www.ariane.

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ARIANEGROUP
ORBITAL PROPULSION
ROBERT-KOCH-STRASSE 1
82024 TAUFKIRCHEN
GERMANY

SUSANA CORTÉS BORGMEYER

SUSANA.CORTES-BORGMEYER@ARIANE.GROUP
PHONE: +49 (0)89 6000 29244
WWW.SPACE-PROPULSION.COM
PYROVALVES
FILL, DRAIN AND VENT VALVES
LATCH VALVES
FLOW CONTROL VALVE
ORBITAL PROPULSION FLUIDIC EQUIPMENT
ORBITAL PROPULSION FLUIDIC EQUIPMENT
PYROVALVES
FILL, DRAIN AND VENT VALVES
LATCH VALVES
FLOW CONTROL VALVE

To assure the highest possible quality, reliability and The range of valves available include:
performance of our spacecraft propulsion systems and ››Pyrovalves
thrusters, ArianeGroup designs, develops and produces its ››Fill, Drain and Vent Valves
own valves for the control of propellants and pressurant’s. ››Latch Valves
These space qualified valves, proven over again in major ››Flow Control Valve
international programs, are available separately or as part
of a complete propulsion system.

Pyrovalve Fill and Drain Valve Ground Half Coupling

Latch Valve Flow Control Valve
PYROTECHNICAL VALVES

Pyrovalves are widely used on spacecrafts and launchers The main function of the Pyrotechnical Valve is to definitely
where reliable one shot devices are needed for permanent shut down or open a fluid circuit. Furthermore, as part of
opening or closing of a fluid circuit. Due to its excellent leak the propulsion subsystem they must ensure a minimal pres-
tightness capability prior to and after firing in combination sure drop as well as perfect external and internal leaktigth-
with its low mass and low complexity, the pyrovalve pre- ness prior to and after actuation. The latter is achieved by
sents state of the art propulsion system equipment suitable an all welded design in combination with a flexible titanium
to fulfil the various mission needs. membrane, which pysically separates the combustion
chamber from the hydraulic flow section. This membrane
ArianeGroup offers a family of Normally Closed (NC) and
ensures a perfect pressure tightness between the pyrotech-
Normally Open (NO) Pyrotechnical Valves with various
nic chambers and the fluid circuits before, during and after
different interfaces in order to fulfil the specific custom-
the actuation.
er needs. The available product portfolio covers screwed
as well as weldable interfaces (1/4” and 3/8”). All valve The Pyrotechnical Valve provides a highly reliable, fast act-
types are provided with redundant ESA standard initiators ing, zero liquid leakage compact design at low equipment
(squibs) which provides the energy needed for actuation. mass. Only a small pulse of electrical power is required for
valve actuation.

Pyrovalve Key Technical Characteristics

Initiators Redundant ESA Standard Initiators

Design All-welded Titanium design
Helium, Argon, Xenon, Nitrogen, MON,
Fluid Compability
MMH, Hydrazine, Deionized Water, IPA
Response Time (Mechanical) < 7ms
Mass < 0.160 kg (depending on type)
Qualified Operating Temperature -90°C ≤ T ≤ 100°C
Qualified Operating Pressure
310 bar
(MEOP)
Proof Pressure 1.5 x MEOP (465 bar)
Burst Pressure (NO and NC)
Pre firing > 4x MEOP
(rupture pressure: > 1240 bar)
Post firing > 2.5x MEOP
(rupture pressure: > 775 bar)

Leakage
Normally Open Internal leak after firing:
< 1x10-6 scc/s (GHe)
External leak before/after firing:
< 1x10-6 scc/s (GHe)

Normally Closed Internal leak before firing:

< 1x10-6 scc/s (GHe)
External leak before/after firing:
< 1x10-6 scc/s (GHe)
Pyrovalve Heritage and Future Missions
The heritage of ArianeGroup regarding Pyrotechnical As of today, ArianeGroup has delivered more than 600
Valves goes back to 1984, when the 1st generation has been NC and more than 600 NO Pyrotechnical valves to leading
developed by Aerospatial Les Mureaux with support from satellite manufactures. More 500 FM units were already
ESA. Following successful qualification in 1987, the first sucessfully actuated on various spacecrafts without any
generation of Pyrovalves was produced until the year 2000. failure. The production stability is continuously monitored
In 1999 a harmonisation and improvement of the first and verified throughout specific Destructive Lot Accept-
Pyrovalve generation was introduced and successfully qual- ance Test (DLAT) campaigns. Meanwhile more than 200
ified in 2001. Following 2 years of production all Pyrovalve units were successfully actuated during extensive DLAT
activities were transferred from ArianeGroup Les Mureaux testing including vibration and shock testing, low and
to ArianeGroup Lampoldshausen in 2004. The transfer was high temperature firings as well as under- and overcharge
finished in 2006 with a successfully performed First Article testing. This demonstrates the excellent reliability of the
validation program. Pyrotechnical Valves manufactured by ArianeGroup.

Spacecraft Launch Year Spacecraft Launch Year Spacecraft Launch Year

Ariane-5 since 1996 Arabsat 5A 2010 Eutelsat W5A 2012

Arabsat 4B 2006 Arabsat 5B 2010 Eutelsat W6A 2012

Anik F3 2007 COM-5 2010 METOP-B 2012

Skynet 5B 2007 Alsat 2B 2010 Skynet 5D 2012

Arabsat 4 AR 2008 Eutelssat W3B 2010 VEGA 2012

Astra 1M 2008 KA-SAT 2010 Yamal 402 2012

ATV FM1 2008 ATV FM 2 2011 ATV FM 4 2013

HotBird 9 2008 Ekspress AM4 2011 Alphasat 2013

Nimiq-4 2008 Arabsat 5C 2011 AMOS 4 2013

Skynet 5C 2008 SSOT (Myriade) 2011 Astra 2E 2013

Amazonas-2 2009 YAHSAT 1A 2011 GAIA 2013

Eutelsat W7 2009 YAHSAT 1B 2011 SES-6 2013

HotBird 10 2009 Astra 1N 2011 ARSAT 1 2014

MILSAT-A 2009 Elisa FM1 2011 Astra 2G 2014

Palapa D 2009 Elisa FM2 2011 Astra 5B 2014

Spirale 1 2009 Elisa FM3 2011 ATV FM5 2014

Spirale 2 2009 Elisa FM4 2011 Arabsat 6B 2015

Thor-6 2009 Atlantic Bird 2011 LISA-Pathfinder 2015

Alsat 2A 2010 Eutelsat W3C 2011 BepiColombo 2016

Nilesat 201 2010 Apstar 7A 2012 ExoMars 2016

RASCOM-2 2010 Astra 2F 2012 METOP-C 2017

MILSAT-B 2010 ATV FM 3 2012

FILL AND DRAIN VALVE

ArianeGroup offers a wide range of Fill and Drain / Vent The following design attributes and features are common
valves for spacecraft applications incorporating either two to all six FDV types:
or three inhibits against leakage pending on customer
demand. Propellant loading / venting valves are designed ››All piece parts of the valve are machined from titanium al-
to provide three independent inhibts, while gas type or test loy (Ti6Al4V) leading to a light weight unit with 0.25 inch/
port FCVs provide 6.4mm outlet diameter tube stub which forms a weldable
2 independent ones. connection to the titanium tubing of the subsystem
››The interface to the subsystem structure is provided by
With regard to the selected materials, the propellant type a triangular flange with triple-screw attachment (thread
and test port FDVs provide an excellant compatibility with size M4)
state of the art storable propellants such as MMH / Hy- ››An all welded housing containing a spring supported
drazine / MON-1 as well as MON-3. Special high pressure guided valve poppet equipped with the primary seal.
gas type FDV are available for operation with Helium (He) This ensures that the valve is kept closed in non actuated
and Xenon (Xe). In general all types are compatible with contions
standard test agents (IPA / HFE 7100 / deionized water) and ››In flight configuration the valve poppet sealing will be
gases (He, N2). additionally protected and sealed by mounting a cap,
In general six different valves types are available, each thus providing a metal-to-metal seal (secondary seal)
providing a different interface to prevent misconnection ››Low pressure drop even at high mass flows ensured by
on spacecraft level. These types differ mainly in thread size design. The flow area is at least as large as the connected
and orientation. tubing
For servicing a dedicated Ground Half Coupling (GHC) has
to be mounted. For each FDV type there is a respective GHC
permitting only mating of the correct type. By this means a
safe and easy to handle, leak-tight connection between the
propulsion system and the ground support equipment is
guaranteed.
Each GHC provides a robust specific opening / closing
mechanism to safely operate the FDV. No specific tooling is
required.
Fill and Drain Valve Heritage and Future Missions
Since their original qualification in 1983, thousands of fill, drain
and vent valves have been produced and delivered for a variety
of spacecraft programmes including Eutelsat W3A, Amazonas,
Inmarsat 4 F1, Anik F3, Skynet 5A, Skynet 5B, Amos 2, Astar, Star 1,
Galaxy 17, Hispasat, MSG-4, Microsats, Herschel Planck, Pleiades,
Spacebus, Eurostar communication satellites, Mars Express, Venus
Express and ESA’s Automated Transfer Vehicle. The outstanding
flight heritage underlines the excellent reliability of the Ariane-
Group Fill and Drain / Vent valves.

Ground Half Coupling

Fill and Drain Valve Propellant Loading

Fill & Drain Valves - 2 Failure Tolerant
(3 inhibits against external leakage)

Various fluids
Operating Media
(Propellants and Pressurants)

Mass < 0.09 kg

Total Length 109 ± 1 mm

Standard Tube Dimensions

- outer diameter 6.4 ± 0.02mm

- inner diameter 4.9 + 0.01mm
- inner diameter (at weld i/f) 5.58 ± 0.02mm

Tube Length 43 mm

Fuel Loading 9/16“ - 18 UNJF - 3A - RH. FDV Fuel Venting

Fuel Venting 7/16“ - 20 UNJF - 3A - RH.
Adapter Thread Ox Loading 9/16“ - 18 UNJF - 3A - LH.
Ox Venting 7/16“ - 20 UNJF - 3A - LH.

Note: All of the above threads require

corresponding ground half couplings

MEOP
Up to 33 bar
- Fuel / Ox Loading / Venting

Burst pressure 1240 bar

Sinusoidal Vibration Up to 20 g

Random Vibration Up to 5 g²/Hz (56.3g RMS)

Pyrotechnic Shock Up to 3250 g

All European Yes

Low Pressure Helium Valve
FILL AND DRAIN VALVE
TECHNICAL CHARACTERISTICS.

Fuel Fill Valve Fuel Vent Valve High Pressure Helium Valve

Operating Media Monomethyl Hydrazine (MMH) Monomethyl Hydrazine (MMH) Helium (High Pressure)

Mass ≤ 0.09 kg ≤ 0.09 kg ≤ 0.06 kg

Total Length 108.8 ± 1 mm 107.2 ± 1 mm 94.5 ± 1 mm

Standard Tube Dimensions

- outer diameter 6.4 ± 0.02mm 6.4 ± 0.02 mm 6.4 ± 0.02 mm

- inner diameter 5.58 + 0.11 mm 5.58 + 0.02 mm 4.98 + 0.02 mm

Tube Length 43 mm 43 mm 43 mm

9/16” - 18 UNJF - 3A - RH. Re- 7/16“ - 20 UNJF - 3A - RH. Requi- M 12 x 1.5 - RH.
Adapter Thread
quires corresponding ground res corresponding ground half Requires corresponding ground
half coupling coupling half coupling
Life
- Operational Life About 16 years About 16 years About 16 years
- Storage Life Up to 5 years in a protected Up to 5 years in a protected Up to 5 years in a protected
environment environment environment

Open/Close Cycles 40 Cycles 40 Cycles 40 Cycles

Standard Operating Temp. -30°C to 80°C -30°C to 80°C -30°C to 80°C

Leakage
- external Leakage < 1x10-6 scc/sec GHe < 1x10-6 scc/sec GHe < 1x10-6 scc/sec GHe
- internal Leakage < 2.8x10-4 scc/sec GHe < 2.8x10-4 scc/sec GHe < 2.8x10-4 scc/sec GHe
Low Pressure Helium Valve Oxidiser Fill Valve Oxidiser Vent Valve High Pressure Xenon Valve

Helium (Low Pressure) Nitrogen Tetroxide (MON) Nitrogen Tetroxide (MON) Xenon (High Pressure)

≤ 0.06 kg < 0.09 kg < 0.09 kg ≤ 0.06 kg

94.5 ± 1 mm 108.8 ± 1 mm 107.2 ± 1 mm 115 ± 1 mm

6.4 ± 0.02 mm 6.4 ± 0.02 mm 6.4 ± 0.02 mm 6.4 ± 0.02 mm

5.58 + 0.02 mm 5.58 + 0.02 mm 5.58 + 0.02 mm 4.9 + 0.1 mm

43 mm 43 mm 43 mm 61 mm

7/16“ - 20 UNJF - 3A - RH. Requi- 9/16“ - 18 UNJF - 3A - LH. Requi- 7/16“ - 20 UNJF - 3A - LH. Re- M 14 x 1.5 - RH.
res corresponding ground half res corresponding ground half quires corresponding ground Requires corresponding
coupling coupling half coupling ground half coupling

About 16 years About 16 years About 16 years About 16 years

Up to 5 years in a protected Up to 5 years in a protected Up to 5 years in a protected Up to 5 years in a protected
environment environment environment environment

40 Cycles 40 Cycles 40 Cycles 40 Cycles

-30°C to 80°C -30°C to 80°C -30°C to 80°C -30°C to 80°C

< 1x10-6 scc/sec GHe < 1x10-6 scc/sec GHe < 1x10-6 scc/sec GHe < 1x10-6 scc/sec GHe
< 2.8x10-4 scc/sec GHe < 2.8x10-4 scc/sec GHe < 2.8x10-4 scc/sec GHe < 2.8x10-4 scc/sec GHe
LATCH VALVE

The ArianeGroup low pressure latching valve (named For switching 2 electromagnetic coils are to be activated to
hereafter LPLV or LV) is a solenoid-operated, bi-stable valve change the status of the valve to open or closed. Switching
constructed essentially of stainless steel and qualified to can be performed by using a non-regulated supply within
operate with a number of different working media, includ- a range of 22VDC < 28VDC ≤ 38 VDC. At room-temperature
ing hydrazine and its most common derivatives. the LPLV can be closed or opened within a switch-time of
30ms while the cycle-time is defined to 50ms.
The LPLV provided by ArianeGroup represents the switch-
able, fully reliable safety barrier in the propellant flow A microswitch is installed for position indication, activated
between tank and thrusters. It is equipped with a back-re- by a pin, which is directly mounted on the LPLV-anchor.
lief-function protecting the downstream lines and equip-
The variant with welded interface is identical to the
ment against over-pressure (e.g. due to environmental
screwed-interface one except for the tubing connection.
effects).

Latch Valve Technical Characteristics

Characteristics Nominal Value Remarks

Tubing Interface 1/4 inch Screwed or welded versions available

Mass 545 g
Operating voltage 22-32 VDC Up to 50VDC for 50ms switching pulses
Response time < 30 ms Opening and Closing;
Coil resistance 37,5 Ω ± 1,5 Ω At ambient temperature
Max.operating pressure 24,25 bar Specified value; higher values possible
Back-Relief Pressure 8 to 14 bar
Flow Rate and Pressure Drop < 0.15 bar at 4.5 g/s Flow rates up to > 20g/s usable

Water, hydrazine, MMH, NTO, IPA, He,

Fluid Compatibility
N2, Xe and others

Opening/Closing cycles > 500

Operating Temperature 9° C to 50° C for use with hydrazine
Electrical connection Flying leads AWG26, 2m long
Leakage
- external Leakage < 10-6 scc/s
- internal Leakage < 5 scc/h GHe
 014 Orbital Propulsion Fluidic Equipment

400N APOGEE
400N ENGINE
APOGEE ENGINEFLOW
FLOWCONTROL
CONTROL VALVE
VALVE
The 400N flow control valve is an electromagnetic controlled, normally closed valve with a non sliding
fit suspended armature design and has redundant electric coils. The moving part, called magnetic
plunger, is actuated with the magnetic force induced by the coil when supplied by direct current voltage.
The 400N
Withflow
no control valve is the
voltage applied, an electromagnetic controlled,
magnetic plunger returns normally
to closed closed
position valve
thanks to the two
with a non slidingmembrane
preloaded fit suspended armature
springs. The springdesign
preloadand has redundant
compresses the PTFEelectric
poppet coils.
on the me-
The moving part,and
tallic seats called magnetic
enables to meetplunger, is actuated
the required tightness with the magnetic
level. After energizing force in- the
of the coil,
duced by theopens
valve coil when
and thesupplied by direct
flow passes current
through voltage.
an annular gap. At the inlet of the valve a 40µ
With nofilter is located
voltage to protect
applied, the PTFE seat
the magnetic for any
plunger pollution.
returns to closed position thanks
to the two
More than 100 units were successfully build and more thancompresses
preloaded membrane springs. The spring preload the used
80 successfully PTFEon
poppetAirbus
on theDS metallic seats and enables
400N engine in orbit. to meet the required tightness level. After
energizing of the coil, the valve opens and the flow passes through an annular gap.
At the inlet of the valve a 40µ filter is located to protect the PTFE seat for any pollu-
tion.
More than 100 units were successfully build and more than 80 successfully used on
ArianeGroup 400N engine in orbit.

400N Apogee Engine Engine

400N Apogee Flow Control Valve (FCV)
Flow Control ValveKey Technical
(FCV) Characteristics
Key Technical Characteristics

Dual-coil-solenoid monostable
Dual-coil-solenoid monostable bipropellant
bipropellant
Valve type
Valve type engine
engine valve (Normally-Closed), non
valve (Normally-Closed), slidingfitfit
non sliding
Operating VoltageVoltage
Operating per Coil
per Coil VDC VDC 21 to2127
to 27
Coil resistance
Coil resistance OhmsOhms 20 ±20
1 at
± 121°C
at 21°C
Power dissipation
Power dissipation Watt Watt 38.438.4
at 27
atVDC
27 VDC
Response time (20°C)
Response time (20°C) ms ms < 30< 30
Pull-in Pull-in VDC VDC ≤ 18,3
≤ 18,3
Drop-out
Drop-out VDC VDC ><
> 1.5, 1.5,
5 <5
HoldingHolding
VoltageVoltage per Coil
per Coil VDC VDC ≥ 7.5≥ 7.5
Max
Max inlet inlet pressure
pressure (operational
(operational bar bar
domain)
domain) 34 34
Burst pressure bar 88
Burst pressure bar 88
Flow Rate / Pressure Drop max 1.1 bar at 70 g/s H2O
Flow Rate / Pressure Drop max 1.1 bar at 70 g/s H2O
Compatible Media NTO, MMH, water
Compatible Media NTO, MMH, water
Seat material PTFE
Seat material PTFE
Other materials in contact with media AISI 430, AISI 347, Elgiloy
Other materials in contact with media AISI 430, AISI 347, Elgiloy
Leakage
Leakage
- external Leakage scc/s < 1x10E−6
- external Leakage
- internal scc/s scc/s
Leakage < 1x10E −6
< 5x10E−4
- internal Leakage scc/s < 5x10E−4
AWG24 flying leads acc. ESA ECSS 3901.002
Electrical connection
AWG241.7mflying leads
(4 single acc. ESA ECSS 3901.002 1.7m
wires)
Electrical connection
Media inlet connector (4 single wires)
AN4 7/16 - 20 UNJF - 3A
Media inlet
Inlet connector
filter AN4Mesh
7/16 type,
- 20 UNJF - 3Asteel, <40µm
stainless
Inlet filter
Temperatures Mesh type, stainless steel, <40µm
Temperatures
Operating °C 0°C to 115°C
Acceptance °C -5°C to 120°C
Operating °C 0°C to 115°C
Qualification °C -10°C to 125°C
Acceptance °C -5°C to 120°C
Number of open/close cycles
Qualification °C 5000
-10°C to 125°C
NumberLife
of time
open/close cycles years 500016
Life time years 16