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

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.

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Research on the optimal capacity ratio of single axis tracking photovoltaic power generation system

IOP Conference Series Earth and Environmental Science ◽

10.1088/1755-1315/188/1/012020 ◽

2018 ◽

Vol 188 ◽

pp. 012020

Author(s):

L Xie ◽

G F Pan ◽

H Wan

Keyword(s):

Power Generation ◽

Generation System ◽

Capacity Ratio ◽

Optimal Capacity ◽

Photovoltaic Power ◽

Power Generation System

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New Contour Design Method for Rocket Nozzle of Large Area Ratio

International Journal of Aerospace Engineering ◽

10.1155/2019/4926413 ◽

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.

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