Also situated at the base is a PCM unit for telemetry acquisition and an S-band telemetry transmitter. Power is supplied by 28 volt silver-zinc triggered batteries. In the interstage section on top of the motor is the pyrotechnic activation unit for motor ignition, separation from the launch platform, and detonation of the cutting cords for motor destruction. 645 x 875 pixels. The motor with 9 tonne solid propellant burns for 52 s and delivers an impulse of 24,500 kNs with an average thrust of 40 tonne.
Control is done by injecting strontium perchlorate into the motor flame.
It is stored in a torus around the nozzle throat and pressurized by means of helium. The second stage also houses the receivers for destruct in case of malfunction. The destruct channels are redundant and destruct is initiated on receipt of a destruct signal or in case of loss of the carrier wave. 640 x 324 pixels. An aluminium aerodynamic sleeve is utilized to provide a constant external diameter between the lower interstage of stage 1 and the avionic section of stage 3.