An Improved Optimal Capacity Ratio Design Method for WSB/HPS System Based on Complementary Characteristics of Wind and Solar

2016 ◽  
pp. 219-242
Keyword(s):  
Design Method ◽  
Capacity Ratio ◽  
Optimal Capacity

scholarly journals An Improved Optimal Capacity Ratio Design Method for WSB/HPS System Based on Complementary Characteristics of Wind and Solar

2015 ◽  
Vol 2015 ◽  
pp. 1-8
Author(s):  
Xiaoju Yin ◽  
Fengge Zhang ◽  
Zhenhe Ju ◽  
Yonggang Jiao
Keyword(s):  
Power Generation ◽  
Energy Storage ◽  
Solar Power ◽  
Design Method ◽  
Experimental Result ◽  
Generation System ◽  
Solar Power Generation ◽  
Capacity Ratio ◽  
Optimal Capacity ◽  
Power Generation System

The reliability and economic value of wind and solar power generation system with energy storage are decided by the balance of capacity distribution. The improved capacity balance matching method is proposed in this paper, which not only utilizes the complementary characteristics of the wind and solar power generation system sufficiently but also reduces the charge and discharge times of the battery. Therefore, the generation reliability is improved and the working lifetime of the whole system is lengthened. Consequently, the investment of the battery energy storage is reduced as well as the whole cost is decreased. The experimental result was presented to verify the effectiveness of the improved optimal capacity ratio design method.

scholarly journals New Contour Design Method for Rocket Nozzle of Large Area Ratio

2019 ◽  
Vol 2019 ◽  
pp. 1-8
Author(s):  
Dechuan Sun ◽  
Tianyou Luo ◽  
Qiang Feng
Keyword(s):  
Design Method ◽  
Rocket Engine ◽  
Specific Impulse ◽  
Area Ratio ◽  
Large Area ◽  
Simple Modification ◽  
Capacity Ratio ◽  
Nozzle Contour ◽  
Expansion Angle ◽  
Calculation Results

A rocket engine for space propulsion usually has a nozzle of a large exit area ratio. The nozzle efficiency is greatly affected by the nozzle contour. This paper analysed the effect of the constant capacity ratio in Rao’s method through the design process of an apogee engine. The calculation results show that increasing the heat capacity ratio can produce an expansion contour of smaller expansion angle and exit area ratio. A simple modification of Rao’s method based on thermally perfect gas assumption was made and verified to be more effective. The expansion contour designed by this method has much thinner expansion section and higher performance. For the space engine, a new extension contour type for the end section of the nozzle is proposed. The extension curve bent outward with increasing expansion angle increases the vacuum specific impulse obviously.

Application of a work-centered design method to support counterspace operations

2005 ◽  
Author(s):  
Michael Szczepkowski ◽  
Kelly Neville ◽  
Ed Popp
Keyword(s):  
Design Method
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