A monopulse guidance method, readable medium for autonomous rapid rendezvous and docking

Abstract

The invention relates to a single-pulse guidance method for autonomous fast rendezvous and docking and a readable medium. The method comprises the following steps of acquiring orbit parameters of a tracking spacecraft and orbit parameters of a target spacecraft; computing parameter deviations between the orbit parameters of the spacecraft and the orbit parameters of the target spacecraft accordingto the orbit parameters of the tracking spacecraft and the orbit parameters of the target spacecraft; computing a characteristic point latitude angle for orbital transfer of the tracking spacecraft according to the parameter deviations; acquiring a reference value of the characteristic point latitude angle for orbital transfer, comparing a computed value of the latitude angle with the reference value, enabling the characteristic point latitude angle for orbital transfer to use the computed value when the usable range is met, and otherwise using the reference value; and computing the trace orbital transfer quantity and the radial orbital transfer quantity of the single orbital transfer of the spacecraft according to the orbit parameters of the tracking spacecraft, the orbit parameters of the target spacecraft, the deviation parameters and the characteristic point latitude angle, and applying the orbital transfer quantity to the autonomous fast rendezvous and docking.

Description

technical field [0001] The invention relates to a monopulse guidance method and a readable medium for autonomous fast rendezvous and docking, and belongs to the technical field of aerospace guidance and control. Background technique [0002] From 2011 to 2017, the SZ-8 / 9 / 10 / 11 manned spacecraft and the TZ-1 cargo spacecraft were successively launched, and successfully conducted multiple automatic and manual rendezvous and docking with the TG-1 target aircraft and the TG-2 space laboratory. A docking that lasted 2 days in each mission brought a huge workload to the ground flight controllers for status monitoring and data interpretation. At the same time, due to the long-distance rendezvous and the change of orbit to ground guidance, it was necessary to measure the orbit and calculate the guidance law on the ground. The frequent rendezvous and track change of docking also brings a huge workload to the ground personnel. In addition, during the normal operation of the space sta...

AI Technical Summary

Problems solved by technology

[0007] The problem solved by the technology of the present invention is: to overcome the defects of the prior art, aiming at the problem of rapid rendezvous and docking long-distance autonomous guidance and guidance with high precision requirements, a single-pulse guidance method for autonomous rapid rendezvous and docking is provided, which can Read media, solve the autonomous guidance problem of high-precision, high-reliability, and short-term rendezvous and docking long-distance guidance segments, and meet the autonomous and rapid requirements for rendezvous and docking technology in future rendezvous and docking missions in manned spaceflight and other fields

Images