Results of Low-Cost Propulsion System Research for Small Satellite Application

1997 ◽  
pp. 203-230 ◽  
Author(s):  
J. J. Sellers ◽  
T. J. Lawrence ◽  
M. Paul
Keyword(s):  
Low Cost ◽  
Propulsion System ◽  
Small Satellite ◽  
System Research

Computational Fluid Dynamic Applications for Jet Propulsion System Integration

1991 ◽  
Vol 113 (1) ◽  
pp. 40-50 ◽  
Author(s):  
R. H. Tindell
Keyword(s):  
System Integration ◽  
Fluid Dynamic ◽  
Low Cost ◽  
Separated Flow ◽  
Propulsion System ◽  
Navier Stokes ◽  
Aerospace Vehicles ◽  
Design Engineers ◽  
Flow Phenomena ◽  
The Impact

The impact of computational fluid dynamics (CFD) methods on the development of advanced aerospace vehicles is growing stronger year by year. Design engineers are now becoming familiar with CFD tools and are developing productive methods and techniques for their applications. This paper presents and discusses applications of CFD methods used at Grumman to design and predict the performance of propulsion system elements such as inlets and nozzles. The paper demonstrates techniques for applying various CFD codes and shows several interesting and unique results. A novel application of a supersonic Euler analysis of an inlet approach flow field, to clarify a wind tunnel-to-flight data conflict, is presented. In another example, calculations and measurements of low-speed inlet performance at angle of attack are compared. This is highlighted by employing a simplistic and low-cost computational model. More complex inlet flow phenomena at high angles of attack, calculated using an approach that combines a panel method with a Navier-Stokes (N-S) code, is also reviewed. The inlet fluid mechanics picture is rounded out by describing an N-S calculation and a comparison with test data of an offset diffuser having massively separated flow on one wall. Finally, the propulsion integration picture is completed by a discussion of the results of nozzle-afterbody calculations, using both a complete aircraft simulation in a N-S code, and a more economical calculation using an equivalent body of revolution technique.

The Preparation of High Quality CIS Films by Spraying Citrate-Capped Cu11In9 Alloy Nanoparticles Ink and RTP Process

2013 ◽  
Vol 787 ◽  
pp. 382-387
Author(s):  
Li Zhou ◽  
Yuan Kui Ding ◽  
Pai Feng Luo
Keyword(s):  
Raw Materials ◽  
Low Cost ◽  
Chalcopyrite Structure ◽  
Alloy Nanoparticles ◽  
System Research ◽  
Spherical Nanoparticles ◽  
Particle Agglomeration ◽  
Energy Band Gap ◽  
High Quality ◽  
Selenization Process

A facile low-cost non-vacuum process for fabrication of high quality CuInSe2(CIS) films is described, which indicates a promising way for the application in thin film solar cells. First, citrate-capped Cu11In9alloy nanoparticles are synthesized by hot-injection method after a system research on the different reaction time and Cu-In ratio of the raw materials. From the TEM and XRD results, we can see that uniform spherical nanoparticles with dominant Cu11In9phase and less particle-to-particle agglomeration are successfully achieved in this study. Then, employing spray and RTP selenization process, high quality CIS films with dense and big grains are obtained, which show the single chalcopyrite structure and the preferred (112) orientation. An energy band gap about 1.01 eV is measured through the absorption spectroscopy measurement in our work.

Low-Cost Small-Satellite Delivery System

2002 ◽  
Vol 39 (5) ◽  
pp. 818-820 ◽  
Author(s):  
Frederick W. Boltz
Keyword(s):  
Delivery System ◽  
Low Cost ◽  
Small Satellite

Development of Appropriate Power Distribution Design for Can-Sized satellite (canSAT)

2021 ◽  
Vol 02 (02) ◽  
Author(s):  
Devina Cristine Marubin ◽  
◽  
Sim Sy Yi ◽  
Keyword(s):  
Power System ◽  
Data Acquisition ◽  
Power Supply ◽  
Communication System ◽  
Power Distribution ◽  
Low Cost ◽  
Small Satellite ◽  
Power Budget ◽  
Space Agency ◽  
Rules Set

Can-Sized satellite (canSAT) is a small satellite that is used for educational purpose. CanSAT offer student to build their satellites with their creativity which make the learning process more effective. In Malaysia, SiswaSAT is held by the Malaysia Space Agency for students in different categories to participate and build their satellites according to rules set and it should be a low-cost project. CanSAT can be divided into few parts which are communication system, onboard data acquisition, ground control station and power system. The power system is one of the important and heaviest subsystems, it needed to supply power, but weight and size are one of the main concerned as the canSAT should not exceed the required weight and selecting power supply that is matched with the overall power budget that has small size and lightweight is challenging. Therefore, the power supply selection should consider this detail. The power distribution design should be able to supply an appropriate amount of current and voltage to the components according to their specification. This study aims to develop and test the proposed prototype which is named ScoreSAT able to provide data and have enough power supply for the whole operation. Therefore, an initiative to develop the appropriate power distribution design for canSAT is taken to overcome the problem of the power system. Moreover, each subsystem needs to be tested by obtaining the results from the onboard data acquisition and transmit the data using the communication system before integrating into the power system. ScoreSAT prototype needs to carry the system that is mounted inside, thus the space inside the prototype needs to be fully utilized for the whole system to fit in. ScoreSAT completes the mission by obtaining data acquisition during the operation.

Subsonic Propulsion System Installation Analysis and Optimization

1991 ◽  
Author(s):  
J. L. Colehour ◽  
B. W. Farquhar ◽  
J. E. Gengler ◽  
T. A. Reyhner
Keyword(s):  
Potential Flow ◽  
Low Cost ◽  
Flow Analysis ◽  
Flow Characteristics ◽  
Simulation Method ◽  
Inviscid Flow ◽  
Wave Drag ◽  
Propulsion System ◽  
Design Development ◽  
Improved Performance

Computational fluid dynamics (CFD) now allows analysis of propulsion system installations on subsonic transports to an extent that many configuration decisions can be made without testing. The methods discussed here utilize low-cost potential flow methods to predict inviscid flow characteristics and utility methods to model geometry, generate computational mesh, estimate wave drag, and perturb geometry in ways that promise improved performance. Jet plume effects are included in the potential flow analysis by means of a plume simulation method. Wave drag predictions yield levels of drag that are consistent with wind tunnel results, and, through contour optimization, wave drag for a trial propulsion installation geometry was reduced by about 50%. We conclude that through the use of methods such as these, many propulsion system installation design decisions can be made by analysis relatively quickly, which should lead to reduced design development time and cost.

Methods of Mass-Flow Characterization of Water-Glycol Mixtures Through Micro/Nano-Channels

2018 ◽  
Author(s):  
John Lee ◽  
Po-Hao Huang
Keyword(s):  
Mass Flow ◽  
Low Cost ◽  
Thermal Characteristics ◽  
Propulsion System ◽  
Optical Tracking ◽  
Gaseous State ◽  
Small Satellites ◽  
Class 1 ◽  
Nano Channel ◽  
Micro Propulsion

The design of a novel micro-propulsion system for small satellites of the nano-satellites class (1–10kg) that is low-cost, non-toxic, non-flammable, and no-pressurized at launch conditions is currently being developed at the University of Arkansas. The goal of the present micro-propulsion system is to achieve milli-Newton thrust levels with specific impulses on the order of 100s. The proposed propellant is the water-propylene glycol. However, little data is available for its fluid and thermal characteristics at the gaseous state, nor the evolution of similar mixtures through micro/nano-channels. This paper will present experimental methods of measuring the mass flow rate of the water-glycol mixtures through micro/nano-channels. A MEMS fluidic chamber fabricated with a nano-channel is used to quantify the mass flow through optical tracking of liquid interfaces confined in the chamber. The dimensions of the channels are designed with the purpose to act as a passive throttling valve that prevent liquid-phase fluids from entering into the nozzle in order to achieve a simple water-based cold-gas propulsion system.

Overview of the Development of a Low Cost High Voltage Hall Accelerator Propulsion System for NASA Science Missions

2011 ◽  
Author(s):  
Hani Kamhawi ◽  
Thomas Haag ◽  
Luis Pinero ◽  
Wensheng Huang ◽  
Todd Peterson ◽  
...  
Keyword(s):  
High Voltage ◽  
Low Cost ◽  
Propulsion System
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