OrbitalHub

Credits: NASA

The James Webb Space Telescope (JWST) is the successor of the Hubble Space Telescope (HST). While Hubble looks at the sky in the visible and ultraviolet light, JWST will operate in the infrared.

JWST is a joint mission of NASA, ESA, and the Canadian Space Agency.

The project started in 1996 and was initially known as the Next Generation Space Telescope (NGST). In 2002, the project was renamed the James Webb Space Telescope in honor of NASA administrator James E. Webb, who led the agency from February 1961 to October 1968.

The JWST will use a large deployable sunshade to keep the temperature of the telescope to about 35K. Operating at this temperature gives the telescope exceptional performance in near-infrared and mid-infrared wavebands. The JWST observatory will have a five to ten year lifetime and it will not be serviceable by astronauts.

JWST will be able to see the first galaxies that formed in the early Universe, and how the young stars formed planetary systems.

Credits: NASA

The JWST observatory includes the Integrated Science Instrument Module (ISIM), the Optical Telescope Element (OTE), and the Spacecraft Element containing a spacecraft bus (which offers the support functions for the observatory) and the sunshield.

I will say a few words about each one of them.

The Optical Telescope Element (OTE) collects the light coming from space. Thanks to a 6.5 meter primary mirror, JWST will be able to see the galaxies from the beginning of the Universe. The OTE is also composed of the Fine Steering Mirror (FSM), the secondary mirror support structure (SMSS), and the primary mirror backplane assembly (PMBA). Other subsystems of the OTE are the tertiary mirror and the fine steering mirror. The PMBA contains the Integrated Instrument Module (IIM).

Because the primary mirror is too large to fit inside any available payload fairing, it had to be made out of eighteen hexagonal segments. Some of the elements will be folded before the launch and unfolded during the commissioning phase at the L2 point. NASA made available some neat animations showing how the observatory will be folded in order to fit into the launcher payload, and how the sun shields and the primary mirror will unfold before the observatory becomes operational.

Credits: NASA

The sunshield will keep the scientific payload of the observatory away from any light from the Sun, the Earth, or the Moon. Because JWST will observe primarily the infrared light from very distant objects, the temperature of the scientific payload must be maintained at very low values (under 50K). This requirement is so important that even a part of the observatory (the spacecraft bus) had to be placed on the warm side of the sunshield.

The sunshield not only protects the scientific instruments from the heat of the Sun, the Earth, the Moon, and the warm spacecraft bus electronics, but it also provides a stable thermal environment. This is necessary in order to maintain the alignment of the eighteen hexagonal components of the mirror while the observatory changes its orientation relative to the Sun.

The primary mirror is the essential component of a telescope. The design of the primary mirror was driven by a number of important requirements: the size, the mass, and the temperature at which the mirror will operate.

Credits: NASA

In order to be able to see galaxies from thirteen billion light-years away, scientists determined that the mirror must have a diameter of at least 6.5 meters.

The weight of the primary mirror has only one tenth of the mass of Hubble’s mirror per unit area. Considering the size of the mirror, this made the task of launching the telescope into space achievable.

Due to the fact that the telescope will observe the light in the infrared spectrum, the temperature of the mirror has to be as low as –220 degrees Celsius. If operating at the same temperature as the ground telescopes do, the infrared glow of the mirror would interfere with the light received from distant galaxies. Basically, these distant galaxies would disappear in the noise generated by the telescope.

The engineering challenge that scientists faced was to build a lightweight mirror that would preserve its optical and geometric properties when cooled to –220 degrees Celsius. Using beryllium was the solution. Beryllium is lightweight (it is widely used in the aerospace industry) and it is very good at holding its shape across a range of temperatures.

As we mentioned above, the PMBA contains the Integrated Instrument Module (IIM), which is the scientific payload onboard the observatory. The scientific payload includes the following scientific instruments: the Mid-Infrared Instrument (MIRI), the Near-Infrared Spectrograph (NIRSpec), the Near-Infrared Camera (NIRCam), and the Fine Guidance Sensor (FGS).

The MIRI is an imager/spectrograph that covers the wavelength range from 5 to 27 micrometers. The nominal operating temperature for the MIRI is 7K. The NIRSpec covers two wavelength ranges: from 1 to 5 micrometers (medium-resolution spectroscopy) and from 0.6 to 5 micrometers (lower-resolution spectroscopy). The NIRCam was provided by the University of Arizona. NIRCam covers the spectrum from 0.6 to 5 micrometers. The FGS is a broadband guide camera that is used for guide star acquisition and fine pointing.

Credits: ESA

The spacecraft bus is composed of every subsystem of the observatory minus the sunshield and the scientific payload, and it provides the necessary support functions for the operations of the observatory. The spacecraft bus contains the Electrical Power Subsystem (EPS), the Attitude Control Subsystem (ACS), the Communication Subsystem (CS), the Command and Data Handling Subsystem (C&DHS), the Propulsion Subsystem (PS), and the Thermal Control Subsystem (TCS).

One interesting thing I would like to mention here is that the C&DH subsystem is using a solid-state recorder as memory/data storage for the observatory. I cannot envision a hard disk drive taking all of the vibrations during the launch and running for ten years without any flaws, so the choice of using radiation hardened solid-state memory units on long-term space mission spacecrafts seems to be the optimal choice.

The launch vehicle chosen for this mission is the European Ariane 5. The Ariane 5, carrying the James Webb Space Telescope, will liftoff from Guiana sometime in 2013. The space telescope will operate from the L2 point of the Sun-Earth system.

All three agencies that are part of the project, ESA, NASA, and CSA, have web pages dedicated to the JWST observatory.

Credits: JAXA

If measures are not taken to address the effects of the greenhouse gases produced by our civilization, extreme climate changes will occur: droughts, heat waves, and floods.

Understanding the behavior of greenhouse gases is critical for developing effective measures to fight climate change.

The Greenhouse Gases Observing Satellite (GOSAT) is the first satellite to observe greenhouse gases from space. The main contributors behind GOSAT are the Japan Aerospace Exploration Agency (JAXA), the National Institute for Environmental Studies (NIES), and the Ministry of Environment (MOE). The chosen nickname for GOSAT is IBUKI, which means breath or puff.

The data collected by the GOSAT satellite will help us make better estimates as to how different areas on Earth contribute to global warming through the emission of greenhouse gases. The data will also help us understand the behavior of the greenhouse gases by combining global observation data collected on orbit with data collected on the ground, and it will also help us improve simulation models.

Credits: JAXA

The observation instrument onboard GOSAT is called the Thermal And Near-infrared Sensor for carbon Observation (TANSO).

There are two sensors that collect data for the instrument: a Fourier Transform Spectrometer (FTS) and a Cloud Aerosol Imager (CAI).

The sensors will observe the infrared light from the Earth’s surface and will return measurements that can be used to calculate the abundance of carbon dioxide (CO₂) and methane (CH₄).

The operational orbit will allow GOSAT to circle the Earth in roughly 100 minutes and to return above the same Earth coordinates every three days. One thing to mention here is that the observations can be done only on cloud-free areas, meaning that on average only ten percent of the total number of measurements can be used for calculating the abundance of CO₂ and CH₄. However, the number of measurement points surpasses the current number of ground measuring points (under 200) and areas that have never been monitored will be covered by GOSAT observations.

Credits: JAXA / MHI

A Mitsubishi H-IIA launch vehicle will inject GOSAT into its predetermined orbit: a sun-synchronous sub-recurrent orbit at a perigee altitude of 667 km, apogee altitude of 683 km, and an inclination of 98 degrees. It will be the fifteenth flight of an H-IIA. The model used for this launch, H2A202, has two solid rocket boosters.

Besides GOSAT, which is the main payload, the payload includes several piggyback payloads. In the case of an excessive launch capability, it is common practice to include in the payload small satellites that are made by private companies or universities.

Seven micro-satellites, six selected through public tender and one JAXA satellite, will be launched by the H-IIA launch vehicle with Ibuki: KAGAYAKI / SORUN CORPORATION (debris detection and Aurora electric current observation mission), STARS / Kagawa University (tether space robot demonstration), KKS-1 / Tokyo Metropolitan College of Industrial Technology (demonstration of the micro cluster and three axis attitude control functions), PRISM / The University of Tokyo (earth image acquisition by using an expandable refracting telescope), SOHLA-1 / ASTRO TECHNOLOGY SOHLA (measurements of thunder and lightning), SPRITE-SAT / Tohoku University (observations of the sprite phenomenon and gamma radiation of the Earth’s origin), and Small Demonstration Satellite-1 (SDS-1) / JAXA (on-orbit verification of the space wire demonstration).

For more details on the additional payload for the GOSAT/Ibuki mission, you can check out the piggyback payload web page on the JAXA web site. Some of the links on the page require knowledge of Japanese or hands-on experience with the Google translation tool.

The launch date for GOSAT/Ibuki has been set. The H-IIA Launch Vehicle No.15 will liftoff sometime between 12:54 and 1:16 PM on January 21, 2009.

Check out the GOSAT / IBUKI program page on the JAXA web site for more information.

Credits: NASA

The Multi-Purpose Logistics Module (MPLM) is a pressurized module that is used on Space Shuttle missions to transfer cargo to and from the International Space Station (ISS).

A typical MPLM mission starts in the cargo bay of a Space Shuttle. The MPLM is carried to the ISS and berthed to one of the docking modules by the Canadian robotic arm. The supplies are offloaded and then finished experiments and waste are loaded on to the module. At the end of the mission, the MPLM is moved to the Space Shuttle cargo bay and returned to Earth.

The Italian Space Agency (ASI) provides the modules to NASA. Three MPLMs have been built and delivered to NASA thus far. NASA owns the MPLMs and ASI receives research time on ISS in exchange. The MPLMs were named after great figures in Italian history: Leonardo, Raffaello, and Donatello. However, some of the mission badges display the ninja turtles instead.

The construction of the first MPLM – Leonardo – began in April 1996. Leonardo was delivered to NASA in August 1998. Raffaello and Donatello followed in August 1999 and February 2001, respectively. Each MPLM can make 25 return trips to space.

Credits: NASA

The MPLM is 6.4 meters long and 4.6 meters in diameter. The module weighs 4.5 tons and it can deliver up to 10 tons to the ISS. The design of the module resembles the payload module that is part of the ATV. In addition, ATV has a service module that offers autonomy. Obviously, ATV was the direct beneficiary of the knowledge gained during the design and operational phases of the MPLM.

There is room for sixteen standard payload racks (International Standard Payload Racks – ISPR) in the MPLM. Even if it is not used to carry a human crew, MPLM has its own life-support system. Furthermore, it has a 3 KW internal power supply.

Credits: NASA

The current Space Shuttle mission – STS 126 – has delivered the MPLM Leonardo to the ISS. Leonardo is on its fifth spaceflight and hauled over 14,000 pounds of supplies and equipment to ISS.

Part (a small part) of the payload was turkey, candied yams, stuffing, and dessert for a Thanksgiving meal at the station.

A special piece of equipment, the GLACIER, was also delivered to the station. GLACIER stands for General Laboratory Active Cryogenic ISS Experiment Refrigerator. GLACIER is a double locker cryogenic freezer that will be used for transporting and preserving science experiments. The payload also included a galley for the Destiny laboratory, an advanced Resistive Exercise Device (aRED), and two new crew quarter racks for the expanded station crew.

Credits: NASA

There are two more MPLM missions scheduled before the Space Shuttle retires. STS-128 will carry Leonardo in July 2009, and Raffaello will be docked to ISS during the STS-131 mission in February 2010.

Credits: NASA

In 2002, an instrument on the Mars Odyssey spacecraft detected hydrogen under the Martian surface. This was regarded as clear evidence that there is subsurface water ice on Mars.

In 2003, NASA decided to revive a mission that was cancelled in 2001 due to the fact that a previous mission, the Mars Polar Lander, was lost in 1999. The revived mission was named Phoenix.

A Lander that could reach out and touch the ice was needed. The half-built spacecraft for the previously cancelled mission already had in place a 7.7-foot robotic arm that could do the trick.

A JPL team reviewed the data from the failed mission in 1999 and corrected the mistakes made. Every system used in the previous design was taken apart, tested, and examined. The suspected culprits were the retrorockets used during landing. More than a dozen issues that could have caused a failure of the new planned mission were found and fixed.

Credits: NASA / JPL

The Phoenix mission inherited a capable spacecraft partially built for the Mars Surveyor Program 2001. As we mentioned, the lessons learned from the Mars Polar Lander helped improve the existing systems. As for any other space mission, the conditions in which the spacecraft operates dictate the design.

In the case of the Phoenix mission, the following phases were considered: the launch, the cruise, the atmospheric entry, the touchdown, and the surface operations phase. The launch induces tremendous load forces and vibrations. The 10-month cruise to Mars exposes the spacecraft to the vacuum of space, solar radiation, and possible impacts with micrometeorites. During the atmospheric entry, the spacecraft is heated to thousands of degrees due to aero braking, and has to withstand tremendous deceleration during the parachute deployment. The extremely cold temperatures of the Martian arctic and the dust storms must be considered during the surface operations phase.

Credits: NASA / JPL

Several instruments are mounted on the Lander: the robotic arm (RA), the robotic arm camera (RAC), the thermal and evolved gas analyzer (TEGA), the Mars descent imager (MARDI), the meteorological station (MET), the surface stereo imager (SSI), and the microscopy, electrochemistry, and conductivity analyzer (MECA).

The RA was built by the Jet Propulsion Laboratory and was designed to perform the scouting operations on Mars, such as digging trenches and scooping the soil and water ice samples. RA delivered the samples to the TEGA and the MECA. RA is 2.35 meters long, it has an elbow joint in the middle, and it is capable of digging trenches 0.5 meters deep in the Martian soil.

The University of Arizona and the Max Planck Institute in Germany built the RAC. The camera is attached to the RA, just above the scoop placed at the end of the arm. RAC provided close-up, full-color images.

Credits: NASA / JPL

TEGA was developed by the University of Arizona and University of Texas, Dallas. TEGA used eight tiny ovens to analyze eight unique ice and soil samples. By employing a process called scanning calorimetry, and by using a mass spectrometer to analyze the gas obtained in the furnaces as the temperature raised to 1000 degrees Celsius, TEGA determined the ratio of various isotopes of hydrogen, oxygen, carbon, and nitrogen.

MARDI was built by Malin Space Science Systems. From what I could gather, the MARDI was not used by the Lander due to some integration issues.

The Canadian Space Agency (YAY Canada!) was responsible for the overall development of the meteorological station (MET). Two companies from Ontario, MD Robotics and Optech Inc., provided the instruments for the station.

The SSI served as the eyes of the Phoenix mission. SSI provided high-resolution, stereo, panoramic images of the Martian arctic. An extended mast holds the SSI, so the images were recorded from two meters above the ground.

Credits: NASA / JPL

MECA was built by the Jet Propulsion Laboratory. The instrument was used to characterize the soil by dissolving small amounts of soil in water. MECA determined the pH, the mineral composition, as well as the concentration of dissolved oxygen and carbon dioxide in the soil samples that were collected.

We would like to highlight some of the important moments during the mission:

August 4, 2007 – Delta II rocket launch from Cape Canaveral. The three-stage Delta II rocket with nine solid rocket boosters lifted off from Cape Canaveral, carrying the Phoenix spacecraft on the first leg of its journey to Mars.

Credits: NASA / JPL -Caltech / University of Arizona

May 25, 2008 – Phoenix Mars Lander touchdown. The Phoenix entered the Martian atmosphere at 13,000 mph. It took 7 minutes for the Lander to slow down with the aid of a parachute and to land using its retrorockets. The mission team did not have to wait long before discovering ice because the blasts from the retrorockets had blown away the topsoil during landing and revealed ice patches under the lander.

November 2, 2008 – Last signal received from the Lander. On this date, communication was established for the last time with Phoenix. Due to the latitude of the landing site, not enough sunlight is available and the solar arrays are unable to collect the power necessary to charge the batteries that operate the instruments mounted on the Lander. At the landing site, the weather conditions are worsening.

November 10, 2008 – Mission declared completed. NASA declares that the Mars Phoenix Lander has completed a successful mission on the Red Planet. Phoenix Mars Lander has ceased communications after being operational for more than five months (the designed operational life of the mission was 90 days).

November 13, 2008 – Mission Honored. NASA’s Phoenix Mars Lander was awarded Best of What’s New Grand Award in the aviation and space category by Popular Science magazine.

Credits: NASA / JPL

The Mars Phoenix Lander made significant contributions to the study of the Red Planet. Phoenix verified the presence of water ice under the Martian surface, and it returned thousands of pictures from Mars. Phoenix also found small concentrations of salts that could be nutrients for life, it discovered perchlorate salt, and calcium carbonate, which is a marker of effects of liquid water.

Phoenix provided a mission long weather record, with data on temperature, pressure, humidity, and wind, as well as observations on snow, haze, clouds, frost, and whirlwinds.

Principal Investigator Peter H. Smith of the University of Arizona led the Phoenix mission. The project management was done at NASA’s Jet Propulsion Laboratory and the development at Lockheed Martin Space Systems in Denver. Other contributors were the Canadian Space Agency, the University of Neuchatel (Switzerland), the University of Copenhagen (Denmark), the Max Planck Institute (Germany), and the Finnish Meteorological Institute.

For more information about the Phoenix mission, check out the NASA Phoenix Mars Lander Page.

Credits: ESA – S. Corvaja 2007

CNES and ESA signed the development contract to build the launch facilities for Soyuz at the Guiana Space Centre on July 19, 2005. The Soyuz launcher will give Europe medium-lift capability and will complete the range of launchers operated by Arianespace, which includes the Ariane 5 heavy-lift launcher and the Vega small launcher.

The Soyuz launchers that will liftoff from Kourou have a number of improvements: an updated digital flight control system, an increased-performance third stage, and the larger Soyuz ST payload fairing.

The launcher has a length of 46.2 meters, a diameter of 10.3 meters, and a liftoff mass of 308 tons. Due to the position of the launch site, close to the equator, the payload capacity of the launcher has increased significantly: 3,150 kg to a geostationary orbit, and 4,900 kg to a sun-synchronous orbit, with a circular altitude of 820 km.

Soyuz is a reliable, four-stage launch vehicle, which has been in production since 1957 and has accounted for more than 1,700 missions to date.

The first stage is composed of the four boosters that are assembled around the central core of the launcher. The RD-107A engines installed on the boosters use liquid oxygen and kerosene as propellant combination. Each engine has four combustion chambers and four nozzles. One aerofin and two movable vernier thrusters per engine are used for the three-axis flight control.

Credits: ESA – S. Corvaja 2008

The second stage consists of the central core surrounded by the boosters. It uses the same propellant combination for powering the RD-108A engine with four combustion chambers and nozzles.

Four vernier thrusters are used for three-axis flight control, after the boosters of the first stage are jettisoned during flight.

The engines of the first two stages are ignited 20 seconds before liftoff. The reason for this is that the launch procedures include monitoring the engine health parameters just before liftoff, while the engines are operating at an intermediate level of thrust. This reminds me of the SpaceX Falcon 1 booster launch procedures. SpaceX engineers perform a similar monitoring procedure for the Merlin engine just before the Falcon 1 liftoff.

The third stage utilizes a RD-0124 engine, also powered by liquid oxygen and kerosene. The liquid oxygen and kerosene tanks are pressurized using helium stored in vessels located in the liquid oxygen tank. The avionics module of the launcher is carried by this stage. The new flight control system improves the accuracy and the control capability for the launcher, as additional flight control authority is needed for the enlarged payload fairing.

Credits: ESA – S. Corvaja 2008

The upper stage of the Soyuz launcher is called Fregat. Fregat is an autonomous and flexible upper stage with its own guidance, navigation, control, tracking, and telemetry systems. It was designed to operate as an orbital vehicle, and it extends the launch capabilities of the Soyuz launcher to medium-Earth orbits, Sun-synchronous orbits, geostationary transfer orbits, and Earth escape trajectories.

The Fregat stage can be restarted up to 20 times in flight, it can provide three-axis stabilization, and perform a spin-up of the spacecraft payload. Fregat uses a bi-propellant propulsion system: UDMH (unsymmetrical dimethylhydrazine) and NTO (nitrogen tetroxide).

The payload fairing is the most visible change to the Soyuz launcher. The new Soyuz fairing has a diameter of 4.11 meters and a length of 11.4 meters. The fairing is based on the configuration used for Ariane 4 vehicles.

The construction of the Soyuz launch base in French Guiana started in early 2007. At the groundbreaking ceremony on February 26, 2007, a number of European space industry officials were present: Jean-Jacques Dordain – ESA Director General, Yannick d’Escatha – President of CNES, Jean-Yves Le Gall – Director General of Arianespace, and Anatoly Perminov – Head of Roscosmos.

In 2007, Arianespace ordered four Soyuz launchers for the early launch missions that are scheduled for the second half of 2009. A contract was also signed in September 2008 for 10 more Soyuz launch vehicles.

The Soyuz launch missions that are scheduled for 2009 signal the beginning of a new chapter in ESA-Russian relations. Stay tuned for more information about the Soyuz launches from French Guiana!

Credits: ESA – J. Huart

The small-payload market is rapidly expanding. Institutional programs (mostly Earth observation and scientific missions) drive this emerging market. In order to meet the demands of the small-payload market, ESA has transformed the small launcher program initiated by the Italian Space Agency (ASI) in the 1990s into Vega, a co-operative project with other Member States within the ESA framework.

The small-payload market consists of satellites up to 3,000 kg and it stands at around five missions per year. There are many classifications for the satellites in this market, so we will present just one classification for informational purposes. The satellites in this class are divided into three categories: micro-satellites (up to 300 kg), mini-satellites (from 300 kg to 1,000 kg), and small satellites (from 1,000 kg to 3,000 kg).

The orbits required for the deployment of these satellites are mainly Sun Synchronous Orbits (SSO) and Low Earth Orbits (LEO). Vega’s in-orbit launch capability benchmark is 1,500 kg into a 700 km altitude polar orbit. Being designed to cope with a wide range of missions, Vega will address the various market requirements for this class of satellites.

Credits: ESA

Vega is a single-body launcher composed of four stages. The first three stages are solid propellant stages, while the fourth stage has a liquid propellant engine. Vega is 30 meters high, has a maximum diameter of three meters and a total of 137 tons at lift-off.

There are three main sections: the Lower Composite, the Restartable Upper Module and the Payload Composite.

The Lower Composite section consists of the first three stages (the solid propellant stages). The first stage is equipped with a P80-FW motor containing 88 tons of propellant. The second stage contains a Zefiro 23 motor with 23 tons of propellant. The third stage consists of a Zefiro 9 motor with 10 tons of propellant and the stage-interfacing structures.

The technology for the three solid-propellant stages (P80, Z23, Z9) is derived from the Zefiro 16 rocket motor. These motors benefit from the experience acquired by Europe in the field of solid propulsion. Each motor is composed of a thermal-insulated carbon-epoxy monolithic case, the solid propellant HTPB 1912, a nozzle, a thrust vector control system driven by two electro-actuators that operate the movable nozzle, and a control unit that provides pitch and yaw control during the flight. Each stage also includes an ignition subsystem, a safety subsystem, and the interfaces to the other stages.

Credits: ESA/CNES-SOV

The P80 engine was designed for the Vega small launcher, and it helps validate technologies applicable to a new generation of solid boosters for the Ariane 5 launch vehicle. This new design was driven by the goal of minimizing recurring costs, a significant reduction being made with respect to the current metal case boosters.

The Restartable Upper Module is the fourth stage of the launcher. It is also known as the Altitude and Vernier Upper Module (AVUM). The AVUM consists of two modules: the AVUM Propulsion Module and the AVUM Avionics Module.

The propulsion system uses NTO (Nitrogen Tetroxide) and UDMH (Unsymmetrical dimethyl hydrazine) as propellants. The propellants are stored in two identical titanium tanks pressurized by helium. Depending on the mission, the propellant load can be between 250 kg and 500 kg.

The avionics system is largely adapted from existing hardware and/or components already under development (namely subsystems already in use by the Ariane 5 launch vehicle).

The Payload Composite section is composed of the fairing and the payload/launcher interface structure. The fairing is composed of two shells that are jettisoned during flight after the separation of the second stage. The payload/launcher interface is an Adaptor 937, which is a standard interface used on the European launchers. Additional payload adapters can be added for multi-payload missions.

Credits: ESA – J. Huart

The dedicated Ground Segment for the Vega launcher comprises of the Launch Zone (ZLV – Zone de Lancement Vega) and the Operational Control Center, all located at the European Spaceport at Kourou, in French Guiana. ESA also built a Payload Preparation Complex that will be used for satellite and equipment unpacking, mechanical inspections, the checkout of the payloads, and the final integration of the payload composite before mounting it on top of the launcher.

On October 24, 2008, the Zefiro 9 rocket engine passed the first qualification test. There is one additional firing test left for the engine. The Vega launcher’s qualification flight is scheduled to take place by the end of 2009.

Credits: Avio SpA (Italy)

ESA is responsible for the qualification of the launch service and also for sustaining the qualification status during the exploitation phase. Ariane Space will be responsible for Vega’s commercialization and launch operations. The expected launch rate for Vega will be up to four launches per year.

Please stay tuned on the OrbitalHub frequency. We will keep you posted!