A Modular Method for Manufacturing Error Analysis of Linkages and Manipulators

Author(s):  
Kwun-Lon Ting ◽  
Kuan-Lun Hsu ◽  
Long-Iong Wu ◽  
Jun Wang

This paper presents a simple and effective methodology to address the issues on the manufacturing error analysis and the tolerance design of linkages and manipulators. It assesses the effect of the dimension tolerances to the performance error and inversely determines the required dimensional tolerances for a prescribed performance tolerance. The methodology is adaptable to assess the effect of an individual tolerance as well as any combination of tolerances. Instead of using complex closed loop equations to describe the linkage geometry, the methodology is focused on using linkage topology. Complex linkages are broken down to basic RR, PR, and RP units. The error and tolerance computation of complex linkages are reduced to repeatedly or alternatively using forward and inverse analysis of basic RR, PR, and RP units. The methodology is exemplified by simple and complex linkages. For design and manufacturing engineers, the proposed method is most useful for quick tolerance allocation and performance error assessment.

Diabetes ◽  
2018 ◽  
Vol 67 (Supplement 1) ◽  
pp. 1376-P
Author(s):  
GREGORY P. FORLENZA ◽  
BRUCE BUCKINGHAM ◽  
JENNIFER SHERR ◽  
THOMAS A. PEYSER ◽  
JOON BOK LEE ◽  
...  

Diabetes ◽  
2018 ◽  
Vol 67 (Supplement 1) ◽  
pp. 207-OR
Author(s):  
BRUCE A. BUCKINGHAM ◽  
JENNIFER SHERR ◽  
GREGORY P. FORLENZA ◽  
THOMAS A. PEYSER ◽  
JOON BOK LEE ◽  
...  

Author(s):  
Yiqi Xu

This paper studies the attitude-tracking control problem of spacecraft considering on-orbit refuelling. A time-varying inertia model is developed for spacecraft on-orbit refuelling, which actually includes two processes: fuel in the transfer pipe and fuel in the tank. Based upon the inertia model, an adaptive attitude-tracking controller is derived to guarantee the stability of the resulted closed-loop system, as well as asymptotic convergence of the attitude-tracking errors, despite performing refuelling operations. Finally, numerical simulations illustrate the effectiveness and performance of the proposed control scheme.


2014 ◽  
Vol 551 ◽  
pp. 337-343
Author(s):  
Hui Chen ◽  
Yong Ling Fu ◽  
Juan Chen ◽  
He Song Liu

With the development of the advanced precision-guided missile and anti-missile system, high precision, high penetration ability and Low energy consumption have become an important direction for the missile. A new missile electro-hydraulic actuation system with dual independent closed-loop is put forward with the trend of high performance and energy-saving, and then the operating principle and process are discussed. Finally the accurate mathematical model is established, and the influence of the different basic pressure on the dynamic performance is analyzed. The simulation results show that the new proposed scheme has made great improvements in reducing the zero-control current of the system, but the efficiency and performance of the actuation system should be considered integrated due to the decrease of the dynamic performance, so it is practical for the future development of the missile electro-hydraulic actuation system.


Sign in / Sign up

Export Citation Format

Share Document