A composite material frame of an aerospace orbit-changing engine

Abstract

The invention provides a composite rack of a spaceflight orbit maneuver engine. The composite rack comprises a cylinder body. A bottom flange and a head flange are arranged at the two ends of the cylinder body correspondingly. The plane where the bottom flange is located and the plane where the head flange is located has a dip angle. A plurality of reinforcing bars are evenly distributed on the outer wall of the cylinder body in the circumferential direction. The cylinder body, the bottom flange, the head flange and the reinforcing bars are all made of carbon fiber composites. Compared with the prior art, the composite rack of the spaceflight orbit maneuver engine has the following beneficial effects that 1 under the premise of structural envelopes with the same size, the rack has the characteristics of high mechanical load resistant capability, simple structure and low weight; and 2 the local structure of the rack has a certain variable design and can be adjusted adaptively according to the different mounting requirements and loading conditions, and thus the rack has the characteristic of wide application range.

Description

technical field [0001] The invention relates to the field of aerospace, in particular to a composite frame of an aerospace orbit-changing engine, which is used for the mounting frame of an orbit-changing engine in an aerospace propulsion system. In particular, it relates to aerospace vehicles with high requirements on mechanical loads and relatively large envelopes of the mounting frame structure of the orbit-changing engine. Background technique [0002] For the propulsion system of the space station, each orbit-changing engine is installed on the space station cabin as an independent module, and the orbit-changing engine and the space station cabin need to be connected through a rack. The rack directly affects the reliability of the connection between the engine and the cabin of the space station. [0003] For the traditional track-changing engine frame, because the engine is close to the bulkhead and the mechanical load requirements are low, the overall structural envelo...

AI Technical Summary

Problems solved by technology

But for the space station, the orbit-changing engine is far away from the bulkhead, and the mechanical load requirements are high. The traditional small envelope structure has an aluminum alloy frame with low strength and rigidity, which cannot meet the requirements of the space station.

However, the high-strength and rigid aluminum alloy frame will cause the frame structure to be complicated, and the weight is too large to exceed the weight design index.

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