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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)



Falcon 9 FT

Falcon Heavy

Falcon 9 v1.1 & F9R

Falcon 9 v1.0
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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

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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

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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
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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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df di b PRO i A d l ? T t th HTML t PDF API

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


Fuel Kerosene




Tank Pressurization Engine Bleed, Helium


Photo: CASC

Long

March

7

i b
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Engine Specs See Stage 1 above

Burn Time ~185 sec


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


Fuel Kerosene

Photo: CASC

Second Stage.The

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Tank Pressurization Helium


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


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


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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