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7/25/2019 Spaceflight101 Com Spacerockets Long March 7
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Saturday, June 25, 2016
Long March 7 Launch VehicleLong
March
7, also
knownas
Chang
Zheng
7 (CZ-
7), is a American Launchers
HOME NEWS CALENDAR ROCKETS ISS NASA ESA COMMERCIAL OTHER
RE -E NTRY S EARCH ARCH IV E
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Photo: via 9ifly.cn
Chinese Space Launch Vehicle that builds the medium-lift component in
Chinas next generation of orbital launch systems, operated alongside the
Long March 5 and 6 as well as the existing CZ-2/3/4 rockets. The new line of
CZ-5/6/7 rockets facilitates a major shift in launch vehicle technology,
switching from mostly hypergolic- or solid-fueled launchers to more
env ironmentally friendly Kerosene /LOX propellants.
Taking the medium-lift spot in the new gene ration of launchers, Long March
7 is joined by the light-lift Long March 6 and the heavy-lift Long March 5. The
new launchers use modular systems and common components across the
different rockets as a cost-saving and simplification measure, allowing a
quick build-up of heritage and permitting a streamlined production of launch
vehicles to support an ever growing number of missions.
The need for the
Antares 100 Series
Atlas V 401
Atlas V 421
Atlas V 501
Atlas V 531
Atlas V 541
Atlas V 551
Delta II 7320
Delta II 7920
Delta IV Heavy
Delta IV Heavy (RS-68A)
Delta IV Medium+ (4,2)
Delta IV Medium+ (5,2)
Delta IV Medium+ (5,4)
Falcon 9 FT
Falcon Heavy
Falcon 9 v1.1 & F9R
Falcon 9 v1.0
http://spaceflight101.com/spacerockets/wp-content/uploads/sites/17/2016/05/cz-7-1.jpghttp://spaceflight101.com/spacerockets/wp-content/uploads/sites/17/2016/05/cz-7-1.jpghttp://spaceflight101.com/spacerockets/wp-content/uploads/sites/17/2016/05/cz-7-1.jpghttp://pdfcrowd.com/http://pdfcrowd.com/redirect/?url=http%3a%2f%2fspaceflight101.com%2fspacerockets%2flong-march-7%2f&id=ma-160625180610-59c7e52chttp://pdfcrowd.com/customize/http://pdfcrowd.com/html-to-pdf-api/?ref=pdfhttp://spaceflight101.com/spacerockets/wp-content/uploads/sites/17/2016/05/cz-7-1.jpghttp://spaceflight101.com/spacerockets/wp-content/uploads/sites/17/2016/05/201521322371382594.jpghttp://spaceflight101.com/spacerockets/antares-100-series/http://spaceflight101.com/spacerockets/atlas-v-401/http://spaceflight101.com/spacerockets/atlas-v-421/http://spaceflight101.com/spacerockets/atlas-v-501/http://spaceflight101.com/spacerockets/atlas-v-531/http://spaceflight101.com/spacerockets/atlas-v-541/http://spaceflight101.com/spacerockets/atlas-v-551/http://spaceflight101.com/spacerockets/delta-ii-7320/http://spaceflight101.com/spacerockets/delta-ii-7920/http://spaceflight101.com/spacerockets/delta-iv-heavy/http://spaceflight101.com/spacerockets/delta-iv-heavy-rs-68a/http://spaceflight101.com/spacerockets/delta-iv-medium-42/http://spaceflight101.com/spacerockets/delta-iv-medium-52/http://spaceflight101.com/spacerockets/delta-iv-medium-54/http://spaceflight101.com/spacerockets/falcon-9-ft/http://spaceflight101.com/spacerockets/falcon-heavy/http://spaceflight101.com/spacerockets/falcon-9-v1-1-f9r/http://spaceflight101.com/spacerockets/falcon-9-v1-0/http://spaceflight101.com/spacerockets/wp-content/uploads/sites/17/2016/05/201521322371382594.jpg7/25/2019 Spaceflight101 Com Spacerockets Long March 7
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development of new
rockets arose due to a
shift in launch
requirements to medium-
and heavy-weight
payloads such as regular
flights of crew and cargo
vehicles to Chinas
upcoming space station.
The existing launchers
were on the lower end of
the required lift-class and
employed highly toxic
propellant combinations,
not ideal for regular crew
missions. The goal of the
new line of rockets is to
establish a safe, reliable,
flexible and economical
space launcharchitecture.
The Long March 7 rocket
started out under the
name Long March 2F/H as
a modernized version of
Minotaur I
Minotaur V
Pegasus XL
SPARK Super Strypi
The Long March In China
10 Best SUVs
Fuel Efficient SUVs
Best New Car Deals
1
2
3
4
Russia
Angara Launch Vehicle Family
Angara 1.2
Angara 1.2PP
Angara A3
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Photo: CASC via 9ifly.cn the CZ-2F used in Chinas
Crewed Space Program.
Later the project evolved into a new medium-lift launcher to employ the
technologies developed for the new-generation of rockets and enable CZ-7
to fill the performance gap between the small CZ-6 and the heavy-lift Long
March 5.
Development work for the Long March 7 was completed by the China
Academy of Launch Vehicle Technology (CALT), starting in 2010. The maiden
flight of the CZ-7 rocket was repe atedly delayed and is currently expected in
mid-2016.
Initially, Long March 7 will be operated from the Wenchang Satellite Launch
Center on Hainan Island, though it is expected that the inland launchcenters will be adapted for use by the CZ-7 in the future. Over a period of
years, the CZ-5/6/7 rockets will demonstrate their capabilities and reliability
before they will become Chinas primary space launch ve hicles when the
CZ-3/4 series re tire in the first half of the 2020s. Crewed launches are
expected to continue using the Long March 2F until the late 2020s before
shifting to a successor vehicle, likely Long March 7.
Angara A5
Angara A7
Dnepr
Proton-M/Block DM-03
Proton-M/Briz-M
Rockot
Soyuz 2-1A
Soyuz 2-1B
Soyuz 2-1v
Soyuz FG
Soyuz FG/Fregat
Soyuz U
Strela
Zenit-3SL
Zenit-3SLB
China
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Type Long March 7 (CZ-7)
Height 53.1 m
Diameter 3.35 m
Dry Mass ~44,000 kg
Launch Mass 595,000 kg
Stages 2
Boosters 4
Mass to LEO 13,500 kg
Mass to GTO 7,000 kg
Photo: CASC
Long March 7 SpecificationsThe
Long
March
7
Long March 2F
Long March 3A
Long March 3B
Long March 3B/E
Long March 3C
Long March 3C/E
Long March 6
Europe
Ariane 5 ECA
Ariane 5 ES
Vega
Japan
Epsilon
H-IIA 202
H-IIA 204
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Mass to SSO 5,500 kg
launch vehicle is a two-stage rocket with four liquid-fueled boosters
clustered around the first stage. Structurally, the vehicle employs a design
similar to the Long March 2F rocket currently used in Chinas manned space
program CZ-7 inherits the overall dimensions of the Long March 2F with
respect to core and booster diameter. The two stages as well as theboosters consume Kerosene fuel and Liquid Oxygen as oxidizer.
Long March 7 stands 56.1 meters tall, has a core diameter of 3.35m, creating
a span of over eight meters from booster side fin to booster side fin. The
vehicle has a launch mass of 595 metric tons and is capable of delivering
payloads of up to 13,500 Kilograms to Low Earth Orbit making it suitable for
the launch of crew and cargo craft to Chinas future space station. Thevehicle can deliver satellites up to 5,500 Kilograms to a 700-Kilometer Sun-
Synchronous Orbit, expanding performance to this particular orbit when
compared to the CZ-2 and 4 vehicles currently employed for SSO missions.
The Long March 7 uses YF-100 engines on its boosters and core stage and
the YF-115 is employed on the second stage. These e ngines were
developed for use across the CZ-5/6/7 series to increase commonality and
streamline production.
H-IIB
India
GSLV Mk.II
GSLV Mk. III
PSLV
The Long March In China
10 Best SUVs
Fuel Efficient SUVs
Best New Car Deals
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Long March Space X NASA Space Rocket FuelAdChoices
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First Stage
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Type K3-1
Length 26m
Diameter 3.35m
Inert Mass ~12,000kg
Propellant Mass ~174,000kg
Fuel Kerosene
Oxidizer Liquid Oxygen
Tank Material Aluminum Alloy
Tank Construction Separate Bulkheads
Tank Pressurization Engine Bleed, Helium
Propulsion 2 x YF-100
Image: Weibo/9ifly
The
first
stage
of the
CZ-7
http://104.131.251.97/spacerockets/wp-content/uploads/sites/17/2015/08/7658969_orig.jpghttp://104.131.251.97/spacerockets/wp-content/uploads/sites/17/2015/08/7658969_orig.jpghttp://104.131.251.97/spacerockets/wp-content/uploads/sites/17/2015/08/7658969_orig.jpghttp://pdfcrowd.com/http://pdfcrowd.com/redirect/?url=http%3a%2f%2fspaceflight101.com%2fspacerockets%2flong-march-7%2f&id=ma-160625180610-59c7e52chttp://pdfcrowd.com/customize/http://pdfcrowd.com/html-to-pdf-api/?ref=pdfhttp://104.131.251.97/spacerockets/wp-content/uploads/sites/17/2015/08/7658969_orig.jpg7/25/2019 Spaceflight101 Com Spacerockets Long March 7
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Engine Type Staged Combustion
Propellant Feed Turbopump
YF-100 Thrust (SL) 1,180kN
YF-100 Thrust (Vac) 1,340kN
Impulse (SL) 300s
Impulse (Vac) 335s
Ox. To Fuel Ratio 2.6
YF-100 Flowrate ~410kg/s
Engine Length 2.99m
Engine Diameter 1.35m
Chamber Pressure 180bar
Throttle Range 65-100%
Burn Time ~215 sec
Attitude Control Two-Axis Engine Gimbaling
launch vehicle is a K3-1 rocket module that shares commonality with the
first stage of the Long March 2F in that it retains the 3.35-meter diameter.
However, changes to the 2F version are stretched tanks, a different
propellant combination and different propulsion system. K3-1 stands
approximately 26 meters tall and has an inert mass on the order of 12.5
metric tons. At liftoff, it holds around 174 metric tons of Liquid Oxygen and
Kerosene propellants.
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The K3-1 rocket module contains the Kerosene fuel tank located below the
Liquid Oxygen Tank. The LOX feedline is routed through a tunnel in the fuel
tank which increases packing efficiency. Aluminum alloy is used for the
propellant tanks with a wall thickness of 1.7 millimeters.
Tanks holding pressurant gas to keep the tanks at the proper pressureduring flight are installed within the LOX tank for improved gas storage
efficiency.
The CZ-7 first stage is powered by a pair of YF-100 engines which are
individually gimbaled to provide three-axis control to the vehicle.
Development of the YF-100 engine started in the early 2000 under direction
by the China National Space Administration.
It is based on the Russian RD-120 engine that was acquired by China in the
1990s and is still in use aboard the Zenit rockets second stage.
The YF-100
engine
entered
its testing
program
in 2005
NASA Space Space Craft Fuel Cost Water TankAdChoices
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Photo: CASC
which was
completed
by the end
of 2007
with
official
acceptance testing complete by May 2012 clearing the engine for use
aboard Chinas future launch vehicles. It is currently in use by the Long
March 5, 6 and 7 ve hicles.
YF-100 is a high-pressure staged combustion engine employing an oxygen-
rich preburner that generates hot, high-pressure gas by burning a portion
of the fuel inflow in an oxygen-rich environment to drive the turbine of the
oxidizer and fue l turbopumps which use a single shaft and deliver the
propellants to the combustion chamber of the engine .
The YF-100 engine operates at a chamber
pressure of 180 bar to generate a sea level
thrust of 1,180 Kilonewtons (120,300
Kilogram force) that rises to 1,340kN in the
rarefied upper atmosphere (136,650kgf) at
corresponding specific impulses of 300 and
335 seconds.
YF-100 is 1.35 meters in diameter and
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Image: CASC
measures 2.99 meters in length. The engine
operates at a mixture ratio of 2.6 and can be
throttled down to 65% of rated performance
to allow the vehicle to fly complex mission
profiles.
YF-100 is available in a one-axis and two-axis gimbaled version. CZ-7 usestwo-axis gimabling for pitch, yaw and roll control throughout first stage
flight.
The first stage operates for approximately three minutes and 20 seconds
into the flight using a pyrotechnic separation system that disconnects the
two stages in the interstage area that remains attached to the first stage to
expose the engine compartment of the second stage. The interstage of theCZ-7 measures approximately 3.3 meters in length.
Boosters
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Type K2-1
Length 26.5m
Diameter 2.25m
Inert Mass ~6,000kg
Propellant Mass ~75,500kg
Fuel Kerosene
Oxidizer Liquid Oxygen
Tank Material Aluminum Alloy
Tank Construction Separate Bulkheads
Tank Pressurization Engine Bleed, Helium
Propulsion 1 x YF-100
Photo: CASC
Long
March
7
i b
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Engine Specs See Stage 1 above
Burn Time ~185 sec
Attitude Control Two-Axis Engine Gimbaling
employs four liquid-fueled rocket boosters clustered around the Core
Stage. They are referred to as K2-1 rocket modules and share the 2.25-meter
diameter of the Long March 2F rocket but are stretched to a length of
around 26.5 mete rs. The inert mass of the booster is around six metric tons.
The boosters also employ the common design facilitating the Liquid Oxygen
tank located above the Kerosene tank with the LOX feedline running
through the center of the fuel tank. The LOX tank of K2-1 is around 13
meters in length while the Kerosene tank is approximately 6.6 meters long,
allowing each booster to hold 75.5 metric tons of propellants.
The four boosters are topped by a light-weight aerodynamic cap and feature
outward facing fins to provide aerodynamic stabilization during the initial
flight sequence. Each of the boosters sports a single YF-100 engine, giving
Long March 7 a total liftoff thrust of 7,080 Kilonewtons (722 metric ton force)
which creates an initial thrust to weight ratio of 1.2.
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Type K3-2
Length ~11.5m
Diameter 3.35m
Inert Mass ~6,000kg
Propellant Mass ~65,000kg
Fuel Kerosene
Photo: CASC
Second Stage.The
Oxidizer Liquid Oxygen
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Oxidizer Liquid Oxygen
Tank Material Aluminum Alloy
Tank Construction Separate Bulkheads
Tank Pressurization Helium
Propulsion 4 x YF-115
Propellant Feed Turbopump
YF-115 Thrust (Vac) 180kN
Impulse (Vac) 341.5s
Total Thrust 720kN
Throttle Range 80-100%
Ox. To Fuel Ratio 2.5
YF-115 Length 2.33m
YF-115 Diameter 0.95m
Restart Capability Yes
Burn Time Variable
Attitude Control Two-Axis Engine Gimbaling
second stage of the Long March 7 rocket is 3.35 meters in diameter, the
same as the first stage. The K3-2 rocket module is around 11.5 meters long
and has an inert mass of approximately 5.5 metric tons.
In design, the second stage is similar to the first stage with the Liquid
Oxygen tank located above the Kerosene tank and facilitating the
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Oxygen tank located above the Kerosene tank and facilitating the
pressurant bottles. At launch, the second stage holds 65 metric tons of
propellants.
The K3-2 rocket module is powered by four YF-115 engines that are also
employed by the Long March 6 rocket. YF-115 has been developed between
2002 and 2014 as Chinas primary Kerolox engine optimized for operation invacuum conditions, making it suitable for upper stages.
It employs an oxidizer-rich staged combustion cycle, following the Russian
example after the Chinese obtained documentation detailing the Russian
RD-120 engine in the 1990s. The engine is Chinas first upper stage engine
to employ a staged-combustion cycle.
YF-115 is 2.33 meters long and 0.95 meters in diameter. It operates at a
chamber pressure of 120 bar to generate a thrust output of 180 Kilonewtons
as a specific impulse of 341.5 seconds. It has a nozzle ratio of 88, optimized
for operation in the rarefied upper atmosphere. The YF-115 engine can be
throttled be tween 80 and 100% of rated pe rformance.
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Fairing Type Composite Fairing
Fairing Diameter 4.2m
Fairing Length 12.4m
Payload Envelope 3.8m
Photo: CASC
Payload FairingThe
Payload Fairing is positioned on top of the stacked vehicle and its
integrated spacecraft. It protects the vehicle against aerodynamic, thermal
and acoustic environments that the launcher experiences during
atmospheric flight. When the launcher has left the atmosphere, the fairing is
jettisoned. Separating the fairing as early as possible increases ascent
performance.
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performance.
The baseline fairing design for the Long March 7 is a fairing 4.2 meters in
diameter and 12.4 meters in length offering a payload envelope 3.8 meters
in diameter suitable for a variety of satellites including Geostationary
Communications Satellites. Other fairing options, based on the current CZ-
2/4 fairing designs will also be adapted for use on the Long March 7 rocket.
Photo: CASC
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Image: CALT (2014)
Vehicle DerivationsIn an initial
design proposal,
there were to be
three different
Long March 7
versions to cater
to different
payload needs by
flying the vehicle
with zero, two or
four liquid-fueled
boosters.
Another proposal
called a pair of
CZ-7 versions
with eithe r two or
four boosters aswell as the option
of adding a small-
diameter HO
Upper Stage
developed for
the Long March 5 rocket.
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g
In a paper published by CALT in 2014, two derived versions of the CZ-7 are
presented to be under study. The first version, tentatively known as CZ-734,
would fly the two-stage CZ-7 as pre sented on this page plus a cryoge nic
third stage identical to that of the Long March 3A rocket. This would
increase the vehicles Geostationary Transfer Orbit capability to 7,000Kilograms, allowing it to lift the heaviest communications satellites curre ntly
in operation.
A second version, CZ-720, would only use the CZ-7 core stage with no
boosters plus a second stage identical to the third stage of Long March 3A
to allow the ve hicle to lift 2,900 Kilograms into a 700-Kilometer Sun
Synchronous Orbit.
Optional 2nd/3rd Stage (as of 2014)
The
CZ-
3A-
The Rocket Water Tank Cost of Gas Mass SpecAdChoices
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Image: CCTV
Type CZ-3A Third Stage
Length 12.38m
Diameter 3.0m
Launch Mass 20,933kg
Empty Mass 2,740kg
Fuel Liquid Hydrogen
Oxidizer Liquid Oxygen
Propellant Mass 18,193kg
Propulsion YF-75
Thrust 156.9kN
Specific Impulse 4,312Ns/kg
Chamber Pressure 37.6bar
Area Ratio 80
Restart Capability Yes
type stage is a
cryogenic upper
stage that provides
re-ignition capability
to perform GTO or
SSO insertions.
Overall, the stage is
12.38 meters long
with a reduce d
diameter of 3.0
meters having an
inert mass of 2,740
Kilograms. The third
stage carries a total
propellant load of
18,193 Kilograms of
Liquid Hydrogen and
Liquid Oxygen.
Prop Utilization Yes The LH2 tank is
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Burn Time 469s
Control Engine Gimbaling (Pitch & Yaw)
Attitude Control Sys 4x70N, 8x40N (Roll, Pitch & Yaw)
Prop Management 2x300N, 2x45N
located above the
LOX tank and the two
share a common
bulkhead. The two
tanks are equipped
with propellant levelsensors that provide information of the Propellant Utilization Sensor of the
vehicle that then provides data to the telemetry and control system to
adjust the mixture ratio to optimize the residual propellants left inside the
stage after burnout and increase overall launch vehicle performance. The
Propellant Level Meters are also used during propellant loading.
The stage is equipped with an YF-75 cluster of two cryogenic main enginesproviding a total vacuum thrust of 156.9 Kilonewtons (1,600 Kilogram-force)
operating at a chamber pressure of 37.6 bar. The engines are optimized for
operation in vacuum conditions with an area ratio of 80:1. Two allow CZ-3E to
fly GTO missions, the engine can re-ignite on a second burn following an
initial boost into a Parking Orbit. This second burn then delive rs that ve hicle
to its elliptical GTO or escape trajectory. The engines can be gimbaled for
vehicle control.
Propellant tank pressurization is accomplished using high-pressure Helium
for the LH2 tank and a combination of Helium and gaseous LOX.
The stage is equipped with a monopropellant Propellant Management and
Attitude Control System. The Propellant Management System is used for
propellant settling burns ahead of main engine burns. The system consists
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p p g g y
of two 300-Newton thrusters and two 45-Newton thrusters. In addition to
propellant management, the thrusters are also used for performance
optimization during engine burns and for a variable Velocity Adjustment
after the second burn of the upper stage to optimize the insertion
trajectory.
The Attitude Control System of the stage is used during coast phases for
vehicle re-orientations and to orient the stack for spacecraft separation. It
consists of three banks of thrusters, one for e ach axis. Pitch control is
provided by two 70-Newton and two 40-Newton thrusters. For Yaw-actuation,
the system also uses two 70N and two 40N jets. Roll control is provided by
four 40N thrusters.
All PM and ACS thrusters are fed from a single Hydrazine tank that is
pressurized using high-pressure gas that is stored in two spherical tanks.
CZ-7 Vehicle Components AllImages: CASC
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Th L M h I Chi1 B R d C2 B H b id C3
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The Long March In China1 Best Rated Cars2 Best Hybrid Cars3
All Season Tires4 Top 10 Luxury Cars5 New Car Prices6
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