Equations were derived for the load deflection relations, the energy dissipation per cycle, and the instantaneous rate of dissipation for a lap joint idealized as two overlapping plates clamped together under a uniform clamping pressure

Diller, S. V.

Metherell, A. F.

English

NASA Technical Reports Server

May 1969	 Brief 69-10141 
NASA TECH BRIEF	
'W 
NASA Tech Briefs are issued to summarize specific innovations derived from the U.S. space program, 
to encourage their commercial application. Copies are available to the public at 15 cents each 
from the Clearinghouse for Federal Scientific and Technical Information, Springfield, Virginia 22151., 
Mechanical Properties of a Lap Joint Under Uniform Clamping Pressure 
An understanding of the factors contributing to the 
nonlinearities in complex structures is important to 
the development of methods for more exact dynamic 
analysis of the structures. Interfacial slip phenomena 
at joints are major contributors to these nonlinear 
factors. A common type of joint found in aerospace 
structures is the lap joint. These are often fastened 
together with bolts or rivets, with the result that loads 
on the structure are transferred through the friction 
at the interface caused by the clamping action of the 
fastenings. The load is not transferred through shear 
in the fastenings until the loading applied to the lap 
is large enough to cause gross sliding over the entire 
interface. 
Equations were derived for the load/deflection 
relations, the energy dissipation per cycle, and the 
instantaneous rate of dissipation for a lap joint ideal-
ized as two overlapping plates clamped together under 
a uniform clamping pressure. The energy dissipation 
per cycle is only valid for steady-state cyclic loading,
whereas the load/deflection equations and instantane-
ous dissipation rate are valid for arbitrary loading and 
take into account the previous loading history. The 
differences between the instantaneous dissipation rate 
in a lap joint and the equivalent linear system are 
illustrated for cases of sinusoidal loading and tri-
angular loading. 
Note: 
Documentatioh is available from: 
Clearinghouse for Federal Scientific 
and Technical Information 
Springfield, Virginia 22151 
Price: $3.00 
Reference: TSP69-10141 
Patent status: 
No patent action is contemplated by NASA. 
Source: A. F. Metherell and S. V. Diller 
of McDonnell Douglas Corporation 
under contract to 
Marshall Space Flight Center 
(MFS- 14538) 
Category 05 
This document was prepared under the sponsorship of the National 
Aeronautics and Space Administration. Neither the United States 
Government nor any person acting on behalf of the United States
Government assumes any liability resulting from the use of the 
information contained in this document, or warrants that such use 
will be free from privately owned rights.
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Mechanical properties of a lap joint under uniform clamping pressure

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