Locations
Contacts

Thorstein Korsvold

Web & Content Manager (Corporate Press Contact)

MAIL P.O. Box 142, NO-2831 Raufoss, Norway
VISIT Enggata 37, 2830 Raufoss, Norway
EMAIL thorstein.korsvold@nammo.com
TEL +4741100055

Norway

Nammo AS

MAIL P.O. Box 142, NO-2831 Raufoss, Norway
VISIT Enggata 40, NO-2830 Raufoss, Norway
EMAIL info@nammo.com
TEL +47 61 15 36 00 (0800 - 1530)
Contact

Adam Watts

Strategic and Business Development Manager

MAIL Nammo (UK) Limited, 47 Westcott Venture Park, Westcott, Buckinghamshire, HP18 0XB, United Kingdom.
EMAIL adam.watts@nammo.com
TEL +44 7768 952 290

NAMMO UK WESTCOTT

GENERAL

  • Dedicated, skilled space engineering team
  • Experienced Assembly Integration and Test Team
  • Cleanroom facility for space hardware
  • Electron Beam Welding
  • Experienced orbital and interplanetary propulsion solutions

TEST FACILITIES

  • National Propulsion Test Facility, for thrusters up to 1.5kN
  • High Altitude Propulsion Test Facility
  • Attitude and Reaction Control Testing
  • Small Thruster Test Facility
  • Sea Level Test Facility
  • Vibration and Resonance Testing

QUALITY

  • Certified to AS9100
  • Focused on customer needs
Location

Nammo (UK) Westcott Westcott, England, HP18 0XB, United Kingdom

LEROS 2b Apogee Engine

The LEROS 2b is a high performance bipropellant chemical thruster.

Contact

Adam Watts

Strategic and Business Development Manager

MAIL Nammo (UK) Limited, 47 Westcott Venture Park, Westcott, Buckinghamshire, HP18 0XB, United Kingdom.
EMAIL adam.watts@nammo.com
TEL +44 7768 952 290

NAMMO UK WESTCOTT

GENERAL

  • Dedicated, skilled space engineering team
  • Experienced Assembly Integration and Test Team
  • Cleanroom facility for space hardware
  • Electron Beam Welding
  • Experienced orbital and interplanetary propulsion solutions

TEST FACILITIES

  • National Propulsion Test Facility, for thrusters up to 1.5kN
  • High Altitude Propulsion Test Facility
  • Attitude and Reaction Control Testing
  • Small Thruster Test Facility
  • Sea Level Test Facility
  • Vibration and Resonance Testing

QUALITY

  • Certified to AS9100
  • Focused on customer needs
Location

Nammo (UK) Westcott Westcott, England, HP18 0XB, United Kingdom

The Nammo Space designed and manufactured 319.5 second Isp, MON/Hydrazine apogee engine delivers a thrust of 420 N.

The LEROS 2b has flown on the NRL Mitex Mission and the 2019 SpaceIL/IAI Beresheet lunar Lander mission.  The LEROS 2b for the Beresheet mission utilized an innovative Additive Manufactured support structure / heatshield.  The engine successfully performed the orbit raising and lunar orbit insertion maneuvers.

This is a cost-efficient, high performance bipropellant engine.  The base material for the thrust chamber and expansion cone is C103 Niobium alloy, coated with R512E Disilicide for oxidation protection.  All Nammo apogee engines are hot-fire tested in the UK National Space Propulsion Test Facility at Nammo Westcott.  Delivery timescales are typically 12-18 months.

Performance Characteristics

  • Typical Application Apogee engine or Main delta V engine
  • Typical Operational Mode Long duration burns, Pulsing capability/Modulated firing capability
  • Propellant MON/MMH
  • Thrust Range 367 N to 456 N
    83 lbf to 103 lbf
  • Thrust, nominal inlet pressure 420 N at nominal inlet pressure
    95 lbf at nominal inlet pressure
  • Mixture Ratio Range 1.43 to 1.81
    Oxidiser to Fuel
  • Mixture Ratio 1.65
    Oxidiser to Fuel, at nominal inlet pressure
  • Specific Impulse 319.5 seconds typical
    318.5 seconds at 15.4 bara [223 psia]. 320 seconds at 17 bara [246 psia]
  • Total Impulse 12,000,000 Ns minimum
  • Propellant Throughput > 4,000 kg
    > 8,818 lb
  • Inlet Pressure 15.4 bara nominal
    223 psia nominal
  • Inlet Pressure Range 13.5 bara to 17.9 bara
    196 psia to 260 psia
  • Restarts 75 off demonstrated
    With the chamber temperature starting at 100°C [212°F] finishing at 1,300°C [2,372°F]
  • Maximum Duration Single Firing 6,600 seconds
    Demonstrated in qualification
  • Cumulative Duration >30,600 seconds
    Demonstrated in qualification
  • Mass 5 kg
    11 lb
  • Nominal Operating Temperature 1,350°C
    2,462°F
  • Propellant Temperature +4°C to +40°C
    +39°F to +104°F
  • Storage Temperature -53°C to +65°C
    -63.4°F to +149°F
  • Storage Life 4 years
  • Operational Life 19 years
  • Reliability 0.995
  • Valve Type 2 off Solenoid, Single Seat, Redundant Coil
    The thruster can be connected fuel/oxidiser primary coils in parallel [24 Vdc] or in series [50 Vdc].
  • Qualified Valve Cycles 10,500 on/off cycles
  • Valve Voltage 19 Vdc to 27 Vdc
    Per coil
  • Technology Readiness Level TRL9

Status

The LEROS 2b was successfully used for the SpaceIL Beresheet mission.