HELICON GRID THRUSTER(RADIO-FREQUENCY THRUSTER WITH EXTERNAL MAGNETIC FIELD)

Avant – Space Systems LLC

Aim of the project: boosting economic effectiveness for satellite missions and supporting commercial market development.

Applications

2

LEO constellations(phasing, station-keeping,

deorbiting)

GEO spacecraft(orbit raising, station-keeping,deorbiting)

Science & Research spacecraft(Deep space research, etc.)

Risingcommercial

efficiency

Launch mass decrease

Lifetime increase

Increase in thruster

specific impulse Helicon grid thrusterSolution

Technical performance

Model Power, W Thrust, mN Specific impulse, s Fuel Discharge chamber size

Mass, kg(except

subsystems)Propulsion system size Lifetime, h

1. GT - 50 70/130/300 3/6/12 1000/1200/3500 Xenon 50 mm × 30 mm 1,2 4U (Cubesat) 20 000

2. GT - 100 180/350/470 8/14/18 1400/2400/3200 Xenon 100 mm × 50

mm 2 8U (Cubesat) 20 000

1 advantage – improved energy deposition (power input)In inductive RF discharge plasma often consumes only part of the total RF-generator power, a large part of power may be dissipated in external circuit. Discharge in external magnetic field whose induction satisfy criteria of resonant excitation waves in plasma will help to significantly increase energy efficiency. 2 advantage – increased ion currentIn external magnetic field directed along the axis of the ion thruster an ion drifts slower to the gas discharge chamber walls which increases plasma density and ion current. Thus thrust and specific impulse are increasing.

Innovation: using of external magnetic field, whose induction satisfy criteria of resonant excitation waves in plasma.

3Thruster scheme

Analogue Stage Power, W Thrust, mН

Specific impulse, s

1. GT - 50 Developing 70/130/300 3/6/12 1000/1200/350

0

2. GT - 100 Developing 180/350/470 8/14/18 1400/2400/320

0

3. 13-cm XIPS On market 450 18 2350

4. BIT-7 Developing 460 11 3300

5. SPT-50М Developing 316 14 900

6. APPT-155М Developing 70 - 140 1.4 - 2.8 1320

7. КМ-45 On market 200-450 10-28 1250-1500

8. RIT 10 EVO On market 145/435/760 5/15/25 1900/3000/3200

Marketability

4

Main competitive advantages:

High specific impulse High energy efficiency Stable characteristics and long

lifetime Low-cost

Experimental development of thruster is carried out in Plasma Physics Laboratory, Lomonosov Moscow

State University.

Our research team consists of high-end professionals, scientists with many years' experience in the field of

radio-frequency thruster development.

5

Current status

Thruster performance predictions made for thruster being developed based on physical laws and specially designed programs

Experimental data acquired proving effectiveness of scheme used for thruster under development

Variety of ballistic patterns analyzed, as well as a set of requirements for the thruster

Comparative study conducted for the thruster under development and other on-market solutions

Team of developers formed

Anticipated results by the end of 2017

Thruster characteristics acquisition Structural and process solutions worked out and tested Thruster ignition and stopping processes worked out and

tested Thruster operating mode chosen based on marketing

analysis Technical design specification for prototype development

prepared

Laboratory model GT-100 in work

Contact person: Kharlan YanaE-mail: kharlan@avantspace.comTel.: +7 926 529 21 34