Vehicle Overview
Note: Payload
performance and estimated cost provided for information only. If you are interested
in contracting for launch services, we recommend that you contact the service provider
directly using the information above.
| |
LEO Payload*
(30.0 deg., 200 km) |
SSO Payload*
(98.0 deg., 800 km) |
Estimated
Launch Price |
Configuration |
Launch Mass |
J-1 |
2,200 lb
1,000 kg |
N/A |
US $52 M |
SRB 1st
stage
M-23 2nd stage
M-38 3rd stage |
195,000 lb
88,500 kg |
J-1A
(Upgrade) |
7,700 lb
3,500 kg |
2,200 lb
1,000 kg |
US $45 M |
NK-33 1st
stage
LNG 2nd stage |
269,600 lb
122,300 kg |
* Performance from NASDA Web Site.
J-I Vehicle COnfiguration
Test Flight #1 |
Stage 1
SRB |
Stage 2
M-23 |
|
Fairing |
| Length |
68.9 ft
21 m |
22 ft
6.7 m |
|
22.6 ft
6.9 m |
| Diameter |
5.9 ft
1.8 m |
5.9 ft
1.8 m |
|
5.4 ft
1.65 m |
| Gross Mass |
156,000 lb
70,800 kg |
38,000 lb
17,200 kg |
|
1325 lb
600 kg |
Propellant
Propellant
Mass |
????
130,300 lb
59,100 kg |
????
22,700 lb
10,300 kg |
|
|
Engine**
Thrust
Isp |
SRB
350,500 lbf SL
1,600 kN SL
273 sec SL |
M-23
118,000 lbf
525 kN
282 sec |
|
|
| Number of Engines |
1 |
1 |
|
|
| Nominal Burn Time |
94 sec |
73 sec |
|
|
| |
Test Flight #2 |
Stage
1
SRB-A |
Stage
2
M-23 |
Stage
3
M-38 |
Fairing |
| Length |
43.6
ft
13.3 m |
22
ft
6.7 m |
8.9
ft
2.7 m |
22.6
ft
6.9 m |
| Diameter |
8.2 ft
2.5 m |
8.2 ft
2.5 m |
4.9 ft
1.5 m |
5.4 ft
1.65 m |
| Gross Mass |
163,600
lb 74,200 kg |
28,880
lb
13,100 kg |
7940
lb
3600 kg |
1325
lb
600 kg |
Propellant
Propellant
Mass |
HTPB
143,300 lb
65,000 kg |
HTPB
22,700 lb
10,300 kg |
HTPB
7275 lb
3300 kg |
|
Engine**
Thrust
Isp |
SRB-A
507,000 lbf SL
2,255 kN SL
280 sec |
M-23
118,000 lbf
525 kN
282 sec |
M-38
29,800 lbf
132 kN
294 sec |
|
| Number of Engines |
1 |
1 |
1 |
|
| Nominal Burn Time |
99
sec |
73
sec |
87
sec |
|
** Note: Vacuum engine
performance unless otherwise specified.
J-IA Vehicle COnfiguration (Estimated)
J-1 Upgrade |
Stage
1 |
Stage
2 |
Fairing |
| Length |
81.7
ft
24.9 m |
30.8
ft
9.4 m |
22
ft
6.7 m |
| Diameter |
10 ft
3.0 m |
10 ft
3.0 m |
10 ft
3.0 m |
| Gross Mass |
246,100
lb
111,600 kg |
20,000
lb
9,070 kg |
3,500
lb
1,590 kg |
Propellant
Propellant Mass |
LOX
/ RP-1
226,400 lb
102,700 kg |
LOX
/ LNG
17,200 lb
7,800 kg |
|
Engine**
Thrust
Isp |
NK-33
339,000 lbf SL
1,505 kN SL
297 sec SL |
TBD
22,500 lbf
100,000 N
368 sec |
|
| Number of Engines |
1 |
1 |
|
| Nominal Burn Time |
198 sec |
281
sec |
|
** Note: Vacuum engine performance
unless otherwise specified.
|
