On-orbit assembling method for manned spacecraft with sub cabin sections

Abstract

The invention relates to an on-orbit assembling method for a manned spacecraft with sub cabin sections. The on-orbit assembling method comprises the steps that (a), the assembling stages of the spacecraft are divided, and the combined body configuration in the assembling process is determined; (b), the basic configurations of all the cabin sections of the spacecraft are determined; (c), accordingto the long-term flying requirement of a combined body, the rendezvous and docking orbit heights of all the cabin sections are determined; (d), the function and index of an assembling auxiliary mechanism are determined; (e), the control scheme of all the cabin sections in the on-orbit assembling process is determined; and (f), the work process of on-orbit assembling of the manned spacecraft with the sub cabin sections is determined. According to the on-orbit assembling method, the on-orbit assembling risk of the spacecraft can be effectively reduced, and the reliability of the assembling process is improved.

Description

technical field [0001] The invention relates to the technical field of overall design of a manned spacecraft, in particular to an on-orbit assembly method of a subdivided manned spacecraft. Background technique [0002] Spacecraft on-orbit assembly technology is a technology that connects different components in space to build a space facility such as a structure, subsystem, and subsystem unit, or separates one or more structures for reassembly. It includes on-orbit connection, replacement, construction, combination and reorganization of spacecraft, space systems or space structures, as small as module replacement, installation and deployment of battery arrays, antennas, etc., as large as on-orbit docking of large independent modules, and more The construction of large-scale large-scale spatial structures. The transfer of docked modules is an important task for the on-orbit assembly and expansion of large manned spacecraft. Each module has the characteristics of large inert...

AI Technical Summary

Problems solved by technology

[0005] 1. Each passive docking interface needs to be equipped with rendezvous and docking sensors, and the layout is difficult

Too many rendezvous and docking sensors will not only increase the weight of the system, but may also cause the solution to fail due to insufficient installation area

[0006] 2. The configuration is single and cannot be changed

Since the space station has to operate in orbit for many years, long-term flight and application requirements put forward configuration requirements, and the simple rendezvous and docking combination cannot take into account

[0007] 3. The dynamics problem is complex

The rendezvous and docking assembly method needs to meet the requirements of docking parallel or perpendicular to the flight direction, and the direction of the impact load on the flexible parts of the assembly is different. Especially, the docking impact in the vertical flight direction does not pass through the center of mass of the assembly, and the dynamics of the docking process are complicated.

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