Chang Zheng 5 Vehicle Configurations
Vehicle Components
Since 1970, Chinas orbital launches have
been performed by Chang Zheng (CZ, or Long March) rockets derived from Dong
Feng (DF, or East Wind) ballistic missiles.
The current CZ-2 to CZ-4 series derived from the two-stage DF-5 intercontinental range ballistic missile. This series, which first flew in 1973, can haul 2.8
to 9.5 metric tons (tonnes) to low earth orbit (LEO) and 2.6 to 5.1 tonnes to
geosynchronous transfer orbit (GTO). The CZ-2F
variant has been used to launch crewed Shenzhou spacecraft.
Now Chinas Academy of Launch
Vehicle Technology (CALT) is working toward development of a more powerful launch vehicle. CZ-5, Chinas first pure space launch vehicle
design, is expected to be able to haul up to 25 tonnes to LEO or up to 14 tonnes to GTO. The new EELV-class rocket, which will not fly
until 2014 at the earliest, will almost certainly support Chinas future manned
spaceflight and lunar exploration plans.
CZ-5 will be powered by a new series of
liquid engines, including a 120 tonne thrust LOX/Kerosene engine identified as YF-100 and
a 50 tonne thrust LOX/LH2 engine named YF-77. The
new engines will do away with the toxic hypergolic UDMH/N2O4 propellants used by the DF-5
based Long March rockets.
Engine development began in 2000-2001,
with testing directed by the China National Space Administration (CNSA) commencing in
2005. Versions of both engines had been
successfully tested by mid-2007.
A complete family of CZ-5 options was
initially envisioned, based on a modular approach. Three
module types, with diameters of 2.25 meters, 3.35 meters, and 5.0 meters, were described
in some detail during the 2001-2003 period [1]. More
recent reports suggest that the core stage diameter may have increased beyond 5 meters.
Original plans called for the 2.25 meter
module to be powered by one 120 tonne thrust kerosene/liquid oxygen (LOX) engine. Two such engines would boost the 3.35 meter module. The 5 meter diameter core stage would use two 50
tonne thrust liquid hydrogen (LH2)/LOX engines. Any
of the modules could be used as first stage units on small and medium launch vehicles. The two smaller modules could also serve as
strap-on boosters for the 3.35 and 5 meter core stages, in combinations of two or four.
Three upper stages, one in each of the
three module diameters, were also planned. The
5 meter upper stage would be powered by two LH2/LOX engines of 8 tonnes thrust each,
similar to the YF-75 engines that currently power the CZ-3B upper stage. The existing CZ-4A second stage might be used as
the 2.25 meter diameter upper stage. A new
3.35 meter kerosene upper stage, powered by four new 15 tonne thrust engines, was also
contemplated.
Development would initially focus on the
5 meter core configurations because existing Long March rockets already handle the payload
range covered by the smaller CZ-5 designs. The
5 meter diameter, 31 meter-long core would weigh 175 tonnes at liftoff, including 158
tonnes of propellant. The core will be
augmented by four strap-on boosters, with either two of each diameter (2.25 and 3.35
meter) or with all four of the same diameter. CZ-5
will fly as a 1.5 stage launcher for LEO missions, and as a 2.5 stage vehicle for GTO and
deep-space missions.
The most powerful CZ-5 version,
identified as CZ-5-504 and equipped with four 3.35 meter modules strapped onto
a 5 meter core stage, would liftoff on more than 1,080 tonnes of thrust produced by a
total of ten engines, suggesting a possible gross liftoff weight exceeding 800 tonnes. This CZ-5 version, if built as originally planned,
would be the worlds most capable launch vehicle in the post-shuttle era, able to
boost more payload mass to orbit than any other launch vehicle. Russias new Angara 5 would not match it in
any category. NASAs Ares I would weigh
more, and both Ares I and Ariane 5 ECA would produce more liftoff thrust, but neither
would out-haul Chinas new heavy lifter.
After the heavy lift versions are
developed, work could begin on small and medium launchers based on the 2.25 and 3.35 meter
modules. These would replace existing Long
March vehicles, but planners hint that this process would occur over a very long period of
time. There are no current plans to replace the CZ-2F human launch vehicle, for
example. As a result, plans given for the small
and medium launchers are unlikely to proceed exactly as originally described.
CZ-5 will be launched from a new site
near Wenchang on Hainan Island off China's southern coastline. It also seems likely
that some CZ-5 versions could fly from some of China's existing launch centers.
Vehicle Configurations
|
LEO
Payload
(metric tons)
|
Geosynchronous
Transfer Orbit
Payload
(metric tons)
Orbit Inclination
not Specified
(using HO second stage)
|
Configuration |
LIftoff
Height
(meters) |
Liftoff
Mass
(metric tons) |
CZ-540(/HO) |
10 t |
6 t |
5m core + 4x2.25m strap-ons
+ optional "HO" 2nd stage |
58 m |
490 t |
CZ-522(/HO) |
20 t |
11 t |
5m core +
2x2.25m strap-ons
+ 2x3.35m strap-ons
+ optional "HO" 2nd stage |
60 m
|
630 t
|
CZ-504(/HO) |
25 t |
14 t |
5m core +
4x3.35m strap-ons
+ optional "HO" 2nd stage |
62 m |
810 t |
CZ-5-340(/HO) |
10 t |
6 t |
3.35m
core + 4x2.25m strap-ons
+ 3.35m "KO" 2nd stg
+ optional "HO" 3rd stg |
55 m |
522 t |
CZ-5-320(/HO) |
3 t |
1.5 t |
3.35m
core + 2x2.25m strap-ons
+ 3.35m "KO" 2nd stg
+ optional "HO" 3rd stg |
52 m |
384 t |
CZ-5-200 |
1.5 t |
N/A |
2.25m
core + 2.25m 2nd stg |
38 m |
86 t |
Vehicle Components
|
2.25 m
Module |
3.35 m
Module |
5 m
Module |
2.25 m
Stage 2
|
3.35 m
Stage 2
"KO" |
3.35 m
Stage 3
"HO" |
5 m
Stage 2
"HO" |
Diameter (m) |
2.25 m |
3.35 m |
5.0 m |
2.25 m |
3.35 m |
3 m |
5 m |
Length (m) |
26.3 m (est) |
26.3 m |
31 m |
8 m (est) |
8 m (est) |
12.38 m |
10 m (est) |
Empty Mass
(tonnes)
|
6 t |
12 t |
17 t |
2 t (est) |
7 t (est) |
2.8 t |
3.52 t (est) |
Propellant Mass (tonnes) |
63 t |
135 t |
158 t |
13 t (est) |
53 t (est) |
18.2 t |
22.9 t |
Total Mass (tonnes) |
69 t |
147 t |
175 t |
15 t (est) |
60 t (est) |
21 t |
26.4 t (est) |
Engine |
YF-100 |
YF-100 (2ea) |
YF-77 (2ea) |
1x15t |
4x15t |
YF-75 (2ea) |
YF-75 (2ea) |
Engine Mfgr |
CAALPT |
CAALPT |
CAALPT |
CAALPT |
CAALPT |
CAALPT |
CAALPT |
Fuel |
Kerosene |
Kerosene |
LH2 |
Kerosene |
Kerosene |
LH2 |
LH2 |
Oxidizer |
LOX |
LOX |
LOX |
LOX |
LOX |
LOX |
LOX |
Thrust
(SL tons) |
122.35 t |
244.7 t |
110 t |
|
|
|
|
Thrust
(Vac tons) |
136.6 t |
273.2 t |
134.6 t |
15 t |
60 t |
16.3 t |
16.3 t |
ISP (SL sec) |
300 s |
300 s |
333 s |
|
|
|
|
ISP (Vac sec) |
336 s |
336 s |
438 s |
335 s (est) |
335 s (est) |
438 s |
438 s |
Burn Time (sec) |
155 s (est) |
165 s (est) |
500 s (est) |
290 s (est) |
296 s (est) |
615 s (est) |
615 s (est) |
No. Engines |
1 |
2 |
2 |
1 |
4 |
2 |
2 |
Comments
|
|
|
|
|
|
|
|
|
2.25 m
Payload
Fairing |
3.35 m
Payload
Fairing
|
5m
Payload
Fairing
|
Diameter (m) |
2.25 m |
3.35 m |
5.0 m |
Length (m) |
5-7 m (est) |
5-10 m (est) |
12-24 m (est) |
Empty Mass (tonnes) |
t |
t |
t |
References
[1]
The New Generation Launch Vehicles of Long March Family, Tangming Cheng, Xiojun
Wang, Dong Li, Beijing Institute of Astronautical Systems Engineering, 54th
International Astronautical Congress of the International Astronautical Federation, the
International Academy of Astronautics, and the International Institute of Space Law,
October 2003, Bremen, Germany.
Last Update: March 2, 2008 |