CZ-2E - Blackboard

CHINA
CZ-2E
1. IDENTIFICATION
1.1
Name
CZ-2E
1.2
Classification
Ø Family
Ø Series
Ø Versions
:
:
:
CZ
CZ-2
CZ-2E
CZ-2E / EPKM (1)
CZ-2E / ETS
CZ-2E / A
:
Ø Category
Ø Class
Ø Type
:
:
:
SPACE LAUNCH VEHICLE
Medium Launch Vehicle (MLV)
Expendable Launch Vehicle (ELV)
1.3
Manufacturer
1.4
Development manager :
Ministry of Astronautics
P.O. Box : 848, Beijing, CHINA
Tel: 89 66 55
Tlx: 20026 MOAFA CN
1.5
Vehicle operator
China satellite Launch Telemetry and tracking & Control general (CLTC)
Mr. Zhang Yougen
No. 4 Beihuan Zhonglu, Beijing, CHINA
Tel: 65 72 79
Tlx: 222695 CLTC CN
1.6
Launch service agency :
:
Beijing Wan Yuan Industry Corporation (BWYIC)
Building No.19, Wan Yuan Road, Beijing, CHINA
P.O. Box : 92000-28, Beijing
Tel: 79 99 80
Tlx: 22097 BWYIC CN
Ø CHINA
China Great Wall Industry
Corporation (CGWIC)
Mr. Zhang Jianye
17 Wenchang Hutong, Xidan,
Beijing, CHINA
P.O. Box: 847 Beijing
Tel: 83 11 808
Tlx: 22651 CGWIC CN
Fax: 83 11 809
Ø USA
GW Aerospace Inc.
Mr. Zuoyi Huang
21515 Hawthorne Blvd. Ste 1035
Torrance, CA 90503, USA
Tel: (213) 373-2334
Becker and Associates
VIRGINIA
1.7
Launch cost
:
50 M$ (1999)
(1) CZ-2E / EPKM: strictly speaking, CZ-2E has two stages and a capacity around 9 t into LEO. This payload
can be used to carry an EPKM motor to send a satellite into GTO.
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CZ-2E
2. STATUS
2.1
Vehicle status
:
Operational
2.2
Development period
:
Approval of the CZ-2E project (growth version of CZ-2C) was made
in 1988
2.3
First launch
:
16.07.1990 (with 2 satellites)
3. PAYLOAD CAPABILITY AND CONSTRAINTS
CZ-2E is based on the technologies of CZ-2C. CZ-2E takes the lengthened CZ-2C as the core stages, with
four liquid boosters.
CZ-2E launch vehicle consists of four versions:
• basic version:
two-stage CZ-2E for LEO missions,
• extended basic version: two-stage CZ-2E(A) with stretched strap-on boosters and an enlarged payload
shroud,
• three-stage version-1:
CZ-2E / ETS for LEO (for orbits > 400 km) and SSO missions; ETS is a threeaxis stabilized upper stage which is capable of delivering one or more satellites,
• three-stage version-2:
CZ-2E/EPKM for GTO missions; EPKM is a spin stabilized upper stage.
3.1
Payload capability
Typical mission performances of CZ-2E versions are shown in Table 1:
LEO
200 km
LEO
1 000 km
SSO
1 000 km
i = 28.5° i = 53° i = 53° i = 86°
GTO
PLANETARY
200 x 38 786 km
I = 28.5 °
See figure
9 500
8 400
-
-
-
-
1 to 5
CZ-2E/ETS
-
-
6 060
4 930
4 340
-
3 to 6
CZ-2E/EPKM
-
-
-
-
-
3 500
CZ-2E
N/A
7
TABLE 1 : CZ-2E CAPABILITIES (kg)
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CZ-2E
3.1.1 Low Earth Orbits
Ø Circular orbits
FIGURE 1 - CZ-2E PAYLOAD CAPABILITY FOR CIRCULAR ORBIT MISSION (JIUQUAN)
FIGURE 2 - CZ-2E PAYLOAD CAPABILITY FOR CIRCULAR ORBIT MISSION (XICHANG)
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CZ-2E
FIGURE 3 - CZ-2E / ETS PAYLOAD CAPABILITY FOR CIRCULAR ORBIT MISSION (JIUQUAN)
Ø Elliptical orbits
FIGURE 4 - CZ-2E PAYLOAD CAPABILITY FOR ELLIPTIC ORBIT MISSION (JIUQUAN)
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CZ-2E
FIGURE 5 - CZ-2E PAYLOAD CAPABILITY FOR ELLIPTIC ORBIT MISSION (XICHANG)
FIGURE 6 - CZ-2E / ETS PAYLOAD CAPABILITY FOR ELLIPTIC ORBIT MISSION (JIUQUAN)
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CZ-2E
3.1.2 Geosynchronous and Interplanetary Orbits
The payload capability in GTO (i: 28.5, perigee: 300 km) ranges from 1.9 t to 3.5 t, according to the upper
stage used:
UPPER STAGE
PAYLOAD CAPABILITY (kg)
PAM - D2
1 900
PAM - A
1 950
AMS
1 650
SCOTS
2 490
HPPM
2 930
EPKM
3 500
FIGURE 7 - CZ-2E / EPKM PAYLOAD CAPABILITY
FOR GEOSYNCHRONOUS TRANSFER MISSION (XICHANG)
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CZ-2E
FIGURE 8 - CZ-2E / EPKM PAYLOAD CAPABILITY FOR PLANETARY MISSION (XICHANG)
3.1.3 Injection accuracy
Ø Two-stage CZ-2E injection accuracy
The injection accuray for typical LEO missions (h = 200 km, i = 53° and i = 28.5°) launching from Jiuquan
and Xichang is shown in Table 2.
SYMBOL
PARAMETERS
DEVIATION
(1 σ )
∆a
Semi-major Axis
2.3 km
∆i
Inclination
0.05°
∆Ω
Right Ascension of Ascending Node
0.10°
∆Hp
Perigee Altitude
2.0 km
TABLE 2 - INJECTION ACCURACY FOR TYPICAL LEO MISSION FROM JIUQUAN
(h = 200 km, i = 53° and i = 28.5°)
Ø CZ-2E / ETS injection accuracy
The injection accuray for typical LEO missions (h = 1 000 km, i = 53° and i = 86°) launching from JSLC is
shown in Table 3.
SYMBOL
PARAMETERS
DEVIATION
(1 σ )
∆a
Semi-major Axis
∆i
Inclination
0.05°
∆Ω
Right Ascension of Ascending Node
0.10°
∆Hp
Perigee Altitude
4.0 km
3.0 km
TABLE 3 - INJECTION ACCURACY FOR TYPICAL LEO MISSION FROM JIUQUAN
(h = 1 000 km, i = 53° and i = 86°)
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CZ-2E
Ø CZ-2E / EPKM injection accuracy
The injection accuray for typical GTO missions (hp = 200 km, ha = 35 786 km and i = 28.5°) from Xichang
is shown in Table 4.
SYMBOL
PARAMETERS
∆a
Semi-major Axis
∆i
Inclination
∆Ω
Right Ascension of Ascending Node
∆Hp
Perigee Altitude
DEVIATION
(1 σ )
650 km
0.3°
0.4°
6.0 km
TABLE 4 - INJECTION ACCURACY FOR TYPICAL GTO MISSION
(hp = 200 km, ha = 35 786 km and i = 28.5°)
3.2
Spacecraft orientation and separation
Ø Deployment mechanism type: spring release
• Separation Attitude
For the CZ-2E and CZ-2E / ETS, the L/V and ETS attitude control system adjusts the pointing direction
of the spacecraft/launch vehicle stack according to user's requirements. It will take about 100 s. The
pointing error at separation is < 1.5°.
• S/C Tip-off Rates
The angular rates introduced into the S/C at separation consist of two parts: one from the separation
system and the other from the residual rates of ETS or LV second stage. The angular rates depend on
the separation scenarios of the S/C separation system.
For spin-up separation scenario, the total angular rate shall not exceed 10°/s in x-axis and 2°/s in y & z
axis.
For non-spin-up separation scenario, the residual rates of ETS or L/V stage-2 will not exceed 0.5°/s in
all axes, and the angular rates from the dispenser (separation system) shall not exceed 1.5°/s in x, y
and z axis, so that the total angular rate shall not exceed 2.0 °/s in x, y and z axis.
• Separation Velocity
When conducting single launch, for the two-stage CZ-2E and for the CZ-2E/ETS, the separation force
generated by the L/V separation mechanism will give the S/C a velocity in a range of 0.5 ~ 0.9 m/s.
When conducting multiple-launch, CZ-2E can provide the S/Cs with different separation velocities in
order to avoid re-contact after separation.
• Spin-up
For two-stage CZ-2E, the attitude-control system of the L/V can spin up the S/C up to 7 rpm along the
L/V longitudinal axis.
For CZ-2E/ETS, the attitude-control system of the ETS is able to spin up the ETS/S/C stack according
to user's need.
CZ-2E/EPKM can spin up the S/C according to the user's need.
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CZ-2E
• Collision and Contamination Avoidance Maneuver
Following the S/C separation, the L/V will perform a series of manœuvres to prevent any collision with
the S/Cs and minimize S/Cs exposure to L/V contaminants. The manœuvres to be performed by the
L/V are different for the different L/V configurations which consist of stage-2 insertion and ETS
insertion.
• Stage-2 Insertion
For stage-2 insertion, the maneuvers are performed by the second stage.
The second stage flight can be divided into 5 phases: main engine working phase, Vernier engines
working phase, re-orientation phase, S/C separation phase and vehicle de-orbit phase.
At the time of main engine shut-off, L/V control system send signals to shut off the valves of the
engine for the propellant supply so as to shut the engine.
The subsequence after shut-off of the Vernier engines is:
-
to adjust the S/C to the attitude of separation,
-
to separate the S/C,
-
to adjust the L/V stage-2 to the attitude of de-orbit,
-
to re-open the valves.
At the time of Vernier engines shut-off, there are residual propellants and pressurization gas in the
tanks. After the stage-2 is re-orientated to the de-orbiting direction, the de-orbiting of stage-2 will be
carried out by depletion of the propellants.
• ETS Insertion
For ETS insertion, the manœuvres are performed by the ETS.
After the S/C separate from the ETS, the ETS will re-orient to de-orbiting direction.
The de-orbiting of ETS will be carried out by depletion of the attitude control system.
3.3
Payload interfaces
3.3.1 Payload compartments and adaptors
Ø Payload /launch vehicle interfaces and adaptors
• CZ-2E / ETS Mechanical Interface
ETS consists of OMS and Dispenser. CZ-2E / ETS provides two types of mechanical interface:
-
type A mechanical interface, used for connecting S/Cs laterally,
-
type B for connecting S/Cs from their bottom.
Type A Mechanical Interface
The S/Cs are connected to the dispenser laterally, and the dispenser is bolted on the main structure of
Orbital Maneuver System (OMS) that is connected with payload adaptor by clampband.
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CZ-2E
FIGURE 9 - ETS CONFIGURATION
FIGURE 10 - OMS
The S/Cs are connected with the dispenser by low-shock explosive nuts and separation springs.
Type B Mechanical Interface
The S/Cs are connected to the dispenser from their bottom, and the dispenser is fixed on the main
structure of the OMS, which is connected with the payload adaptor by clampband. There are 4 S/C
adaptors fixed on the main structure of the typical type B dispenser. The S/Cs are mounted on the S/C
adaptors by low-shock explosive nuts and separation springs. The separation system can provide a
S/C separation velocity according to user's requirements.
FIGURE 11 - TYPE B MECHANICAL INTERFACE
FIGURE 12 - SEPARATION SYSTEM
• CZ-2E / EPKM Mechanical Interface
The S/C adaptor is connected with the S/C on the top, and bolted with EPKM on the bottom The
EPKM is bolted with the interface adaptor, which is connected with the L/V adaptor by clampband.
When the clampband is released, the EPKM-S/C stack, together with interface adaptor, separates
from L/V adaptor. In general, S/C will control the EPKM flight as well as EPKM-S/C separation.
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CZ-2E
Ø Payload access provisions
The dome of the fairing is made of fiberglass, and the forward cone section is made of fiberglass
honeycomb sandwich except for the aluminum frames.
FIGURE 13 : FAIRING STATIC ENVELOPPE
The RF transparency rates of dome and forward cone section are all larger than 85%. Therefore, there is
no RF window on the fairing. Necessary access doors will be prepared on user's request and the opening
locations chosen through negociations with the user.
Six standard access doors are provided in the cylindrical section to permit limited access to the Payload
after the fairing encapsulation, according to User’s needs (see Figure 13).
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3.4
CZ-2E
Environments
3.4.1 Mechanical environment
The maximum longitudinal acceleration during LV flight will not exceed 5.6 g.
The variation of static longitudinal acceleration with time is depicted in the following figures:
FIGURE 14 : CZ-2E - VARIATION OF ACCELERATION WITH TIME
(200 km circular orbit mission from Jiuquan)
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CZ-2E
FIGURE 15 : CZ-2E / ETS - VARIATION OF ACCELERATION WITH TIME
(1 000 km circular orbit mission from Jiuquan)
FIGURE 16 : CZ-2E / EPKM - VARIATION OF ACCELERATION WITH TIME
(GTO mission from Xichang)
The maximum lateral acceleration will not exceed 0.4 g.
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CZ-2E
The sinusoidal vibration mainly occurs in the processes of engine ignition and shut-down, transonic flight and
stage separations. Sinusoidal and low frequency vibrations at payload-L/V interface are shown in the
following table:
Longitudinal
Lateral
FREQUENCY
(Hz)
AMPLITUDE OR ACCELERATION
(0-PEAK VALUE)
5 - 10
10 - 100
2.5 mm
1.0 g
2-5
5 - 10
10 - 100
0.2 g
2.0 mm
0.8 g
Random vibrations mainly induced by noise involve the following acceleration:
FREQUENCY RANGE
(Hz)
POWER SPECTRAL
DENSITY
ACCELERATION TOTAL
ROOT MEAN SQUARE
20 - 150
150 - 800
800 - 2 000
3 dB/octave
2
0.04 g /Hz
- 3 dB/octave
7.63 g Grms
3.4.2 Acoustic vibrations
The maximum noise under fairing is the following:
CENTRAL FREQUENCY OF OCTAVE
BANDWIDTH (Hz)
SOUND PRESSURE
LEVEL (dB)
31.5
63
125
250
500
1 000
2 000
4 000
8 000
122
128
134
139
135
130
125
120
116
Total acoustic pressure level = 142 dB
3.4.3 Shock
The maximum shock level seen by the payload occurs at the payload separation. The shock response
spectrum at Payload separation plane is shown in Figure 17.
December 2003
FREQUENCY RANGE (Hz)
RESPONSE
ACCELERATION (Q = 10)
100 - 1 500
1 500 - 4 000
9.0 dB/octave
4 000 g
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CZ-2E
FIGURE 17 : TYPICAL SHOCK RESPONSE SPECTRUM
AT S/C-L/V SEPARATION PLANE
3.4.4 Thermal environment
The environmental conditions to which the payload is submitted are summarized hereafter:
IN PAYLOAD
PROCESSING FACILITIES
INSIDE FAIRING
BEFORE LAUNCH
Temperature (°C)
15 - 25
15 - 25 (adjustable)
Relative humidity (%)
33 - 55
33 - 55
Cleanliness
100.000
100.000
ENVIRONMENT
Air flow speed inside fairing (m/s)
≤2
Noise inside fairing (dB)
≤ 70
3
Max air flow rate (m /h)
December 2003
3 000 - 4 000
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CZ-2E
Radiation heat flux density and radiant rate from the inner surface of the fairing are shown in Figure 18.
FIGURE 18 : RADIATION HEAT FLUX DENSITY AND RADIANT RATE
3.4.5 Variation of static pressure under fairing
3.4.6 Spacecraft compatibility
Ø Sinusoidal vibration
Table 5 below specifies the vibration acceleration level (zero - peak) of S/C qualification and acceptance
levels at S/C - L/V interface:
FREQUENCY
(Hz)
ACCEPTANCE
QUALIFICATION
Longitudinal
5 - 10
10 - 100
2.5 mm
1.0 g
3.125 mm
1.25 g
Lateral
0-5
5 - 10
10 - 100
0.2 g
2.0 mm
0.8 g
0.25 g
2.5 mm
1.0 g
4 oct/min
2 oct/min
DESIGNATION
Sweep rate
TABLE 5 : SINUSOIDAL VIBRATIONS SPECIFICATIONS
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CZ-2E
Ø Random vibration
Table 6 below specifies the S/C qualification and acceptance levels at S/C - L/V interface:
ACCEPTANCE
FREQUENCY
(HZ)
SPECTRUM
DENSITY
20 - 150
3 dB/octave
150 - 800
0.04 g²/Hz
800 - 2 000
- 3 dB/octave
TOTAL RMS
(grms)
QUALIFICATION
SPECTRUM
DENSITY
3 dB/octave
7.63 g
10.79 g
0.08 g²/Hz
- 3 dB/octave
1 min
Duration
TOTAL RMS
(grms)
2 min
TABLE 6 : RANDOM VIBRATIONS SPECIFICATIONS
3.5
Operation constraints
Ø Integration process
The launch vehicle is transported from CALT facility (Beijing) to launch site and undergoes various
checkouts and processing up to launch.
The typical LV working flow in Jiuquan is shown in Figure 19.
Unloading L/V and transfer to BL1
Unit tests of electrical system on-board equipment
L/V vertical integration in BLS
Tests to separate subsystem
matching test among subsystem
Overall checkouts on L/V in BLS
Payload - L/V combined
operations
Functional check and transferring
L/V from BLS to launch center
Overall checkouts on L/V in
launch center
Preparation for fuelling
Fuelling and launch
FIGURE 19 : INTEGRATION PROCESS IN JIUQUAN
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CZ-2E
The typical L/V working flow in Xichang is shown in Table 7.
Nb
T
E
C
H
1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
C 16
E 17
N 18
T
E 19
R 20
21
L
A
U
N
C
H
ITEM
To Unload LV from the Train and Transfer LV to BL1
Unit Tests of Electrical System
Tests to Separate Subsystems
Matching Test Among Subsystems
Three Overall Checkouts
Review on Checkout Results
LV Status Recovery before Transfer
To Transfer LV to Launch Center
Erecting LV on the Launch Pad
Tests to Separate Subsystems
Matching Test Among Subsystems
The first and second overall checkouts
To Transfer S/C/Fairing Stack to Launch Center
EMC Testing
The Third Overall Checkout (S/C Involved)
The Fourth Overall Checkout
Review on Checkout Results
Functional Check before Fueling, Gas Replacement of
Tanks
N2O4/UDMH Fueling Preparation
N2O4/UDMH Fueling
Launch
Total
WORKING
PERIODS
(day)
1
7
3
4
4
1
2
1
ACCUMULATIVE
PERIODS
(day)
1
8
11
15
19
20
22
23
2
3
3
2
1
1
1
1
1
2
25
28
31
33
34
35
36
37
38
40
1
0.5
0.5
41
41.5
42
42
42
TABLE 7 : L/V WORKING FLOW IN XICHANG
Ø Launch window
If weather permits, two-stage CZ-2E, CZ-2E/ETS or CZ-2E/EPKM can be launched at any time of the
day. The recommended launch window is longer than 45 mn.
4. LAUNCH INFORMATION
4.1
Launch site
Ø Jiuquan Satellite Launch Center (JSLC)
JSLC is mainly used for conducting LEO and SSO missions.
JSLC is located in Jiuquan region, Gansu Province, Northwestern China. Figure 20 shows the location of
Jiuquan, as well as the layout of JSLC.
South Launch Site is dedicated for launching two-stage CZ-2E and CZ-2E/ETS, as well as CZ-2A.
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CZ-2E
FIGURE 20 : JSLC MAP
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CZ-2E
Ø Xichang Satellite Launch Center (XSLC)
This launch site is mainly to conduct GTO missions.
XSLC is located in Xichang region, Sichuan Province, southwestern China.
This site is located 41° 2' N - 100°13' E.
FIGURE 21 : XSLC MAP
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4.2
CZ-2E
Sequence of flight events
Ø Two-stage CZ-2E Flight Sequence
Two-stage CZ-2E is mainly used for conducting Low Earth Orbit (LEO) missions. Two typical LEO
missions are recommended to the User:
-
two-stage CZ-2E launches payloads into a typical circular orbit with following injection parameters
from JSLC: Orbit Altitude = 200 km; Inclination = 53°,
-
two-stage CZ-2E can also launch payloads into a typical LEO with following injection parameters from
XSLC: Orbit Altitude = 200 km; Inclination = 28.5°.
The typical flight sequence of CZ-2E launching from JSLC is shown in Table 8.
FLIGHT TIME (s)
EVENTS
Liftoff
0
12.0
Pitch Over
139.3
Boosters Shutdown
140.8
Boosters Separation
158.4
Stage-1 Shutdown
159.9
Stage-1/Stage-2 Separation
200.9
Fairing Jettisoning
464.6
Stage-2 Main Engine Shutdown
574.6
Stage-2 Vernier Engine Shutdown
677.6
End of Attitude Adjustment
680.9
S/C-L/V Separation
TABLE 8 - CZ-2E FLIGHT SEQUENCE
Ø CZ-2E / ETS Flight Sequence
CZ-2E/ETS is mainly used for Low Earth Orbit (LEO) and Sun-synchronous Orbit (SSO) missions. The
typical flight sequence of CZ-2E / ETS launching from JSLC is shown in Table 9 and Figure 22.
FLIGHT TIME (s)
0
EVENTS
Liftoff
12.0
Pitch Over
139.3
Boosters Shutdown
140.8
Boosters Separation
158.4
Stage-1 Shutdown
159.9
Stage-1/Stage-2 Separation
200.9
Fairing Jettisoning
464.6
Stage-2 Main Engine Shutdown
574.6
Stage-2 Vernier Engine Shutdown
577.6
Stage-2/ETS Separation
3 223.9
End of Ballistic Phase and ETS Solid Motor Ignition
3 283.5
ETS Solid Motor Shutdown
3 353.5
Terminal Velocity Adjustment
3 403.5
S/C-L/V Separation
TABLE 9 - CZ-2E / ETS FLIGHT SEQUENCE
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CZ-2E
FIGURE 22 : CZ-2E / ETS FLIGHT PROFILE
4.3
Launch record data
LAUNCH DATE
NUMBER OF
SATELLITES
ORBIT
RESULT
REMARK
16.07.90
2
LEO - GTO
Failure
EPKM
13.08.92
1
GTO
Success
21.12.92
1
GTO
27.08.94
1
GTO
Success
STAR 63F
25.01.95
1
GTO
Failure
STAR 63 F
28.11.95
1
GTO
Success
28.12.95
1
GTO
Success
Success
(**)
STAR 63F
(*)
STAR 63F
EPKM / FG46
(***)
EPKM / FG46
(*) Thiokol kick motor
(**) Satellite was lost in an explosion approximately 48 s after launch. Seven months of
investigation concluded that neither satellite or CZ-2E were to blame. Chinese
official position is that the launch was a success.
(***) First use of the China's first commercial kick motor and the largest produced. The
motor appeared to be 2.4 - 3 m long. Its total mass is 5.9 t. EPKM / FG 46 is
manufactured by the Hexi chemical & Manufacturing Co.
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CZ-2E
Ø Failures
:
two
LAUNCH DATE
RESULT
CAUSE
16.07.90
CZ-2E lifted the Pakistan satellite The attempt to fire the upper
stage EPKM to put a satellite into
into LEO orbit.
GTO failed.
However the dummy satellite
failed to achieve GTO orbit.
25.01.95
A premature opening of the
payload fairing occured. The
subsequent ram-air pressures
crushed the satellite and
subsequently led to the explosion
about 50 s after lift-off.
The shear wind aloft conditions
set up a resonance that caused
the attachment fitting, or
interface, between the booster's
upper stage and the satellite to
fail.
Ø Previsional reliability : no information available
Ø Success ratio
4.4
: 71.4% (according to CGWIC)
Planned launches
No available data
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CZ-2E
5. DESCRIPTION
5.1
Launch vehicle
FIGURE 23 - CUT-OUT VIEW OF CZ-2E
5.2
Overall vehicle
Ø Overall length
: 49.7 m
Ø Maximum diameter : 3.35 m (4.20 m with fairing)
Ø Lift-off mass
: 460 t
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5.3
CZ-2E
General characteristics of the stages
STAGE
0
1
2
UPPER STAGE
LB 40 (1)
L 180
L 90
EPKM
-
SBA
SBA
HEXI
15.326
28.465
15.188
2.936
Diameter (m)
2.25
3.35
3.35
1.70
Dry mass (t)
3.2 x 4
9.5
5.5
0.541
Ø Type
Liquid (storable)
Liquid (storable)
Liquid (storable)
Solid
Ø Fuel
UDMH
UDMH
UDMH
-
N2O4
N2O4
N2O4
-
37.768 x 4
186.306
84.777
5.444
Ø Fuel
-
-
-
-
Ø Oxidizer
-
-
-
-
Ø Water
-
-
-
-
Tank pressure
(bar)
-
-
-
-
41 x 4
195.7
93.5
5.98
Designation
Manufacturer
Length (m)
Propellant:
Ø Oxidizer
Propellant mass (t)
Total lift-off
mass (kg)
(1) 4 liquid rocket boosters
Launch vehicle growth
Ø CZ-2E / TS incorporates a CZ-2E and a top stage which includes a solid motor, avionics and a multiple
satellite dispenser for middle-high orbit mission. 12 satellites are mounted on the dispenser.
Ø CZ-2E / A (CZ-2E / stretched) is a 2-stage launcher with 4 strap-on extended boosters which each use
two DaFY5-1 engines versus one on the CZ-2E (lift-off mass 650 t; LEO 15 t into 185 / 285 km/28°; fairing
∅ 5.2 m and 12.39 m long).
December 2003
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CHINA
5.4
CZ-2E
Propulsion
STAGE
Designation
Engine
0
1
2
UPPER STAGE
LR-40
L 180
L 90
EPKM
YF-24B/DaFY20-1
=
SPTM-17
YF-20B/DaFY5-1 YF-21B/DaFY6-2
=
YF-20B x 4
YF-22B
YF-23B (1)
x4
SLREC
SLREC
SLREC
SLREC
HEXI
Number of engines
4
4
1
4
1
Engine mass (kg)
-
-
-
-
6 001
Turbopump
Turbopump
-
-
-
2.12
2.12
-
-
-
Chamber pressure
(bar)
-
-
-
-
-
Cooling
-
-
-
-
-
260.66
260.66
-
-
-
297.9
-
292
Manufacturer
Feed syst. type
Mixture ratio
Specific impulse (s)
Ø Sea level
Ø Vacuum
Thrust (kN)
Ø Sea level
740.4 x 4
2 961.6
-
-
-
Ø Vacuum
-
-
741.4
11.8 x 4
210 max
127
160
129
413
87
Nozzle expansion
ratio
-
12.69
26.57
-
-
Restart capability
No
No
No
No
No
Burning time (s)
(1) Vernier engine
5.5
Guidance and control
5.5.1 Guidance
Inertial
December 2003
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CHINA
CZ-2E
5.5.2 Control
STAGE
Pitch, yaw, roll
1
2
UPPER STAGE
Gimballed
(4 nozzles)
By 4 Vernier
engines
-
-
-
Spinning rate
≤ 10 rpm
Deflection
6. DATA SOURCE REFERENCE
1
-
Long March 2E user's manual, issue 1999
2
-
Chinese Space program 12.10.1988
3
-
China Space Report 1980
4
-
China Defence Space Today 2003
5
-
Encyclopedia Astronautica 2003
December 2003
Page 27