who we are - wordpress.com · 2019. 5. 29. · regulus-a configuration 6u orbital changes for a...

➢ Who we are

➢ The Market

➢ The Problem

➢ The Solution

➢ Next development stages

➢ The team

➢ Conclusions

Index

Who we are

We are born in March 2014 as a Spin-Off of the University of Padua.

We are an innovative start-up founded by an entrepreneur and some researchers with international experience and several years of expertise in developing innovative systems.

Main working areas:

• ELECTRIC PROPULSIONDevelopment of space thrusters based on helicon source technology

• CHEMICAL PROPULSIONDevelopment of mono-bipropellant motors and hybrid rockets for aeronautics and spaceapplications

• SUPPORT TO AEROSPACE INDUSTRIES

- Company Confidential -

Who we are

Milan, 29th May 2019 4/24

The Market

39% Europe, 41% USA, 20% Others

Over 7,000 micro satellites are projected to be launched by 2027

Small satellites to be launched between 2019 and 2022 (sorted by area)

Small satellites < 50 kg to be launched between 2019 and 2023 (sorted by mass)

The SmallSat market

Milan, 29th May 2019 6/24- Company Confidential -

The Problem

The Problem: satellite mobility

Orbit phasing

Precision orbit

De orbiting

Collision avoidance

Continuous drag compensation

Mobility

Satellite operational needs

Affordable

Compatible performances

Easy integration

Reduced impact @system level

Availability

Thruster requirements

Satellite potential is limited by availability of suitable propulsion units


The Solution

Complex physics to understand, now simple to implement

• Based on an innovative low-cost magnetically enhanced plasma thruster

• Based on more than 10 years of development

• Patented plasma source technology

• Throttleable thus suitable for different mission needs

• Flexible for operations with different propellants (Xenon, Iodine, others)

The Solution: REGULUS propulsion system

- Company Confidential -Milan, 29th May 2019 10/24


After 10 years of research and development REGULUS is the T4i solution to satellite mobility needs

Thrust0.6 mN @50W (0.25-0.7) mN

Specific Impulse

600 s @ 50 W (up to 700 s)

Total Impulse3000-11000 (up to unlimited) Ns

Required power

50 W (range 20-60 W)

Mass flow 0.1 mg/sPropellant Solid Iodine (I2)Volume1U = (10x10x10cm)

1,5 U @ 3000 Ns2 U @ 11000 Ns

Weight 2.5 kg @ 3000 Ns

SIMPLEVERSATILEAFFORDEABLE

Discharge chamber RF antenna Magnetic system Gas injector Outlet diaphragm Plume screen

No ElectrodesNo NeutralizersNo ErosionMultiple gas


Key features BenefitsNo electrodes / grids (no cathodes and anodes exposes to plasma)

No neutralizer

Suitable for high Total DeltaV missions, enabling different and new mission scenarios and interplanetary flights.

Long lifetime.

Plug & Play All-in propulsion unit, easy to be integrated, require only signal and power.

Versatile technology Flexibility of the system to adapt to different mission scenarios

Flexibility of the system to match customers’ particular needs

Solid high-density propellant, no pressurized gas,no transportation issues, compact tank

Simple Versatile Affordable



Total Impulse 3000 Ns

Density 4,94 g/m3

Volume 12 mm x 9 mm x 9 mm

Total Mass 430 g

• 2x Volume reduction with respect to Xenon

• No pressurized tank (Xenon supercritical state @ 150 bar)

• Transportation of the satellite to the launch site with propellant onboard

• FM integration on the satellite platform with propellant onboard

The Solution: the use of Iodine

Being stored in the solid state, the use of Iodine results in a huge reduction of the storage volume


The Solution: the system


Orbital changesCubeSat

decommissioningDrag Compensation

REGULUS-A Configuration

6U orbital changes for a total of 500 km altitude in 1.7 month overall

6U decommissioning from 750km altitude in 1.6 month

- 6U >3 years life guaranteed@ 300 km

- 6U > 5 years life guaranteed@ 350 km

REGULUS-B Configuration

12U orbital changes for a total of 950 km altitude in6.0 months overall

- 12U from 1200 km altitudein 6.0 months

- Decommissioning isguaranteed from higheraltitudes

- 12U >65 years life guaranteed@ 300 km

Still propellant onboard for formation flying and/or decommissioning

Natural orbital decay of 1 month considered @350 km

Without compensatingpropulsion:

- 1U 21.6 days @ 300 km

The Solution: the applications


First Experiment

First Prototype

Go to high Power

Go Mini

Let’sFly!

The Solution: development history


Next development stages

REGULUS REGULUS+

Specific impulse @50W

600 s 1200s

Thrust @50W 0.6 mN 1.2 mN

Recurring cost Reference -30%

New MaterialsNew AntennaNew Magnets

To become the reference propulsion system for mini satellites

Next development stages


The Team

CEO OF THE COMPANY, Ph.D.

PROJECTMANAGER ELECTRIC PROPULSION, Ph.D.

BUSINESSDEVELOPMENT MANAGER, Ph.D.

PLASMA THRUSTER DESIGN, Ph.D.

THRUSTERTECHNOLOGY DEVELOPER, Ph.D.

Daniele Pavarin

Marco Manente

Fabio Trezzolani

Nicolas Bellomo

Elena Toson

The Team


One team, one dream, one commitment


→ Design a compact system, obtained 1.5U for 3000 Ns Itot, 2U for 11000 Ns Itot

→ REGULUS will allow combined maneuvers thanks to high Itot and thruster robustness

→ REGULUS is flexible to different mission scenarios and to match customers’ particular needs

→ No high pressure systems thanks to 𝐈𝟐 propellant

→ Low production costs and COTS components

→ REGULUS will be integrated into UniSat-7 microsatellite, the launch will be during Q2 2020

Conclusions


Daniele Pavarin, PhD

Chief Executive Officer

Email: [email protected]

Technology for Propulsion and Innovation S.r.l.

www.t4innovation.com

HeadquartersVia Altinate 125, 35121 Padova (PD) ITALY

Operative OfficesVia Della Croce Rossa 112,35129 Padova (PD) ITALYTel. (+39) 049 9271547

Alessia Gloder, MSc

Sales and Marketing Engineer

Email: [email protected]

Contacts


To Thrust a different world

who we are - wordpress.com · 2019. 5. 29. · regulus-a configuration 6u orbital changes for a...

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