Preliminary Design of a Micro-scale Solar Thermal Propulsion System

2002 ◽  
Author(s):  
Fred Kennedy ◽  
Philip Palmer
Keyword(s):  
Propulsion System ◽  
Solar Thermal ◽  
Preliminary Design ◽  
Micro Scale ◽  
Solar Thermal Propulsion

Deployable umbrella-shaped keel concentrator used in solar thermal propulsion system

2010 ◽  
Vol 22 (10) ◽  
pp. 2295-2298
Author(s):  
戴剑锋 Dai Jianfeng ◽  
赵沛 Zhao Pei ◽  
毛根旺 Mao Genwang ◽  
孙毅彬 Sun Yibin ◽  
李星 Li Xing ◽  
...  
Keyword(s):  
Propulsion System ◽  
Solar Thermal ◽  
Solar Thermal Propulsion

Flow Analysis of Solar Thermal Propulsion System

2010 ◽  
Author(s):  
Dai Jian-feng ◽  
Li Xing ◽  
Zhao Pei ◽  
Sun Yi-bin ◽  
Mu Xiao-wen ◽  
...  
Keyword(s):  
Flow Analysis ◽  
Propulsion System ◽  
Solar Thermal ◽  
Solar Thermal Propulsion

Small Satellite Solar Thermal Propulsion System Design: An Engineering Model

2014 ◽  
Author(s):  
Mookesh Dhanasar ◽  
William Edmonson ◽  
Frederick Ferguson ◽  
Isaiah M. Blankson
Keyword(s):  
System Design ◽  
Propulsion System ◽  
Solar Thermal ◽  
Small Satellite ◽  
Engineering Model ◽  
Solar Thermal Propulsion

Influence of Thermal Decomposition of Ammonia Propellant in Solar Thermal Propulsion

2014 ◽  
Vol 598 ◽  
pp. 257-264 ◽  
Author(s):  
Bao Yu Xing ◽  
Min Chao Huang ◽  
Mou Sen Cheng ◽  
Kun Liu
Keyword(s):  
Heat Exchanger ◽  
Specific Impulse ◽  
Propulsion System ◽  
Solar Thermal ◽  
Space Propulsion ◽  
Dissociation Process ◽  
Finite Rate ◽  
Potential Applications ◽  
Solar Thermal Propulsion ◽  
Chemical Reaction Method

Solar thermal propulsion is a kind of space propulsion technology with great potential applications. Due to the difficulty of hydrogen storage in orbit, ammonia becomes an ideal candidate propellant as its stability and easier storage. In solar thermal propulsion system, the working temperature is usually above 2300K, and in this condition the dissociation of ammonia will occur. Thus, using ammonia as a single component propellant to compute and analysis the performance of thruster is not precise, and the mixture components produced from ammonia dissociation must be taken into account. In this paper a novel heat exchanger configuration with platelet technology is designed, and based on finite-rate chemical reaction method and computational fluid dynamics, the dissociation process of ammonia in the heat exchanger and nozzle is simulated. Then the influence to the specific impulse of the solar thermal propulsion system is comparatively analyzed. The simulation result indicates that the main productions of the dissociation are N2and H2, and the mole fraction of other components is small value that can be neglected. The specific impulse considering dissociation reaction is higher than not considering, so that this research can estimate the performance of solar thermal propulsion with ammonia propellant more precisely.

scholarly journals On a New Type of Combined Solar–Thermal/Cold Gas Propulsion System Used for LEO Satellite’s Attitude Control

2020 ◽  
Vol 10 (20) ◽  
pp. 7197
Author(s):  
Constantin Sandu ◽  
Valentin Silivestru ◽  
Grigore Cican ◽  
Horațiu Șerbescu ◽  
Traian Tipa ◽  
...  
Keyword(s):  
Attitude Control ◽  
Propulsion System ◽  
Solar Thermal ◽  
Concave Mirror ◽  
Leo Satellites ◽  
New Type ◽  
Solar Thermal Propulsion ◽  
Leo Satellite ◽  
Service Duration ◽  
Cold Gas

This paper presents the development, construction and testing of a new type of solar–thermal propulsion system which can be used for low earth orbit (LEO) satellites. Currently, the vast majority of LEO satellites are fitted with a cold gas propulsion system. Although such a propulsion system is preferred, the service duration of an LEO satellite is limited by the amount of cold gas they carry onboard. In the case of the new type of solar–thermal propulsion system proposed in this paper, the cold gas is first transferred from the main tank in a cylindrical service tank/buffer tank which is placed in the focal line of a concave mirror. After the gas is heated by the solar light focused on the service tank by the concave mirror, it expands by opening the appropriate solenoid valve for the satellite’s attitude control. In this way the service duration of LEO satellite on orbit can increase by 2.5 times compared with a classic cold gas propulsion system. This is due to the propellant’s internal energy increase by the focused solar light. This paper also presents the results achieved by carrying out tests for the hot gas propulsion system in a controlled environment.

Solar thermal propulsion IHPRPT Demonstration Program

2000 ◽  
Author(s):  
Dean Lester ◽  
Steven Wassom ◽  
James Pearson ◽  
Michael Holmes
Keyword(s):  
Solar Thermal ◽  
Demonstration Program ◽  
Solar Thermal Propulsion
Sign in / Sign up

Export Citation Format

Share Document