TM65

TM65
Country of origin  Denmark
Designer Copenhagen Suborbitals
Manufacturer Copenhagen Suborbitals
Application lower stage booster
Predecessor XLR-3A, XLR-3B [1]
Status In development
Liquid-fuel engine
Propellant LOX / Ethanol
Mixture ratio 75 % vol Ethanol / 25 % water [2]
Cycle Gas-generator
Configuration
Chamber L* = 200 cm
Nozzle ratio 1:4.5
Performance
Thrust (vac.) 85 kN (19,000 lbf)
Thrust (SL) 65 kN (15,000 lbf)[3]
Thrust-to-weight ratio 75:1
Chamber pressure 1.2 MPa (12 bar)[4]
Isp (vac.) 230 seconds (2.3 km/s)[4]
Isp (SL) 200 seconds (2.0 km/s)[4]
Burn time 100 sec as used in HEAT 2X launch vehicle
Dimensions
Length total 1700 mm
Diameter chamber 400 mm
Dry weight 75 kg
Used in
Planned use in HEAT 2X launch vehicle

TM65 is a rocket engine developed by Copenhagen Suborbitals. TM65 uses Ethanol and liquid oxygen as propellants in a pressure-fed power cycle.

Development

Construction of the prototype rocket engine TM65 was started in 2010,[5] completed in the spring of 2012 and test fired in May and November 2012.[6] It is planned to change the engine to be fed by a turbine pump.

Description

The TM65 uses a 75% ethanol/water mixture for fuel and liquid oxygen (LOX) for oxidizer.[4] It has a regeneratively cooled nozzle. Nitrogen was used in the first tests to pressurize the propellant tanks, heated in a heat exchanger in the nozzle.[7]

TM65 Engine Specifications

Propellants

Cooling

Injector

Cooling Jacket

Combustion Chamber

Nominal Operating Data

TM65 Turbopump Specifications

Liquid Oxygen Pump

Fuel Pump

Gas Generator

The turbopump is controlled by an electronic controller which measures outlet pressure and RPM, adjusting H2O2 flow as necessary. Each of the two turbine & pump units have a gas generator, and the units are mounted back to back but rotate in opposite directions and at different speeds.[2]

History

Construction of the prototype rocket engine Tordenskjold 65 (TM65) was started in the fall of 2010[5] after a range of successful tests with its predecessor XLR-3A.[1] The project was run parallel to Copenhagen Suborbitals hybrid rocket engine project that was used to power the HEAT-1X rocket and its payload Tycho Brahe.

After a few months of development the project was halted to focus on the launch of HEAT-1X in the summer of 2011.

The development and testing of TM65 was restarted in 2012 to explore if it was a viable replacement for the hybrid engine that Copenhagen Suborbitals previously had favored. Construction of the first prototype TM65 engine was completed in the spring of 2012 and successfully test fired in May 2012.[6] Tests were planned and executed throughout the fall and winter of 2012 in an attempt to raise chamber pressure to the planned 12 bars, which should produce 65 kN of thrust.

See also

References

  1. 1 2 "A rocket is born (Danish)".
  2. 1 2 "TM65 in numbers (Danish)".
  3. ↑ "TM65 Liquid propellant rocket engine".
  4. 1 2 3 4 "TM65 testes den 17 maj, og et åbent brev til tyskerne...".
  5. 1 2 "TM65 is under construction (Danish)".
  6. 1 2 "A big day for Copenhagen Suborbitals (Danish)".
  7. ↑ "TM65 Liquid Propellant Rocket Engine - Episode 1".
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