Coordinatore | UNIVERSITA DEGLI STUDI DI PADOVA
Organization address
address: VIA 8 FEBBRAIO 2 contact info |
Nazionalità Coordinatore | Italy [IT] |
Sito del progetto | http://www.hphcom.eu |
Totale costo | 4˙873˙436 € |
EC contributo | 3˙572˙011 € |
Programma | FP7-SPACE
Specific Programme "Cooperation": Space |
Code Call | FP7-SPACE-2007-1 |
Funding Scheme | CP |
Anno di inizio | 2008 |
Periodo (anno-mese-giorno) | 2008-12-01 - 2012-05-31 |
# | ||||
---|---|---|---|---|
1 |
UNIVERSITA DEGLI STUDI DI PADOVA
Organization address
address: VIA 8 FEBBRAIO 2 contact info |
IT (PADOVA) | coordinator | 0.00 |
2 |
AGENZIA NAZIONALE PER LE NUOVE TECNOLOGIE,L'ENERGIA E LO SVILUPPO ECONOMICO SOSTENIBILE
Organization address
address: Lungotevere Grande Ammiraglio Thaon di Revel 76 contact info |
IT (ROMA) | participant | 0.00 |
3 |
ALMA MATER STUDIORUM-UNIVERSITA DI BOLOGNA
Organization address
address: Via Zamboni 33 contact info |
IT (BOLOGNA) | participant | 0.00 |
4 |
AOES Group BV - Advanced Operations and Engineering Services Group BV
Organization address
address: Huygensstraat 34 contact info |
NL (Noordwijk) | participant | 0.00 |
5 |
BRADFORD ENGINEERING BV
Organization address
address: DE WIJPER 26 contact info |
NL (HEERLE) | participant | 0.00 |
6 |
CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE
Organization address
address: Rue Michel -Ange 3 contact info |
FR (PARIS) | participant | 0.00 |
7 |
KELDYSH INSTITUTE OF APPLIED MATHEMATICS OF THE RUSSIAN ACADEMY OF SCIENCES
Organization address
address: "MIUSSKAYA PL., 4" contact info |
RU (MOSCOW) | participant | 0.00 |
8 |
LMS IMAGINE
Organization address
address: Place des Minimes 7 contact info |
FR (Roanne) | participant | 0.00 |
9 |
NATIONAL AEROSPACE UNIVERSITY KHARKIV AVIATION INSTITUTE NAMED BY N ZUKOVSKIY
Organization address
address: CHKALOVA STR 17 contact info |
UA (KHARKIV) | participant | 0.00 |
10 |
OFFICE NATIONAL D'ETUDES ET DE RECHERCHES AEROSPATIALES
Organization address
address: Avenue de la Division Leclerc 29 contact info |
FR (CHATILLON) | participant | 0.00 |
11 |
ROVSING A/S
Organization address
address: Dyregaardsvej 2 contact info |
DK (Skovlunde) | participant | 0.00 |
12 |
STUDIO PROGETTAZIONE E REALIZZAZIONE DI APPARATI ELETTRO NICI DI SELMO ANTONIO
Organization address
address: VIA ROMA 17 contact info |
IT (ALBAREDO D ADIGE) | participant | 0.00 |
13 |
THALES ALENIA SPACE ITALIA SPA
Organization address
address: Via Saccomuro 24 contact info |
IT (ROMA) | participant | 0.00 |
14 |
UNIVERSIDAD POLITECNICA DE MADRID
Organization address
address: Calle Ramiro de Maeztu 7 contact info |
ES (MADRID) | participant | 0.00 |
15 |
UNIVERSITA DEGLI STUDI DI ROMA LA SAPIENZA
Organization address
address: Piazzale Aldo Moro 5 contact info |
IT (ROMA) | participant | 0.00 |
Esplora la "nuvola delle parole (Word Cloud) per avere un'idea di massima del progetto.
'The objective of the research program is to design, optimize and develop a space plasma thruster based on helicon-radio-frequency technology and its application to a nano-satellite for attitude and position control. Moreover a detailed feasibility study will be also conducted to evaluate the possibility of using the plasma thruster to heat and decompose a secondary propellant. The feasibility study will asses the possibility of building up a combined-two-mode-thruster able to operate in the low-thrust high-efficiency plasma-mode and high-thrust low-efficiency secondary-propellant-plasma-enhanced mode. Only the plasma thruster will be developed and fully tested during this study. The main characteristics of the thruster are: Power 50 W Weight within 1.5 kg Thrust >1.5 mN Specific Impulse (Isp) >1200 s The program will develop thought the following steps: a) Deep numerical-theoretical investigation through dedicated plasma-simulation tools. b) Extensive experimental campaign to validate codes, to investigate the physics phenomena involved and to proof thruster performance. c) The development of a thruster-prototype to be mounted on board of a mini-satellite to demonstrate technology feasibility, d)The study of all the critical issues related to the application to a mini-satellite e) the design and manufacturing of the mini-satellite mock up including all critical components f) analysis of scaling law to lower and higher power. As a final results of the project, a detailed analysis will be conducted in order to evaluate the possible application of the thruster in space missions requiring low thrust accurate attitude and position control.'
The bulky rocket engines of the past may be replaced in the future by electrically powered ion engines allowing more versatility while using less fuel. EU-funded researchers have made an important step towards making such ion engines a reality for the next generation of spacecraft.
Ion engines use electric power to create charged particles of the fuel, usually xenon gas, and accelerate them to extremely high speeds. The exhaust speed of conventional rocket engines is limited to the chemical energy stored in the fuel's molecular bonds. On other hand, ion engines are in principle limited by the electrical power available on the spacecraft, but in practice are much more efficient than chemical ones.
In particular, helicon thrusters are at the frontier of ion propulsion systems. They operate with a variety of propellants and have a longer lifetime compared to conventional thrusters. Scientists initiated the HPH.COM (Heliconplasmahydrazine.COmbinedMicro) project to design a new plasma thruster based on helicon radiofrequency technology.
With EU funding, the researchers explored its application for a mini satellite to allow a low-cost demonstration mission. Their feasibility study also covered the possibility of developing a combined two-mode thruster for both attitude and orbit control. It combined a low-thrust, high-efficiency plasma mode and a high-thrust, low-efficiency hydrazine mode.
For this purpose, HPH.COM partners developed dedicated plasma simulation tools allowing the detailed investigation of complex physical phenomena. The numerical models, along with intensive experimentation, resulted in an innovative helicon technology with significantly higher ionisation efficiency compared to conventional helicon plasma sources.
The engineering model of the thrusters was tested in three separate laboratories to reduce the development time. Finally, a mini satellite mock-up was designed and manufactured to prove the feasibility of the new technology that will be demonstrated in flight. Its structure is modular and easy to assemble and disassemble as well as adapt for any launch vehicle.
Thanks to the long lifetime and capability to operate with a wide variety of gases, theHPH.COM technology should be attractive for a variety of space missions, including Earth observation and telecommunications. Combining high efficiency with low cost, the new plasma thruster is poised to boost the competitiveness of the European space industry.