Magnetic sail

From Wikipedia, the free encyclopedia

 

A magnetic sail or magsail is a proposed method of spacecraft propulsion which would use a static magnetic field to deflect charged particles radiated by the Sun as a plasma wind, and thus impart momentum to accelerate the spacecraft. A magnetic sail could also thrust directly against planetary and solar magnetospheres.

History

The magnetic sail was proposed by Dana Andrews and Robert Zubrin working in collaboration in 1988. At that time, Andrews was working on a concept to use a magnetic scoop to gather ions to provide propellant for a nuclear electric ion drive spacecraft, allowing the craft to operate in the same manner of a Bussard ramjet, but without the need for a proton-proton fusion propulsion drive. He asked Zubrin to help him compute the drag that the magnetic scoop would create against the interplanetary medium. Zubrin agreed, but found that the drag created by the scoop would be much greater than the thrust created by the ion drive. He therefore proposed that the ion drive component of the system be dropped, and the device simply used as a sail. Andrews agreed, and the magsail was born. The two then proceeded to elaborate their analysis of the magsail for interplanetary, interstellar, and planetary orbital propulsion in a series of papers published from 1988 through the 1990s.

Principles of operation and design

The magsail operates by creating drag against the local medium (planet's magnetic field, solar wind, or interstellar winds), thereby allowing a spacecraft accelerated to very high velocities by other means, such as a fusion rocket or laser pushed lightsail, to slow down – even from relativistic velocities – without requiring the use of onboard propellant. It can thus reduce the delta-V propulsion required for an interstellar mission by a factor of two. This capability is the most unusual feature of the magsail, and perhaps the most significant in the long term. 

In typical magnetic sail designs, the magnetic field is generated by a loop of superconducting wire. Because loops of current-carrying conductors tend to be forced outwards towards a circular shape by their own magnetic field, the sail could be deployed simply by unspooling the conductor and applying a current through it.

Solar wind example

The solar wind is a continuous stream of plasma that flows outwards from the Sun: near the Earth's orbit, it contains several million protons and electrons per cubic meter and flows at 400 to 600 km/s (250 to 370 mi/s). The magnetic sail introduces a magnetic field into this plasma flow which can deflect the particles from their original trajectory: the momentum of the particles is then transferred to the sail, leading to a thrust on the sail. One advantage of magnetic or solar sails over (chemical or ion) reaction thrusters is that no reaction mass is depleted or carried in the craft.

For a sail in the solar wind one AU away from the Sun, the field strength required to resist the dynamic pressure of the solar wind is 50 nT. Zubrin's proposed magnetic sail design would create a bubble of space of 100 km in diameter (62 mi) where solar-wind ions are substantially deflected using a hoop 50 km (31 mi) in radius. The minimum mass of such a coil is constrained by material strength limitations at roughly 40 tonnes (44 tons) and it would generate 70 N (16 lb_f) of thrust,^[3] giving a mass/thrust ratio of 600 kg/N. If operated within the solar system, high temperature superconducting wire would be required to make the magsail practical. If operated in interstellar space conventional superconductors would be adequate.

The operation of magnetic sails using plasma wind is analogous to the operation of solar sails using the radiation pressure of photons emitted by the Sun. Although solar wind particles have rest mass and photons do not, sunlight has thousands of times more momentum than the solar wind. Therefore, a magnetic sail must deflect a proportionally larger area of the solar wind than a comparable solar sail to generate the same amount of thrust. However, it need not be as massive as a solar sail because the solar wind is deflected by a magnetic field instead of a large physical sail. Conventional materials for solar sails weigh around 7 g/m² (0.0014 lb/sq ft), giving a thrust of 0.01 mPa (1.5×10⁻⁹ psi) at 1 AU (150,000,000 km; 93,000,000 mi). This gives a mass/thrust ratio of at least 700 kg/N, similar to a magnetic sail, neglecting other structural components.

The solar and magnetic sails have a thrust that falls off as the square of the distance from the Sun. 

When close to a planet with a strong magnetosphere such as Earth or a gas giant, the magnetic sail could generate more thrust by interacting with the magnetosphere instead of the solar wind, and may therefore be more efficient.

Mini-magnetospheric plasma propulsion (M2P2)

In order to reduce the size and weight of the magnet of the magnetic sail, it may be possible to inflate the magnetic field using a plasma in the same way that the plasma around the Earth stretches out the Earth's magnetic field in the magnetosphere. In this approach, called mini-magnetospheric plasma propulsion (M2P2), currents that run through the plasma will augment and partially replace the currents in the coil. This is expected to be especially useful far from the Sun, where the increased effective size of a M2P2 sail compensates for the reduced dynamic pressure of the solar wind. The original NASA design proposes a spacecraft containing a can-shaped electromagnet into which a plasma is injected. The plasma pressure stretches the magnetic field and inflates a bubble of plasma around the spacecraft. The plasma then generates a kind of miniaturized magnetosphere around the spacecraft, analogous to the magnetosphere that surrounds the Earth. The protons and electrons which make up the solar wind are deflected by this magnetosphere and the reaction accelerates the spacecraft. The thrust of the M2P2 device would be steerable to some extent, potentially allowing the spacecraft to 'tack' into the solar wind and allowing efficient changes of orbit.

In the case of the (M2P2) system the spacecraft releases gas to create the plasma needed to maintain the somewhat leaky plasma bubble. The M2P2 system therefore has an effective specific impulse which is the amount of gas consumed per newton second of thrust. This is a figure of merit usually used for rockets, where the fuel is actually reaction mass. Robert Winglee, who originally proposed the M2P2 technique, calculates a specific impulse of 200 kN·s/kg (roughly 50 times better than the space shuttle main engine). These calculations suggest that the system requires on the order of a kilowatt of power per newton of thrust, considerably lower than electric thrusters, and that the system generates the same thrust anywhere within the heliopause because the sail spreads automatically as the solar wind becomes less dense. However, this technique is less understood than the simpler magnetic sail and issues of how large and heavy the magnetic coil would have to be or whether the momentum from the solar wind can be efficiently transferred to the spacecraft are under dispute.

The expansion of the magnetic field using plasma injected has been successfully tested in a large vacuum chamber on Earth, but the development of thrust was not part of the experiment. A beam-powered variant, MagBeam, is also under development.

Modes of operation

A magnetic sail in a wind of charged particles. The sail generates a magnetic field, represented by red arrows, which deflects the particles to the left. The force on the sail is opposite.

In a plasma wind

When operating away from planetary magnetospheres, a magnetic sail would force the positively charged protons of the solar wind to curve as they passed through the magnetic field. The change of momentum of the protons would thrust against the magnetic field, and thus against the field coil. 

Just as with solar sails, magnetic sails can "tack". If a magnetic sail orients at an angle relative to the solar wind, charged particles are deflected preferentially to one side and the magnetic sail is pushed laterally. This means that magnetic sails could maneuver to most orbits.

In this mode, the amount of thrust generated by a magnetic sail falls off with the square of its distance from the Sun as the flux density of charged particles reduces. Solar weather also has major effects on the sail. It is possible that the plasma eruption from a severe solar flare could damage an efficient, fragile sail.

A common misconception is that a magnetic sail cannot exceed the speed of the plasma pushing it. As the speed of a magnetic sail increases, its acceleration becomes more dependent on its ability to tack efficiently. At high speeds, the plasma wind's direction will seem to come increasingly from the front of the spacecraft. Advanced sailing spacecraft might deploy field coils as "keels", so the spacecraft could use the difference in vector between the solar magnetic field and the solar wind, much as sailing yachts do.

Inside a planetary magnetosphere

A magnetic sail in a spatially varying magnetic field. Because the vertical external field B_ext is stronger on one side than the other, the leftward force on the left side of the ring is smaller than the rightward force on the right side of the ring, and the net force on the sail is to the right.

 

Inside a planetary magnetosphere, a magnetic sail can thrust against a planet's magnetic field, especially in an orbit that passes over the planet's magnetic poles, in a similar manner to an electrodynamic tether.

The range of maneuvers available to a magnetic sail inside a planetary magnetosphere are more limited than in a plasma wind. Just as with the more familiar small-scale magnets used on Earth, a magnetic sail can only be attracted towards the magnetosphere's poles or repelled from them, depending on its orientation.

When the magnetic sail's field is oriented in the opposite direction to the magnetosphere it experiences a force inward and toward the nearest pole, and when it is oriented in the same direction as the magnetosphere it experiences the opposite effect. A magnetic sail oriented in the same direction as the magnetosphere is not stable, and will have to prevent itself from being flipped over to the opposite orientation by some other means.

The thrust that a magnetic sail delivers within a magnetosphere decreases with the fourth power of its distance from the planet's internal magnetic dynamo.

This limited maneuvering capability is still quite useful. By varying the magnetic sail's field strength over the course of its orbit, a magnetic sail can give itself a "perigee kick" raising the altitude of its orbit's apogee.

Repeating this process with each orbit can drive the magnetic sail's apogee higher and higher, until the magnetic sail is able to leave the planetary magnetosphere and catch the solar wind. The same process in reverse can be used to lower or circularize the apogee of a magsail's orbit when it arrives at a destination planet.

In theory, it is possible for a magnetic sail to launch directly from the surface of a planet near one of its magnetic poles, repelling itself from the planet's magnetic field. However, this requires the magnetic sail to be maintained in its "unstable" orientation. A launch from Earth requires superconductors with 80 times the current density of the best known high-temperature superconductors.

Interstellar travel

Interstellar space contains very small amounts of hydrogen. A fast-moving sail would ionize this hydrogen by accelerating the electrons in one direction and the oppositely charged protons in the other direction. The energy for the ionization and cyclotron radiation would come from the spacecraft's kinetic energy, slowing the spacecraft. The cyclotron radiation from the acceleration of particles would be an easily detected howl in radio frequencies. In a paper published in 1995, "Detecting Extraterrestrial Civilizations via the Spectral Signatures of Advanced Interstellar Spacecraft", Zubrin suggested that such radiation could be used as a means of detecting advanced extraterrestrial civilizations.

Thus, in interstellar spaceflight outside the heliopause of a star a magnetic sail could act as a parachute to decelerate a spacecraft. This removes any fuel requirements for the deceleration half of an interstellar journey, which would benefit interstellar travel enormously. The magsail was first proposed for this purpose in 1988 by Robert Zubrin and Dana Andrews, predating other uses, and evolved from a concept of the Bussard ramjet which used a magnetic scoop to collect interstellar material. More recently a combination of magnetic sail and electric sail was proposed by Perakis and Hein. The magnetic sail is used for deceleration from higher velocities and the electric sail at lower velocities. The simulation shows a considerable mass saving for the combined system.

Magnetic sails could also be used with beam-powered propulsion by using a high-power particle accelerator to fire a beam of charged particles at the spacecraft. The magsail would deflect this beam, transferring momentum to the vehicle. This would provide much higher acceleration than a solar sail driven by a laser, but a charged particle beam would disperse in a shorter distance than a laser due to the electrostatic repulsion of its component particles. This dispersion problem could potentially be resolved by accelerating a stream of sails which then in turn transfer their momentum to a magsail vehicle, as proposed by Jordin Kare.

Theory in the limit of small plasma densities

A magnetic sail of an interstellar craft needs to brake from the protons of the interstellar medium. The density ${\displaystyle n_{p}}$ of protons is very low, of the order of 0.3 atoms per cubic centimeter for the Local Interstellar Cloud, which reaches up to a distance of 30 light years from the sun, and of the order for ${\displaystyle n_{p}\approx 0.05\,/{\mbox{cm}}^{3}}$ for the surrounding Local Bubble. A bow shock can be neglected in the limit of small plasma densities. A spacecraft with an overall mass ${\displaystyle m_{tot}}$ then changes its velocity ${\displaystyle v}$ via

${\displaystyle m_{tot}{\dot {v}}=-\left(A(v)n_{p}v\right)(2m_{p}v),}$

where ${\displaystyle m_{p}}$ is the proton mass and ${\displaystyle A(v)}$ the effective reflection area. The number of protons reflected per second is ${\displaystyle A(v)n_{p}v}$, with every impacting proton transferring a momentum of ${\displaystyle 2m_{p}v}$ to the craft. Overall momentum is conserved.

Effective reflection area

The effective reflection area ${\displaystyle A(v)}$ must be determined numerically by evaluating the trajectories of the impacting protons within the magnetic field generated by the superconducting loop. The German Physicist Claudius Gros found that the effective reflection area can be approximated, for a magnetic sail in the axial configuration, to a high precision by.

${\displaystyle A(v)=0.081\pi R^{2}\left[\log \left({\frac {cI}{vI_{c}}}\right)\right]^{3},}$

where ${\displaystyle \pi R^{2}}$ is the area enclosed by the current carrying loop, ${\displaystyle c}$ the speed of light, ${\displaystyle I}$ the current through the loop and ${\displaystyle I_{c}=1.55\cdot 10^{6}\,{\mbox{Ampere}}}$ a critical current. Protons are not reflected at all if ${\displaystyle v>c(I/I_{c})}$.

Explicit solution

The analytic expression for the effective reflection area ${\displaystyle A(v)}$ allows for an explicit solution of the equation of motion ${\displaystyle m_{tot}{\dot {v}}=-2A(v)n_{p}m_{p}v^{2}}$. The result is that the velocity drops to zero at a distance ${\displaystyle x_{max}}$. Minimizing the stopping distance ${\displaystyle x_{max}}$ for a given mass ${\displaystyle m_{tot}}$ of the craft one finds

${\displaystyle x_{max}={\frac {3.1}{m_{p}n_{p}}}\,{\frac {m_{tot}}{\pi R^{2}}}.}$

The velocity ${\displaystyle v}$ of a craft starting to brake with an initial velocity ${\displaystyle v_{0}}$ is given via

${\displaystyle v(x)=v_{0}\,e\,\exp \left({\frac {-1}{\sqrt {1-x/x_{max}}}}\right),}$

as a function of the distance ${\displaystyle x\in [0,x_{max}]}$ traveled, with

${\displaystyle t=\int _{0}^{x}{\frac {dx'}{v(x')}}={\frac {1}{v_{0}\,e}}\int _{0}^{x}dx'\exp \left({\frac {1}{\sqrt {1-x'/x_{max}}}}\right)}$

being the time ${\displaystyle t=t(x)}$ needed to cruise the distance ${\displaystyle x}$. The time ${\displaystyle t(x\to x_{max})}$ needed to come to a full stop therefore diverges.

Mission profiles

Using the analytic result for ${\displaystyle v(x)}$ and the current carrying capacity of state of the art coated superconducting wires , one can estimate the mass required for the magnetic sail.

• For a high speed mission to Alpha Centauri, with ${\displaystyle v_{0}=c/10}$, one finds ${\displaystyle R\approx 1600\,{\mbox{km}}}$ and ${\displaystyle m_{tot}\approx 1500\,{\mbox{tons}}}$. These requirements exceed by far the specifications of projected launch systems, such as of the Breakthrough Starshot initiative.
• For a low speed mission to TRAPPIST-1, with ${\displaystyle v_{0}=c/300\approx 1000\,{\mbox{km/s}}}$, one obtains ${\displaystyle R\approx 50\,{\mbox{km}}}$ and ${\displaystyle m_{tot}\approx 1.5\,{\mbox{tons}}}$. These requirements are well within the specifications of projected launch systems.

Long duration missions, such as missions aimed to offer terrestrial life alternative evolutionary pathways, e.g. as envisioned by the Genesis project, could therefore brake passively using magnetic sails.

Fictional uses in popular culture

Magnetic sails have become a popular trope in many works of science fiction although the solar sail is more popular:

1. The ancestor of the magsail, the Bussard magnetic scoop, first appeared in science-fiction in Poul Anderson's 1967 short story To Outlive Eternity, which was followed by the novel Tau Zero in 1970.
2. The magsail appears as a crucial plot device in The Children's Hour, a Man-Kzin Wars novel by Jerry Pournelle and S.M. Stirling (1991).
3. It also features prominently in the science-fiction novels of Michael Flynn, particularly in The Wreck of the River of Stars (2003); this book is the tale of the last flight of a magnetic sail ship when fusion rockets based on the Farnsworth-Hirsch Fusor have become the preferred technology.

Long March 5

From Wikipedia, the free encyclopedia

 

Long March 5

Long March 5 Y2 transporting to launch site
Function	Heavy orbital launch vehicle
Manufacturer	CALT
Country of origin	China
Size
Height	57 m (187 ft)
Diameter	5 m (16 ft)
Mass	867,000 kg (1,911,000 lb)
Stages	2
Capacity
Payload to LEO (200 km × 400 km × 42°)	25,000 kg (55,000 lb)
Payload to GTO	14,000 kg (31,000 lb)
Payload to TLI	8,200 kg (18,100 lb)
Associated rockets
Family	Long March
Comparable	Ariane 5 Delta IV Heavy Falcon 9 Proton-M Vulcan
Launch history
Status	Active
Launch sites	Wenchang LC-1
Total launches	2
Successes	1
Failures	1
First flight	3 November 2016
Boosters – CZ-5-300
No. boosters	4
Length	27.6 m (91 ft)
Diameter	3.35 m (11.0 ft)
Gross mass	155,700 kg (343,300 lb)
Propellant mass	144,000 kg (317,000 lb)
Engines	2 × YF-100
Thrust	SL: 2,400 kN (540,000 lbf) Vac.: 2,680 kN (600,000 lbf)
Total thrust	9,600 kN (2,200,000 lbf)
Specific impulse	SL: 300 seconds (2.9 km/s) Vac: 335 seconds (3.29 km/s)
Burn time	180 seconds
Fuel	RP-1/LOX
First stage – CZ-5-500
Length	31.7 m (104 ft)
Diameter	5 m (16 ft)
Gross mass	175,600 kg (387,100 lb)
Propellant mass	158,300 kg (349,000 lb)
Engines	2 × YF-77
Thrust	SL: 1,020 kN (230,000 lbf) Vac: 1,400 kN (310,000 lbf)
Specific impulse	SL: 310.2 seconds (3.042 km/s) Vac: 430 seconds (4.2 km/s)
Burn time	480 seconds
Fuel	LH2/LOX
Second stage – CZ-5-HO
Length	10.6 m (35 ft)
Diameter	5 m (16 ft)
Gross mass	22,200 kg (48,900 lb)
Propellant mass	17,100 kg (37,700 lb)
Engines	2 × YF-75D
Thrust	176.52 kN (39,680 lbf)88.26
Specific impulse	442 seconds (4.33 km/s)
Burn time	700 seconds
Fuel	LH2/LOX
Third stage – YZ-2(Optional)
Diameter	3.8 m (12 ft)
Engines	2 x YF-50D
Thrust	6.5 kN (1,500 lbf)
Specific impulse	316 seconds (3.10 km/s)
Burn time	1105 seconds
Fuel	N2O4/UDMH

Long March 5 (LM-5, CZ-5, or Changzheng 5) is a Chinese heavy lift launch system developed by China Academy of Launch Vehicle Technology (CALT). CZ-5 is the first Chinese vehicle designed from the ground up to focus on non-hypergolic liquid rocket propellants. Currently, two CZ-5 vehicle configurations are planned, with maximum payload capacities of ~25,000 kilograms (55,000 lb) to LEO and ~14,000 kilograms (31,000 lb) to GTO. The Long March 5 roughly matches the capabilities of American EELV heavy-class vehicles such as the Delta IV Heavy.

On its first launch from Wenchang Spacecraft Launch Center on 3 November 2016, the CZ-5 placed its payload in a suboptimal but workable initial orbit. Its second launch on 2 July 2017 failed due to an engine problem in the first stage.

History

Since 2010, Long March launches have made up 15–25% of all space launches globally. Growing domestic demand has maintained a healthy manifest. International deals have been secured through a package deal that bundles the launch with a Chinese satellite, circumventing the U.S. embargo.

The Chinese government approved the development of the Long March 5 rocket in 2007 following two decades of feasibility studies. It was to be manufactured at a facility in Tianjin, a coastal city near Beijing. In 2008 the first launch of the Long March 5 was predicted to occur in Wenchang of the southernmost island province of Hainan, where a new satellite launch center was allegedly being constructed.

The first CZ-5 rocket to be launched completed production and testing in Tianjin manufacturing facility around 16 August 2016 and shipped to the launch centre on Hainan island shortly after.

Development

The Chief Designer for the CZ-5 rocket was Long Lehao. The main objective for the CZ-5 rocket was to fulfill China's requirement for large payload to LEO and GTO missions for the next 20–30 years. The CZ-5 project was initially announced in February 2001, with initial development slated to begin in 2002 and the first versions of the vehicle to go into service by 2008. However, funding was only finally granted in 2007 as revealed by the developers during the Northeast China exhibition.

On 30 October 2007, the construction of the CZ-5 production plant began in the TEDA West area near Binhai New Area in Tianjin. The production facility was constructed near the harbor to reduce the logistical problems associated transporting rockets over land and allow easier transportation by sea from Tianjin to Wenchang Launch Facility on Hainan Island. The new production facility would have an area totaling more than half a million square meters and cost RMB 4500 million (USD 650 million), with the first stage of the construction scheduled to be completed by 2009. When the production facility is completed in 2012, it would be capable of a maximum output of thirty CZ-5s annually. As of July 2012, development of the 1,200 kN thrust LOX/kerosene engine was test fired. New photos of CZ-5 and of its tests were released in March 2015.

The first CZ-5 was shipped from the port of Tianjin in North China at 20 September 2015 for a rehearsal (some of the drills carried out at Wenchang Satellite Launch Center involved both the launch vehicle and a probe) of a scheduled Chang'e-5 lunar mission planned around 2017. The first test flight was initially scheduled for 2014, but this subsequently slipped to 2016.

First flight

The launch was planned to take place at around 10:00 UTC 3 November 2016, but several issues, involving an oxygen vent and chilling of the engines, were detected during the preparation, causing a delay of nearly three hours. The final countdown was interrupted three times due to problems with the flight control computer and the tracking software. The rocket finally launched at 12:43 UTC. According to an internet blogger on the Chinese microblogging platform Weibo, a minor problem occurred during flight and the rocket put the YZ-2 upper stage and satellite into an orbit that was less accurate than expected. However, the trajectory was corrected with the YZ-2 upper stage and the payload was inserted into the desired orbit.

Second flight

Its second launch on 2 July 2017 experienced an anomaly shortly after launch and was switched to an alternate, gentler trajectory. However, it was declared a failure 45 minutes into the flight. The cause of the failure was confirmed by CASC and related to an anomaly which happened on one of the YF-77 engines in the first stage.

The YF-77 booster engine was test-fired in 2018 after CASC redesigned it. The next Long March 5 launch date was estimated to be in January 2019, Still, after repeated cancellations and delays, the next launch is expected to return to flight late in 2019, but not sure exactly when.

Design

The chief designer of CZ-5 is Mr. Li Dong of the China Academy of Launch Vehicle Technology (CALT). The CZ-5 family will include three primary modular core stages of 5.2-m diameter (maximum). The total length of the vehicle is 60.5 metres and its weight at launch is 643 tons, with a thrust of 833.8 tons. Boosters of various capabilities and diameters ranging from 2.25 metres to 3.35 metres would be assembled from three modular core stages and strap-on stages. The first stage and boosters would have a choice of engines that use different liquid rocket propellants: 1,200 kN thrust LOX/kerosene engines or 500 kN thrust LOX/LH2. The upper stage would use improved versions of the YF-75 engine. 

Engine development began in 2000–2001, with testing directed by the China National Space Administration (CNSA) commencing in 2005. Versions of both new engines, the YF-100 and the YF-77, had been successfully tested by mid-2007.

The CZ-5 series can deliver ~23 tonnes payload to LEO or ~13 tonnes payload to GTO (geosynchronous transfer orbit). It will replace the CZ-2, CZ-3, and CZ-4 series in service, as well as provide new capabilities not possessed by the previous Long March rocket family. The CZ-5 launch vehicle would consist of a 5.0-m diameter core stage and four 3.35-m diameter strap-on boosters, which would be able to send a ~25 tonne payload to low earth orbit (LEO). 

Six CZ-5 variants were originally planned, but the light variants were cancelled in favor of CZ-6 and CZ-7 family launch vehicles.

In 2019, Russia offered China its technology to fix the current technical issues of Long March 5's cryogenic engines since “China urgently needs heavy-booster liquid-fuel rocket engines, of which Russia has some good offerings,” said by Zhou Chenming, a military analyst. 

Specifications

In development

Version	CZ-5	CZ-5B
Boosters	4×CZ-5-300, 2×YF-100	4×CZ-5-300, 2×YF-100
First stage	CZ-5-500, 2×YF-77	CZ-5-500, 2×YF-77
Second stage	CZ-5-HO, 2×YF-75D	--
Third stage (optional)	Yuanzheng-2	--
Thrust (at ground)	10565 KN	10565 KN
Launch weight	867 t	837 t
Height	62 m	53.66 m
Payload (LEO 200 km)	--	~25 t[26]
Payload (GTO)	~14 t[26]	--

Proposed

Version	CZ-5-200	CZ-5-320	CZ-5-522	CZ-5-540
Boosters	--	2×CZ-5-200, YF-100	2×CZ-5-200, YF-100; 2×CZ-5-300, 2×YF-100	4×CZ-5-200, YF-100
First stage	CZ-5-200, YF-100	CZ-5-300, 2×YF-100	CZ-5-500, 2×YF-77	CZ-5-500, 2×YF-77
Second stage	CZ-YF-73, YF-73	CZ-5-KO,	CZ-5-HO, 2×YF-75D	CZ-5-HO, 2×YF-75D
Third stage (not used for LEO)	--	CZ-5-HO, YF-75	--	--
Thrust (at ground)	134 Mgf (1.34 MN)	720 Mgf (7.2 MN)	824 Mgf (8.24 MN)	584 Mgf (5.84 MN)
Launch weight	82 t	420 t	630 t	470 t
Height (maximal)	33 m	55 m	58 m	53 m
Payload (LEO 200 km)	1.5 t	10 t	20 t	10 t
Payload (GTO)	--	6 t	11 t	6 t

List of launches

Flight №	Date (UTC)	Launch site	Upper stage	Payload	Orbit	Result
Y1	3 November 2016 12:43	Wenchang LC-1	YZ-2	Shijian 17	GEO	Success
Y2	2 July 2017 11:23	Wenchang LC-1	YZ-2	Shijian 18	GTO	Failure
Y3	27 December 2019	Wenchang LC-1	YZ-2	Shijian 20	GTO	Planned
Y4	Q4 2020	Wenchang LC-1	None	Chang'e 5, lunar sample return	TLI	Planned
LM5B Y1	Second half of 2020	Wenchang LC-1	None	Test flight for a new-generation crewed spacecraft	LEO	Planned
	23 July 2020	Wenchang LC-1	None	Mars Global Remote Sensing Orbiter and Small Rover	TMI	Scheduled
	2020	Wenchang LC-1	None	Tianhe, space station core module	LEO	Planned
	2021	Wenchang LC-1	None	Wentian, space station experiment module 1	LEO	Planned
	2022	Wenchang LC-1	None	Mengtian, space station experiment module 2	LEO	Planned
	2024	Wenchang LC-1	None	Chang'e 6, lunar sample return	TLI	Planned
	2024	Wenchang LC-1	None	Xun Tian, space telescope	LEO	Planned
	2024	Wenchang LC-1	None	SPORT (Solar Polar Orbit Telescope)	Heliocentric	Planned