Rendez vous with Saturn's rings

1984 ◽  
Vol 75 ◽  
pp. 743-759 ◽  
Author(s):  
Kerry T. Nock

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.

Author(s):  
Nicolas Bellomo ◽  
Mirko Magarotto ◽  
Marco Manente ◽  
Fabio Trezzolani ◽  
Riccardo Mantellato ◽  
...  

AbstractREGULUS is an Iodine-based electric propulsion system. It has been designed and manufactured at the Italian company Technology for Propulsion and Innovation SpA (T4i). REGULUS integrates the Magnetically Enhanced Plasma Thruster (MEPT) and its subsystems, namely electronics, fluidic, and thermo-structural in a volume of 1.5 U. The mass envelope is 2.5 kg, including propellant. REGULUS targets CubeSat platforms larger than 6 U and CubeSat carriers. A thrust T = 0.60 mN and a specific impulse Isp = 600 s are achieved with an input power of P = 50 W; the nominal total impulse is Itot = 3000 Ns. REGULUS has been integrated on-board of the UniSat-7 satellite and its In-orbit Demonstration (IoD) is currently ongoing. The principal topics addressed in this work are: (i) design of REGULUS, (ii) comparison of the propulsive performance obtained operating the MEPT with different propellants, namely Xenon and Iodine, (iii) qualification and acceptance tests, (iv) plume analysis, (v) the IoD.


Author(s):  
Mahmoud Abdelhamid ◽  
Imtiaz Haque ◽  
Rajendra Singh ◽  
Srikanth Pilla ◽  
Zoran Filipi

The challenge of meeting the Corporate Average Fuel Economy (CAFE) standards of 2025 has resulted in the development of systems that utilize alternative energy propulsion technologies. To date, the use of solar energy as an auxiliary energy source of on-board fuel has not been extensively investigated, however. The authors investigated the design parameters and techno-economic impacts within a solar photovoltaic (PV) system for use as an on-board auxiliary power source for the internal combustion engine (ICE) vehicles and plug-in electric vehicles (EVs). The objective is to optimize, by hybridizing, the conventional energy propulsion systems via solar energy based electric propulsion system by means of the on-board PVs system. This study is novel in that the authors investigated the design parameters of the on-board PV system for optimum well-to-tank energy efficiency. The following design parameters were analyzed: the PV device, the geographical solar location, thermal and electrical performances, energy storage, angling on the vehicle surface, mounting configuration and the effect on aerodynamics. A general well-to-tank form was derived for use in any other PV type, PV efficiency value, or installation location. The authors also analyzed the techno-economic value of adding the on-board PVs for ICE vehicles and for plug-in EVs considering the entire Powertrain component lifetime of the current and the projected price scenarios per vehicle lifetime, and driving by solar energy cost ($ per mile). Different driving scenarios were used to represent the driving conditions in all the U.S states at any time, with different vehicles analyzed using different cost scenarios to derive a greater understanding of the usefulness and the challenges inherent in using on-board PV solar technologies. The addition of on-board PVs to cover only 1.0 m2 of vehicle surfaces was found to extend the daily driving range to up to 2 miles for typical 2016 model vehicles, depending upon on vehicle specifications and destination, however over 7.0 miles with the use of extremely lightweight and aerodynamically efficient vehicles in a sunny location. The authors also estimated the maximum possible PV installation area via a unique relationship between the vehicle footprint and the projected horizontal vehicle surface area for different vehicles of varying sizes. It was determined that up to 50% of total daily miles traveled by an average U.S. person could be driven by solar energy, with the simple addition of on-board PVs to cover less than 50% (3.25 m2) of the projected horizontal surface area of a typical mid-size vehicle (e.g., Nissan Leaf or Mitsubishi i-MiEV). Specifically, the addition of the proposed PV module to a 2016 Tesla Model S AWD-70D vehicle in San Diego, CA extended the average daily range to 5.2 miles in that city. Similarly, for the 2016 BMW i3 BEV in Texas, Phoenix, and North Carolina, the range was extended to more than 7.0 miles in those states. The cost of hybridizing a solar technology into a vehicle was also estimated for current and projected prices. The results show for current price scenario, the expense of powering an ICE vehicle within a certain range with only solar energy was between 4 to 23 cents per mile depending upon the vehicle specification and driving location. Future price scenarios determined the driving cost is an optimum of 17 cents per mile. However, the addition of a PV system to an EV improved the economics of the system because of the presence of the standard battery and electric motor components. For any vehicle in any assumed location, the driving cost was found to be less than 6.0 cents per mile even in the current price scenario. The results of this dynamic model are applicable for determining the on-board PV contribution for any vehicle size with different powertrain configurations. Specifically, the proposed work provides a method that designers may use during the conceptual design stage to facilitate the deployment of an alternative energy propulsion system toward future mobility.


2013 ◽  
Vol 393 ◽  
pp. 510-515
Author(s):  
Norhisyam Jenal ◽  
Wahyu Kuntjoro ◽  
Thomas Arthur Ward ◽  
Khairul Imran Sainan ◽  
Firdaus Mohamad

Combustion engines are increasingly being regarded as unsustainable in the long-term, because of their negative impact on the environment (e.g. pollution, green-house gas production, and global warming). This has generated worldwide interest in propulsion systems based on renewable alternative energy sources for the future. Fuel cell technology is a promising alternative power source because of their high specific energy, efficiency, and reliability. Hydrogen proton exchange membrane fuel cell (PEMFC) in particular produces zero carbon emissions by having only water vapor as the exhaust. Although there has been much research by automotive industries in developing fuel cell hybrid electric vehicles (FCHEV), fuel cell research for aircraft application is relatively new. Therefore, there is a pressing need for research related to development of aircraft fuel cell electric propulsion systems. Universiti Teknologi MARA (UiTM) is conducting static experiments on different configurations of fuel cell electric propulsion systems. The objective of this study is to understand the behavior of a PEMFC propulsion system under a ground-based static test. A 1 kW PEMFC was used as the main power source for a brushless DC motor electric propulsion system. The electrical characteristics, rotational speed, and thrust data were presented for two different electrical propellers. Analyses of the results were used to characterize the effectiveness of the fuel cell system and its balance of plant. The results were beneficial as a predictive method on defining the optimum electric propulsion system performance needed for future actual flight development.


1984 ◽  
Vol 75 ◽  
pp. 75-86
Author(s):  
Bruno Sicardy ◽  
Pierre Laques ◽  
Jean Lecacheux ◽  
André Brahic ◽  
Gérard Wlerick

ABSTRACTThe reductions of electronographic plates taken during ground-based observations of Saturn at the times of the transits of the Sun and the Earth through the ring plane (March 1980) are interpreted.1. The variation of the ring’s brightness vs. elevation angle around Earth’s crossing is different from the variation around Sun’s crossing. Furthermore, the ring’s brightness increases with the distance to Saturn’s centre around Earth’s crossing and decreases around Sun’s crossing. This allows to derive the illumination of the Saturn’s disc on the rings and indicates that the rings do not behave like an homogeneous scattering layer when observed or lit almost edge-on.


2009 ◽  
Vol 2009 ◽  
pp. 1-14 ◽  
Author(s):  
Carlos Renato Huaura Solórzano ◽  
Antonio Fernando Bertachini de Almeida Prado ◽  
Alexander Alexandrovich Sukhanov

Exploration of the outer planets has experienced new interest with the launch of the Cassini and the New Horizons Missions. At the present time, new technologies are under study for the better use of electric propulsion system in deep space missions. In the present paper, the method of the transporting trajectory is used to study this problem. This approximated method for the flight optimization with power-limited low thrust is based on the linearization of the motion of a spacecraft near a keplerian orbit that is close to the transfer trajectory. With the goal of maximizing the mass to be delivered in Saturn, several transfers were studied using nuclear, radioisotopic and solar electric propulsion systems.


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