Author Topic: ChangZheng 6 (Long March 6) Launch Vehicle  (Read 13126 times)

Offline Dmitry_V_home

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Re: ChangZheng 6 (Long March 6) Launch Vehicle
« Reply #15 on: 11/09/2009 03:16 PM »
I would tell that the left engine is equivalent RD-120K

Offline Lsquirrel

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Re: ChangZheng 6 (Long March 6) Launch Vehicle
« Reply #16 on: 11/27/2009 06:59 AM »
I doubt it because we've already seen mentions of CZ-2F/H using the 3.35 m core stage with YF-100 engines. Also, if the payload mass is not misquoted I can't imagine a 3.35 m vehicle with such a low capacity.

Only one YF-100 engine in the the 3.35 m core stage of the small launch vehicle, the upper stage is 2.25 m diameter with a 15 tonne thrust YF-115 engine. the payload mass is appropriate with thrust。
CZ-2F/H using the 3.35 m core stage with TWO YF-100 engines,while four boosters with ONE YF-100 engine each others, the rocket lift off using six YF-100 engines.

Offline Salo

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Re: ChangZheng 6 (Long March 6) Launch Vehicle
« Reply #17 on: 11/27/2010 10:35 AM »
Only one YF-100 engine in the the 3.35 m core stage of the small launch vehicle, the upper stage is 2.25 m diameter with a 15 tonne thrust YF-115 engine. the payload mass is appropriate with thrust。
K3-1 3.35 m core have а total mass 147t. YF-100 engine have a trust 120tf.
« Last Edit: 11/27/2010 09:04 PM by Salo »

Offline Salo

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Re: ChangZheng 6 (Long March 6) Launch Vehicle
« Reply #18 on: 11/27/2010 10:28 PM »
http://www.sinodefence.com/space/launcher/cz6.asp
Quote
Changzheng 6 is the PRCís new generation liquid-propellant, small-load launch vehicle, currently being developed by the Shanghai Academy of Spaceflight Technology (SAST). The launch vehicle is designed to send at least 500kg payload into the Sun Synchronous Orbit (SSO) of 700km.
The launch vehicle is based on a 3.35m diameter core stage, which consists of a single 120t-thrust YF-100 rocket engine. The second stage uses a single 15t-thrust YF-115 engine. Both engines burn an oxygen and kerosene (LOX/Kerosene) propellant. The third stage is 2.25m in diameter and consists of four 1kN-thrust rocket motors.

Last update: 1 Nov 2010
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Offline Salo

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Re: ChangZheng 6 (Long March 6) Launch Vehicle
« Reply #19 on: 11/28/2010 09:56 AM »
From "Novosti kosmonavtiki" #10 2006: 


Online Galactic Penguin SST

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Re: ChangZheng 6 (Long March 6) Launch Vehicle
« Reply #21 on: 03/04/2012 01:40 AM »
I have found a Chinese paper by someone in CALT that describes the design rationale of the next generation small launch vehicle, now known as CZ-6. It also gives a rough description of the different configurations considered. The first stage uses a 3.35 m diameter first stage, modified to hold only one YF-100 kerolox engine (as opposed to two of them in the common 3.35 m kerolox block), and holds 76 tonnes of propellant. The second stage is powered by a restartable 150 kN thrust kerolox engine (the YF-115) that holds 15.15 tonnes of propellant. The most unusual aspect, however, is the thrusters on the ACS of the first two stages and a third "trim stage": they all use thrusters powered by a mixture of kerosene and hydrogen peroxide! Specifically:

- the first stage uses four 1000N thrusters for roll control
- the second stage uses four 25N thrusters for roll control
- the trim stage is powered by four 1000N thrusters, along with eight 100N thrusters for attitude control

The basic parameters for the chosen configuration (type "C" in the paper) is given as follows:

Length: 29.237 m
Total mass at liftoff: 103.217 tonnes
Thrust to weight ratio at launch: 1.20
Maximum dynamic pressure: 22.3 kPa
Maximum axial acceleration: 5.0 g
Fairing diameter: 2.25 m / 2.6 m
Payload to 700 km SSO: 1080 kg (500 kg if only Chinese tracking stations are used)
Dry mass of the three stages combined: 9.02 tonnes

The paper also shows why the original configuration considered (the one using the 2.25 m diameter kerolox block, i.e. configuration "B" in the paper) was not chosen:

1. The rocket would be too long and thin for current facilities (Length to diameter ratio = 15.9), and launching large satellites or multiple satellites would be a PITA.
2. The maximum loads are rather high (T/W ratio = 1.459, MDP = 36.9 kPa), and would require measures to reduce the load on the payloads.
3. The maximum payload isn't that high (payload to 700 km SSO = 870 kg).

 
Hmm....where can I apply for the job of United Launch Alliance internet cheerleader?

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