A Design Method for Thermal Load Release of Bolted Connections

Abstract

The invention discloses a heat load release design method for a bolt connection, which is a heat load release design method for a hypersonic aircraft bolt connection with metal as the main structural material. Use countersunk head screws and self-locking nuts with double lugs to fix the aircraft hatch and fuselage and realize thermal load release. The bolts described above are used to connect two thermally deformed mismatched structural parts of the hypersonic vehicle, and the method realizes the design by determining the minimum clearance meeting the thermal load release condition; The fixed structure is recorded as the gap between structure one and the bolt. The present invention can realize simple and effective release of extreme loads in all directions of bolted joints caused by thermal stress without changing the main structural scheme of the aircraft, increase the bearing capacity of the structural connection of the all-metal hypersonic aircraft, and reduce the structural design and processing costs of the aircraft .

Description

technical field [0001] The invention relates to a bolt connection thermal load release method for a hypersonic vehicle with metal as the main structural material, and belongs to the field of aerospace vehicle structure design. Background technique [0002] In order to reduce costs, the fuselage of the aircraft for hypersonic flight tests is generally designed and processed with all-metal design, such as structural steel, stainless steel, and high-temperature alloys that still have high performance at relatively high temperatures. The bottom of the aircraft fuselage is mostly designed or processed in one piece, and the upper part is opened for equipment installation, debugging and maintenance. The hatch cover is generally connected with the fuselage by bolts. [0003] For hypersonic vehicles that generally use metal as the main structural material, the metal also acts as a heat sink. The thickness of the shell is generally large, and the structural strength far exceeds the r...

AI Technical Summary

Problems solved by technology

However, due to the small number of connection points and small size of the connection between the hatch cover and the fuselage, there is a deformation coordination problem, and the load on the bolts may be very large. Some parts are difficult to solve by increasing the size or number of bolts, and it has become a metal processing aircraft. technical bottleneck

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