CN112395686A - Stratospheric aerostat flight trajectory prediction system and method based on meteorological detection - Google Patents
Stratospheric aerostat flight trajectory prediction system and method based on meteorological detection Download PDFInfo
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Abstract
The invention discloses a system and a method for predicting flight path of an stratospheric aerostat based on meteorological detection, wherein the method comprises the steps of collecting meteorological data comprising wind speed, wind direction, temperature and pressure; filtering and averaging the meteorological data to obtain vertical layered meteorological data; based on vertical layered meteorological data, obtaining a distribution change rule of wind speed, wind direction, temperature and pressure along with vertical height, judging a stratosphere quasi-zero wind layer by combining wind speed and wind direction information, and converting the collected original meteorological data into meteorological feature data in a specified height range; configuring model characteristic data; and analyzing the attitude and the motion rule of the aerostat at different moments based on the meteorological characteristic data and the model characteristic data to complete flight track simulation. According to the method, the quasi-zero wind layer diagnosis is carried out through meteorological collection, the flight track simulation is carried out by using the calculation software comprising the stratospheric aerostat dynamics model and the thermodynamics model, and the flight track of the stratospheric aerostat can be accurately predicted.
Description
Technical Field
The invention relates to the technical field of data prediction, in particular to a flight trajectory prediction system and method of an stratospheric aerostat based on meteorological detection.
Background
The stratospheric aerostat is arranged above a common aircraft and below a spacecraft, and has the advantages which are not possessed by aviation and aerospace aircrafts. As a high-resolution earth observation platform, the high-resolution earth observation platform has a wide coverage range, has great development potential in the aspects of communication guarantee, information collection, early warning, civil use and the like, and is widely applied to the fields of monitoring, scientific investigation, data communication and the like.
The atmospheric parameters such as air temperature, air pressure, density and wind speed which change constantly at any time and in the air near the 20km height of the stratosphere have obvious influence on the flight attitude and power control of the low-speed aircraft in the adjacent space. The quasi-zero wind layer of the stratosphere is an atmosphere layer near the 20km height of the lower layer of the stratosphere, the east-west wind directions of the upper layer and the lower layer are opposite, namely the west wind (east wind) of the lower layer turns to east wind (west wind), the south-north wind component is very small, and the aerostat flies in the air generally in the quasi-zero wind layer of the stratosphere.
Therefore, how to diagnose and analyze the stratosphere quasi-zero wind layer and predict the flight trajectory of the stratosphere aerostat is an urgent problem to be solved by those skilled in the art.
Disclosure of Invention
In view of the above, the invention provides a flight trajectory prediction system and method for an stratospheric aerostat based on meteorological detection, which can accurately predict the flight trajectory of the stratospheric aerostat.
In order to achieve the purpose, the invention adopts the following technical scheme:
stratosphere aerostat flight trajectory prediction system based on meteorological detection includes: the flight path simulation system comprises a data acquisition module, a data processing module, a data analysis and display module, a parameter configuration calculation module and a flight path simulation module;
the data acquisition module is used for acquiring meteorological data including wind speed, wind direction, temperature and pressure;
the data processing module is used for filtering and averaging the meteorological data to obtain vertical layered meteorological data;
the data analysis and display module is used for obtaining the distribution change rule of wind speed, wind direction, temperature and pressure along with the vertical height based on the vertical layered meteorological data, judging stratosphere quasi-zero wind layer definition elements such as shear wind height, south-north minimum wind speed and minimum wind speed height by combining wind speed and wind direction information, converting the meteorological data into meteorological feature data in an appointed height range, and searching for an expected parking height through the stratosphere quasi-zero wind layer;
the parameter configuration calculation module is used for configuring model characteristic data;
and the flight trajectory simulation module analyzes the attitude and the motion rule of the aerostat at different moments based on the meteorological characteristic data and the model characteristic data to complete flight trajectory simulation.
Preferably, the data analysis and display module is specifically configured to:
and converting the meteorological data into meteorological characteristic data of wind speed, wind direction, temperature and pressure in an appointed altitude range by setting the actual ground altitude, the actual analysis altitude range and the data density.
Preferably, the parameter configuration calculation module is specifically configured to:
based on the set diameter of the aerostat envelope, the weight of a platform including the pod, the instrument cabin and the solar panel, the magnitude of interference of helium filled in the aerostat envelope and the margin of helium filled in the aerostat envelope, outputting the mass of helium required by the aerostat for flying, the mass of ground helium filled, the volume of the ground envelope, the counterweight mass of the pod, the net buoyancy, the volume of ground air filled and the mass of ground air filled.
Preferably, the flight trajectory simulation module is specifically configured to:
based on the meteorological characteristic data and the helium mass, the ground helium filling volume, the ground capsule volume, the nacelle counterweight mass, the net buoyancy, the ground air filling volume and the ground air filling mass required by the flight of the aerostat in the model characteristic data, thermodynamic and kinetic model calculation is completed, the influence of heat conduction, heat radiation and heat convection on the internal temperature of the aerostat is obtained, and the surface thermal stress of the aerostat is output;
and transferring the internal temperature of the aerostat and the surface thermal stress of the aerostat, which are obtained by the calculation of the thermodynamic model, to the kinetic model for calculation, adjusting the flying height of the aerostat according to the expected flying height of the aerostat, obtaining the attitude and motion rule of the aerostat at each moment in the whole flying process, and completing the flight trajectory simulation.
The stratosphere aerostat flight trajectory prediction method based on meteorological detection comprises the following steps:
collecting meteorological data including wind speed, wind direction, temperature and pressure;
filtering and averaging the meteorological data to obtain vertical layered meteorological data;
obtaining a distribution change rule of wind speed, wind direction, temperature and pressure along with vertical height based on the vertical layered meteorological data, judging a stratosphere quasi-zero wind layer by combining wind speed and wind direction information, converting the meteorological data into meteorological feature data in an appointed height range, and searching an expected parking height through the stratosphere quasi-zero wind layer;
configuring model characteristic data;
and analyzing the attitude and the motion rule of the aerostat at different moments based on the meteorological characteristic data and the model characteristic data, and completing flight trajectory simulation.
Preferably, the specific steps of converting the meteorological data into meteorological feature data are as follows:
and converting the meteorological data into meteorological characteristic data of wind speed, wind direction, temperature and pressure in an appointed altitude range by setting the actual ground altitude, the actual analysis altitude range and the data density.
Preferably, the specific steps of configuring the model characteristic parameters are as follows:
based on the set diameter of the aerostat envelope, the weight of a platform including the pod, the instrument cabin and the solar panel, the magnitude of interference of helium filled in the aerostat envelope and the margin of helium filled in the aerostat envelope, outputting the mass of helium required by the aerostat for flying, the mass of ground helium filled, the volume of the ground envelope, the counterweight mass of the pod, the net buoyancy, the volume of ground air filled and the mass of ground air filled.
Preferably, the specific steps of calculating the flight trajectory include:
based on the meteorological characteristic data and the helium mass, the ground helium filling volume, the ground capsule volume, the nacelle counterweight mass, the net buoyancy, the ground air filling volume and the ground air filling mass required by the flight of the aerostat in the model characteristic data, completing thermodynamics and dynamics model calculation to obtain the influence of heat conduction, heat radiation and heat convection on the internal temperature of the aerostat and outputting the surface thermal stress of the aerostat;
and transferring the internal temperature of the aerostat and the surface thermal stress of the aerostat, which are obtained by the calculation of the thermodynamic model, to the kinetic model for calculation, adjusting the flying height of the aerostat according to the expected flying height of the aerostat, obtaining the attitude and motion rule of the aerostat at each moment in the whole flying process, and completing the flight trajectory simulation.
According to the technical scheme, compared with the prior art, the invention discloses and provides a flight trajectory prediction system and method of an stratospheric aerostat based on meteorological detection, which obtains the distribution rule of wind speed, wind direction, pressure and temperature elements along with height, simultaneously performs judgment and analysis on a stratospheric quasi-zero wind layer, performs flight trajectory simulation by using calculation software comprising a stratospheric aerostat dynamic model and a thermodynamic model, and can accurately predict the flight trajectory of the stratospheric aerostat.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the provided drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a flight trajectory prediction system of an stratospheric aerostat based on meteorological detection.
FIG. 2 is a flowchart of a method for predicting a flight trajectory of an aerostat on the stratosphere based on meteorological detection.
FIG. 3 is a graph of wind speed as a function of altitude for an example embodiment.
FIG. 4 is a graph of wind direction as a function of height for an embodiment.
FIG. 5 is a graph of pressure as a function of height for the examples.
FIG. 6 is a graph of temperature as a function of height for the examples.
FIG. 7 is a diagram illustrating the judgment of the quasi-zero wind layer in example 1.
FIG. 8 is a diagram illustrating the judgment of the quasi-zero wind layer in example 2.
FIG. 9 is a diagram illustrating a criterion of a quasi-zero wind layer in example 3.
Fig. 10 is a simulation predicted flight trajectory of example 1.
Fig. 11 the attached drawings show the simulated flying height of example 1.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The embodiment discloses a flight trajectory prediction system of an stratospheric aerostat based on meteorological detection, which comprises a data acquisition module, a data processing module, a data analysis and display module, a parameter configuration calculation module and a flight trajectory simulation module, as shown in fig. 1.
The data acquisition module is specifically an air sounding system, the air sounding system comprises a ground system and an air sounding instrument, and the ground system comprises a terminal, a receiver, a base measuring box and an antenna. The terminal directly operates Beidou sounding software and is used for controlling the receiver and the base measuring box, and data are collected and stored; the receiver is used for receiving and demodulating a sonde radio signal; the base measurement box is used for changing the transmitting frequency of the sonde and carrying out ground base measurement; the antenna is divided into a ground Beidou antenna and a sonde receiving antenna and is used for receiving and transmitting signals; the sonde is connected with the sounding balloon and used for acquiring and transmitting meteorological data.
And the data processing module is used for performing Kalman filtering on the meteorological data to remove data noise points, and performing mean processing on the time sequence data to obtain vertical layered meteorological data with a layering height of 50 meters.
The data analysis and display module is used for obtaining the distribution change rule of wind speed, wind direction, temperature and pressure along with the vertical height based on the vertical layered distribution data, judging stratosphere quasi-zero wind layer definition elements such as shear wind height, south-north minimum wind speed and minimum wind speed height by combining wind speed and wind direction information, and converting meteorological data into meteorological feature data in a specified height range based on configured actual ground height, actual analysis height range and data density. The displayed data comprises stratosphere quasi-zero wind layer definition elements such as shear wind height, south-north minimum wind speed and minimum wind speed height, and data such as actual ground height, actual analysis height range, data density and meteorological feature data.
And the parameter configuration calculation module is used for realizing initialization calculation according to the designated meteorological characteristic data, inputting parameters such as the diameter of an aerostat envelope, the platform weight including a nacelle, an instrument cabin, a solar cell panel and the like, helium interference magnitude, helium allowance and the like according to the selected meteorological data file and height parameters, and outputting parameters such as flight helium mass, ground helium filling volume, ground envelope volume, nacelle counterweight mass, net buoyancy, ground air filling volume, ground air filling mass and the like.
The flight path simulation module is used for completing thermodynamic and kinetic model calculation based on the meteorological characteristic data and the mass of the helium gas, the mass of the helium gas filled on the ground, the volume of the capsule body on the ground, the counterweight mass of the nacelle, the net buoyancy, the volume of the air filled on the ground and the mass of the air filled on the ground in the model characteristic data, obtaining the influence of heat conduction, heat radiation and heat convection on the internal temperature of the aerostat and outputting the surface thermal stress of the aerostat; and calculating a dynamic model according to the internal temperature of the aerostat and the surface thermal stress of the aerostat obtained by thermodynamic calculation, adjusting the flying height of the aerostat according to the expected flying height of the aerostat, obtaining the attitude and motion rule of the aerostat at each moment in the whole flying process, and completing the flight trajectory simulation.
The embodiment provides a method for predicting a flight trajectory of an stratospheric aerostat based on meteorological detection, as shown in fig. 2, the method includes:
collecting meteorological data including wind speed, wind direction, temperature and pressure;
performing Kalman filtering on meteorological data to remove data noise, and performing mean processing on time sequence data to obtain vertical layered meteorological data with 50m of layering height;
obtaining a distribution change rule of wind speed, wind direction, temperature and pressure along with vertical height based on the vertical layered meteorological data, judging stratosphere quasi-zero wind layer definition elements such as shear wind height, south-north minimum wind speed and minimum wind speed height by combining wind speed and wind direction information, and converting the meteorological data into meteorological characteristic data such as wind speed, wind direction, temperature and pressure in a specified height range by setting parameters such as actual ground height, actual analysis height range and data density;
outputting flight helium mass, ground helium filling volume, ground balloon volume, pod counterweight mass, net buoyancy, ground air filling volume and ground air filling mass based on the set aerostat capsule diameter, platform weight including a pod, an instrument cabin and a solar panel, helium interference magnitude and helium allowance;
based on meteorological characteristic data and flight helium mass, ground helium filling volume, ground capsule volume, nacelle counterweight mass, net buoyancy, ground air filling volume and ground air filling mass in model characteristic data, thermodynamic and kinetic model calculation is completed, the influence of heat conduction, heat radiation and heat convection on the internal temperature of the aerostat is obtained, and the thermal stress on the surface of the aerostat is output; transferring the internal temperature of the aerostat and the thermal stress on the surface of the aerostat, which are obtained by thermodynamic calculation, to a kinetic model for calculation, and adjusting the flying height of the aerostat according to the expected flying height of the aerostat to obtain the attitude and motion rule of the aerostat at each moment in the whole flying process; including the regular curves of horizontal displacement and height along with time, and completes the flight trajectory simulation.
In this embodiment: and (3) carrying out multiple meteorological data acquisition on the test area by using a sounding system, wherein the acquired original data is time sequence data with one piece per second, and about 10 data acquisition points are arranged in every 50 meters. The data processing module adopts Matlab software, removes data noise points by using Kalman filtering, and then processes time sequence data of one data point per second into vertical layered distribution data with 50 meters of layered height to obtain data such as ambient atmospheric wind speed, wind direction, temperature, pressure and the like in a flight airspace range below 22 kilometers of height (50 meters of layered distance).
And the data analysis module analyzes the meteorological data distribution characteristics of the region by using the data and carries out stratosphere quasi-zero wind layer diagnosis.
The wind speed distribution is shown in fig. 3, in late 6 months of 2020, the wind speed gradually increases from the ground to the storm zone, the wind speed gradually decreases from the storm zone to the stratosphere, and the wind speed of the stratosphere tends to be stable. The wind speed in a fast wind area can reach 50m/s, the wind speed of 19-22km is basically not more than 10m/s, a weak wind layer with small wind speed exists, the minimum wind of an advection layer appears at the height of 19.5-20.2km, and the minimum wind speed is not more than 1.00 m/s.
The wind direction distribution is shown in fig. 4, the angle of the coordinate point represents the wind direction angle, and if the coordinate point falls in the first quadrant, the wind direction is represented as northeast. The position of the coordinate point from the origin represents the altitude of the current wind direction, the origin is the sea level (the altitude is 0), and the maximum diameter circle is 25km in height. In late 6 months of 2020, the ground is 18km high, the wind direction is basically northwest wind, and a change interval with the wind direction change of more than 180 degrees exists at the 18-22km height, namely typical shear wind exists. The wind direction fluctuation is not large from the ground to the height of 18km in different time periods, and the wind direction of the ground and a high-wind area is relatively stable.
The pressure distribution is shown in fig. 5, in late 6 months of 2020, and overall, the ground pressure is about 650hpa, and the pressure gradually decreases with increasing height. Within each height layering range, pressure data in different time periods have no obvious fluctuation and are relatively stable. The pressure of the stratosphere 19-22km is gradually reduced, and the pressure is reduced from 65.40hpa to 40.00 hpa.
The temperature distribution is shown in fig. 6, in the late 6 months of 2020, overall, the temperature is stable in each height layering range, the phenomenon that different time points are slightly different occurs in a sharp wind area due to the difference of wind speeds, the lowest temperature is 17-19km, and the lowest temperature is-71 ℃. The temperature of the stratosphere at the height of 19-22km gradually rises along with the increase of the height, and the temperature rises from-70 ℃ to-59 ℃.
And (3) judging the quasi-zero wind layer of the sample 1, and analyzing the quasi-zero wind layer of the stratosphere of the area by combining the synthesized wind speed and the wind speed component distribution rule according to the wind speed and wind direction elements of the area as shown in fig. 7. In the sampling interval 1 time period of 6 Laetian in 2020, the synthetic wind speed gradually increases from the ground to the urgent flow area, gradually decreases from the urgent flow area to 18km, slightly fluctuates between 18km and 22km, and is basically not more than 10 m/s. The north and south wind is the north wind from the ground to 17km, the wind speed is gradually increased from the ground to the height of 9km, the wind speed of 9-17km is gradually reduced to zero, the south and north wind transformation occurs in multiple sections of 17-22km, and the wind speed is small. The east-west wind is basically east wind from the ground to 18km, the wind speed gradually increases from the ground to the height of 12km until the resultant wind speed approaches, and the wind speed gradually decreases to zero from 12km to 18 km. Within the 19-22km layering height, west wind is below 19.40km height, a certain height layering interval above 19.40km height becomes east wind, meanwhile, the north-south wind speed is not more than 5m/s, the north-south wind speed component is small, typical shear wind characteristics appear, the height is near 20km, the standard zero wind layer definition of an stratosphere is met, and 19.40km within a time period 1 is the standard zero wind layer height of the area.
And (3) performing quasi-zero wind layer judgment on the sample 2 and the sample 3, as shown in fig. 8 and 9, wherein the quasi-zero wind layer judgment is basically consistent with the wind field distribution of the sampling interval 1 in the sampling interval 2 time period and the sampling interval 3 time period in the 6 th month late 2020, 19.35km in the time period 2 is the quasi-zero wind layer height of the area, and 19.25km in the time period 3 is the quasi-zero wind layer height of the area.
Comprehensively considering, in different sampling interval time periods of the area in late 6 months of 2020, the distribution rules of the synthetic wind, east-west wind and north-south wind are basically consistent, the different layering heights are slightly different, and the wind speed and wind direction meteorological elements are stable. In the 19-20km height interval, below a certain height, west wind appears, above a section of height, east wind appears, and the south-north wind speed component is also very small, so that a quasi-zero wind layer with the height of 19.25-19.40km exists. Overall, in the sampling interval time quantum, can satisfy stratospheric aerostat ground and fly off and the short-time sky demand of staying.
Flight trajectory simulation is carried out on the stratosphere aerostat through detected meteorological data in simulation calculation software, total simulation time and controlled descent time are appointed at an interface before simulation calculation, and simulation time is visually adjusted. The simulation result is represented by two-dimensional coordinate graphs of the change of the simulation height along with the time and the simulation horizontal displacement, as shown in fig. 10 and 11, wherein the vertical axis of the simulation horizontal displacement coordinate graph represents the displacement in the north-south direction, and the horizontal axis represents the displacement in the east-west direction. According to the simulation result in the graph, the three sample simulated flight trajectories have the same trend and are mainly divided into an ascending stage, a standing-in-the-air stage and a descending stage, and two inflection points of the trajectories are respectively the starting point and the end point of the standing-in-the-air stage.
The horizontal displacement of the aerostat in the whole flight process is obtained through simulation, and the current wind field is combined to judge that the actual flight process cannot exceed a given airspace. And the drop point prediction part adjusts the descending section control strategy according to the longitude and latitude coordinates of the current flight position when the flight drop point is in a no-drop zone or a zone which is difficult to search, and performs iterative adjustment again to ensure that the target zone is controllable.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (8)
1. Stratosphere aerostat flight trajectory prediction system based on meteorological detection is characterized by comprising: the flight path simulation system comprises a data acquisition module, a data processing module, a data analysis and display module, a parameter configuration calculation module and a flight path simulation module;
the data acquisition module is used for acquiring meteorological data including wind speed, wind direction, temperature and pressure;
the data processing module is used for filtering and averaging the meteorological data to obtain vertical layered meteorological data;
the data analysis and display module is used for obtaining the distribution change rule of wind speed, wind direction, temperature and pressure along with the vertical height based on the vertical layered meteorological data, judging stratosphere quasi-zero wind layer definition elements such as shear wind height, south-north minimum wind speed and minimum wind speed height by combining wind speed and wind direction information, converting the meteorological data into meteorological feature data in an appointed height range, searching the expected parking height of the aerostat through the height of the stratosphere quasi-zero wind layer, and using the parking height as the basis of the aerostat parking flight;
the parameter configuration calculation module is used for configuring model characteristic data;
and the flight trajectory simulation module analyzes the attitude and the motion rule of the aerostat at different moments based on the meteorological characteristic data and the model characteristic data to complete flight trajectory simulation.
2. The system of claim 1, wherein the data analysis and display module is specifically configured to:
and converting the meteorological data into meteorological characteristic data of wind speed, wind direction, temperature and pressure in an appointed altitude range by setting the actual ground altitude, the actual analysis altitude range and the data density.
3. The system of claim 1, wherein the parameter configuration calculation module is specifically configured to:
based on the set diameter of the aerostat envelope, the weight of a platform including the pod, the instrument cabin and the solar cell panel, the magnitude of interference of helium filled in the aerostat envelope and the margin of helium filled in the aerostat envelope, calculating and outputting the mass of helium required by the aerostat for flying, the mass of ground helium filled, the volume of the ground envelope, the counterweight mass of the pod, the net buoyancy, the volume of ground air filled and the mass of ground air filled.
4. The system of claim 3, wherein the flight trajectory simulation module is specifically configured to:
based on the meteorological characteristic data and the helium mass, the ground helium filling volume, the ground capsule volume, the nacelle counterweight mass, the net buoyancy, the ground air filling volume and the ground air filling mass required by the flight of the aerostat in the model characteristic data, thermodynamic and kinetic model calculation is completed, the influence of heat conduction, heat radiation and heat convection on the internal temperature of the aerostat is obtained through the thermodynamic model calculation, and the surface thermal stress of the aerostat is output;
and transferring the internal temperature of the aerostat and the surface thermal stress of the aerostat, which are obtained by the calculation of the thermodynamic model, to the kinetic model for calculation, adjusting the flying height of the aerostat according to the expected flying height of the aerostat, obtaining the attitude and motion rule of the aerostat at each moment in the whole flying process, and completing the flight trajectory simulation.
5. A method for predicting the flight track of an stratospheric aerostat based on meteorological detection is characterized by comprising the following steps:
collecting meteorological data including wind speed, wind direction, temperature and pressure;
filtering and averaging the meteorological data to obtain vertical layered meteorological data;
obtaining a distribution change rule of wind speed, wind direction, temperature and pressure along with vertical height based on the vertical layered meteorological data, judging a stratosphere quasi-zero wind layer by combining wind speed and wind direction information, converting the meteorological data into meteorological feature data in an appointed height range, and searching an expected parking height through the stratosphere quasi-zero wind layer;
configuring model characteristic data;
and analyzing the attitude and the motion rule of the aerostat at different moments based on the meteorological characteristic data and the model characteristic data, and completing flight trajectory simulation.
6. The method for predicting the flight trajectory of the stratospheric aerostat based on meteorological sounding as claimed in claim 5, wherein the specific steps of converting the meteorological data into meteorological feature data are as follows:
and converting the meteorological data into meteorological characteristic data of wind speed, wind direction, temperature and pressure in an appointed altitude range by setting the actual ground altitude, the actual analysis altitude range and the data density.
7. The method for predicting the flight trajectory of the stratospheric aerostat based on meteorological sounding as claimed in claim 5, wherein the specific steps for configuring the model characteristic parameters are as follows:
based on the set diameter of the aerostat envelope, the weight of a platform including the pod, the instrument cabin and the solar panel, the magnitude of interference of helium filled in the aerostat envelope and the margin of helium filled in the aerostat envelope, outputting the mass of helium required by the aerostat for flying, the mass of ground helium filled, the volume of the ground envelope, the counterweight mass of the pod, the net buoyancy, the volume of ground air filled and the mass of ground air filled.
8. The method for predicting the flight trajectory of the stratospheric aerostat based on meteorological sounding as claimed in claim 7, wherein the specific step of calculating the flight trajectory comprises:
based on the meteorological characteristic data and the helium mass, the ground helium filling volume, the ground capsule volume, the nacelle counterweight mass, the net buoyancy, the ground air filling volume and the ground air filling mass required by the flight of the aerostat in the model characteristic data, thermodynamic and kinetic model calculation is completed, the influence of heat conduction, heat radiation and heat convection on the internal temperature of the aerostat is obtained through the thermodynamic model calculation, and the surface thermal stress of the aerostat is output;
and transferring the internal temperature of the aerostat and the surface thermal stress of the aerostat, which are obtained by the calculation of the thermodynamic model, to the kinetic model for calculation, and adjusting the flying height of the aerostat according to the expected flying height of the aerostat to obtain the attitude and motion rule of the aerostat at each moment in the whole flying process to complete the flight trajectory simulation.
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