scholarly journals Development and Laboratory Testing of a CubeSat-Compatible Staged Ionic-Liquid Electrospray Propulsion System

2022 ◽  
Author(s):  
Gustav M. Pettersson ◽  
Oliver Jia-Richards ◽  
Paulo C. Lozano
Keyword(s):  
Ionic Liquid ◽  
Laboratory Testing ◽  
Propulsion System

scholarly journals Fuel Cell Powered Drone: Use of Fuel Cells to Extend Multirotor Drone Endurance

2021 ◽  
Author(s):  
Jørgen Apeland
Keyword(s):  
Fuel Cells ◽  
Fuel Cell ◽  
Laboratory Testing ◽  
Current System ◽  
Peak Load ◽  
Industrial Applications ◽  
Cell System ◽  
Propulsion System ◽  
Third Party ◽  
Unmanned Aerial Systems

Unmanned aerial systems can be used for a range of industrial applications to reduce risk, cost, and time. Fuel cell-based propulsion systems are outlined as a solution to extend mission endurance, one of the current main barriers for further adoption. This coincides with a general societal push towards more sustainable aviation and the use of fuel cells and hydrogen as important zero-emission enablers. In this thesis, results from research about the use of fuel cells to extend multirotor drone flight endurance are presented. This application entails certain challenges compared to fixed-wing drones, which has been the scope of most previous research. The research explores the performance threshold between batteries and a fuel cell-based propulsion system, the prospects of further adoption, and how the performance can be improved. A prototype fuel cell system is developed and integrated into an X8 multirotor drone with a take-off mass of 21 kg and flight-tested. The specific energy on a power plant level was 243 Wh/kg, and the gross endurance for the current system is estimated to be 76 minutes, a 90% increase from the comparable endurance of the battery-powered alternative. The performance of the 2 kW fuel cell hybrid system is characterized in laboratory testing and exposed to relevant load profiles with a peak load of 2.8 kW. This is one of few independent third-party multirotor drone integrations of a fuel cell-based propulsion system. Based on experimental data from laboratory testing and full-scale flight in a realistic operating environment, a unique overview of associated challenges and further work is provided. As there is little published research on this topic, the work should be valuable for the research community, as well as drone operators and technology providers.

scholarly journals Experimental Study on Thermal and Catalytic Decomposition of a Dual-Mode Ionic Liquid Propellant

2021 ◽  
Vol 257 ◽  
pp. 01041
Author(s):  
He Gao ◽  
Shaolong Li ◽  
Zhaopu Yao ◽  
Shuiqing Li
Keyword(s):  
Ionic Liquid ◽  
Mass Loss ◽  
High Performance ◽  
Catalytic Decomposition ◽  
Decomposition Temperature ◽  
Propulsion System ◽  
Decomposition Process ◽  
Liquid Propellant ◽  
Water Solvent ◽  
Electrical Propulsion

With the increasing of space activities and people’s awareness of environmental protection, it is necessary to develop a new non-toxic space propulsion system with high performance. Hydroxylammonium nitrate (HAN)/1-ethyl-3-methyl-imidazolium ethylsulfate([Emim][EtSO4]) blend ionic liquid propellant is a potential replacement with non-toxic and high-performance characteristics for hydrazine type liquid propellants, which can be used in both chemical and electrical propulsion system. This paper introduced the thermogravimetric experimental analysis (TGA-DSC) results of HAN/[Emim][EtSO4] ionic liquid propellant with the thermal decomposition and catalytic decomposition process. Its mass-loss process and exothermic process under different reaction conditions at a heating rate of 5K/min~15K/min were studied. Generally, the mass-loss results showed that there were four characteristic stages during the decomposition process of the HAN/[Emim][EtSO4] ionic liquids, which were the evaporation of the water solvent, decomposition of the HAN component, further decomposition of the [Emim][EtSO4], and slow loss of the residual substances. At the same time, two exothermic peaks were observed, which respectively corresponded to the decomposition of HAN and the further decomposition of [Emim][EtSO4]. Using catalyst can significantly reduce the decomposition temperature of the propellant and the residual mass. The contents in this paper proved that this propellant had a good application prospect within the catalytic ignition aerospace thruster.

Rendez vous with Saturn's rings

1984 ◽  
Vol 75 ◽  
pp. 743-759 ◽  
Author(s):  
Kerry T. Nock
Keyword(s):  
Solar Energy ◽  
Electric Propulsion ◽  
Power Source ◽  
Propulsion System ◽  
Low Thrust ◽  
Ring Plane ◽  
The Earth ◽  
Total Impulse ◽  
Saturn's Rings

ABSTRACTA mission to rendezvous with the rings of Saturn is studied with regard to science rationale and instrumentation and engineering feasibility and design. Future detailedin situexploration of the rings of Saturn will require spacecraft systems with enormous propulsive capability. NASA is currently studying the critical technologies for just such a system, called Nuclear Electric Propulsion (NEP). Electric propulsion is the only technology which can effectively provide the required total impulse for this demanding mission. Furthermore, the power source must be nuclear because the solar energy reaching Saturn is only 1% of that at the Earth. An important aspect of this mission is the ability of the low thrust propulsion system to continuously boost the spacecraft above the ring plane as it spirals in toward Saturn, thus enabling scientific measurements of ring particles from only a few kilometers.

Soft ionic liquid based resistive memory characteristics in a two terminal discrete polydimethylsiloxane cylindrical microchannel

2020 ◽  
Vol 8 (38) ◽  
pp. 13368-13374
Author(s):  
Muhammad Umair Khan ◽  
Gul Hassan ◽  
Jinho Bae
Keyword(s):  
Ionic Liquid ◽  
Acrylic Acid ◽  
Sodium Hydroxide ◽  
Sodium Salt ◽  
Resistive Memory ◽  
Cylindrical Microchannel ◽  
Memory Characteristics ◽  
Poly Acrylic Acid

This paper proposes a novel soft ionic liquid (IL) electrically functional device that displays resistive memory characteristics using poly(acrylic acid) partial sodium salt (PAA-Na+:H2O) solution gel and sodium hydroxide (NaOH) in a thin polydimethylsiloxane (PDMS) cylindrical microchannel.

Assessing Sexual Dysfunction, Part 1: Male Sexual Dysfunction

2016 ◽  
Vol 21 (2) ◽  
pp. 3-8
Author(s):  
Seth D. Cohen ◽  
Steven Mandel ◽  
David B. Samadi
Keyword(s):  
Sexual Dysfunction ◽  
Health Care Professionals ◽  
Laboratory Testing ◽  
Aging Male ◽  
Testosterone Deficiency ◽  
Subjective Complaint ◽  
Validated Questionnaire ◽  
Male Sexual Dysfunction ◽  
Multiple Health

Abstract To properly assess men and women with sexual dysfunction, evaluators should take a biopsychosocial approach that may require consultation with multiple health care professionals from various fields in order to get to the root of the sexual dysfunction; this multidisciplinary methodology offers the best chance of successful treatment. For males, this article focuses on erectile dysfunction (ED) and hypogonadism. The initial evaluation of ED involves a thorough case history, preferably taken from the patient and partner, physical examination, and proper laboratory and diagnostic tests, including an acknowledgment of the subjective complaint. The diagnosis is established on the basis of an individual's report of the consistent inability to attain and maintain an erection sufficient to permit satisfactory sexual intercourse. Initial workups for ED should entail a detailed history that can be obtained from a validated questionnaire such as the International Index of Erectile Function and the Sexual Health Inventory for Men. Hypogonadism is evaluated using the validated Androgen Deficiency in the Aging Male questionnaire and laboratory testing for testosterone deficiency. Treatments logically can begin with the least invasive and then progress to more invasive strategies after appropriate counseling. The last and most important treatment component when caring for men with sexual dysfunction—and, arguably, the least practiced—is close follow-up.

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