Power Processing Unit and Feed System Development for a Multimode Spacecraft Propulsion System

2021 ◽  
Author(s):  
Jacob Eisen ◽  
Bryan Cline ◽  
Steven P. Berg ◽  
Joshua Rovey
Keyword(s):  
System Development ◽  
Propulsion System ◽  
Processing Unit ◽  
Feed System ◽  
Spacecraft Propulsion

scholarly journals An automated system analysis and design tool for spacecrafts ceas space journal

2021 ◽  
Author(s):  
Manfred Ehresmann ◽  
Georg Herdrich ◽  
Stefanos Fasoulas
Keyword(s):  
Evolutionary Algorithms ◽  
Evolutionary Algorithm ◽  
Degrees Of Freedom ◽  
System Analysis ◽  
Propulsion System ◽  
Optimal System ◽  
Automated System ◽  
Processing Unit ◽  
Data Set ◽  
Analysis And Design

AbstractIn this paper, a generic full-system estimation software tool is introduced and applied to a data set of actual flight missions to derive a heuristic for system composition for mass and power ratios of considered sub-systems. The capability of evolutionary algorithms to analyse and effectively design spacecraft (sub-)systems is shown. After deriving top-level estimates for each spacecraft sub-system based on heuristic heritage data, a detailed component-based system analysis follows. Various degrees of freedom exist for a hardware-based sub-system design; these are to be resolved via an evolutionary algorithm to determine an optimal system configuration. A propulsion system implementation for a small satellite test case will serve as a reference example of the implemented algorithm application. The propulsion system includes thruster, power processing unit, tank, propellant and general power supply system masses and power consumptions. Relevant performance parameters such as desired thrust, effective exhaust velocity, utilised propellant, and the propulsion type are considered as degrees of freedom. An evolutionary algorithm is applied to the propulsion system scaling model to demonstrate that such evolutionary algorithms are capable of bypassing complex multidimensional design optimisation problems. An evolutionary algorithm is an algorithm that uses a heuristic to change input parameters and a defined selection criterion (e.g., mass fraction of the system) on an optimisation function to refine solutions successively. With sufficient generations and, thereby, iterations of design points, local optima are determined. Using mitigation methods and a sufficient number of seed points, a global optimal system configurations can be found.

scholarly journals UWE-4: First Electric Propulsion on a 1U CubeSat—In-Orbit Experiments and Characterization

Aerospace ◽  
2020 ◽  
Vol 7 (7) ◽  
pp. 98
Author(s):  
Alexander Kramer ◽  
Philip Bangert ◽  
Klaus Schilling
Keyword(s):  
Electric Propulsion ◽  
Propulsion System ◽  
Heating Process ◽  
Processing Unit ◽  
Electric Propulsion System ◽  
Thrust Vector ◽  
Limited Power ◽  
Vector Direction ◽  
Orbit Period ◽  
Digital Components

The electric propulsion system NanoFEEP was integrated and tested in orbit on the UWE-4 satellite, which marks the first successful demonstration of an electric propulsion system on board a 1U CubeSat. In-orbit characterization measurements of the heating process of the propellant and the power consumption of the propulsion system at different thrust levels are presented. Furthermore, an analysis of the thrust vector direction based on its effect on the attitude of the spacecraft is described. The employed heater liquefies the propellant for a duration of 30 min per orbit and consumes 103 ± 4 mW. During this time, the respective thruster can be activated. The propulsion system including one thruster head, its corresponding heater, the neutralizer and the digital components of the power processing unit consume 8.5 ± 0.1 mW · μ A−1 + 184 ± 8.5 mW and scales with the emitter current. The estimated thrust directions of two thruster heads are at angles of 15.7 ± 7.6∘ and 13.2 ± 5.5∘ relative to their mounting direction in the CubeSat structure. In light of the very limited power on a 1U CubeSat, the NanoFEEP propulsion system renders a very viable option. The heater of subsequent NanoFEEP thrusters was already improved, such that the system can be activated during the whole orbit period.

A Fault Isolation Method Based on Analytical Redundancy Relations for Spacecraft Propulsion System

2012 ◽  
Vol 232 ◽  
pp. 331-336 ◽  
Author(s):  
Xiao Hui Peng ◽  
Zheng Yan ◽  
Yan Jun Li ◽  
Jian Jun Wu
Keyword(s):  
Diagnostic Criteria ◽  
Fault Isolation ◽  
Propulsion System ◽  
Time Varying ◽  
Isolation Method ◽  
Analytical Redundancy ◽  
Tendency Analysis ◽  
Time Invariant ◽  
Signature Matrix ◽  
Spacecraft Propulsion

Based on time-varying characters of spacecraft propulsion system, which generates tremendous difficulty to establish diagnostic criteria artificially, the fault isolation method based on Analytical Redundancy Relations (ARRs) generating from Diagnostic Bond Graph (DBG) has been proposed. The ARRs for Spacecraft Propulsion System are built on time-invariant structural characters, which can overcome the challenges from artificially establishing time-varying diagnostic criteria beforehand. By the tendency analysis of the residuals of ARRs, the fault signature matrix can be established. Then faults are isolated by comparison of observed signature and fault signature. Through the analysis of isolation results of a spacecraft propulsion system, it shows that ARRs is valid and practicable at fault isolation with rapid rates.

The Development of a Japanese 20N Thruster Valve for a Spacecraft Propulsion System

2006 ◽  
Author(s):  
Taiichi Nagata ◽  
Kenichi Kushiki ◽  
Kenichi Kajiwara ◽  
Yoshiharu Sugimura ◽  
Masayuki Kobayashi ◽  
...  
Keyword(s):  
Propulsion System ◽  
Spacecraft Propulsion
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