CN-121997588-A - Rain-enhancing hail-suppression rocket projectile trajectory prediction method and system integrating three-dimensional meteorological fields

CN121997588ACN 121997588 ACN121997588 ACN 121997588ACN-121997588-A

Abstract

The invention discloses a method and a system for predicting a rain-enhancing hail-suppressing rocket projectile trajectory by integrating a three-dimensional meteorological field, which belong to the technical field of weather modification. According to the invention, a three-dimensional gas image field is constructed by carrying out continuous interpolation on meteorological data, an engine thrust-temperature self-adaptive model is established, a six-degree-of-freedom dynamics equation is constructed according to the rocket exterior ballistics theory, and the whole process of rocket projectile launching to landing is simulated by combining a numerical integration method, so that the precision and reliability of track prediction are effectively improved, and a scientific basis is provided for safety control and effect evaluation of weather operation affected by manpower.

Inventors

ZHANG XUEFENG
ZHANG ZHIQIANG
ZHANG YANXIA
CAI TAO
LI YONGLIN

Assignees

安徽工业大学

Dates

Publication Date: 20260508
Application Date: 20260123

Claims (9)

1. The method for predicting the trajectory of the hail-suppression rocket projectile by fusing the three-dimensional meteorological field is characterized by comprising the following steps of: S1, three-dimensional gas image field construction Constructing a three-dimensional meteorological field which continuously changes along with the height through interpolation and smoothing according to discrete meteorological data acquired by a sounding device; S2, thrust-temperature self-adaptive modeling Taking the emission temperature as input, and generating a thrust-time curve at the emission temperature by adopting a thrust-temperature self-adaptive modeling method based on the thrust-time curves of the engine at a plurality of reference temperatures; S3 six-degree-of-freedom dynamics modeling Based on rocket external ballistics theory, establishing a six-degree-of-freedom external ballistics dynamics model which is coupled with a mass center translation equation set and a rotation equation set around the mass center; s4, solving numerical integration of trajectory Taking the three-dimensional gas image field generated in the step S1 and the thrust-time curve generated in the step S2 as external inputs, substituting the external inputs into the dynamics model established in the step S3, and performing numerical integration on the dynamics equation in the time dimension to obtain a complete trajectory; S5, outputting and applying results And outputting a ballistic trajectory simulation result for operation planning, effect evaluation and safety management.
2. The method for predicting the trajectory of a rainadded hail-suppression rocket projectile fused with a three-dimensional weather field according to claim 1, wherein in the step S1, the specific processing procedure is as follows: S11, acquiring original wind speed and wind direction data of each height layer, decomposing a wind direction angle into an east-west component U and a north-south component V, and respectively carrying out linear interpolation on U, V two components, temperature and air pressure on the vertical height to acquire a data sequence of the middle height layer; S12, restoring the intermediate height layer U, V components obtained by interpolation into wind speed and wind direction by vector synthesis, and performing polynomial smoothing on all interpolation sequences including wind speed, wind direction, temperature and air pressure; And S13, finally generating a three-dimensional gas image field with physical continuity and smoothness.
3. The method for predicting the trajectory of a rainadded hail-suppression rocket projectile fused with a three-dimensional weather field according to claim 1, wherein in the step S2, the specific processing procedure of the thrust-temperature adaptive modeling method is as follows: S21 time axis normalization Selecting a plurality of thrust-time curves actually measured at a reference temperature, uniformly scaling and resampling the time axes of the thrust-time curves to a standardized time axis; s22, temperature dimension interpolation Performing piecewise linear interpolation on thrust values of a plurality of reference curves by taking temperature as a variable at each time point of a standardized time axis, so as to obtain thrust values corresponding to the standard time points at the transmitting temperature; s23, time axis reverse scaling And (3) reversely scaling the standardized time axis according to the estimated combustion duration of the engine at the emission temperature, recovering to the actual physical time, and finally generating a thrust-time curve at the emission temperature.
4. The method for predicting the trajectory of a rainadded hail-suppression rocket projectile fused with a three-dimensional weather field according to claim 1, wherein in the step S3, the specific processing procedure is as follows: and S31, before the parachute is unfolded, the rocket projectile is regarded as a variable-mass rigid body, the motion of the rocket projectile is jointly described by a mass center translation equation set and a mass center rotation equation set, and the corresponding mass center motion equation is expressed as follows in a trajectory coordinate system: ; ; ; Wherein, the The mass center speed of the rocket projectile; and (3) with Respectively describing the direction of a velocity vector in a horizontal plane and the included angle of the velocity vector and the horizontal plane, wherein the direction is a trajectory yaw angle and a trajectory dip angle; the position coordinates of the rocket projectile mass center in the geodetic coordinate system; To include thrust, resistance And the projection of the combined force of the gravity components on the three axes of the ballistic coordinate system; Is the instantaneous mass of the rocket projectile; In order to achieve the atmospheric density, the air is compressed, Is a reference area, changes along with the state of opening the umbrella, As a coefficient of resistance (f) of the material, Is a wind speed vector; s32, rotating equation around mass center in spring axis coordinate system ) The euler kinetic equation set describing the angular movement of the projectile and the attitude kinematics equation are as follows: ; Wherein, the The component of the angular velocity of the projectile body on the triaxial of the projectile axis coordinate system; and (3) with Polar moment of inertia and equatorial moment of inertia of the projectile body respectively; is the component of the external moment on the corresponding shaft; , , respectively yaw, pitch and roll attitude angles of the projectile body; S33, introducing pre-launch angle correction based on actual measurement wind field in the initial stage of simulation according to the target shooting azimuth angle aiming at systematic deviation of the low-layer wind field to the uncontrolled rocket trajectory Calculating the relative included angle between the wind vector and the emitted light . Decomposing wind vectors into longitudinal wind components along the firing plane And cross wind component perpendicular to the firing plane And according to the longitudinal wind coefficient Coefficient of crosswind Calculating correction of pitch angle and yaw angle And (3) with The calculation formula is as follows: ; ; Final binding emission angle is The pre-suppression of the wind-induced deviation is realized; s34, after the rocket projectile is opened, the dynamic characteristics are suddenly changed, the model is switched into a high-damping particle model, at the moment, the air resistance becomes a dominant factor, and a first-order inertia link which changes along with time is introduced to describe the effective resistance area for simulating the dynamic process of inflation and deployment of the canopy Is a law of variation of: ; Wherein, the For the projected area of the fully inflated canopy, Is the inflation time constant.
5. The method for predicting the trajectory of a hybrid three-dimensional gas-image-field hail-suppressing rocket projectile as recited in claim 4 wherein in said step S3, the six-degree-of-freedom external ballistic dynamics model divides the rocket projectile' S flight process into at least four phases, phase 1 is the active phase, and the mass is assumed to be consumed due to continuous and uniform combustion of the propellant, following the formula , The method is characterized in that the method is used for controlling the loss rate of the propellant, the stage 2 is a free-running stage, the fuel is exhausted, the thrust is 0, the stage 3 is a catalyst throwing stage, and the catalyst is uniformly scattered, so that the requirements are met , The stage 4 is an parachute opening falling stage, a rocket projectile safe landing system is started, and the rocket projectile drifts along with wind to fall to the ground.
6. The method for predicting the trajectory of a rainadded hail suppression rocket projectile fused with a three-dimensional weather field according to claim 1, wherein in the step S4, the numerical integration of the kinetic equation is performed by adopting an RK4 method and setting a time step, and the formula is as follows: ; ; Wherein, the The time step that is the numerical integration, For the current moment State vectors of (2); To the point of Representing the rate of change of state at different predicted points during the current time step.
7. The method for predicting the trajectory of a raindrop hail-suppression rocket projectile fused with a three-dimensional weather field according to claim 1, wherein in the step S5, the trajectory simulation result includes time, three-dimensional position, velocity vector, attitude angle, engine thrust, aerodynamic force, gravity, air density and trajectory graph data for visualization.
8. The method for predicting the trajectory of a rainadded hail suppression rocket in combination with a three-dimensional weather field according to claim 1, further comprising the steps of: s6, model verification and parameter calibration Comparing the trajectory track output in the step S4 with the actually measured track, and pertinently modifying the longitudinal wind coefficient according to the errors of simulation and actual measurement Coefficient of crosswind Coefficient of resistance To optimize model performance.
9. A raining hail suppression rocket projectile trajectory prediction system integrated with a three-dimensional weather field, which is applied to the method as claimed in any one of claims 1 to 8, and comprises the following steps: The gas image field construction module is used for constructing a three-dimensional gas image field which continuously changes along with the height through interpolation and smoothing treatment according to discrete meteorological data acquired by the exploration equipment; The thrust-temperature modeling module is used for taking the emission temperature as input, and generating a thrust-time curve at the emission temperature by adopting a thrust-temperature self-adaptive modeling method based on engine thrust-time curves at a plurality of reference temperatures; the dynamics modeling module is used for establishing a six-degree-of-freedom external ballistic dynamics model which is coupled with the mass center translation equation set and the mass center rotation equation set based on the rocket external ballistics theory; the trajectory solving module is used for taking the three-dimensional gas image field generated in the step S1 and the thrust-time curve generated in the step S2 as external inputs, substituting the external inputs into the dynamics model established in the step S3, and carrying out numerical integration on the dynamics equation in the time dimension so as to obtain a complete trajectory; And the output and application module is used for outputting a ballistic trajectory simulation result and is used for job planning, effect evaluation and safety management.

Description

Rain-enhancing hail-suppression rocket projectile trajectory prediction method and system integrating three-dimensional meteorological fields Technical Field The invention relates to the technical field of weather modification, in particular to a method for predicting a raining hail-suppression rocket projectile trajectory by fusing a three-dimensional weather field. Background The weather modification is a comprehensive project for achieving the purposes of increasing precipitation, relieving hail disasters and the like by changing local meteorological conditions. The rain-increasing hail-suppression rocket projectile is used as common operation equipment, and the flying track after being launched is directly related to the space position and the operation safety range of the sowing area. In precipitation or hail suppression operations, operators typically choose the firing elevation and azimuth based on ground and high-altitude weather conditions to cause the rocket projectile to spread catalyst in the target cloud. However, due to complex wind fields, air temperature distribution and aerodynamic characteristics of the projectile, the actual flight trajectory often deviates significantly from the ideal trajectory, resulting in failure of the catalyst to release in the predetermined cloud zone, affecting the working efficiency and possibly even creating a safety risk. The existing rocket projectile trajectory prediction method is mostly based on a simplified two-dimensional or three-degree-of-freedom external trajectory model, only considers the air resistance and gravity influence in the vertical direction, and ignores factors such as complex wind fields, atmospheric density, crosswind interference and the like. The model has high calculation speed, but has lower prediction precision, and can not accurately reflect the space motion state of the rocket projectile in the real atmospheric environment. Meanwhile, meteorological data is mainly discrete height data output by a sonde or a numerical forecasting mode, and discontinuity and numerical instability of track simulation can be caused by directly using the discrete data. In addition, the thrust curves of rocket engines are obviously different at different launching temperatures. The traditional method generally adopts an experimental curve or an empirical correction coefficient at a single temperature to approximate, and is difficult to accurately describe the thrust change rule at different environment temperatures, so that the accuracy of track simulation is further reduced. Therefore, a high-precision track prediction method capable of realizing the dynamic simulation of the whole process from the launching, sowing and parachute opening of the precipitation-enhanced/hail-suppressing rocket projectile based on actual meteorological data and fusion of the thrust temperature characteristics of the engine and considering the coupling effect of the full three-dimensional wind field and the aerodynamic force is needed, and a scientific decision basis and a safety evaluation means are provided for the artificial influence on the weather operation. Disclosure of Invention The invention aims to solve the technical problems of discrete meteorological data, lack of temperature adaptability of a thrust model, oversimplification of aerodynamic modeling, lack of full-flow simulation and actual measurement verification and the like in the conventional artificial precipitation hail suppression rocket projectile trajectory prediction, and provides a precipitation hail suppression rocket projectile trajectory prediction method integrating a three-dimensional weather field. The invention solves the technical problems through the following technical proposal, and the invention comprises the following steps: S1, three-dimensional gas image field construction Constructing a three-dimensional meteorological field which continuously changes along with the height through interpolation and smoothing according to discrete meteorological data acquired by a sounding device; S2, thrust-temperature self-adaptive modeling Taking the emission temperature as input, and generating a thrust-time curve at the emission temperature by adopting a thrust-temperature self-adaptive modeling method based on the thrust-time curves of the engine at a plurality of reference temperatures; S3 six-degree-of-freedom dynamics modeling Based on rocket external ballistics theory, establishing a six-degree-of-freedom external ballistics dynamics model which is coupled with a mass center translation equation set and a rotation equation set around the mass center; s4, solving numerical integration of trajectory Taking the three-dimensional gas image field generated in the step S1 and the thrust-time curve generated in the step S2 as external inputs, substituting the external inputs into the dynamics model established in the step S3, and performing numerical integration on the dynamics equation in the time d