Abstract: In a search and tracking method for full time-domain laser detection of space debris, a set of latest precision orbital parameters of a debris object and start and end moments of a current transit of the object are first obtained. Search-specific guidance data is generated based on the above information and in combination with estimation of a maximum along-track error of the orbital parameters of the object during the current transit. A DLR system performs multi-elevation search on the object based on the search-specific guidance data, obtains a plurality of pieces of detection data of the object after detecting the object during the search, determines an along-track error of the orbital parameters of the object based on the detection data, and corrects the orbital parameters of the object in real time based on the along-track error, so as to guide the DLR system to subsequently track and detect the object.

Abstract: In a search and tracking method for full time-domain laser detection of space debris, a set of latest precision orbital parameters of a debris object and start and end moments of a current transit of the object are first obtained. Search-specific guidance data is generated based on the above information and in combination with estimation of a maximum along-track error of the orbital parameters of the object during the current transit. A DLR system performs multi-elevation search on the object based on the search-specific guidance data, obtains a plurality of pieces of detection data of the object after detecting the object during the search, determines an along-track error of the orbital parameters of the object based on the detection data, and corrects the orbital parameters of the object in real time based on the along-track error, so as to guide the DLR system to subsequently track and detect the object.

Abstract: A method for constructing a free trajectory of a ballistic missile at a specified launch angle includes: setting of an initial state of iterations: based on geodetic coordinates of a launch point and a target point, a launch epoch and the specified launch angle, assuming that the earth does not rotate and a flight time is zero; generating a new flight time in a two-body force model by using known quantities and obtained auxiliary quantities; taking a difference between flight times obtained before and after the iterations as a condition for judging convergence; outputting designed parameters of the ballistic missile after the convergence is reached, or performing a differential correction including the J2 perturbation to improve the precision of the trajectory constructed, and taking a position error of the target point as a convergence condition of the differential correction.