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A Design Method for Thermal Load Release of Bolted Connections

A design method and thermal load technology, applied in aircraft component testing, aircraft assembly, etc., can solve the problems of small size, large bolt load, and small number of connection points, so as to reduce design and production costs, increase bearing capacity, and reduce design. and processing cost

Active Publication Date: 2021-07-13
CHINA ACAD OF AEROSPACE AERODYNAMICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

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  • A Design Method for Thermal Load Release of Bolted Connections
  • A Design Method for Thermal Load Release of Bolted Connections
  • A Design Method for Thermal Load Release of Bolted Connections

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Embodiment Construction

[0032] The present invention will be further elaborated below in conjunction with embodiment.

[0033] The aircraft hatch cover and the fuselage are connected by lap joints. The overlapping edges 1 and 2 are reserved at the corresponding positions of the fuselage and the hatch cover, and the hatch cover and the fuselage are fixed with the countersunk head screw 3 and the self-locking nut 4 of the two-ear movable support plate. The self-locking nut 4 of the two-ear movable supporting plate comprises two parts of a supporting plate 41 and a nut 42, and the supporting plate is fixed on the overlapping edge of the fuselage using a rivet 5. The rivets are countersunk head rivets, and the rivet heads need to be repaired to ensure that there are no protrusions on the surface of the overlapping edges of the fuselage. The screw is a countersunk screw 3, which is processed by high-quality structural steel or superalloy. The nut 42 is a self-locking nut with anti-loosening capability. ...

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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...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64F5/10B64F5/60
CPCB64F5/10B64F5/60
Inventor 陈占军韩海涛任昆高阳潘宏禄
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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