Ares I-X

Ares I-X

End of mission

Ares I-X was the first test flight in the Ares I program, a launch system for human spaceflight currently under development by the United States space agency NASA. Ares I-X was successfully launched on October 28, 2009.

The Ares I-X vehicle used in the test flight was similar in shape, weight, and size to the planned configuration of later Ares I vehicles, but had largely dissimilar internal hardware. Ares I vehicles are intended to launch Orion crew exploration vehicles. Along with the Ares V launch system and the Altair lunar lander, Ares I and Orion are part of NASA's Constellation Program, which is developing spacecraft for U.S. human spaceflight after the Space Shuttle fleet is expected to retire from service in 2010.

Configuration

Rollout of Ares I-X at Kennedy Space Center Launch Complex 39. Secured by only four bolts on a mobile launcher platform, it took the 327-foot (100 m) tall Ares I-X rocket 8 hours and 40 minutes to move 4.2 miles (6.8 km) from the Vehicle Assembly Building to Launch Pad 39B at a speed of 0.48 mph (0.78 km/h).

Section data: AIAA'

• First stage: live, four-segment reusable solid rocket booster with a dummy fifth segment.
• Second stage: dummy (future upper stage, J-2X motor)
• Third stage: dummy (future instrument package)
• Fourth stage: Orion Boilerplate with Launch Abort System (LAS)

The liftoff weight of the rocket was 1.8 million pounds (816,466 kg).

Test objectives

Ares I-X was the first test flight of a launch vehicle like the Ares I. The test flight objectives included:

• Demonstrating control of a dynamically similar vehicle using control algorithms similar to those used for Ares I.
• Performing an in-flight separation/staging event between an Ares I-similar First Stage and a representative Upper Stage.
• Demonstrating assembly and recovery of an Ares I-like First Stage at Kennedy Space Center (KSC).
• Demonstrating First Stage separation sequencing, and measuring First Stage atmospheric entry dynamics, and parachute performance.
• Characterizing the magnitude of integrated vehicle roll torque throughout First Stage flight.

The flight also had several secondary objectives, including:

• Quantifying the effectiveness of the first stage booster deceleration motors.
• Characterizing induced environments and loads on the vehicle during ascent.
• Demonstrating a procedure for determining the vehicle’s position to orient the flight control system.
• Characterize induced loads on the Flight Test Vehicle while on the launch pad.
• Assess potential Ares I access locations in the VAB and on the Pad.
• Assess First Stage electrical umbilical performance.

The Ares I-X flight profile closely approximated the flight conditions that Ares I will experience through Mach 4.5, at an altitude of about 130,000 feet (39,600 m) and through a maximum dynamic pressure (“Max Q”) of approximately 800 pounds per square foot (38.3 kPa).

The Ares I-X flight profile resembled the uncrewed Saturn I flights of the 1960s, which tested the Saturn propulsion concept.

By flying the vehicle through first stage separation, the test flight also verified the performance and dynamics of the Ares I solid rocket booster in a “single stick” arrangement, which is different from the solid rocket booster’s current “double-booster” configuration alongside the external tank on the space shuttle.

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Description

The rocket was split into independent parts that separated at different times in the launch.

The Ares I–X vehicle consisted of a functional four-segment solid rocket booster stage, a fifth segment mass simulator, an upper stage simulator (USS), which was similar in shape and heavier than the actual upper stage, as well as a simulated Orion crew module (CM) and launch abort system (LAS). Since the actual upper stage hardware could not be produced in time for the flight test, the upper stage mass simulator allowed the booster to fly approximately the same trajectory through the first stage of flight. The USS and the CM/LAS mass simulators launched by the Ares I-X were not recovered because they fell into the Atlantic Ocean. The first stage, including the fifth segment mass simulator, was recovered to retrieve flight data recorders and reusable equipment.

First stage

The first stage

The four-segment solid rocket motor and aft skirt for Ares I-X was drawn directly from the Space Shuttle inventory. The motor was manufactured by ATK Launch Services of Promontory, Utah. The new forward structures were manufactured by Major Tool & Machine of Indianapolis, Indiana. The first stage element was managed by Marshall Space Flight Center in Huntsville, Alabama. Modifications to the solid rocket booster include:

• The aft skirt was modified to include eight booster deceleration motors, which pulled the booster directly away from the upper stage simulator, as well as four booster tumble motors, which caused the booster to tumble horizontally to decrease its velocity prior to reentry. The aft skirt also housed one of two Redundant Rate Gyro Units (RRGUs), which provided data to inform the Fault Tolerant Inertial Navigation Unit (FTINU) of the vehicle’s attitude and position. Steel ballast of 3,500 pounds (1,589 kg) was also added to the aft skirt to move the first stage’s center of gravity aft to ensure that the first stage would tumble properly after separation.

• An extended service tunnel along the exterior, which accommodated:

• An extended linear shaped charge for the flight termination system, to cover all four segments in the event the stage needed to be self-destructed.

• Cabling for additional pressure and environmental instrumentation.

• A fifth segment simulator, which allowed the Ares I-X to simulate the length and mass of the Ares I five-segment motor and housed the First Stage Avionics Module (FSAM). The FSAM contained the electronics boxes that:

• Captured and stored flight data for recovery after splashdown.

• Provided electrical power for the avionics systems.

• Performed separation and parachute deployment commands.

• Contained video cameras that record the first stage separation.

• A hollow forward skirt which simulated the Ares I First Stage forward skirt.

• A forward skirt extension, which housed new, larger parachutes. The three main parachutes each had a 150-foot (46 m) diameter, compared to the Shuttle booster main parachutes, which are 136 feet (41 m) across. It also had a Shuttle booster heritage nosecap that covers the pilot and drogue parachutes. Jettisoning the nosecap released the pilot parachute which pulled out the drogue. The forward skirt extension separated from the booster deploying the main parachutes.

• A frustum, which was a hollow, inverted half-cone that connected the 12-foot-diameter first stage to the 18-foot-diameter upper stage simulator.

For the Ares I-X flight test, the frustum and forward skirt extension were made of aluminum. The forward skirt and fifth segment simulator were made of steel.

Upper stage simulator

The upper stage simulator

The upper stage simulator (USS) was manufactured by NASA personnel at Glenn Research Center in Cleveland. Because of transportation limitations (bridge heights on highways and rivers), the simulator was built out of eleven steel segments 9.5 feet (2.9 m) tall by 18 feet (5.5 m) wide. The USS simulated the shape, mass, and center of gravity characteristics of Ares I from the interstage to the top of the service module of the Orion Crew exploration vehicle. The centers of mass for the liquid hydrogen and liquid oxygen tanks were simulated through the use of steel ballast plates.

The USS included a variety of temperature, vibration, thermal, and acoustic sensors to collect the primary data needed to meet the mission objectives. It also housed the Fault Tolerant Inertial Navigation Unit (FTINU), which controlled the vehicle’s flight and primary avionics functions. For stability, the FTINU was mounted on the underside of the lower ballast plates. Ground operations personnel accessed the FTINU through a crew hatch on the side of the interstage segment, which also housed the roll control system. Each USS segment included a ladder and ring-shaped platform to allow access to the sensors and cabling for the developmental flight instrumentation. The stairs and platforms were necessary because Launch Complex 39B is not tall enough to provide crew access to the upper parts of Ares I-X.

Roll control system

The roll control system (artist's impression of launch)

The active roll control system (RoCS) was needed because the flight test vehicle had a tendency to roll around its axis of forward motion. The RoCS for Ares I-X consisted of two modules containing engines originally used on now-decommissioned Peacekeeper missiles. The RoCS performed two primary functions:

• Rolling the vehicle 90 degrees after liftoff to emulate the Ares I roll attitude at launch.
• Maintaining a constant roll attitude during ascent up to stage separation.

The RoCS modules, placed on opposite sides of the outer skin of the Upper Stage Simulator, used hypergolic monomethyl hydrazine (MMH) and nitrogen tetroxide (NTO) for propellants and each included two nozzles, which fired tangential to the skin and at right angles to the roll axis in order to provide a controlling roll torque. The propellants were loaded into the modules at Kennedy Space Center’s Hypergol Maintenance Facility (HMF) and transported on the ground for installation into the USS in the Vehicle Assembly Building (VAB) prior to rollout to Launch Complex 39B.

The RoCS modules were designed and constructed to fit into the Interstage segment of the USS by Teledyne Brown Engineering in Huntsville, Alabama. The engines were hot-fire tested at White Sands Test Facility in 2007 and 2008 to verify that they could perform the pulsing duty cycle required by Ares I-X.

Crew module/launch abort system simulator

At the top of the Ares I-X flight test vehicle was a combined Orion crew module and launch abort system simulator, resembling the structural and aerodynamic characteristics of Ares I. The full-scale crew module (CM) is approximately 16 feet (5 m) in diameter and 7 feet (2.1 m) tall, while the launch abort system (LAS) is 46 feet (14 m) long.

The CM/LAS simulator was built with high fidelity to ensure that its hardware components accurately reflect the shape and physical properties of the models used in computer analyses and wind tunnel tests. This precision enables NASA to compare CM/LAS flight performance with preflight predictions with high confidence. The CM/LAS simulator also helps verify analysis tools and techniques needed to further develop Ares I.

Ares I-X flight data were collected with sensors throughout the vehicle, including approximately 150 sensors in the CM/LAS simulator that recorded thermal, aerodynamic, acoustic, vibration and other data. Data were transmitted to the ground via telemetry and also stored in the First Stage Avionics Module (FSAM), located in the empty fifth segment.

Aerodynamic data collected from sensors in the CM/LAS contribute to measurements of vehicle acceleration and angle of attack. How the tip of the rocket slices through the atmosphere is important because that determines the flow of air over the entire vehicle.

The CM/LAS splashed down in the ocean along with the upper stage simulator (USS) after the boost phase of the mission.

This simulator was designed and built by a government-industry team at Langley Research Center in Virginia. It was flown to Kennedy Space Center by C-5 transport and was the last piece of hardware stacked onto the rocket in the Vehicle Assembly Building.

Avionics

Avionics

Ares I-X used avionics hardware from the Atlas V Evolved Expendable Launch Vehicle (EELV) to control its flight. This hardware included the Fault Tolerant Inertial Navigation Unit (FTINU) and Redundant Rate Gyro Units (RRGUs), and cable harnesses. The first stage was controlled primarily by heritage hardware from existing Space Shuttle systems. A new electronics box, the Ascent Thrust Vector Controller (ATVC), acted as a translation tool to communicate commands from the Atlas-based flight computer to the solid rocket booster’s thrust vector control system. The ATVC was the only new avionics box for the flight. All other components were existing or off-the-shelf units. Ares I-X also employed 720 thermal, acceleration, acoustic, and vibration sensors as part of its developmental flight instrumentation (DFI) to collect the data necessary for the mission. Some of this data was transmitted real-time via telemetry while the rest was stored in electronics boxes located in the First Stage Avionics Module (FSAM), located inside the hollow first stage fifth segment.

The ground-based portion of the mission’s avionics included a ground control, command, and communications (GC3) unit, which was installed on the Mobile Launch Platform (MLP) for launch at Launch Complex 39B at Kennedy Space Center. The GC3 unit enabled the flight control system to interface with computers on the ground. The flight test vehicle flew autonomously and was controlled by the FTINU, located on the underside of the lower ballast plates of the upper stage simulator (USS).

The avionics were developed by Lockheed-Martin of Denver, Colorado, a subcontractor to Jacobs Engineering of Huntsville, Alabama, and is managed by Marshall Space Flight Center in Huntsville, Alabama.

Commemorative payload

Three shoebox-size packages were affixed inside the fifth segment simulator of the first stage to carry:

• Three DVDs with 60-second home videos recorded by the public and submitted through NASA's website.
• 3,500 flags to be distributed to Ares I-X team members.

Processing

Ground operations

Ares I-X at the Launch Pad

Ground operations include activities such as vehicle stacking, integration, rollout, and liftoff, while ground systems include vehicle interfaces and lightning protection. Several new procedures and hardware items were developed for Ares I-X, including:

• A new, taller lightning protection system for Launch Complex 39B, which is taller than the existing tower used for Space Shuttle operations.
• A Shuttle-era firing room has been updated with new computer hardware to support Constellation.
• A platform inside the Vehicle Assembly Building was removed to allow the Ares I-X vehicle to fit and roll out.
• A new vehicle stabilization system (VSS), which kept the vehicle from swaying on the launch pad after rollout. The VSS uses off-the-shelf hydraulic shock absorbers from the Monroe division of Tenneco, Inc.
• Environmental control systems (ECS) regulated temperatures inside the VSS and fifth segment simulator to keep the avionics and ground crew cool.
• Improved computer systems in Firing Room 1 at Launch Complex 39B.
• The ECS interfaces to the rocket are “T-0” units, meaning they disconnected from the launch vehicle automatically when the countdown reached zero.

Ground operations and ground systems were handled by United Space Alliance and NASA personnel at Kennedy Space Center.

Systems engineering and integration

The Ares I-X Systems Engineering & Integration (SE&I) Office, managed by the NASA Langley Research Center, was responsible for integrating the vehicle’s parts into a complete rocket and making sure they work together as a system to meet flight test objectives. SE&I was responsible for ensuring all components functioned collectively to satisfy primary and secondary mission objectives. Detailed management of system interfaces, mission level requirements, validation plans, and flight instrumentation management were key SE&I contributions. SE&I provided the structural, thermal and aerodynamic analyses for the overall system to allow the components to be designed and built. SE&I also managed the mass of the vehicle and developed the trajectory and the guidance, navigation, and control algorithms used for vehicle flight.

To complete these tasks, wind tunnel testing and computational fluid dynamics (CFD) were used to investigate forces acting on the vehicle in various phases of flight, including lift-off, ascent, stage separation and descent. Once the basic design was understood SE&I provided structural analyses for the system to assure the rocket would behave properly once it was integrated.

Scheduling support was provided by Arctic Slope Research of Barrow, Alaska.

Flight

Ares I-X launches from LC-39B, 15:30 UTC, October 28, 2009.

Ares I-X had been scheduled for launch on October 27, 2009, the 48th anniversary of the first Saturn I launch. The launch on the 27th was delayed due to weather concerns (including upper-level winds) and other last-minute concerns. Weather finally caused the mission to be scrubbed for the day at 15:20 UTC on October 27, 2009, and rescheduled for a four-hour launch window opening at 12:00 UTC on October 28, 2009.

Ares I-X launched on October 28, 2009 at 11:30 EDT (15:30 UTC) from the Kennedy Space Center, successfully completing a brief test flight. The vehicle's first stage ignited at T-0 seconds and Ares I-X lifted off from Launch Complex 39B. The first stage separated from the upper stage simulator and parachuted into the Atlantic Ocean roughly 150 miles (240 km) downrange of the launch site. The maximum altitude of the rocket was not immediately known, but had been expected to be 28 miles (45 km). The upper portion of the rocket, which was never meant to be retrieved, impacted further out into the Atlantic Ocean.

References

Mission managers watch the launch.

External links

• NASA web site of Ares I-X
• Ares I-X Blog
• Spherical panorama of the completed stack of the Ares 1-X in highbay 3 of the VAB
• Ares 1-X components on the floor of highbay 4 of the VAB
• Ares 1-X components on the floor of highbay 4 of the VAB seen from above
• Ares 1-X upper stage in the VAB, highbay 3
• Top-to-bottom view of Ares 1-X at mid vehicle in the VAB, highbay 3
• Video of the Ares 1-X test flight on YouTube
• Ares 1-X launch videos from various camera angles (silent) at YouTube
• "Glenn Provides Key Support for Ares I-1 Flight Test". NASA.
• "Kennedy Space Center to become a moonport again". spaceflightnow.com.
• "About the Ares I-X Rocket". nasa.gov.