Solid Rocket propulsion

Solid_Six_logo_edgeIntroduction

The Solid Six team from DARE specialises in solid rocket propulsion. Most of DARE’s rockets have been powered by DARE’s internally developed solid propellant rocket engines. While Solid propellant powered rocket engines have been developed within DARE since DARE’s conception, it has been a team since 2009.

Since its founding, contributions from various team members have added to the body of knowledge to create a tested system for solid rocket design. Its past creations include the reliable Small Rocket Project and DX-1 engine, the latter used on CanSat and the active control rocket. It also produced the two-stage solid engines for Stratos I.

The team’s work ranges from the in-house development of its own solid propellant (ALAN-7) to the design, production and testing of several solid rocket motors, and more recently, to the design, manufacturing, assembly, and launching of rockets based on solid rocket motors.

Current Work

This year the team will optimize the known kalinidex engines (rocket candy propellant) to build a bigger and more powerful solid rocket motor, the DXS Asimov (DARE eXperimental Solid ‘Asimov’). The motor will be designed for the Aether – launcher, which has to reach supersonic speeds as one of its top requirements. For the Solid Six team, this means designing and manufacturing the biggest solid engine ever built by DARE.

Key points for the motor with respect to the Leonidas-5 engine shall be improved igniter design, mainly to improve the start-up transient (more steep thrust curve and increased specific impulse). Moreover, Solid Six will improve on optimized nozzle design, which will improve the nozzle efficiency and therefore increase thrust.

Successively multiple single grain motor (SGM) and igniter tests will be performed to study and improve the efficiency of our motor and its burn parameters. Afterward, the single grain motor will be up-scaled to the full-scale motor (FSM), a 7 grain motor equivalent of about 2 meters long, and again tested to validate its performance. The latter yields the final design and performance characteristics of the DXS Asimov.

Thereupon the Aether-laucher, propelled by the DXS Asimov, will be launched in April 2017.

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The Solid Propulsion Team (Solids) testing single grain motors at the TU Delft Campus  

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The Solid Propulsion Team (Solids) testing single grain motors at the Artillerieschietkamp ‘t Harde


 

 

Engines

DXS Asimov FSM

  • Propellant: Kalinidex (Potassium Nitrate – Sorbitol)
  • Total impulse: 40,335 Ns
  • Specific impulse: 126 s
  • Max Thrust: 7714 N
  • Average Thrust: 6464 N
  • Burn Time: 6 s
  • Chamber Pressure: 500 psi
  • Number of static tests: 0
  • Number of flights: 0

DXS Asimov SGM

  • Propellant: Kalinidex (Potassium Nitrate – Sorbitol)
  • Total impulse: 4800 Ns
  • Specific impulse: 126 s
  • Max Thrust: 860 N
  • Average Thrust: 600 N
  • Burn Time: 8 s
  • Chamber Pressure: 500 psi
  • Number of static tests: 2

LEONIDAS 5

  • Propellant: Kalinidex (Potassium Nitrate – Sorbitol)
  • Total impulse: 30,000 Ns
  • Specific impulse: 120 s
  • Max Thrust: 6500 N
  • Average Thrust: 5500 N
  • Burn Time: 5.5 s
  • Chamber Pressure: 500 psi
  • Number of static tests: 1
  • Number of flights: 0

L5SGM

  • Propellant: Kalinidex (Potassium Nitrate – Sorbitol)
  • Total impulse: 5000 Ns
  • Specific impulse: 100 s
  • Max Thrust: 1000 N
  • Average Thrust: 850 N
  • Burn Time: 6 s
  • Chamber Pressure: 500 psi
  • Number of static tests: 2
  • Number of flights: 0

MAXIMUS-C

  • Propellant: Alan-7 (Ammonium Nitrate – Aluminium)
  • Total impulse: 20,000 Ns
  • Specific impulse: 200 s
  • Max Thrust: 10,000 N
  • Average Thrust: 10,000 N
  • Burn Time: 5 s
  • Chamber Pressure: 450 psi
  • Number of static tests: 0
  • Number of flights: 0

BEM

  • Propellant: Alan-7 (Ammonium Nitrate – Aluminium)
  • Total impulse: 5000 N
  • Specific impulse: 200 s
  • Max Thrust: 1500 N
  • Average Thrust: 1000 N
  • Burn Time: 5 s
  • Chamber Pressure: 550 psi
  • Number of static tests: 20+
  • Number of flights: 1

FLAMING TIGER

  • Propellant: Alan-7 (Ammonium Nitrate – Aluminium)
  • Total impulse: 900 Ns
  • Specific impulse: 200 s
  • Max Thrust: 400 N
  • Average Thrust: 300 N
  • Burn Time: 3 s
  • Chamber Pressure: 450 psi
  • Number of static tests: 2
  • Number of flights: 1