A method for predicting the falling trajectory of the main debris of artificial rain-making rockets

Abstract

The present invention discloses a method for predicting the falling trajectory of the main debris of an artificial rainfall enhancement rocket, comprising the following steps: obtaining the launch elevation angle, azimuth angle, and longitude and latitude coordinates of the artificial rainfall enhancement rocket launch point; calculating the longitude and latitude coordinates of the starting point of the main debris of the rocket after parachute deployment; fusing sounding, wind profiler radar, and the falling velocity data of the main debris of the rocket to construct a gridded meteorological falling velocity data space; establishing a unified storage and indexing strategy for managing the gridded data with the same longitude and latitude coordinates in the gridded meteorological falling velocity data space; and iteratively calculating the trajectory points of the main debris of the rocket on each data layer of the gridded meteorological falling velocity data space based on a longitude and latitude variation model between two points above the Earth, the falling starting point data of the main debris of the rocket after parachute deployment, and the constructed gridded meteorological falling velocity data space, layer by layer, to obtain the falling trajectory of the main debris of the rocket. The present invention can effectively predict the falling trajectory of the main debris of the rocket, thereby improving the safety of ground-based rocket rainfall enhancement operations.

Description

Technical Field

[0001] The invention belongs to the technical field of meteorological rockets, and in particular relates to a method for predicting the falling trajectory of main debris of an artificial rainfall enhancement rocket. Background Art

[0002] Artificial rainmaking is one of the important ways to regulate drought and water shortage in arid areas. At the same time, artificial weather modification is also an important means of meteorological disaster prevention and mitigation. Ground-based rocket operation systems play a significant role in rainmaking and drought relief, hail prevention and mitigation, air pollution prevention and control, reservoir water storage and power generation, and forest fire prevention (extinguishing).

[0003] After the artificial rain-making rocket is spread in the air, its main debris is usually dropped by parachute. The landing site is easily affected by high-altitude winds and may land in densely populated areas, highways, rail transit, etc., which can easily cause various accidents. Therefore, the trajectory prediction to ensure the safe landing of the main debris of the larger rocket has become a key issue to consider in artificial rain-making rocket operations. Summary of the Invention

[0004] In order to address the deficiencies in the prior art, the present invention provides a method for predicting the falling trajectory of the main debris of an artificial rainfall rocket. By creating a vector value function F(x) of the falling starting point of the main debris of the artificial rainfall rocket and constructing a gridded meteorological fall velocity data space, the falling trajectory of the main debris of the artificial rainfall rocket is predicted by applying a longitude and latitude change model between two points above the earth, thereby improving the safety of ground rocket rainfall enhancement work and promoting the development of artificial weather modification work.

[0005] To achieve the above-mentioned object, a method for predicting the falling trajectory of the main debris of an artificial rainfall enhancement rocket according to one embodiment of the present invention comprises the following steps:

[0006] S1. Obtain the launch elevation angle ɑ, launch azimuth angle β and the longitude and latitude coordinates of the launch operation point A (E A , N A );

[0007] S2. Calculate the longitude and latitude coordinates (E0, N0) of the starting point B0 where the main debris of the rocket falls after the parachute is deployed based on the acquired data. Specifically,

[0008] S21. Create a vector value function F(x) of the falling starting point of the main debris of the artificial rainfall enhancement rocket;

[0009]

[0010] Among them, x is the rocket launch elevation angle, g(x) is the horizontal projection distance displacement function of the rocket main debris falling starting point, and h(x) is the height function of the rocket main debris falling starting point;

[0011] S22. Based on the acquired launch elevation angle ɑ and the vector value function F(x), obtain the horizontal plane projection distance AB0 from the rocket launch operation point A to the starting point B0 of the main rocket debris falling, and the height H0 of the starting point B0 of the main rocket debris falling;

[0012] Among them, AB 0＝ g(ɑ),H 0＝ h(ɑ);

[0013] S23. Calculate the longitude and latitude coordinates (E0, N0) of the starting point B0 where the main debris of the rocket falls based on the longitude and latitude variation model between two points above the Earth and the obtained rocket launch azimuth angle β;

[0014] E0=E A +AC / (2×π×r)×360°

[0015] N0=N A +B0C / (2×π×R)×360°

[0016] Among them, E A is the longitude coordinate of the launch operation point A, N A is the latitude coordinate of the launch operation point A; AC=AB0×sin(β), B0C=AB0×cos(β), AB0 is the horizontal plane projection distance from the launch operation point A to the starting point B0 of the main debris of the rocket, β is the azimuth of the rocket launch; r=R×cos(N A ), is the radius of the section at the latitude of point A; R is the radius of the earth;

[0017] S3. Fusing the sounding data, wind profiler radar data, and the rocket debris fall velocity data to construct a gridded meteorological fall velocity data space; the gridded meteorological fall velocity data space is composed of multiple data layers at different altitudes, each data layer is divided into multiple grids according to a calibrated spatial resolution, and each grid is configured with wind speed data, wind direction data, rocket debris fall velocity data, altitude data, and longitude and latitude coordinate data;

[0018] S4. Establishing a unified storage and indexing strategy for managing gridded data of the same longitude and latitude coordinates in the gridded meteorological falling velocity data space for easy access;

[0019] S5. Calculate the coordinates (E1, N1) and height H1 of the first trajectory point B1 of the main rocket debris falling in the constructed gridded meteorological fall velocity data space based on the longitude and latitude variation model between two points above the Earth and the data of the starting point B0 of the main rocket debris after parachute deployment;

[0020] E1=E0+B0C / (2×π×r)×360°

[0021] N1=N0+B1C / (2×π×R)×360°

[0022] Where E0 is the longitude coordinate of point B0, the starting point of the main debris of the rocket, and N0 is the latitude coordinate of point B0; B0C = L1 × sin(θ0), B1C = L1 × cos(θ0); L1 = V0t1, where L1 is the horizontal projection distance between B0 and B1; V0 is the wind speed at point B0; t1 = (H1 - H0) / V H , t1 is the time it takes for the main debris of the rocket to drift from point B0 to point B1 in the data layer below the closest data space, θ0 is the wind direction at point B0; H1 is the height data of the data layer in the data space below point B0, H0 is the height of point B0, V H is the falling velocity of the main debris of the rocket at the height H0; r = R × cos (N0), is the radius of the section at the latitude of point B0; R is the radius of the earth;

[0023] S6. Calculate all path coordinate points of the subsequent main debris of the rocket during its falling process to obtain the falling trajectory of the main debris of the rocket.

[0024] Furthermore, the falling speed of the main debris of the rocket at various altitudes is: above 7000m, the falling speed is 13m / s; in the range of 7000m-6000m, the falling speed is 12m / s; in the range of 6000m-4000m, the falling speed is 11m / s; in the range of 4000m-2000m, the falling speed is 10m / s; in the range of 2000m-1000m, the falling speed is 9m / s; below 1000m, the falling speed is 8m / s.

[0025] Furthermore, the above S3 integrates the falling velocity data of the sounding, wind profiler radar and the main debris of the rocket to construct a gridded meteorological falling velocity data space, specifically:

[0026] S31, obtaining sounding wind factor meteorological data, processing it into gridded data according to the calibrated spatial resolution, and establishing gridded sounding data layers at different altitudes according to the height intervals of the sounding data;

[0027] S32, acquiring wind profiler radar data, processing it into meteorological factor gridded data according to the calibrated spatial resolution, and establishing gridded radar data layers at different altitudes according to the height intervals of the wind profiler radar data;

[0028] S33. After interpolating the gridded sounding data layer and the gridded radar data layer in descending order, the falling velocity of the main debris of the rocket is matched into each layer of grids according to the height, and a gridded meteorological falling velocity data space is constructed.

[0029] Furthermore, step S5 calculates the coordinates (E1, N1) and height H1 of the first trajectory point B1 of the main rocket debris according to the longitude and latitude variation model between two points above the Earth, the data of the starting point B0 of the main rocket debris after parachute deployment, and the constructed gridded meteorological fall velocity data space, specifically:

[0030] S51. Find a group of grid data with the same longitude and latitude coordinates in the gridded meteorological falling speed data space according to the coordinates (E0, N0) of point B0 and the indexing strategy;

[0031] S52. Based on the height H0 of point B0, obtain the two grid data of the upper and lower layers closest to point B0 from the set of grid data with the same latitude and longitude coordinates found, interpolate the wind speed data and wind direction data in the two grid data to obtain the wind speed V0 and wind direction θ0 at the falling starting point B0, and obtain the height data of the closest lower grid data, which is H1;

[0032] S53, calculating the time t1 of the main debris of the rocket falling from the falling starting point B0 to the data layer B1 point in the closest data space below;

[0033] t1=(H1-H0) / V H ,

[0034] Among them, H1 is the height data of the data layer in the data space closest to B0, V H is the falling velocity of the main debris of the rocket at the height H0;

[0035] S55, calculating the horizontal projection distance displacement L1 between B0 and B1;

[0036] L1=V0t1

[0037] Among them, V0 is the wind speed at the falling starting point B0;

[0038] S56. Calculate the longitude and latitude coordinates (E1, N1) of the first falling trajectory point B1 of the main rocket debris based on the longitude and latitude variation model between two points above the Earth and the obtained wind direction data θ0;

[0039] E1=E0+B0C / (2×π×r)×360°

[0040] N1=N0+B1C / (2×π×R)×360°

[0041] Where E0 is the longitude coordinate of point B0, the starting point of the main debris of the rocket, and N0 is the latitude coordinate of point B0; B0C = L1 × sin(θ0); B1C = L1 × cos(θ0), L1 = V0t1, L1 is the horizontal projection distance between B0 and B1; V0 is the wind speed at point B0, and θ0 is the wind direction at point B0; t1 = (H1-H0) / V H , t1 is the time it takes for the main debris of the rocket to float from point B0 to point B1 in the data layer below the closest data space; H1 is the height data of the data layer below point B0 in the data space closest to point B0, H0 is the height of point B0, V H is the falling speed of the main debris of the rocket at the height H0; r = R × cos (N0), is the radius of the section at the latitude of point B0; R is the radius of the earth.

[0042] Furthermore, in S52 , when the height H0 is equal to a certain layer height in the gridded meteorological falling speed data space, the wind speed V0 and wind direction θ0 of the falling starting point B0 are corresponding data in the grid of this layer.

[0043] Furthermore, the step S6 of calculating all path coordinate points of the main debris of the rocket in the subsequent falling process in the gridded meteorological falling velocity data space to obtain the falling trajectory of the main debris of the rocket includes the following steps:

[0044] S61, set k=1;

[0045] S62, according to B k The coordinates of the point (E k , N k ) Find a set of grid data with the same longitude and latitude coordinates in the gridded meteorological falling speed data space according to the indexing strategy; and obtain a grid data with a height equal to B k The height of the point H k The wind speed V in the target grid data k and wind direction θ k and the height H of the next layer of grid data k+1 ;

[0046] S63, calculate the main debris of the rocket from the gridded meteorological falling velocity data space k layer B k Point falls to the k+1th layer B k+1 Time t k+1 ;

[0047] t k+1 =(H k+1 -H k ) / V H k

[0048] Among them, H k+1 To obtain B kClick the height of the next layer of grid data, H k is the height of the target grid data, V H k is the falling velocity of the main debris of the rocket in the target grid data;

[0049] S64, Calculation B k B k+1 The horizontal projection distance between k ;

[0050] L k =V k t k+1

[0051] Among them, V k is the wind speed in the target grid data;

[0052] S65, based on the longitude and latitude change model between two points above the earth and the wind direction θ in the target grid data obtained. k , calculate the trajectory B of the main debris of the rocket k+1 The longitude and latitude coordinates of the point (E k+1 , N k+1 );

[0053] E k+1 =E k +B k C / (2×π×r)×360°

[0054] N k+1 =N k +B k+1 C / (2×π×R)×360°

[0055] Among them, B k C=L k ×sin(θ k );B k+1 C=L k ×cos(θ k ); r=R×cos(N k ), r is B k The radius of the tangent plane at the latitude of the point; R is the radius of the earth;

[0056] S66. Determine whether the current k layer is the layer closest to the ground in the gridded meteorological falling velocity data space. If so, end the prediction; otherwise, set k = k + 1, repeat steps S62-S66, calculate all path coordinate points in the subsequent process of the main debris of the rocket falling, and obtain the falling trajectory of the main debris of the rocket.

[0057] Furthermore, k is the number of altitude layers that the main debris of the rocket falls through in the gridded meteorological fall velocity data space.

[0058] Furthermore, the falling velocity, wind direction, and wind speed of the main debris of the rocket from the kth layer to the k+1th layer can also be the average value of the kth layer and the k+1th layer.

[0059] Furthermore, the calibration spatial resolution is 0.03 degrees*0.03 degrees.

[0060] Furthermore, the artificial rain-making rocket is a WR-98 artificial rain-making rocket.

[0061] The beneficial effects of the present invention are:

[0062] 1. The present invention obtains the horizontal projection distance from the rocket launch operation point A to the rocket main debris falling starting point B0 and the height of the rocket main debris falling starting point based on the rocket launch elevation angle ɑ and the created vector value function of the artificial rainfall enhancement rocket main debris falling starting point, thereby calculating the key point of the rocket main debris falling trajectory, that is, the longitude and latitude coordinates of the falling starting point, so that the falling starting point of the rocket main debris is accurately located, effectively ensuring the accuracy of subsequent prediction of the rocket main debris falling trajectory;

[0063] 2. The present invention converts sounding data and wind profiler radar data into grid point data, interpolates them from high to low, and integrates the fall velocity data of the main rocket debris to construct a gridded meteorological fall velocity data space. Metadata is then used to establish a unified storage and indexing strategy to achieve effective management of multi-layer gridded meteorological data with the same longitude and latitude coordinates in the gridded meteorological data space. Such a management strategy can help the system quickly locate and obtain the required meteorological data and promote data sharing and exchange.

[0064] 3. Based on the longitude and latitude variation model between two points above the Earth, the B0 data of the starting point for the main debris of the rocket to fall after parachute opening, and the constructed gridded meteorological fall velocity data space, the present invention iteratively and progressively calculates the path coordinate points and the wind speed and wind direction of each path coordinate point on all data layers of the gridded meteorological fall velocity data space during the falling process of the main debris of the rocket, thereby obtaining the falling trajectory of the entire main debris of the rocket. The method is fast and achieves good prediction results. BRIEF DESCRIPTION OF THE DRAWINGS

[0065] Figure 1 This is a flow chart of a method for predicting the falling trajectory of the main debris of an artificial rainfall enhancement rocket according to the present invention;

[0066] Figure 2 This is a model diagram of longitude and latitude changes between two points on the Earth for calculating the longitude and latitude coordinates (E0, N0) of the starting point B0 of the main debris of a rocket falling according to an embodiment of the present invention;

[0067] Figure 3A model diagram of longitude and latitude changes between two points above the Earth for calculating the longitude and latitude coordinates (E1, N1) of the first trajectory point B1 of the falling trajectory of the main debris of a rocket according to an embodiment of the present invention;

[0068] Figure 4 This is a comparison chart of the trajectory predicted by the method of the present invention using sounding data, the trajectory predicted by integrating wind profiler radar sounding data, and the trajectory measured by the rocket GPS module;

[0069] Figure 5 This is a schematic diagram of an interface of a rocket debris landing zone assessment system for predicting an application state of an embodiment of the present invention;

[0070] Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 、 Figure 10 The figure is a comparison between the falling trajectory of the main debris of the WR-98 rocket calculated by the method of the present invention and the actual trajectory measured by the GPS module carried by the rocket. DETAILED DESCRIPTION

[0071] In order to make the purpose, technical solutions and advantages of the present invention more clear, further description is given below with reference to the accompanying drawings and embodiments.

[0072] It should be noted that, in this document, relational terms such as first and second, etc., are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that includes a list of elements includes not only those elements but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus.

[0073] Taking the WR-98 artificial rainfall rocket as an example, the rocket reaches its highest point around 28-29 seconds after launch. (Because the rocket's horizontal velocity has already dropped to 100-150 m / s near its highest point, the onboard GPS module can locate the rocket's position. The rocket reaches its highest point when its vertical velocity turns from positive to negative.) Afterward, the rocket begins its descent, and the parachute is deployed around 32 seconds later. After deployment, the rocket maintains a horizontal velocity of 40-130 m / s and continues forward for a short distance in the direction of launch. The safety landing gear activates, and the capsule housing, containing the large and small parachutes, separates from the rocket itself. The large and small parachutes are deployed mid-air, with the small parachute carrying the capsule housing downward, while the large parachute carries the remaining rocket debris downward. The explosion, the deployment of the parachute, and other factors affect the rocket's aerial motion. For a short period after deployment, the horizontal motion of the main rocket debris fluctuates unpredictably, representing a period of oscillation that gradually stabilizes after two seconds. At the moment of parachute deployment, the vertical downward acceleration increases rapidly. Once the parachute stabilizes, an upward acceleration is generated. After two seconds, the downward trend gradually slows, and then approaches a constant speed. Seconds after the parachute is deployed, the main rocket debris, driven by the parachute, drifts from its starting point, driven by the high-altitude wind, until it lands.

[0074] As an example, Figure 1 As shown, the present invention provides a method for predicting the falling trajectory of the main debris of a WR-98 artificial rainfall enhancement rocket, comprising the following steps:

[0075] S1. Obtain the launch elevation angle ɑ, launch azimuth angle β and the longitude and latitude coordinates of the launch point A (E A , N A );

[0076] S2. Calculate the longitude and latitude coordinates (E0, N0) of the starting point B0 where the main debris of the rocket falls after the parachute is deployed based on the acquired data. Specifically:

[0077] S21. Create a vector value function F(x) of the falling starting point of the main debris of the artificial rainfall enhancement rocket;

[0078]

[0079] Among them, x is the rocket launch elevation angle, g(x) is the horizontal projection distance displacement function of the starting point of the rocket's main debris falling, and h(x) is the height function of the starting point of the rocket's main debris falling;

[0080] S22. According to the launch elevation angle ɑ and the vector value function F(x), the horizontal plane projection distance AB0 from the rocket launch operation point A to the starting point B0 of the main rocket debris falling and the height H0 of the starting point B0 of the main rocket debris falling are obtained;

[0081] Among them, AB 0＝ g(ɑ),H 0＝ h(ɑ);

[0082] S23. Calculate the longitude and latitude coordinates (E0, N0) of the starting point B0 where the main debris of the rocket falls based on the longitude and latitude variation model between two points above the Earth and the obtained rocket launch azimuth angle β;

[0083] As attached Figure 2 As shown, the distance from point A (E A , N A ) is displaced to the longitude and latitude change model of point B0 (E0, N0). According to the longitude and latitude change model between two points above the earth, the longitude and latitude of the starting point B0 of the main debris of the rocket is determined by the known position of the rocket launch operation point A (E A , N A ), the launch azimuth angle β, combined with the different launch elevation angles ɑ of the rocket corresponding to different parachute opening distances and heights, the specific calculation method is as follows:

[0084] Since the maximum altitude of the WR-98 artificial rain-making and hail-prevention rocket is only about 8 km, which is almost negligible compared to the radius of the earth, the movement of the rocket can be approximately regarded as displacement on the ground. Figure 2 In the equation, N and O are the North Pole and the center of the Earth respectively. P is the center of the circle on the latitude plane where point A is located. Line segment AC is parallel to the latitude line, line segment B0C is parallel to the longitude line, and ∠AB0C is a right angle. R is the radius of the Earth, which is approximately 6371011m. If the longitude and latitude coordinates of point A are (E A , N A ), the longitude and latitude coordinates of point B0 are (E0, N0), then the longitude and latitude coordinates of point C are (E c , N A ), AB0 is the horizontal projection distance from the launch operation point A to the starting point B0 of the main debris of the rocket falling; β is the azimuth of the rocket launch, and the distance AC between points A and C and the distance B0C between points C and B0 are:

[0085] AC=AB0×sin(β)

[0086] B0C=AB0×cos(β)

[0087] △APC is parallel to the equatorial plane, and the radius r of the section at the latitude of point A is:

[0088] r=R×cos(N A )

[0089] The longitude and latitude of point B are:

[0090] E0=E A +AC / (2×π×r)×360°

[0091] N0=N A +B0C / (2×π×R)×360°

[0092] Among them, E A is the longitude coordinate of the launch operation point A, N A is the longitude coordinate of the launch operation point A; AB0 is the horizontal plane projection distance from the launch operation point A to the starting point B0 where the main debris of the rocket falls; r is the radius of the section at the latitude of point A; R is the radius of the earth.

[0093] S3. Integrate the falling velocity data of sounding, wind profiler radar and rocket debris to construct a gridded meteorological falling velocity data space. Specifically:

[0094] S31, obtaining sounding wind factor meteorological data, processing it into gridded data according to the calibrated spatial resolution, and establishing gridded sounding data layers at different altitudes according to the height intervals of the sounding data;

[0095] Sounding data refers to the use of vehicles such as balloons to carry meteorological observation instruments into the atmosphere for observation, so as to obtain data such as temperature, humidity, air pressure and wind speed at various altitudes in the atmosphere. As the balloon ascends, the sounding instrument records atmospheric parameters in real time and transmits the data back to the ground. These data can be used to analyze information such as the temperature structure, humidity distribution, wind direction and wind speed of the atmosphere, which plays an important role in weather forecasting and climate research. Wherein, the sounding data of the present invention is L-band radar sounding data.

[0096] Generally speaking, the height interval of sounding data can range from tens to hundreds of meters. Sounding wind factor meteorological data is obtained and processed into gridded data at a calibrated spatial resolution of 0.03 degrees by 0.03 degrees. Gridded sounding data layers are then created at different heights based on the height interval of the sounding data.

[0097] S32, acquiring wind profiler radar data, processing it into meteorological factor gridded data according to the calibrated spatial resolution, and establishing gridded radar data layers at different altitudes according to the height intervals of the wind profiler radar data;

[0098] Wind broadside radar is a commonly used instrument in atmospheric science research, primarily used to measure meteorological parameters such as precipitation, cloud structure, wind speed, and direction. Wind broadside radar uses remote sensing inversion measurements to obtain wind speed and direction data.

[0099] Generally speaking, the height interval of wind profiler radar can range from hundreds of meters to several kilometers. Obtain wind profiler radar data and process it into meteorological factor gridded data at a consistent calibrated spatial resolution of 0.03 degrees * 0.03 degrees. Gridded radar data layers are created at different heights based on the height interval of wind profiler radar data.

[0100] S33, after interpolating the gridded sounding data layer and the gridded radar data layer in descending order, match the falling velocity of the main debris of the rocket into each layer of grids according to the height, and construct a gridded meteorological falling velocity data space;

[0101] The method of the present invention combines the sounding data with the wind broadening radar data after special consideration:

[0102] Because sounding data is an in-situ measurement, its data quality is better than the remote sensing inversion measurement used by wind broad-line radar. However, because sounding data is observed by carrying meteorological observation instruments into the atmosphere through vehicles such as balloons, its release time (only twice a day, such as 8 o'clock and 20 o'clock) and location (must be a designated location) must comply with strict air traffic control to avoid causing harm to other air routes (the release cost factor must also be considered). Therefore, if it is an area close to its launch time and location, the data used is of better quality (in this special case, as an embodiment of the method of the present invention, it is also possible to consider using only sounding data to form a data space). However, the time of most other rainmaking operations may be relatively long apart from the sounding release time, or the location distance may be relatively far, or there may be weather changes in the middle. In this case, the effectiveness of using sounding data is questionable, and even very different data results may be obtained! This is a problem that must be paid attention to!

[0103] At this time, it is necessary to introduce wind profiler radar data. Wind profiler radar is a 24-hour uninterrupted detection. It does not have the hard limitations and shortcomings of sounding data in terms of distance and time. Therefore, compared with artificial rainmaking rocket launch operations that have uncertain work requirements at most times and locations, the method of the present invention integrates sounding data with wind profiler radar data, and uses wind profiler radar data and sounding data to complement each other, which reflects both the stability of the data (sounding) and the real-time nature of the data (wind profiler). According to the corresponding experiments conducted during the research process, the effect of using wind profilers alone or soundings alone is not as good as the fusion of the two data! Among them, the effect of using wind profilers alone is the worst. As shown in the attached figure Figure 4 Comparing the trajectories shown, data fusion can significantly correct the real-time, low-altitude wind factor data (the image shows that the divergence is mainly in the part of the trajectory close to landing, which also shows that the wind changes at high altitudes are relatively stable, while the wind factor data at low altitudes are more prone to large changes due to time and distance). Facts have proved that the fusion of sounding data and wind broad-line radar data can indeed obtain better prediction results of trajectories and ground landing point coordinates.

[0104] After being processed at the same calibrated spatial resolution, the sounding wind factor data and wind profiler radar data can be processed into the same meteorological factor gridded data, and they can correspond one to one. This is because during the processing, the two different types of raw data (sounding data and radar data) are converted to the same spatial grid, ensuring that they have the same spatial resolution and data format, allowing for direct comparison and analysis.

[0105] Interpolating the gridded sounding data layer and the gridded radar data layer in order from high to low according to their altitude can generate a continuous atmospheric parameter field, that is, the atmospheric data space, for subsequent calls. Interpolation uses the Kriging interpolation method in statistics: first, the sounding and radar data need to be prepared, including the location, altitude and corresponding meteorological parameter values. Ensure that the data quality and accuracy are reliable, and that the data format is consistent. Convert the sounding and radar data into grid point data, usually forming grid points in the horizontal and vertical directions; select the Kriging interpolation method, and deduce the values ​​of unknown points in the entire area based on the values ​​and spatial positions of the known points. Other interpolation methods may also include bilinear interpolation, cubic spline interpolation, etc.; and use methods such as cross-validation to evaluate the accuracy and reliability of the interpolation results to ensure that the interpolated data has physical meaning.

[0106] After generating a continuous multi-layer atmospheric parameter field using interpolation methods, the fall velocity of the main rocket debris is matched to each layer of grids according to altitude, constructing a gridded meteorological fall velocity data space. This gridded meteorological fall velocity data space is composed of multiple data layers at different altitudes. Each data layer is divided into multiple grids according to the calibrated spatial resolution. Each grid is configured with wind speed data, wind direction data, the fall velocity data of the main rocket debris, altitude data, and longitude and latitude coordinate data.

[0107] Among them, the falling speed data of the main debris of the rocket is:

[0108] Above 7000m, the falling speed is 13m / s; in the range of 7000m-6000m, the falling speed is 12m / s; in the range of 6000m-4000m, the falling speed is 11m / s; in the range of 4000m-2000m, the falling speed is 10m / s; in the range of 2000m-1000m, the falling speed is 9m / s; below 1000m, the falling speed is 8m / s.

[0109] As shown in Table 1 below:

[0110] Table 1 Observed falling speed and launch information of test rockets equipped with GPS modules at different altitudes

[0111]

[0112]

[0113] After installing a GPS module on the WR-98 artificial rainfall rocket, the fall velocity of the WR-98 rocket's main debris was observed at different altitudes, as shown in Table 1. The tests were conducted in February, March, April, September, and November; the test locations included Qingyuan, Shaoguan, Zhanjiang, and Meizhou, comprehensively covering a wide range of common atmospheric conditions. The results in Table 1 clearly demonstrate that the fall velocity of the WR-98 rocket's main debris is not significantly affected by changes in atmospheric conditions. With the exception of a few individual rockets with data anomalies, missing data, or slightly higher fall velocities, the observed fall velocity data for the other 37 rockets is highly consistent. Therefore, based on the experimental observation data, we can determine the fall velocity of the WR-98 rocket's main debris. Similarly, after installing a GPS module on the WR-98 artificial rainfall rocket, we can also observe and verify the starting point height of the WR-98 rocket's main debris and the horizontal projection distance from the launch point to the starting point of the main debris' fall.

[0114] S4. Establishing a unified storage and indexing strategy for managing gridded data of the same latitude and longitude coordinates in the gridded meteorological fall velocity data space for easy access;

[0115] As an optional implementation, metadata can be used to establish a unified storage and indexing strategy for managing multi-layer gridded meteorological data with the same longitude and latitude coordinates within the gridded meteorological fall velocity data space. This can be achieved by selecting a common file format, such as NetCDF or HDF5, to store multi-layer gridded meteorological data. This allows wind speed data, wind direction data, fall velocity data, altitude data, and longitude and latitude coordinate data to be stored in the same file. Metadata attributes can be added to the file to describe the meaning, units, and range of each dataset. For example, altitude information can be added to each dataset (such as wind speed, wind direction, and fall velocity), and the altitude range for each layer can be recorded. Furthermore, information such as the range and resolution of the longitude and latitude coordinate data can be recorded. Metadata can be used to establish a unified indexing strategy to ensure that data for each grid is uniquely indexed by longitude, latitude, and altitude. This can be achieved by defining standard metadata attributes in the file to quickly locate data at a specific longitude, latitude, and altitude. Standardized naming conventions can also be used to incorporate metadata information into the file name. For example, the longitude, latitude, and altitude information can be included in the file name to quickly identify and locate data. Metadata Document: Create a metadata document to record the meaning, units, altitude range, and other information for each data field. This information helps users better understand and use the data and provides a reference for data management. Through the above methods, metadata can be used to establish a unified storage and indexing strategy, enabling effective management of multi-layer gridded meteorological data with the same latitude and longitude coordinates within the gridded meteorological data space. This management strategy helps users quickly locate and obtain the required meteorological data and promotes data sharing and exchange.

[0116] S5. Calculate the coordinates (E1, N1) and height H1 of the first trajectory point B1 of the main rocket debris falling in the constructed gridded meteorological fall velocity data space based on the longitude and latitude variation model between two points above the Earth and the data of the starting point B0 of the main rocket debris after parachute deployment;

[0117] Specifically:

[0118] S51. Find a group of grid data with the same longitude and latitude coordinates in the gridded meteorological falling speed data space according to the coordinates (E0, N0) of point B0 and the indexing strategy;

[0119] S52. Based on the height H0 of point B0, obtain the two grid data of the upper and lower layers closest to point B0 from the set of grid data with the same latitude and longitude coordinates found, interpolate the wind speed data and wind direction data in the two grid data to obtain the wind speed V0 and wind direction θ0 at the falling starting point B0, and obtain the height data of the lower grid data, which is H1;

[0120] As a special case, if the height H0 is equal to the height of a certain layer in the gridded meteorological falling speed data space, then the wind speed V0 and wind direction θ0 at the falling starting point B0 are the corresponding data in this grid;

[0121] S53, calculating the time t1 of the main debris of the rocket falling from the falling starting point B0 to the point B1 on the data layer of the closest data space below it;

[0122] t1=(H1-H0) / V H

[0123] Among them, H1 is the height data of the data layer in the data space closest to B0, V H is the falling velocity of the main debris of the rocket at the height H0;

[0124] Furthermore, when calculating the falling velocity, wind direction, and wind speed from the current layer to the next layer, there are three methods for determining the values: the current layer's value, the next layer's value, or the average of the two layers. For ease of demonstration, this embodiment uses the current layer's value. Alternatively, the calculation can be performed using a unified latitude and longitude indexing strategy, by calling the next layer or by calling the data from the upper and lower layers separately, obtaining the average value, and then performing the calculation. Measurement and simulation results show that the average of the two layers performs better.

[0125] S54, calculating the horizontal projection distance displacement L1 between B0 and B1;

[0126] L1=V0t1

[0127] Among them, V0 is the wind speed at the falling starting point B0;

[0128] S55, as attached Figure 3 As shown, based on the above-mentioned longitude and latitude change model between two points above the earth and the obtained wind direction data θ0, the longitude and latitude coordinates (E1, N1) of the first falling trajectory point B1 of the main debris of the rocket are calculated;

[0129] E1=E0+B0C / (2×π×r)×360°

[0130] N1=N0+B1C / (2×π×R)×360°

[0131] Among them, B0C=L1×sin(θ0); B1C=L1×cos(θ0); r=R×cos(N0), which is the radius of the section at the latitude of point B0; R is the radius of the earth.

[0132] S6. Based on the longitude and latitude variation model between two points above the Earth, calculate the coordinates of all paths of the main debris of the rocket during its subsequent drift in the gridded meteorological fall velocity data space. Specifically,

[0133] S61. Let k = 1, where k is the number of altitude layers that the main debris of the rocket passes through in the gridded meteorological fall velocity data space;

[0134] S62, according to B k The coordinates (E k , N k ) Find a set of grid data with the same longitude and latitude coordinates in the gridded meteorological falling speed data space according to the index strategy; and obtain a grid data with a height equal to B k The height of the point H k The wind speed V in the target grid data k and wind direction θ k and the height H of the next layer of grid data k+1 ;

[0135] S63, calculate the main debris of the rocket from the gridded meteorological falling velocity data space k layer B k Point falls to the k+1th layer B k+1 Time t k+1 ;

[0136] t k+1 =(H k+1 -H k ) / V H k

[0137] Among them, H k+1 To obtain B k Click the height of the next layer of grid data, H k is the height of the target grid data, V H k is the falling velocity of the main debris of the rocket in the target grid data;

[0138] S64, Calculation B k B k+1 The horizontal projection distance between k ;

[0139] L k =V k t k+1

[0140] Among them, V k is the wind speed in the target grid data;

[0141] S65, based on the longitude and latitude change model between two points above the earth and the wind direction θ in the target grid data obtained. k , calculate the trajectory B of the main debris of the rocket k+1 The longitude and latitude coordinates of the point (E k+1 , N k+1 );

[0142] E k+1 =E k +B k C / (2×π×r)×360°

[0143] N k+1 =N k +B k+1 C / (2×π×R)×360°

[0144] Among them, B k C=L k ×sin(θ k );B k+1 C=L k ×cos(θ k ); r=R×cos(N k ), for B k The radius of the tangent plane at the latitude of the point; R is the radius of the earth;

[0145] S66. Determine whether the current k layer is the layer closest to the ground in the gridded meteorological falling velocity data space. If so, end the prediction; otherwise, set k = k + 1, repeat steps S62-S66, calculate all path coordinate points in the subsequent process of the main debris of the rocket falling, and obtain the falling trajectory of the main debris of the rocket.

[0146] Because the altitude data of the lowest data layer (closest to the ground layer) in the gridded meteorological fall velocity data space can approximately represent the average altitude data of the surrounding terrain, the longitude and latitude coordinates of the path coordinate point closest to the ground layer can be approximately used as the ground impact point coordinates of the main rocket debris.

[0147] As another embodiment of the present invention, based on geographic information data published by the National Administration of Surveying, Mapping and Geoinformation of China (including terrain and elevation data, available for query and download on their website), average ground elevation data for a certain range below the coordinates of the primary debris path closest to the ground can be obtained. Based on this average ground elevation data, the coordinates of the ground impact point can also be calculated using the aforementioned model of longitude and latitude changes between two points above the Earth and similar steps.

[0148] The steps include: first, using the coordinates of the closest ground layer trajectory point in the gridded meteorological fall speed data space, and finding a group of grid data with the same longitude and latitude coordinates in space according to the index strategy; and obtaining the wind speed data, wind direction data and the rocket main debris fall speed in the target grid data with a height equal to the height of the closest ground layer trajectory point, and then obtaining the average altitude data of the ground within a certain range below the main debris path coordinate point closest to the ground layer as the height of the ground landing point (the direction of the rocket main debris falling is considered when the range is limited), and calculating the time for the rocket main debris to fall from the closest ground layer to the ground landing point height according to the rocket main debris fall speed; then calculating the horizontal plane projection distance displacement between the closest ground layer trajectory point and the ground landing point according to the time and the wind speed in the obtained target grid data; finally, according to the longitude and latitude change model between two points above the earth and the wind direction in the obtained target grid data, the longitude and latitude coordinates of the ground landing point of the rocket main debris are calculated according to the above similar steps, thereby obtaining the complete falling trajectory of the rocket main debris.

[0149] As attached Figure 5 As shown in FIG, a system for evaluating the falling area of ​​rocket debris using the method of the present invention is used; Figures 6-10 The figure shows a comparison of the trajectory of the main debris of the WR-98 rocket calculated using the method of the present invention and the actual trajectory measured by the GPS module carried by the rocket. The bright white line in the figure is the actual trajectory measured by the GPS module carried by the rocket, and the light white line is the trajectory calculated by the method of the present invention. The radius of each circle is 1 km. In the test of 43 WR-98 artificial rainmaking rockets tested with the method of the present invention, only one rocket had an error greater than 2 km between the calculated trajectory endpoint and the measured trajectory endpoint, two rockets had an error within the range of (1-1.3), seven rockets had an error equal to 1 km, and 33 rockets had an error less than 1 km. Therefore, the proportion of rockets with an error of less than or equal to 1 km is 40 / 43 = 93%. The test results favorably demonstrate that the trajectory prediction method proposed in the present invention can effectively simulate the actual trajectory of the main debris of the WR-98 rocket, meeting the requirements of the scientific research project.

[0150] Optionally, in this embodiment, a person of ordinary skill in the art may understand that all or part of the steps in the various methods of the above embodiments may be completed by instructing the hardware related to the terminal device through a program, and the program may be stored in a computer-readable storage medium, which may include: a flash drive, a read-only memory (ROM), a random access memory (RAM), a magnetic disk or an optical disk, etc.

[0151] The technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution can be embodied in the form of a software product. The computer software product is stored in a storage medium and includes a number of instructions for enabling one or more computer devices (which may be personal computers, servers, or network devices, etc.) to execute all or part of the steps of the methods of various embodiments of the present invention.

[0152] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

[0153] The present invention and its embodiments are described above. This description is not restrictive. The drawings show only one embodiment of the present invention, and the actual structure is not limited thereto. In short, if a person skilled in the art is inspired by this and, without departing from the purpose of the present invention, designs structures and embodiments similar to this technical solution without inventiveness, they shall fall within the scope of protection of the present invention.

Claims

1. A method for predicting the falling trajectory of the main debris of an artificial rainfall enhancement rocket, characterized in that: It includes the following steps: S1. Obtain the launch elevation angle ɑ, launch azimuth angle β and the longitude and latitude coordinates of the launch operation point A (E A , N A ); S2. Calculate the longitude and latitude coordinates (E0, N0) and altitude H0 of the starting point B0 where the main debris of the rocket will fall after the parachute is deployed based on the acquired data, including: Create a vector value function for the falling starting point of the main debris of the artificial rainfall rocket , which is used to accurately locate the key point of the rocket's main debris's falling trajectory, that is, the starting point of the rocket's main debris's fall: ； in, is the rocket launch elevation angle, is the horizontal projection distance displacement function of the starting point of the main debris of the rocket falling, is the height function of the starting point of the rocket's main debris falling; The longitude and latitude coordinates (E0, N0) and the altitude H0 of the starting point B0 where the main debris of the rocket falls are: ； Among them, E A is the longitude coordinate of the launch operation point A, N A is the latitude coordinate of the launch point A, β is the rocket launch azimuth, R is the radius of the Earth; S3, integrating sounding data, wind profiler radar data and the falling velocity data of the main rocket debris to construct a gridded meteorological falling velocity data space; S4. Establishing a unified storage and indexing strategy for managing gridded data of the same longitude and latitude coordinates in the gridded meteorological falling velocity data space for easy access; S5. Based on the created vector value function of the falling starting point of the main debris of the artificial rainmaking rocket , the longitude and latitude variation model between two points above the Earth and the data of the starting point B0 where the main debris of the rocket falls after the parachute is deployed, and the coordinates (E1, N1) and height H1 of the first trajectory point B1 of the main debris of the rocket falling in the constructed gridded meteorological fall velocity data space; ； H1 is the height data of the data layer in the data space closest to the falling starting point B0; Among them, E0 is the longitude coordinate of point B0, the starting point of the main debris of the rocket, N0 is the latitude coordinate of point B0, V0 is the wind speed at point B0, θ0 is the wind direction at point B0, V H is the falling speed of the main debris of the rocket at the height H0; S6. Calculate all path coordinate points of the main debris of the rocket during the subsequent falling process in the gridded meteorological falling velocity data space to obtain the falling trajectory of the main debris of the rocket.

2. The method for predicting the falling trajectory of the main debris of the artificial rainmaking rocket according to claim 1 is characterized in that: The step S3, fusing the sounding data, wind profiler radar data and the rocket main debris falling velocity data to construct a gridded meteorological falling velocity data space, is specifically as follows: S31, obtaining sounding wind factor meteorological data, processing it into gridded data according to the calibrated spatial resolution, and establishing gridded sounding data layers at different altitudes according to the height intervals of the sounding data; S32, acquiring wind profiler radar data, processing it into meteorological factor gridded data according to the calibrated spatial resolution, and establishing gridded radar data layers at different altitudes according to the height intervals of the wind profiler radar data; S33. After interpolating the gridded sounding data layer and the gridded radar data layer in descending order, the falling velocity of the main debris of the rocket is matched into each layer of grids according to the height, and a gridded meteorological falling velocity data space is constructed.

3. The method for predicting the falling trajectory of the main debris of the artificial rainmaking rocket according to claim 2, characterized in that: Step S5, based on the longitude and latitude variation model between two points above the Earth and the data of the starting point B0 of the main debris of the rocket after parachute opening, calculates the coordinates (E1, N1) and height H1 of the first trajectory point B1 of the main debris of the rocket falling in the constructed gridded meteorological falling velocity data space, specifically: S51, finding a group of grid data with the same longitude and latitude coordinates in the gridded meteorological falling speed data space according to the coordinates (E0, N0) of point B0 according to the indexing strategy; S52. Based on the height H0 of point B0, obtain the two grid data of the upper and lower layers closest to point B0 from the set of grid data with the same latitude and longitude coordinates found, interpolate the wind speed data and wind direction data in the two grid data to obtain the wind speed V0 and wind direction θ0 at the falling starting point B0, and obtain the height data of the closest lower grid data, which is H1; S53. Calculate the time t of the main debris of the rocket falling from the falling starting point B0 to the data layer B1 point in the closest data space below. 1； ； Among them, H1 is the height data of the data layer in the data space closest to B0, V H is the falling velocity of the main debris of the rocket at the height H0; S55. Calculate the horizontal projection distance displacement between B0 and B1 L 1; ； Among them, V0 is the wind speed at the falling starting point B0; S56, based on the longitude and latitude change model between two points above the Earth and the wind direction data θ0, calculate the main debris of the rocket falling trajectory falling first track point B1 longitude and latitude coordinates (E1, N1) and height H1; ； H1 is the height data of the data layer in the data space closest to the falling starting point B0; Among them, E0 is the longitude coordinate of point B0 where the main debris of the rocket falls, N0 is the latitude coordinate of point B0, V0 is the wind speed at point B0, and θ0 is the wind direction at point B0. is the height function of the starting point of the falling of the main debris of the rocket, R is the radius of the Earth, V H is the falling speed of the main debris of the rocket at height H0.

4. The method for predicting the falling trajectory of the main debris of the artificial rainfall enhancement rocket according to claim 3 is characterized in that: In step S52, when the height H0 is equal to the height of a certain layer in the gridded meteorological falling speed data space, the wind speed V0 and wind direction θ0 of the falling starting point B0 are the corresponding data in this layer of grids.

5. The method for predicting the falling trajectory of the main debris of the artificial rainfall enhancement rocket according to claim 4, characterized in that: The step S6, calculating all path coordinate points of the main debris of the rocket in the subsequent falling process in the gridded meteorological falling velocity data space to obtain the falling trajectory of the main debris of the rocket, includes the following steps: S61, let k=1; S62, according to B k The coordinates of the point (E k , N k ) Find a set of grid data with the same longitude and latitude coordinates in the gridded meteorological falling speed data space according to the indexing strategy; and obtain the data with a height equal to B k The height of the point H k The wind speed V in the target grid data k and wind direction θ k and the height H of the next layer of grid data k+1 ; S63, calculate the main debris of the rocket from the gridded meteorological falling velocity data space k layer B k Point falls to the k+1th layer B k+1 Time t k+1； ； Among them, H k+1 To obtain B k Click the height of the next layer of grid data, H k is the height of the target grid data, V H k is the falling velocity of the main debris of the rocket in the target grid data; S64, Calculation B k B k+1 The horizontal projection distance between L k ; ； Among them, V k is the wind speed in the target grid data; S65, based on the longitude and latitude change model between two points above the earth and the wind direction θ in the target grid data obtained. k , calculate the trajectory B of the main debris of the rocket k+1 The longitude and latitude coordinates of the point (E k+1 , N k+1 ); ； S66. Determine whether the current k layer is the layer closest to the ground in the gridded meteorological falling velocity data space. If so, end the prediction; otherwise, set k=k+1, repeat steps S62-S66, calculate all path coordinate points in the subsequent falling process of the main debris of the rocket, and obtain the falling trajectory of the main debris of the rocket.

6. The method for predicting the falling trajectory of the main debris of the artificial rainfall enhancement rocket according to claim 5, characterized in that: k is the number of altitude layers that the main debris of the rocket passes through in the gridded meteorological fall velocity data space.

7. The method for predicting the falling trajectory of the main debris of the artificial rainfall enhancement rocket according to claim 6, characterized in that: The falling speed, wind direction and wind speed of the main debris of the rocket from the kth layer to the k+1th layer can also be the average value of the kth layer and the k+1th layer.

8. The method for predicting the falling trajectory of the main debris of the artificial rainfall enhancement rocket according to claim 1, characterized in that: The calibration spatial resolution is 0.03 degrees * 0.03 degrees.

9. The method for predicting the falling trajectory of the main debris of an artificial rainfall enhancement rocket according to claim 1, characterized in that: The artificial rain-making rocket is a WR-98 artificial rain-making rocket.

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