Development of CAMUI Hybrid Roket

Develop small sounding hybrid rocket systems realizing lowcost, safety, and eco-friendly. Decrease the launch cost as low as 1/10 of conventional solid rocket systems by using solid-liquid hybrid propellants and a reusable fuselage.

Items under

@ 400 kgf thrust flight model engine
@ 1tonf thrust engineering model engine

Applications @ Three minutes microgravity experiments (1tonf class)
@ Observation and atmospheric air sampling of stratosphere (400 kgf class)

What is hybrid rocket?
Hybrid rocket

E Rocket motors using a combination of solid fuel (plastics for example) and liquid oxidizer as propellants
E Safe because of explosive-free propellants
E Low consumable and operational costs because of inexpensive and explosive-free propellants
E Additional cost reduction is possible by reusing the vehicle.
E Practical use is not yet because of the low thrust due to the small regression rate of the solid fuel.

CAMUI type hybrid rocket engine

CAMUI type hybrid rocket engine

A new fuel grain design that makes the jet of the combustion gas collide with burning surfaces repeatedly, resulting in the high regression rate of the solid fuel. CAMUI is an abbreviation of Cascaded Multistage Impinging-jet.

Solid rocket
CAMUI rocket
Conventional hybrid rocket

Demonstration model of CAMUI hybrid rocket
Demonstration model of CAMUI hybrid rocket

PMMA/LOX as propellants
E Generates 50 kgf thrust with a combustion chamber of 50 mm in inner diameter.
E The development of fundamental technology has been made. The next step is verification experiment necessary to scale-up of the engine.
E Launch experiments have been made successfully in March 2002, January 2003, March 2004, and March 2005.

CAMUI rocket Launch experiment
The launch vehicle The launch experiment

The design of the vehicle was made using examples from the vehicle developed by Yuasa Lab.

Winged launch, gliding, gliding turn, and recovery experiment
Winged launch

A delta wing of 1000 mm in width and 1,280 mm in length was mounted on the 50 kgf CAMUI rocket. The vehicle launched with the launch angle of 50 degrees shifted to horizontal gliding, made a 180 degrees gliding turn, and softly landed on the snow ground.
The initial and final weights were 16.5 kg and 15.3 kg, respectively.
The elevon on the delta wing was radio controlled from the ground.
A barometer and an acceleration sensor obtain the histories of height and trajectory.

Experimental result
The vehicle reached 220 m height and moved to horizontal flight and made a gliding turn. The gliding velocity was almost constant at 140 km/h, which agrees with the terminal velocity of the vehicle.
The vehicle was successfully recovered without injury. An onboard camera recorded the movie of the image from the flying vehicle.
The fact that the vehicle was recovered from the terminal velocity gliding demonstrates that the winged recovery of the vehicle from the stratosphere flight is possible.

The flight movie by the onboard camera is here


Division of Mechanical and Space Engineering, Graduate School of Engineering, Hokkaido University