试模块5与数据存储和处理模块7相连，拉力测试模块5与浮空器的系留绳相连，用于测量浮空器的浮升力数据，浮空器的浮生力等于浮空器的浮力减去浮空器的重力。
浮空器1是结冰特性试验对象，包括飞艇、系留气球、零压气球或超压气球等浮空器。
水滴喷射器2设置在浮空器1的上方，水滴喷射器2由主管道和一系列喷头组成，用于模拟降雨状态，喷头喷出的为空气和水滴的混合流体，通过调节喷头可以调节混合流体中的水滴直径、喷水含量和流速，喷水含量是指每立方米空气中含有的水滴质量。
环境数据采集模块3，由环境大气温度、环境大气压力、环境大气湿度、环境风速风向测试仪器组成，用来测量环境大气温度数据、环境大气压力数据、环境大气湿度数据和环境风速风向数据。
浮空器压差数据采集模块4，包括压差传感器，用于测量浮空器内外压差。
拉力测试模块5，包括张力计，用于测量浮空器的浮升力数据。
数据存储和处理模块6，主要由计算机硬件和数据处理软件组成，用于存储和处理各个模块传输来的数据。
试验状态记录模块7，由两架摄像机组成，用于记录试验过程中，浮空器结冰特性变化情况。
低温环境实验室8，用于提供0-20℃的室内温度。
采集所有数据并存于计算机中，试验数据用来验证和完善浮空器结冰特性计算模型。
利用浮空器结冰特性试验系统，可以进行浮空器结冰特性的试验，包括以下步骤：
步骤S1，将数据采集仪器与数据存储和处理模块连接，并调试运行状态。
步骤S101,将环境数据采集模块、浮空器压差数据采集模块、拉力测试模块连接到数据存储和处理模块，开启环境数据采集模块、浮空器压差数据采集模块、拉力测试模块，确保环境数据采集模块，拉力测试模块功能正常，采集数据准确；
步骤S102,调试试验状态记录模块，确保试验状态记录模块功能正常；
步骤S2，准备低温环境实验室。
步骤S201，开启低温环境实验室，确保低温环境实验室功能正常，可以调节室温；
步骤S202，根据试验需求，调节室温。
步骤S3，调试水滴喷射器。
步骤S301，开启水滴喷射器，确保水滴喷射器功能正常，可以调节喷出的水滴直径、喷水含量和流速；
步骤S302，根据试验需求，调节喷出的水滴直径、喷水含量和流速。
步骤S4，在浮空器上安装数据采集模块，并调试浮空器。
步骤S401，在浮空器上安装浮空器压差数据采集模块，浮空器压差数据采集模块连接到数据采集和处理模块；
步骤S402，往浮空器充入氦气，将浮空器移到水滴喷射器下方，将浮空器连接到拉力测试模块上再固定在地面；
步骤S5，测试浮空器结冰特性，浮空器结冰特性试验的试验工况与浮空器结冰特性计算模型的边界条件相同。
浮空器表面结冰特性受环境温度、浮空器压差、水滴直径、喷水含量、流速和结冰时间等六个因素的影响，本试验方法采用单一变量法，定量地测试单独每种因素对浮空器结冰特性的影响，设定环境温度、浮空器压差、水滴直径、喷水含量、流速和结冰时长的基准值，保持其中五个变量不变并保持基准值，使第六个变量单独变化，变化的数值围绕基准值上下浮动。
步骤S510，在相同环境温度、浮空器压差、水滴直径、喷水含量、流速条件下，即环境温度、浮空器压差、水滴直径、喷水含量、流速为基准值时，测试不同结冰时长条件下，浮空器结冰特性的变化。
步骤S511，开启环境实验室，将室内温度调节到试验所需的环境温度，设置浮空器压差为基准值，测试浮空器在没有结冰时的浮升力；
步骤S512，保持水滴直径、喷水含量、流速和浮空器压差为基准值，测试浮空器浮升力随结冰时间的变化；
步骤S513，将511测量的浮空器浮升力数据减去512测量的浮空器浮升力数据，得到在一定环境温度、水滴直径、喷水含量、流速和浮空器压差条件下，不同结冰时长条件下浮空器表面的结冰质量；
步骤S514，完成步骤S513之后，将浮空器表面水膜擦拭干净。
步骤S520，重复步骤510，固定其他五个参量，将变量依次换成环境温度、浮空器压差、水滴直径、喷水含量、流速，测量每种因素影响下的浮空器表面结冰特性。
步骤S5还包括在试验过程中，使用试验状态记录模块记录试验过程中浮空器结冰状态的变化情况。
步骤S6，试验完成后对试验数据进行处理和分析，从而与浮空器结冰特性计算模型计算结果相互验证和相互完善。
上述实施例为本发明较佳的实施方式，但本发明的实施方式并不受上述实施例的限制，其他的任何未背离本发明的精神实质与原理下所作的改变、修饰、替代、组合、简化，均应为等效的置换方式，都包含在本发明的保护范围之内。

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  1. 一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于，包括：
    浮空器结冰特性计算模型，所述浮空器结冰特性计算模型用于通过数值仿真的方式获得浮空器结冰数据；
    浮空器结冰特性试验系统，所述浮空器结冰特性试验系统用于通过物理模拟试验获得浮空器结冰特性数据；
    通过数值仿真的方式获得浮空器结冰数据和通过物理模拟试验获得浮空器结冰特性数据相互验证，相互完善，从而为深入研究和准确分析浮空器的结冰特性提供数值仿真的依据和试验验证的依据。
  2. 根据权利要求1所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于，所述浮空器结冰特性试验系统包括：
    浮空器，结冰特性试验对象；
    水滴喷射器，用于模拟降雨状态；
    环境数据采集模块，用来测量环境数据；
    浮空器压差数据采集模块，用于测量浮空器内外压差；
    拉力测试模块，用于测量浮空器的浮升力；
    数据存储和处理模块，用于存储和处理各个模块传输来的数据；
    试验状态记录模块，用于记录试验过程中浮空器结冰特性的变化情况；
    低温环境实验室，用于提供0-20℃的室内温度；
    其中，所述水滴喷射器设置在所述浮空器的上方，所述环境数据采集模块、浮空器压差数据采集模块、拉力测试模块与所述数据存储和处理模块相连，所述拉力测试模块与所述浮空器的系留绳相连。
  3. 根据权利要求1所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于：所述浮空器包括飞艇、系留气球、零压气球或超压气球。
  4. 根据权利要求1所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于，所述浮空器结冰特性计算模型包括：浮空器温度场-流场特性计算模块，浮空器过冷水滴撞击特性计算模块，浮空器表面冰型生长计算模块。
  5. 根据权利要求4所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于，浮空器结冰特性计算模型的建模包括：根据浮空器飞行任务需求，计算浮空器飞行参数及设计参数；计算浮空器大气环境参数和热环境参数；基于浮空器几何特征及传热模式，建立浮空器温度场-流场特性计算模块。
  6. 根据权利要求4所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于，浮空器结冰特性计算模型的建模包括：利用浮空器温度场-流场特性计算模块，建立浮空器过冷水滴撞击特性计算模块。
  7. 根据权利要求4所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于，浮空器结冰特性计算模型的建模包括：利用浮空器温度场-流场特性计算模块、浮空器过冷水滴撞击特性模块，建立浮空器表面冰型生长计算模块。
  8. 根据权利要求1所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于：所述浮空器结冰特性数据包括浮空器表面的结冰厚度和结冰分布。
  9. 根据权利要求1所述的一种浮空器结冰特性的数值仿真与试验验证系统，其特征在于，浮空器结冰特性试验系统的试验工况与浮空器结冰特性计算模型的边界条件相同。
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