Mortise and tenon type machine frame used for liquid rocket engine

Abstract

The invention discloses a mortise and tenon type machine frame used for a liquid rocket engine. The mortise and tenon type machine frame used for the liquid rocket engine comprises a cross-shaped beam, force bearing beams and cross beams, mortise and tenon plugs are arranged at four ends of the cross-shaped beam; the number of the force bearing beams is four, the lower ends of the force bearing beams are provided with mortise and tenon sockets which are inserted into the mortise and tenon plugs, the upper ends of the force bearing beams are provided with two mortise and tenon insertion grooves; and the number of the cross beams is four, the cross beams are arranged between every two adjacent force bearing beams, and the two ends of each cross beam are each provided with a mortise and tenon insertion piece inserted into the corresponding mortise and tenon insertion groove. The four force bearing beams are inserted and fixed to the four ends of the cross-shaped beam respectively through insertion of the mortise and tenon plugs and the mortise and tenon sockets, the four cross beams are inserted and fixed between every two adjacent force bearing beams respectively through insertion of the mortise and tenon insertion pieces and the mortise and tenon insertion grooves, and therefore assembly of the cross-shaped beam, the force bearing beams and the cross beams is achieved, and the whole machine frame is formed, the welding steps are reduced, the deformation of the machine frame is small, the machining quality is improved, meanwhile, stress concentration does not occur, and the reliability of the machine frame in the using process can be improved.

Description

technical field [0001] The invention belongs to the technical field of rocket engine racks, in particular to a mortise and tenon rack for liquid rocket engines. Background technique [0002] As an important force transmission mechanism, the rocket engine rack is generally composed of various beams. The structural design should meet the requirements of compact geometric size, lightest structural mass, uniform stress distribution and sufficient structural rigidity. Under constraints, the axial and radial stiffness of the rocket and the fulcrum stiffness of the servo actuator are guaranteed to the maximum extent. [0003] In the prior art, the frame of the rocket engine is generally a truss structure or a truss structure. The truss structure or truss structure is manufactured through welding operations. The size of the frame is relatively large, and large positioning tooling is required during welding, and the load-bearing beams and connections during the welding process The b...

AI Technical Summary

Problems solved by technology

[0003] In the prior art, the rocket engine frame is generally a truss structure or a truss structure. The truss structure or truss structure is manufactured through welding operations. The size of the frame is relatively large, and large positioning tooling is required during welding, and the load-bearing beams and connections during the welding process The beams of the load-bearing beams will have a large deformation, which requires very high welding skills of the welders. Due to the different welding skills of the welders, the quality of the welding is difficult to guarantee; and the welding joints are easy to cause Stress concentration, lower bearing capacity, lower fatigue strength

Images