EBAD Provides Critical Release Mechanisms for NASA’s Nancy Grace Roman Space Telescope
Following the successful launch and completion of the Nancy Grace Roman Space Telescope’s on-orbit deployment sequence, Ensign-Bickford Aerospace & Defense (EBAD) is highlighting the release mechanism technology manufactured at its Moorpark, California facility that supported the observatory’s transition from its launch configuration to its deployed flight configuration.
A number of release mechanisms supported critical spacecraft deployment functions using EBAD technology.
The Roman hardware included EBAD TiNi™ P50 Pin Pullers supporting cover release, as well as NEA® release mechanisms supporting boom and solar-array release functions. These systems are part of EBAD’s broader portfolio of non-pyrotechnic hold-down and release solutions, including TiNi™ Pin Pullers offered in multiple force levels and configurations, and NEA® products available as hold-down release mechanisms, pin pullers, lithium-ion cell bypass switches and isolation valves. Both product families can be configured or customized to meet the mechanical, electrical and environmental requirements of spacecraft, launch vehicle and defense applications.
Roman launched aboard a SpaceX Falcon Heavy at NASA’s Kennedy Space Center and traveled approximately one million miles to a quasi-halo orbit around the Sun-Earth second Lagrange point, or L2. From this operating location, the observatory will conduct wide-field infrared surveys focused on dark energy, dark matter, exoplanets and galaxy evolution.
TiNi P50 Pin Pullers
The TiNi™ P50 is part of EBAD’s flight-qualified TiNi™ Pin Puller family, which uses shape-memory-alloy technology and a patented trigger mechanism to rapidly retract the output pin and release restrained hardware. The product family includes five standard configurations: the P5, P10, P25, P50 and P100, providing different pull-force levels for a range of aerospace and defense applications.
The P50 provides a nominal 50 lbf, or 222 N, pull force and is designed for demanding aerospace applications. EBAD’s published specifications list an operating temperature range of -65°C to +70°C for the P50, with a maximum function time of 100 milliseconds at 4 amps. Across the TiNi™ family, the pin pullers offer non-pyrotechnic operation, electrical redundancy, millisecond response times and front- or rear-reset capability.
For the Roman application, the P50 configuration was optimized for low-temperature performance, providing a compact, fast-acting release solution for the spacecraft’s Deployable Aperture Cover release sequence.
NEA Release Mechanisms
NEA® mechanisms are non-pyrotechnic hold-down and release technologies designed for high-preload spacecraft applications. The product family includes hold-down and release mechanisms, pin pullers, lithium-ion cell bypass switches and isolation valves. NEA® mechanisms are available in standard and customized configurations to address specific mechanical interfaces, preload requirements, electrical interfaces and environmental conditions.
Their ultra-low release shock is particularly valuable for spacecraft carrying sensitive optical and scientific instruments. The mechanisms release stored preload in a controlled manner while maintaining fast actuation times, making them suitable for applications requiring synchronized release, including solar-array deployment and spacecraft stage separation.
For Roman, EBAD mechanisms supported the release of critical deployable structures, including spacecraft booms and solar-array hardware. The mechanisms maintained secure restraint throughout launch and then executed their commanded release sequences after the spacecraft reached orbit.
EBAD’s NEA® technology has extensive spaceflight heritage. NEA® mechanisms have flown on more than 750 spacecraft, with thousands of on-orbit actuations without failure.
Supporting Roman’s On-Orbit Deployment and Mission Architecture
Roman’s deployment sequence was a coordinated series of mechanical release and structural deployment events. The spacecraft had to maintain launch restraint through high vibration and acceleration, then execute time-critical release commands while managing stored preload, release shock, dynamic coupling and deployment clearances. Successful deployment also depended on the resulting structures reaching their required on-orbit positions and maintaining the stability needed for communications and infrared science operations.
The spacecraft’s High-Gain Antenna, or HGA, provides the primary high-rate science communications link between Roman and ground stations. Its dual-band architecture supports S-band uplink and downlink for command and housekeeping telemetry, while Ka-band communications support the high-rate transmission of science data.
The HGA incorporates a lightweight carbon-composite reflector and multi-axis pointing gimbals to establish and maintain the required ground-station pointing geometry. A Ka-band transmitter and traveling-wave-tube amplifier support science data rates of up to 500 megabits per second, enabling the downlink of the high-volume imagery and science data generated by Roman’s wide-field surveys.
The Lower Instrument Sun Shade, or LISS, is a deployable thermal-control structure designed to limit solar energy input to Roman’s infrared instrument suite. The assembly consists of two large aluminum honeycomb sandwich panels covered with a 17-layer polymer film system.
The LISS deployment incorporated mechanical damping to control panel motion and reduce transient loads transmitted into the observatory structure. This was particularly important for limiting dynamic disturbances during deployment and maintaining the mechanical and optical stability required by the instrument assemblies.
The Deployable Aperture Cover, or visor, provided launch-phase protection for the primary mirror and telescope aperture. It constrained the aperture during launch and early flight, limiting exposure to particulate and molecular contamination before being released from the optical path.
The visor also contributes to the observatory’s stray-light and thermal-control architecture. Its reinforced thermal blanket system limits localized solar heating of the surrounding structure, helping control thermally induced distortion and preserve the alignment and focus stability required for precision infrared observations.
The Solar Array Sun Shield, or SASS, integrates electrical power generation with thermal management. The solar arrays provide power to the spacecraft bus and onboard electronics, while the shield reduces solar energy transfer toward the observatory’s cold side, where the Wide Field Instrument is located.
This system-level architecture places demanding requirements on every deployment device. Release mechanisms must provide positive restraint during launch, predictable release performance, low disturbance to sensitive payloads and compatibility with the spacecraft’s electrical and mechanical interfaces. Once released, the associated structures must achieve their deployed configuration without compromising pointing, thermal balance, contamination control or optical performance.
Roman therefore represents more than a collection of individual deployment events. It is an integrated spacecraft system in which release mechanism performance directly supports the transition from launch configuration to a stable, operational observatory.
To learn more about EBAD’s mechanisms and the part they played in Nancy Grace Roman Space Telescope’s success mission to space watch the video below.