sea launch - Blackboard

CIS
SEA LAUNCH
1. IDENTIFICATION
1.1
Name
SEA LAUNCH
1.2
Classification
¾ Family
¾ Series
¾ Version
:
:
:
ZENIT
ZENIT 3
ZENIT-3SL
¾ Category
¾ Class
¾ Type
:
:
:
:
1.3
Manufacturer
1.4
Development manager :
Sea Launch Company LLC
One World Trade Centre – Suite 950
Long Beach, CA 90831-0950, USA
1.5
Vehicle operator
Boeing Commercial Space Company
1.6
Launch service agency :
Boeing Launch Services
One World Trade Centre, Suite 950
Long Beach, CA 90831-0950, USA
1.7
Launch cost
:
65-85 M$
:
SPACE LAUNCH VEHICLE
Medium Launch Vehicle (MLV)
Expendable Launch Vehicle (ELV)
Several manufacturers in Russia and Ukraine and US coordinated by
Sea Launch Company
2. STATUS
2.1
Vehicle status
:
Operational
2.2
Development period
:
1993 to 1999
2.3
First launch
:
28.03.1999 (success)
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3. PAYLOAD CAPABILITY AND CONSTRAINTS
3.1
Payload capability
Sea Launch made a series of minor improvements on the Zenit 3SL vehicle to gradually increase its GTO
launch capability from 5,250 kg in 1999 to about 6000 kg.
The launch capability should be increased again with the modernized version of the RD-171 engine (RD171M) with a thrust of 7,800 kN.
3.1.1 Low Earth Orbits
ORBIT TYPE
Altitude
(km)
(Perigee/Apogee)
Inclination
MEO CIRCULAR
PEO CIRCULAR
15 000
15 000
45
90
3 050
2 000
(°)
Payload mass (kg)
3.1.2 Geosynchronous and Interplanetary Orbits
ORBIT TYPE
STANDARD GTO
200 - 35 786 km ; i = 0°
INTERPLANETARY
C3 : 0 km²/s²
6 066 (1)
4 005
Payload mass (kg)
(1) One burn of the Block DM-SL
The maximum payload capability for a range of typical GTO perigees and apogees is shown in Figures 1 and
2.
3.1.3 Injection accuracy
The table shows the injection accuracies for a standard GTO mission (2.3σ).
Perigee altitude
± 10 km
Apogee altitude
± 80 km
Inclination
± 0.25°
Argument of Perigee
December 2004
N.A.
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SEA LAUNCH
FIGURE 1 - GTO PAYLOAD CAPABILITY - LOWER PERIGEES
FIGURE 2 - GTO PAYLOAD CAPABILITY - HIGHER PERIGEES
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SEA LAUNCH
FIGURE 3 - CIRCULAR ORBIT PAYLOAD CAPABILITY
FIGURE 4 - ELLIPTICAL ORBIT PAYLOAD CAPABILITY
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SEA LAUNCH
FIGURE 5 - HIGH ENERGY/ESCAPE ORBITS
3.2
¾
¾
¾
¾
3.3
Spacecraft orientation and separation
Thermal control manœuvres
:
Nominal payload separation velocity
Rotation rate
:
Deployment mechanism type
:
yes
:
≥ 0.3 m/s
30 °/s
spring release
Payload interfaces
3.3.1 Payload compartments and adapters
¾ Payload fairing (PLF)
The PLF is made of two sections of graphite composite external and internal skins, with an aluminium
honeycomb core, and is 11.39 m long and 4.15 m in diameter.
The baseline design includes two PLF access doors, approximately 610 mm in diameter, located on
opposite sides of the PLF longitudinal separation plane and at least 17 deg from the separation plane.
Within PLF structural constraints, variations in the number, location, and size of the doors can be
accommodated.
External thermal insulation protects the PLF structure and limits the interior PLF surface temperatures.
¾ Interface Skirt (IS)
The IS that joins the PLF and adaptor to the Block DM-SL is constructed of aluminium with integral
stiffeners. The IS is 0.81 m long and accommodates the transition from a 3.715 m diameter on the Block
DM-SL to a 4.15 m diameter on the PLF.
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SEA LAUNCH
¾ Spacecraft adaptors (SCA)
The standard spacecraft adaptors are procured from Saab Ericsson Space.
The Spacecraft Adaptor (SCA) mechanical interface with the SC can be either a bolted or a typical clamp
band (Marmon type) interface of 1194 mm, 1 664 mm and 1 666 mm.
FIGURE 6 - SEA LAUNCH PAYLOAD UNIT
FIGURE 7 – SPACECRAFT STATIC ENVELOPE
December 2004
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3.4
SEA LAUNCH
Environments
This section outlines the expected spacecraft environments. The following description of the flight
environment encompasses the period from stage 1 ignition through completion of Block DM-SL
contamination and collision avoidance manoeuvre.
3.4.1 Mechanical environment
¾ The quasi-static limit loads factors during the flight are given in Figure 8.
FIGURE 8 -TYPICAL QUASI-STATIC LOAD FACTORS DURING THE FLIGHT
¾ Sinusoidal vibrations
The low-frequency sinusoidal vibrations environment generated at the spacecraft separation plane during
launch and flight will not exceed that defined in Figure 9.
FIGURE 9 – SINUSOIDAL VIBRATION AT THE SPACECRAFT INTERFACE
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¾ Random vibrations.
The random vibrations environment during flight measured at the spacecraft interface is shown in Figure
10.
FIGURE 10 - RANDOM VIBRATION ENVIRONMENT DURING FLIGHT
3.4.2 Acoustic vibrations
The launch vehicle internal acoustic levels shown in Figure 11 are average sound pressure levels internal to
the payload unit. These values apply to a spacecraft with an equivalent radius that results in a spacecraft-topayload fairing gap of 0.43 m.
FIGURE 11 - ACOUSTIC ENVIRONMENT DURING FLIGHT
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3.4.3 Shock
The shock spectrum shown in Figure 12 represents the maximum expected shock environment for the
spacecraft adapter with a diameter of 1666 mm and a Marmon clamp separation system.
FIGURE 12 - SEPARATION SHOCK FOR SCA1666 SPACECRAFT ADAPTER
3.4.4 Thermal environment
The maximum internal payload fairing surface temperatures during the ascent period are presented in
Figure 13.
FIGURE 13 - MAXIMUM INTERNAL PAYLOAD FAIRING SURFACE TEMPERATURES
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3.4.5 Variation of static pressure under fairing
FIGURE 14 - PAYLOAD FAIRING INTERNAL PRESSURE DURING ASCENT
3.5
Operation constraints
¾ Ground constraints
Coordination is exercised by Sea Launch.
¾ Launch rate capability
6 launches per year.
¾ Procurement lead time
18 months.
December 2004
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SEA LAUNCH
FIGURE 15 - GENERIC INTEGRATION TIMELINE
December 2004
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SEA LAUNCH
4. LAUNCH INFORMATION
4.1
Launch site
¾ Standard Launch site
The standard ZENIT-3SL launch site is located in Pacific Ocean at 0° N, 154° W.
FIGURE 16 - STANDARD LAUNCH SITE LOCATION
For inclined missions that affect range safety (e.g., a population located along the ascent groundtrack) an
alternate launch site may be selected.
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¾ Home Port
The Home Port is located in Southern California in the Port of Long Beach. This site is part of the former
Long Beach Naval Station.
The Sea Launch Home Port complex provides the facilities, equipment, supplies, personnel, and
procedures necessary to receive, transport, process, test, and integrate the spacecraft and its associated
support equipment with the launch system. It also serves as the home base for launch operations with
facilities to support and service the Sea Launch vessels, office facilities, and storage facilities.
The Home Port complex consists of a Payload Processing Facility (PPF), sea launch building, customer
office facilities, several warehouse buildings, and a pier.
The payload accommodation is integrated in a class 100 000 clean facility during ground processing at
the Home Port.
FIGURE 17 - HOME PORT LOCATION AND VICINITY
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SEA LAUNCH
NOTE :
The marine segment of the Sea Launch system includes:
-
the Assembly & Command Ship (ACS),
-
the Launch Platform (LP),
which together support integration of the Launch Vehicle (LV), transportation to launch site, mission
control and launch.
-
Assembly and Command Ship (ACS)
The ACS performs four functions for Sea Launch operations:
a. serves the facility for assembly, processing and checkout of the LV,
b. houses the Launch Control Center (LCC), which monitors and controls all operations at the launch
site,
c. acts as the base for tracking the initial ascent of the launcher,
d. provides accommodations for the marine and launch crews during transit to and from the launch
site.
The ACS (Figure 18) is designed with a double-bottom hull and is constructed specifically to suit the
unique requirements of Sea Launch operations. The basic structure of the ACS is that of a roll-on/rolloff cargo vessel. The ship's overall length is approximately 200 m, and its beam is 32.3 m. Its overall
displacement is approximately 30.830 t.
LV stages are loaded on board the ACS in the Home Port through the stern ramp. Processing and
assembly of the stages is conducted on the rail systems in the rocket assembly compartment on the
main deck, as shown in Figure 17. A special area in the bow of the main deck is dedicated for
processing and fuelling of the Block DM-SL.
Processing and assembly of the LV is typically done in port in parallel with SC processing operations.
Encapsulated Payloads (EP) are loaded onto the ACS from land through the stern ramp. Once
onboard, the EP and its transportation dolly are positioned on the center rail in the rocket assembly
compartment for integration with the LV. Accommodations are available for payload contractors to
conduct checkouts of the SC and verification of interfaces prior to and after integration with the LV.
After the payload is integrated with the LV and all checkouts are complete, the integrated LV is
transferred to the LP (Figure 18). Environmental conditioning and monitoring of the encapsulated SC
is continuous from SC encapsulation through launch.
FIGURE 18 - ASSEMBLY & COMMAND SHIP
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SEA LAUNCH
FIGURE 19 – LAUNCH VEHICLE PROCESSING - MAIN DECK
FIGURE 20 - LAUNCH VEHICLE TRANSFER FROM ACS TO LP IN THE HOME PORT
The Launch Control Center (LCC) is located on the ACS as shown in figure 19. The LCC contains
operator consoles and seating, and provides connections with all shipboard communications systems.
The heart of the LCC is the Mission Management and Display System (MMDS), which is a serverbased computer system providing standard computer support services, mission displays, and
countdown clock displays.
Directly aft of the LCC are two conference rooms for use by Sea Launch and payload contractor
personnel. Each conference room has seating, overhead projectors, and teleconferencing equipment.
An additional conference room is dedicated solely for customer use on the first bridge deck.
FIGURE 21 - LV CONTROL CENTER - SHELTER DECK
December 2004
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SEA LAUNCH
Launch Plaftorm
In the Home Port, the integrated LV is transferred to the LP from the ACS and is transported to the
launch location in the enclosed hangar on the launch deck. After LP ballasting at the launch site is
complete, the LV is rolled out of the hangar to the launch pad, erected, and prepared for launch
(Figure 20). The LP has all the necessary systems for LV erection, fueling, and conduct of launch
operations. It also provides accommodations for the marine crew and part of the launch crew during
transit to and from the launch site.
The LP is a stable platform from which to conduct launch operations. The LP rides catamaran style on
a pair of large pontoons and is self-propelled by four screw propulsion systems (two in each aft lower
hull), which is powered by eight direct current double armature-type motors rated at 3,000 hp each.
Once at the launch location, the pontoons are submerged by ballasting to achieve the stable launch
position, level to within approximately 1 deg. The ballast tanks are located in the pontoons and in the
lower part of the columns, which are served by six ballast pumps, three pumps in each pontoon. The
LP has an overall length (at the pontoons) of approximately 133 m, and the launch deck is 78 m by
66.8 m. Its overall transit displacement is approximately 27,400 t.
The LP crew is evacuated during final launch operations. After the LV has been erected and all launch
system checks are complete, the crewmembers are transferred by motor launch to the ACS. Vessel
stationkeeping and launch operations are conducted from the ACS through redundant RF links.
FIGURE 22 - LAUNCH PLATFORM DURING FINAL COUNTDOWN
December 2004
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4.2
SEA LAUNCH
Sequence of flight events
FIGURE 23 – TYPICAL FLIGHT PROFILE - TWO BURNS OF BLOCK DM - 6 000 KG GTO MISSION
Time, sec
0
8
10 to 20
64
114
114 to 131
141
143
146
151
229
429
504
505
506
514
784
2,584
3,009
3,609
Event
Liftoff
Begin pitchover
Roll to launch azimuth
Maximum dynamic pressure
Maximum axial acceleration
Stage 1 engine throttle to 50 %
Stage 2 vernier engine ignition
Stage 1 engine shutdown
Stage 1 separation
Stage 2 main engine ignition
Payload fairing jettison
Stage 2 main engine shutdown
Stage 2 vernier engine shutdown
Stage 2 separation
Block DM-SL middle adapter jettison
Block DM-SL main engine ignition 1
Block DM-SL main engine shutdown 1
Block DM-SL main engine ignition 2
Block DM-SL main engine shutdown 2
Spacecraft separation
FIGURE 24 - FLIGHT TIMELINE - TWO BURNS OF BLOCK DM - 6 000 KG GTO MISSION
December 2004
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4.3
SEA LAUNCH
Launch record data
LAUNCH DATE
NUMBER OF
SATELLITES
ORBIT
RESULT
28.03.99
1
GTO
Success
10.10.99
1
GTO
Success
12.03.00
1
-
Failure
28.07.00
1
GTO
Success
21.10.00
1
GTO
Success
18.03.01
1
GTO
Success
08.05.01
1
GTO
Success
15.06.02
1
GTO
Success
10.03.03
1
GTO
Success
07.08.03
1
GTO
Success
01.10.03
1
GTO
Success
10.01.04
1
GTO
Success
04.05.04
1
GTO
Success
28.06.04
1
GTO
Success (*)
REMARK
(*) Satellite delivered to lower than expected orbit but reached its operational orbit position with fuel surplus
¾ Failures
LAUNCH DATE
RESULT
CAUSE
12.03.2000
Excessive loss of helium and
ultimately the vehicle does not
reach orbital velocity.
Lack of a ground software command
to close a pneumatic valve on the
2nd stage prior lift-off.
About 8 minutes into the flight,
premature engine shutdown
and automatic termination.
¾ Previsional reliability :
¾ Success ratio
4.4
: 92.8% (13/14)
Planned launches
Sea Launch has 4 launches planned in 2005.
December 2004
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SEA LAUNCH
5. DESCRIPTION
5.1
Launch vehicle
FIGURE 26 - ZENIT-3SL LAUNCH VEHICLE
5.2
Overall vehicle
¾ Overall length
¾ Maximum diameter
¾ Lift-off mass (approx.)
December 2004
: 59.64 m
: 3.9 m (4.15 m with fairing)
: 471 t
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5.3
SEA LAUNCH
General characteristics of the stages
STAGE
1
2
3
Stage 1
Stage 2
Block DM-SL
NPO Yuzhmash
NPO Yuzhmash
RSC Energia
Length (m)
32.9
10.4
5.6
Diameter (m)
3.9
3.9
3.7
Dry mass (t)
32.3
9.02
3.8
¾ Type
Liquid
Liquid
Liquid
¾ Fuel
Kerosene
Kerosene
Kerosene
Oxygen
Oxygen
Oxygen
¾ Fuel
88.77
22.83
4.6
¾ Oxidizer
233.51
58.91
11.3
-
-
-
354.58
90.76
19.7 (2)
Designation
Manufacturer
Propellant:
¾ Oxidizer
Propellant mass (t)
TOTAL
Tank pressure
(bar)
Total lift-off
mass (t)
(1) The Block DM has flown as the fourth stage of the Proton
(2) 19.71includes the Block DM-SL lower and middle adaptor
December 2004
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SEA LAUNCH
5.4
Propulsion
STAGE
1
Designation
Engine
2
3
-
Main
Vernier
Block DM-SL
RD-171
RD-120
RD-8
11D58M
Manufacturer
NPO EnergoMash
Number of engines
RSC Energia
1 (4 chambers)
1
1 (4 chambers)
1
~ 13 000
1 125
-
-
turbopump
turbopump
turbopump
-
-
-
-
-
245
163
77
77.4
¾ Sea level
309.5
N.A.
N.A.
N.A.
¾ Vacuum
337.2
350
342.8
356
¾ Sea level
7 259
N/A
N/A
N/A
¾ Vacuum
7 911
992
78
79.5
140 - 150
200 to 315
300 to 1 100
~ 600
Nozzle expansion
ratio
37
106
104
280
Restart capability
No
No
No
Yes (7 times)
Engine mass (kg)
Feed syst. type
Mixture ratio
Chamber pressure
(bar)
Specific impulse (s)
Thrust (kN)
Burning time (s)
5.5
Guidance and control
5.5.1 Guidance
Inertial
5.5.2 Control
STAGE
Pitch, yaw, roll
1
2
3
Nozzle gimbal (± 6.3°)
Verniers engines
nozzle gimbal
Attitude control engines
gimballing
6. DATA SOURCE REFERENCES
1
-
Sea Launch User’s Guide – Revision C – January 2003
2
-
International Reference Guide to Space Launch Systems (AIAA) - Fourth Edition - July 2004
December 2004
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