Effective load space cabin structure applicable to orbiter

Abstract

The invention discloses an effective load space cabin structure applicable to an orbiter, comprising a cabin body and cabin doors; the cabin doors are connected to the cabin body; the cabin doors can open and close the cabin body; the cabin doors are two symmetrical opposite-opening structures, and every cabin door comprises an inner skin, an outer skin, main force bearing beams, honeycomb cores, a reinforcing rib and a heat protecting structure; the honeycomb cores are located between the inner skin and the outer skin; a guide flow slot is arranged on a contact position of the honeycomb cores and the outer skin, the reinforcing rib is arranged between the honeycomb cores, and connected to the main force bearing beams; three cabin door locks are evenly distributed on the main force bearing beams, the two cabin doors are locked to each other in the process of closing; the thermal protecting structure is arranged on the outer skin, and arranged in a staggering manner; the vapor return absorption of the surface of the thermal protecting structure under the natural environment is not more than 0.15%, thus the effective load cabin door structure is high in structural rigidity, good in structure compatibility and sealing property; meanwhile, the effective load space cabin structure can meet integration and lightweight requirements at the same time.

Description

technical field [0001] The invention relates to a payload space cabin structure suitable for an orbiter, in particular to a space capsule structure with a large-size payload cabin door, and belongs to the field of aircraft structure design. Background technique [0002] The orbiter is a weapon platform with comprehensive combat capabilities that can stay in orbit for a long time, go back and forth between space and space, and maneuver to change orbits. The payload compartment is the equipment container for the aircraft to perform space missions, and is a key component to protect the safety of the payload during launch and recovery. It needs to adapt to the different working conditions of the three stages of aircraft entry, orbital maneuvering and re-entry and return. The payload compartment is located in the middle compartment of the aircraft, and is repeatedly unfolded, retracted and locked through the hatch mechanism. According to the mission profile requirements of the a...

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Problems solved by technology

In addition, the payload door is required to be able to expand and retract in space multiple times, and to withstand the flight environment during reentry and return. Therefore, the structural design of the payload door also needs to consider space requirements, compatibility with surrounding structures, and strict Strict heat sealing requirements are a typical optimal design problem under multiple constraints. Without effective, fast and feasible design methods and technologies, it is impossible to realize the optimal design of the scheme and satisfy the use of the orbiter's payload hatch system. Require

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