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
ESA
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 1b Apogee Engine

The LEROS 1b is a high performance bipropellant chemical thruster, used for satellites and spacecraft.

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 317 second Isp, MON/ Hydrazine dual mode apogee engine delivers a thrust of 635 N.

Nammo has supplied the LEROS 1b engine in large quantities, which have flown successfully on deep space missions and telecoms platforms.  The JPL Juno mission to Jupiter used a LEROS 1b engine, which was highly praised for its faultless and predictable performance on this demanding 5.5 year mission.  The LEROS 1b engine has also successfully completed interplanetary missions to Mercury and Mars.

This renowned LEROS apogee engine is the default selection for deep space and Earth orbital missions where high thrust and reliability are crucial to the mission success.  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 or Main delta V engine
  • Typical Operational Mode Long duration burn, with pulsing capability
  • Propellant MON/Hydrazine
  • Thrust Range 587 N to 707 N
    132 lbf to 159 lbf
  • Thrust, nominal inlet pressure 635 N at nominal inlet pressure
    143 lbf at nominal inlet pressure
  • Mixture Ratio Range 0.8 to 0.9
    Oxidiser to Fuel
  • Mixture Ratio 0.85
    At nominal inlet pressure
  • Specific Impulse 317 seconds
    Minimum value
  • Total Impulse 12,965,000 Ns
  • Propellant Throughput 4,170 kg
    9,193 lb
  • Inlet Pressure Range 15 bar to 21 bar
    217.5 psi to 304.6 psi
  • Restarts 70 off Demonstrated
    With the chamber temperature starting at 1,300°C [2,372°F]
  • Maximum Duration Single Firing 2,520 seconds
    Demonstrated in qualification
  • Cumulative Duration 20,500 seconds
    Demonstrated in qualification
  • Mass 4.5 kg
    9.9 lb
  • Operating Temperature 1,380°C Maximum
    2,516°F Maximum
  • Propellant Temperature +10°C to +35°C
    +50°F to +95°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
  • Qualified Valve Cycles 10,500 on/off cycles
  • Valve Voltage 24 Vdc to 35.5 Vdc
    Per coil
  • Technology Readiness Level TRL9

Status

Has flown on the following missions: