Chennai, Feb 6 (UNI) The Second Developmental Flight of the
Small Satellite Launch Vehicle (SSLV-D2) carrying the Earth
Observation Satellite (EOS-07) and two co-passenger satellites
will take place on February 10 from the spaceport of Sriharikota.
Indian Space Research Organisation (ISRO) sources on Monday
said the SSLV-D2 will lift off from the First Launch Pad at 0918 hrs
on Friday.
While EOS-07 will be the primary satellite, the two co-passengers
satellites are Janus-01 from Antaris US Firm and the other is from
a domestic player.
SSLV-D2 will launch a total payload mass of about 334 kg including
EOS-07 satellite and the two co-passenger satellites.
The satellite will be injected into a Circular Low Earth Orbit at an
altitude of 450 km with an inclination of 37.2 Deg to the equator.
The SSLV is designed to be affordable and amenable to industry
production and will function as a launch-on-demand platform for
Mini, Micro or Nano satellites.
It is a three-stage vehicle with all solid propulsion stages and liquid
propulsion-based Velocity Trimming Module (VTM) as the terminal
stage.
The launcher also targets many novel features including low
turn-around time, flexibility in accommodating multiple satellites,
launch-on-demand, minimal launch infrastructure requirements,
etc.
The first Developmental FLight of SSLV-D1/E0S-02 that took place
on August seven last year was unsuccessful.
The objective of the mission was to inject EOS-02 satellite into a
circular orbit of 356.2 km with an inclination of 37.21 Deg. It also
carried Azaadisat, a student satellite.
However, the spacecraft were injected into a highly elliptical unstable
orbit due to a shortfall in velocity, leading to their decay and deorbiting
immediately, in spite of the normal performance of all solid propulsion
stages.
The orbit achieved was 360.56 km x 75.66 km with an inclination
of 36.56 deg.Initial investigations with the flight data indicated that
the lift-off of SSLV D1 was normal along with normal performance
of all solid propulsion stages.
However, the mission could not be achieved due to an anomaly
during the second stage (SS2) separation, which triggered a mission
salvage mode (which is a procedure adopted to attempt minimum
stabilized orbital conditions for the Spacecraft in case of an anomaly
in the vehicle system).
The Failure Analysis Committee (FAC) of ISRO, which went into the
causes of the failure, found that vibration distance for a short duration
led to the failure.
In its report, the FAC said "subsequent detailed analysis of the flight
events and observations ranging from countdown, lift-off, propulsion
performance, stage separations and satellite injection revealed that
there was a vibration disturbance for a short duration on the Equipment
Bay (EB) deck during the SS2 separation, that affected the Inertial
Navigation System (INS), resulting in declaring the sensors faulty by
the logic in Fault Detection & Isolation (FDI) software
Considering the clear identification of the cause of the flight anomaly
and suggested corrective actions, the SSLV-D2 is being executed
complying to the recommendations, its satisfactory implementation,
review and approval by the authorized committees.
UNI GV 1603