Lift-off Vehicle = 0 sec |
Omid |
Rasad |
Navid |
Fajr-3 |
Burnout first
stage
|
|
+ 152 |
|
|
Separation first
stage
|
|
+ 152 |
|
|
Coast phase
|
|
+ 152 ... + 194 |
|
|
Jettison fairing
|
|
+ 194 |
|
|
Ignition second
stage
|
|
+ 215 |
|
|
Burnout second
stage
|
|
+ 460 |
|
|
Separation
spacecraft
|
|
+ 465 |
|
|
The Iranian Aerospace Organization
(IAO) with the support of the ministry of defense and armed logistics:
"The latest video of Rasad satellite
being launched in space, that was received by using the telemetry (sub)system,
is published.
The video images were filmed using cameras that were attached to the body
of the SLV and filmed the different stages of the launch, the separation
of the first stage booster, the separation of the cone and the distance
it has from earth.
The cameras were connected to the body of the rocket in the following
configuration:
- Top-left camera, outside, connected to the second stage facing downward.
- Bottom-left camera, outside, connected to the second stage facing upward.
- Top-right camera, inside in the payload shroud.
- Bottom-right camera, inside, between stages two and one, and next to
the second stage engine.
|
The first stage booster had
a burn time of 152 seconds, as can be seen
on camera 01.
After burn out of the first stage and coupled with the fact that the vehicle
had reached an altitude of 70 km above ground, and had reached a velocity
of 2400 m/s, the first stage was separated and the second stage booster
started to operate (can be witnessed on cameras 1 and 3). On continuation
of its path, after the second stage booster (small solid rockets)
has burned for 42 seconds, had reached an
altitude of 120 km and a velocity of 2550 m/s, the payload shroud (the
housing covering the satellite at the tip) was separated (this can be
witnessed on cameras 1, 3 and 4).
After that was done, and the second stage booster has burned for a total
of 313 seconds, the SLV has reached the correct
velocity and altitude for injection of the satellite, an altitude of 260
km and a velocity of 7600 m/s, the satellite was injected into the orbit
(can be witnessed on cameras 2 and 3)."
|
Estimation of the
terminal
velocity (dV)
[dV = Isp [Ns/kg] * ln (Mf/Me)]
Safir-1
(Omid)
|
vac Isp (sec) |
=Ns/kg |
Mf (kg) |
Me (kg) |
Mf/Me |
ln Mf/Me |
Isp * ln (Mf/Me) |
1st |
272 |
2667 |
25,183 |
6,983 |
3.606 |
1.28272
|
3,421
|
|
|
|
|
|
|
|
|
2nd |
279 |
2736 |
3,425
|
375
|
9.140
|
2.21264
|
6,054
|
|
|
|
|
|
|
dV Total*
|
9,475 [m/sec]
|
* dV
(vacuum); without losses of about 15-20% of velocity
Therefore is the real dV nearby
7,817 m/sec
for payload 27 kg
Safir-1A
(Rasad)
|
vac Isp (sec) |
=Ns/kg |
Mf (kg) |
Me (kg) |
Mf/Me |
ln Mf/Me |
Isp * ln (Mf/Me) |
1st |
283 |
2775 |
25,248 |
7,048 |
3.582 |
1.27595
|
3,541
|
|
|
|
|
|
|
|
|
2nd |
290 |
2844 |
3,490
|
440
|
7.924
|
2.06994
|
5,887
|
|
|
|
|
|
|
dV Total*
|
9,428 [m/sec]
|
* dV
(vacuum); without losses of about 15-20% of velocity
Therefore is the real dV nearby
7,778 m/sec for
payload 15 kg
Safir-1B
(Navid)
|
vac Isp (sec) |
=Ns/kg |
Mf (kg) |
Me (kg) |
Mf/Me |
ln Mf/Me |
Isp * ln (Mf/Me) |
1st |
283 |
2775 |
25,164 |
6,964 |
3.614 |
1.28471
|
3,565
|
|
|
|
|
|
|
|
|
2nd |
290 |
2844 |
3,497
|
446
|
7.831
|
2.05808
|
5,853
|
|
|
|
|
|
|
dV Total*
|
9,418 [m/sec]
|
* dV
(vacuum); without losses of about 15-20% of velocity
Therefore is the real dV nearby 7,770
m/sec for payload 50 kg
Safir-1B+
(Fajr)
|
vac Isp (sec) |
=Ns/kg |
Mf (kg) |
Me (kg) |
Mf/Me |
ln Mf/Me |
Isp * ln (Mf/Me) |
1st |
295 |
2893 |
25,261 |
7,061 |
3.578 |
1,27467
|
3,688
|
|
|
|
|
|
|
|
|
2nd |
290 |
2844 |
3,503
|
453
|
7.732
|
2.04534
|
5,817
|
|
|
|
|
|
|
dV Total*
|
9,505 [m/sec]
|
* dV
(vacuum); without losses of about 15-20% of velocity
Therefore is the real dV nearby
7,841 m/sec for
payload 52 kg
|