Purpose of the flight and payload description

Microgravity can be achieved by different means: drop towers, parabolic flights, or Space based platforms like satellites or the International Space Station. On one hand the first two systems are low cost but have a short duration, on the other hand space based systems have longer durations but huge costs.

A half way option is the use of aerodinamically designed vehicles that droped in free-fall from a balloon flying in the stratosphere can offer between 30 and 60 seconds of good quality microgravity environment for scientific purposes.

On this regard ISAS (Institute of Space and Astronautical Science, presently a part of JAXA) had developed balloon-dropped experiment systems since 1978 achieving 10 seconds of microgravity in 1983. The main setback for that project was the limitations on the balloon technology of those years.

However Japanese scientists returned to this concept and developed since 2004 the Balloon-based Operation Vehicle (BOV). It consists of two main parts: a flight capsule body rocket-like shaped (outer shell) and an experiment module that floats free in the interior of the capsule (inner shell). The system is carried to the stratosphere by a new kind of balloon capable of reaching 40 kms of altitude, thus assuring 30 seconds of good quality microgravity. To allow this, the inner shell must be isolated from the outer shell so no disturbance forces work on it during the free-fall. At left can be seen a detailed scheme (click to enlarge). BOV measures four meters of length, 0.55 mts of diameter and weights 310 kgs. As can be seen in the image it have a rocket-like shape to reduce aerodynamic disturbance.

The inner shell can fall freely since the outer shell measures it's relative position with laser displacement sensors activating several gas-jet thrusters to avoid any colition with it and let him free from the dynamic pressure and other aerodynamic disturbances. As Air drag is almost proportional to the square of the velocity and also proportional to the air density, to achieve 30 seconds of microgravity duration, 100 Newtons of thrust are required. Therefore, the body have 16 cold gas jet thrusters, four of them located in the front and the remaining twelve in the rear.

This system is all managed by a Central Procees Unit running at 200MHz, Linux based and powered by lithium-ion batteries (12V and 24V). This CPU stores house-keeping data as temperature, acceleration, tank pressure and so on and also transmits it to the ground via a telemetry link. Four video cameras are located in different BOV parts to obtain images of the experiment and location of the inner shell as well a downward external view.

In the middle of BOV's body, there are four laser displacement sensors to measure clearance between the inner shell and the outer shell. This system estimates the center position of the inner shell by the Newton-Raphson method and proceeds to fire the thrusters to correct the outer shell location to maintain it isolated from the inner shell. Attitude control is also necessary to maintain stable micro gravity experiments, so there are three fiber optical gyros to measure the body attitude ans send to the thrusters the correction firings. To realize these corrections each of the 16 thrusters are commanded to be fired as required using a distribution matrix calculated from the relation between each thruster's force and the total force and torque output that actuates on BOV's body.

Inside the inner shell there are space to allocate the microgravity experiment payload. Since the experimental module is isolated from the data handling and communication components located on the outer shell, telemetry data such as video image or accelerometer output is transmited internally through a wireless system which also is used to transmit commands to the experimental module. To reduce the power consumption all these commands are transmited by infrared communication.

Plans of future development of the system include the addition of an air-breathing engine called "S-Engine" which currently is being developed by JAXA. This higher thrust propulsion system is essential to compensate rapidly increasing air-drag. This will allow to achieve up to 60 seconds of microgravity in the future.

Details of the balloon flight

Balloon launched on: 5/29/2007 at 6:03 jst
Launch site: Sanriku Balloon Center, Iwate, Japan  
Balloon launched by: Institute of Space and Astronautical Science (ISAS) / Japan Aerospace Exploration Agency (JAXA)
Balloon manufacturer/size/composition: Zero Pressure Balloon model B300 300.000 m3
Flight identification number: B300-1
End of flight (L for landing time, W for last contact, otherwise termination time): 5/29/2007 at 9:40 jst
Balloon flight duration (F: time at float only, otherwise total flight time in d:days / h:hours or m:minutes - ): 4 h 25 m
Landing site: On the sea 30 km E of Kamaishi, Japan
Payload weight: 300 kg

The balloon was launched by semi-dynamic method on May 29 at 6:03 local time. After a nominal ascent at 250 meters per second and a displacement to the east of 80 km over the sea, during 2 hours and 40 minutes, the balloon reached flight altitude of 41 km. After that it started a westward path until 9:40 local time when a command was transmited to let free the microgravity experiment which started a free fall. Ten minutes later the balloon was destructed and fell also to the sea.

The experiment was recovered with help of a ship and an helicopter from the sea 20 km east of Kamaishi.

This was the second flight of the microgravity experiment nomenclated as BOV-2. This time, as payload was located in the inner shell a Japanese sparkler that was set to ignite at the time of the starting of the microgravity phase of the flight.

After released the system achieved near 30 seconds of micro gravity with good quality. The Japanese sparkler burned in first several seconds but after that the fire went out and wasn't able to ignite again since there was no oxygen present.

After the experiment was over, the pilot-parachute was opened for speed reduction and when BOV achieved a height of 7.5 km the main parachute was released.

Post flight examination of the data concluded that the inner shell and the BOV�s body collided 27 seconds after the beginning of the microgravity time. This was caused by rotation of the inner shell which began when BOV was separated from the balloon. Since the shape of the inner shell is oval, it collided with the rocket body earlier than expected.

Nevertheless all systems performed well and offered a good microgravity environment.

External references

Images of the mission


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