CN-121997546-A - Kinetic energy impact asteroid orbit deflection efficiency improving method and trajectory calculation system by utilizing final stage passivation effect

CN121997546ACN 121997546 ACN121997546 ACN 121997546ACN-121997546-A

Abstract

The application provides a kinetic energy impact asteroid orbit deflection efficiency improving method and a track computing system by utilizing a final stage passivation effect, wherein the method comprises the steps that after an impact device is launched by a carrier rocket, the final stage is not separated from the impact device, and an assembly body enters a preset orbit to impact asteroid; and finally, performing passivation treatment, and improving the speed of the assembly by utilizing thrust generated by passivation. The method comprises the steps of utilizing a Lanbert problem to solve an orbit parameter of an earth departure of a combination body and an orbit parameter of an impact moment, utilizing an gravitation escape model to solve an orbit departure parameter of a berth, utilizing an earth high-precision dynamics model to obtain an orbit parameter of the combination body at an earth-impact ball boundary, utilizing a solar system high-precision orbit dynamics model to solve the orbit parameter of the combination body before impact and the orbit parameter of an asteroid before the impact moment, utilizing the earth high-precision dynamics model and a deflection distance calculation model to solve a asteroid near-place parameter, and calculating a deflection distance. The method effectively improves the asteroid defense efficiency.

Inventors

Wang Kaiduo
LI MINGTAO
WANG YOULIANG
ZHENG JIANHUA
LI ZHONGYUAN
WANG JIANMING

Assignees

中国科学院国家空间科学中心
北京宇航系统工程研究所

Dates

Publication Date: 20260508
Application Date: 20251222

Claims (6)

1. A kinetic energy impact asteroid orbit deflection efficiency enhancing method utilizing a final stage passivation effect, comprising: the final stage is not separated from the impacter after the impacter is launched by a carrier rocket, and the combination body formed by the final stage and the impacter enters a preset orbit to impact the asteroid; the track calculation process of the combination body comprises the following steps: Obtaining the positions of the earth and the asteroid at two moments according to the earth departure time and the asteroid collision time, and solving the orbit parameters of the earth departure and the orbit parameters of the collision moment of the combined body as the input of the Lanbert problem; The orbit parameter of the combination body at the boundary of the earth influence sphere is obtained by recursively pushing the orbit to the boundary of the earth influence sphere by using the high-precision dynamics model of the earth which considers passivation, and finally, the orbit parameter of the combination body before collision is solved by recursively pushing the orbit to the collision moment of the asteroid by using the two-body model or the solar system high-precision orbit dynamics model; The method comprises the steps of utilizing an initial epoch of the asteroid and the impact time of the asteroid, recursively estimating an orbit of the asteroid through a solar system high-precision orbit dynamics model, solving orbit parameters of the asteroid before the impact time, then combining orbit parameters of a combination before the impact, solving orbit parameters of the asteroid after the impact through a deflection distance calculation model, and finally searching a near-place of the asteroid and solving a geocentric distance through the solar system high-precision dynamics model and the deflection distance calculation model, and calculating the deflection distance.
2. The method for improving the deflection efficiency of a kinetic energy impact asteroid orbit using a final passivation effect according to claim 1, wherein the gravitational escape model comprises: Solving the lambert problem to obtain the combined body earth escape velocity Calculating the right ascent point Declination of weft : ; ; Under the geocentric inertial system, declination is the included angle between the escape velocity vector and the x-o-y plane, and the declination is the included angle between the projection of the escape velocity vector on the x-o-y plane and the x axis; 、 And Representing projections of escape velocities on x, y and z axes, respectively; determination of the unit direction vector of the hyperbolic asymptote in the B plane : ; The unit vector in oz direction is The superscript T indicates the vector transposition, and the unit vectors of the other two coordinate axis directions of the B plane are expressed as: ; ; Included angle of B plane From declination and track inclination The calculation results are that: ; ; unit angular momentum of hyperbola The method comprises the following steps: ; unit vector of near-to-ground position and speed of hyperbolic track And Calculated from the following formula: ; ; Wherein, the For a true near point angle when the velocity goes to infinity, The sine and cosine of the constant are calculated by the following formula: ; ; The position and speed vector at the near-place is calculated by a unit vector: ; ; Wherein, the And Respectively representing the near-place position and the speed of the hyperbolic track; And Scalar quantities representing the near-to-the-spot position and velocity of the hyperbolic track, respectively.
3. The method for improving the deflection efficiency of the orbit of the asteroid by utilizing the kinetic energy impact of the final passivation effect according to claim 1, wherein the high-precision kinetic model of the earth comprises: ; Wherein the method comprises the steps of A vector of the position of the center of the sun of the assembly; 、、 The earth, sun and moon gravitational constants, respectively; is the geocentric position vector of the sun; a geocentric position vector that is moon; A position vector representing the sun-to-assembly; a position vector representing moon to combination; 、 And Acceleration due to earth J2 perturbation, atmospheric drag, and passivation, respectively.
4. The method for improving the deflection efficiency of the kinetic energy impact asteroid orbit by utilizing the final passivation effect according to claim 1, wherein the solar system high-precision orbit dynamics model comprises the following steps: ; in the formula, A sun position vector that is a combination or asteroid; The gravitational constant of the ith planet; Is the first A sun center position vector of the planet; A position vector representing the i-th planet to the combination or asteroid; from 1 to 9 represent, respectively, water star, gold star, earth, mars, wood star, earth star, heaven star, sea star and meditation star; And Acceleration due to lunar attraction and relativistic effects, respectively.
5. The method for improving the deflection efficiency of the kinetic energy impact asteroid orbit by utilizing the final passivation effect according to claim 1, wherein the deflection distance calculation model comprises the following steps: Solving for the velocity of an asteroid after impact using a momentum transfer formula : ; Wherein, the Indicating the time after impact; indicating the moment of impact; And Representing asteroid mass and impact relative velocity; representing momentum transfer factors; Representing the mass of the assembly at the moment of impact; The post-impact asteroid position is the same as the pre-impact asteroid position, the post-impact asteroid position speed is used as the initial position speed, the solar system high-precision model is utilized for track recursion, and the near-earth moment is searched for and the near-earth distance is calculated The formula of (2) is as follows: ; Wherein, the And The positions of the asteroid and the earth near-site moment are respectively; representing the modulus of the vector.
6. A kinetic energy impact asteroid orbit deflection efficiency improvement trajectory calculation system utilizing a final stage passivation effect, realized based on the method of any one of claims 1-5, characterized in that the system comprises: The device comprises an earth departure orbit parameter module, an impact moment orbit parameter module, a primary orbit module, a secondary orbit module, a primary orbit module and a secondary orbit module, wherein the earth departure orbit parameter module is used for setting the earth departure time, the impact asteroid time and the primary epoch of the asteroid; The orbit parameter module is used for solving the orbit parameter of the combination body at the berthing orbit when the earth escapes, taking the orbit parameter of the combination body at the berthing orbit as an initial value, and solving the orbit parameter of the combination body at the berthing orbit by utilizing an gravitation escape model to obtain the orbit parameter of the combination body at the berthing orbit when the earth escapes; The orbit parameter module is used for recursively pushing the orbit to the boundary of the earth influence sphere by using the high-precision orbit dynamics model of the earth which is considered to be passivated, acquiring the orbit parameters of the assembly at the boundary of the earth influence sphere, recursively pushing the orbit parameters to the time of minor planet collision by using the two-body model or the solar system high-precision orbit dynamics model, and solving the orbit parameters of the assembly before collision; The orbit parameter module is used for solving the orbit parameters of the asteroid before the impact moment by utilizing the initial epoch of the asteroid and the impact time of the asteroid and recursively estimating the orbit of the asteroid by utilizing a solar system high-precision orbit dynamics model; A module for solving the parameters of the minor planet orbit after the impact, which is used for solving the parameters of the minor planet orbit after the impact by utilizing a deflection distance calculation model in combination with the parameters of the orbit of the combination before the impact, and And the deflection distance calculating module is used for searching the asteroid near-place by utilizing the solar system high-precision dynamics model and the deflection distance calculating model, calculating the ground center distance and further calculating the deflection distance.

Description

Kinetic energy impact asteroid orbit deflection efficiency improving method and trajectory calculation system by utilizing final stage passivation effect Technical Field The application belongs to the field of asteroid defense and aerospace, and particularly relates to a method for improving the deflection efficiency of a kinetic energy impact asteroid orbit by utilizing a final stage passivation effect and a track computing system. Background Kinetic energy impact is known as the most feasible and highest-maturity planetary defense on-orbit treatment technical means in the prior art. In 2022, the U.S. completes the task of "double asteroid redirection test", a technical test of kinetic energy impact defense asteroid is carried out in space for the first time, the revolution period of the Di Morse double asteroid system is successfully shortened by 33 minutes, and the Di Morse double asteroid system is evaluated as one of ten scientific breakthroughs in the 2022 world by Science journal. While the "double asteroid redirection test" task test was highly successful, the test was only about 2.7 mm/s for a 160 meter diameter Di Mo Fusi asteroid orbital speed change. With this speed increase, about 25 years are required to deflect the asteroid orbit out of a safe distance of one earth radius. It can be seen that even the most practical kinetic energy impact technique at present is still unable to effectively deflect the orbit of the near-earth asteroid with a diameter greater than 140 meters under the condition of short mid-term early warning time. Therefore, the existing kinetic energy impact technology is limited by carrying capacity, impact quality is difficult to effectively improve, and the track deflection capacity of the existing kinetic energy impact technology is still obviously insufficient when the early warning time is limited and the target size is large. Disclosure of Invention The application aims to overcome the defect that the prior art cannot effectively deflect the orbit of the near-earth asteroid with the diameter larger than 140 meters under the condition of short and medium-term early warning time. In order to achieve the above object, the present application provides a method for improving the deflection efficiency of a kinetic energy impact asteroid orbit by using a final passivation effect, comprising: the final stage is not separated from the impacter after the impacter is launched by a carrier rocket, and the combination body formed by the final stage and the impacter enters a preset orbit to impact the asteroid; the track calculation process of the combination body comprises the following steps: Obtaining the positions of the earth and the asteroid at two moments according to the earth departure time and the asteroid collision time, and solving the orbit parameters of the earth departure and the orbit parameters of the collision moment of the combined body as the input of the Lanbert problem; The orbit parameter of the combination body at the boundary of the earth influence sphere is obtained by recursively pushing the orbit to the boundary of the earth influence sphere by using the high-precision dynamics model of the earth which considers passivation, and finally, the orbit parameter of the combination body before collision is solved by recursively pushing the orbit to the collision moment of the asteroid by using the two-body model or the solar system high-precision orbit dynamics model; The method comprises the steps of utilizing an initial epoch of the asteroid and the impact time of the asteroid, utilizing a solar system high-precision orbit dynamics model to recursively estimate the orbit of the asteroid, solving the orbit parameters of the asteroid before the impact time, then combining the orbit parameters of the combination before the impact, utilizing a deflection distance calculation model to solve the orbit parameters of the asteroid after the impact, and finally utilizing an earth high-precision dynamics model and a deflection distance calculation model to search the near-place of the asteroid and calculate the earth center distance, and further calculating the deflection distance. As a further introduction to the above method, the gravitational escape model includes: Solving the lambert problem to obtain the combined body earth escape velocity Calculating the right ascent pointDeclination of weft: ; ; Under the geocentric inertial system, declination is the included angle between the escape velocity vector and the x-o-y plane, and the declination is the included angle between the projection of the escape velocity vector on the x-o-y plane and the x axis;、 And Representing projections of escape velocities on x, y and z axes, respectively; determination of the unit direction vector of the hyperbolic asymptote in the B plane : ; The unit vector in oz direction isThe superscript T denotes a vector transpose, and the unit vectors of the other two coordinate axes of the B pla