A spacecraft fragment meteorite landing area forecasting method

Abstract

A spacecraft fragment meteorite landing area forecasting method comprises the following steps of establishing a basic pneumatic database according to a current spacecraft to be processed or fragment,wherein the basic pneumatic database comprises a basic static pneumatic database and a basic dynamic pneumatic database; storing aerodynamic force and torque data corresponding to the flight conditions in a basic static pneumatic database; storing pneumatic derivative data corresponding to the flight conditions in a basic dynamic pneumatic database; obtaining the real-time aerodynamic force data through interpolation from the basic static aerodynamic database, obtaining the aerodynamic derivative data of corresponding conditions through interpolation from the basic dynamic aerodynamic database, and obtaining the real-time stress data of the spacecraft or the fragments through calculation; and performing six-degree-of-freedom trajectory simulation according to the determined real-time stress data of the spacecraft / fragment, determining the meteorite trajectory of the spacecraft or fragment, and further determining the meteorite region of the spacecraft or fragment.

Description

technical field [0001] The invention relates to a method for predicting the fall area of ​​spacecraft fragments. Background technique [0002] Space launch activities will generate a large number of relatively large space debris when sending the spacecraft into the predetermined orbit, such as empty fuel tanks, fairings, separation devices, spacecraft bodies, boosters, etc. These spacecraft will re-enter the atmosphere. During the re-entry process, they will flow through the free molecular flow region, transition flow region, slip flow region and continuous flow region. During the high-speed and high-temperature reentry process, the air will undergo real gas effects such as vibration, dissociation, ionization, and recombination. The huge energy will cause ablation, explosion, and disintegration of the spacecraft. Part of the debris from the disintegration of the spacecraft will be ablated during reentry, and the rest will hit the ground. These fragments fall into the groun...

AI Technical Summary

Problems solved by technology

This method is efficient, but due to the accuracy of the model, and the usual aerodynamic model is based on static aerodynamic data, the influence of dynamic factors on aerodynamic characteristics is not considered, so the usual aerodynamic model may cause certain errors

Due to the large time / space scale calculations required during the falling of debris, errors will continue to accumulate during this process, resulting in a large deviation between the falling point and the actual situation

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