Tiny NASA Spacecraft Delivers Exoplanet Mission’s First Images

Tiny NASA Spacecraft Delivers Exoplanet Mission’s First Images

This pair of images shows stars observed Feb. 6, 2026, by the SPARCS space telescope simultaneously in the near-ultraviolet, left, and far-ultraviolet, right. The fact that one star is seen in the far-UV while multiple are seen in near-UV offers insights into the temperatures of these stars, with the one visible in both colors being the hottest.
NASA/JPL-Caltech/ASU

With the first images from the spacecraft now in hand, the team behind NASA’s Star-Planet Activity Research CubeSat, or SPARCS, is ready to begin charting the energetic lives of the galaxy’s most common stars to help answer one of humanity’s most profound questions: Which distant worlds beyond our solar system might be habitable? 

Initial, or “first light,” images mark the moment a mission proves its instruments are functioning in space and ready to transition to full science operations. This milestone is especially important for SPARCS, whose observations depend on highly precise ultraviolet (UV) measurements, making the demonstration of the camera’s performance critical to achieving its science goals. The spacecraft launched Jan. 11; the images came down Feb. 6 and were subsequently processed. 

Roughly the size of a large cereal box, SPARCS will monitor flares and sunspot activity on low-mass stars — objects only 30% to 70% the mass of the Sun. These stars are among the most common in the Milky Way and host the majority of the galaxy’s roughly 50 billion habitable-zone terrestrial planets, which are rocky worlds close enough to their stars for temperatures that could allow liquid water and potentially support life. 

“Seeing SPARCS’ first ultraviolet images from orbit is incredibly exciting. They tell us the spacecraft, the telescope, and the detectors are performing as tested on the ground and we are ready to begin the science we built this mission to do,” says SPARCS Principal Investigator Evgenya Shkolnik, professor of Astrophysics at the School of Earth and Space Exploration at Arizona State University, which leads the mission. 

The SPARCS spacecraft is the first dedicated to continuously and simultaneously monitoring the far-ultraviolet and near-ultraviolet radiation from low-mass stars for extended periods. Over its one-year mission, SPARCS will target approximately 20 low-mass stars and observe them over durations of five to 45 days.  

Although such stars are small, dim, and cool compared to the Sun, they are also known to flare far more frequently than our solar system’s star. The flares can dramatically affect the atmospheres of the planets they host. Understanding the host star is key to understanding a planet’s habitability.

Future focused  

“I am so excited that we are on the brink of learning about exoplanets’ host stars and the effect of their activities on the planets’ potential habitability,” said Shouleh Nikzad, the lead developer of the SPARCS camera (dubbed SPARCam) and the chief technologist at NASA’s Jet Propulsion Laboratory in Southern California. “I’m doubly excited that we are contributing to this mission with detector and filter technologies we developed at JPL’s Microdevices Laboratory.” Created in 1989, the facility is where inventors harness physics, chemistry, and material science, including quantum, to deliver first-of-their-kind devices and capabilities for the nation. 

The filters were made using a technique that improves sensitivity and performance by enabling them to be directly deposited onto the specially developed UV-sensitive “delta-doped” detectors. The approach of detector-integrated filters eliminated the need for a separate filter element, resulting in a system that is among the most sensitive of its kind ever flown in space.  

“We took silicon-based detectors — the same technology as in your smartphone camera — and we created a high-sensitivity UV imager. Then we integrated filters into the detector to reject the unwanted light. That is a huge leap forward to doing big science in small packages,” Nikzad said, “and SPARCS serves to demonstrate their long-term performance in space.” 

This technology paves the way for future missions like NASA’s next potential UV-capable flagship mission, the Habitable Worlds Observatory mission concept, as well as smaller interim missions, such as the agency’s forthcoming UVEX (UltraViolet EXplorer), which is led by Caltech in Pasadena.  

The mission takes advantage of advances in computational processing as well, with an onboard computer that can perform data processing and intelligently adjust the observation parameters to better sample the development of flares as they happen.  

“The SPARCS mission brings all of these pieces together — focused science, cutting-edge detectors, and intelligent onboard processing — to deepen our understanding of the stars that most planets in the galaxy call home,” said David Ardila, SPARCS instrument scientist at JPL. “By watching these stars in ultraviolet light in a way we’ve never done before, we’re not just studying flares. These observations will sharpen our picture of stellar environments and help future missions interpret the habitability of distant worlds.”

More about SPARCS 

Funded by NASA and led by Arizona State University, SPARCS is managed under the agency’s Astrophysics Research and Analysis program. The agency’s CubeSat Launch Initiative (CSLI) selected SPARCS in 2022 for a ride to orbit. The initiative is a low-cost pathway for conducting scientific investigations and technology demonstrations in space, enabling students and faculty to gain hands-on experience with flight hardware design, development, and building.  

Blue Canyon Technologies fabricated the spacecraft bus.

News Media Contact

Matthew Segal
Jet Propulsion Laboratory, Pasadena, Calif.
818-354-8307
matthew.j.segal@jpl.nasa.gov

Alise Fisher / Karen Fox
NASA Headquarters, Washington
202-358-2546 / 202-385-1287
alise.m.fisher@nasa.gov / karen.c.fox@nasa.gov

Kim Baptista  
Arizona State University, School of Earth and Space Exploration  
480-727-4662
Kim.Baptista@asu.edu 

2026-016

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Naomi Hartono

Canadarm2 Releases Cygnus XL Spacecraft Ending Cargo Mission

Canadarm2 Releases Cygnus XL Spacecraft Ending Cargo Mission

The Cygnus XL cargo spacecraft departs the International Space Station after its release from the Canadarm2 robotic arm.
The Cygnus XL cargo spacecraft, with its prominent cymbal-shaped UltraFlex solar arrays, departs the International Space Station after its release from the Canadarm2 robotic arm.
NASA+

At 7:06 a.m. EDT, Northrop Grumman’s Cygnus XL was released from the Canadarm2 robotic arm, which earlier detached the cargo spacecraft from the Earth-facing port of the International Space Station’s Unity module. At the time of release, the station was flying about 260 miles over the south Atlantic Ocean.

The Cygnus XL spacecraft successfully departed the space station more than seven months after arriving at the orbiting laboratory to deliver about 11,000 pounds of supplies, scientific investigations, commercial products, hardware and other cargo for NASA and its international partners.

The spacecraft will be commanded to deorbit on Saturday, March 14, to dispose of several thousand pounds of trash during its re-entry into Earth’s atmosphere, where it will harmlessly burn up.

Learn more about station activities by following the space station blog, @space_station on X, as well as the ISS Facebook and ISS Instagram accounts.

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Mark A. Garcia

Cygnus XL Spacecraft Departing Station Soon Live on NASA+

Cygnus XL Spacecraft Departing Station Soon Live on NASA+

Northrop Grumman's Cygnus XL cargo craft, carrying over 11,000 pounds of new science and supplies for the Expedition 73 crew, is pictured in the grips of the International Space Station's Canadarm2 robotic arm following its capture. Both spacecraft were orbiting 257 miles above Tanzania. Cygnus XL is Northrop Grumman's expanded version of its previous Cygnus cargo craft increasing its payload capacity and pressurized cargo volume.
Northrop Grumman’s Cygnus XL cargo craft is pictured in the grips of the Canadarm2 robotic arm following its capture on Sept. 18, 2025. Cygnus XL is Northrop Grumman’s expanded version of its previous Cygnus cargo craft increasing its payload capacity and pressurized cargo volume.
NASA

Live coverage of the departure of Northrop Grumman’s Cygnus XL cargo spacecraft from the International Space Station is underway on NASA+Amazon Prime, and the agency’s YouTube channel. The spacecraft’s release is scheduled for 7:05 a.m. EDT.  

Flight controllers on the ground will send commands for the space station’s Canadarm2 robotic arm to detach the Cygnus XL spacecraft from the Unity module’s Earth-facing port and maneuver it into position for release. ESA (European Space Agency) astronaut Sophie Adenot will monitor Cygnus’ systems as it departs.  

Cygnus XL will be commanded to deorbit on Saturday, March 14, to  dispose of several thousand pounds of trash during its re-entry into Earth’s atmosphere, where it will harmlessly burn up.  

The Northrop Grumman spacecraft launched in September 2025 on a SpaceX Falcon 9   rocket from Space Launch Complex 40 at Cape Canaveral Space Force Station in Florida. This mission was the first flight of the larger, more cargo-capable version of the solar-powered spacecraft.  

Northrop Grumman named the spacecraft the S.S. William “Willie” McCool in honor of the NASA astronaut who perished in 2003 during the space shuttle Columbia accident.  

Learn more about station activities by following the space station blog, @space_station on X, as well as the ISS Facebook and ISS Instagram accounts.

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Mark A. Garcia

Efficient Large Displacement/Large Rotation Dynamic Simulations Using Nonlinear Dynamic Substructures

Efficient Large Displacement/Large Rotation Dynamic Simulations Using Nonlinear Dynamic Substructures

Download PDF: Efficient Large Displacement/Large Rotation Dynamic Simulations Using Nonlinear Dynamic Substructures

Utilizing reduced-order dynamic math models (DMM) in linear system-level dynamic analyses is a well-known practice that enables extreme computational efficiencies. But what about nonlinear system dynamics? Reduced-order DMMs have found their way into contact dynamics. The engineer must look no further than the Henkel-Mar pad separation analysis methodology to verify this fact. More sophisticated applications of DMMs in contact dynamics are possible when certain repetitive geometry pattens are present. For example, Figure 1 shows a type of pipe known as a “flexible” pipe used by the subsea industry. This design features four layers of helically wound steel wires that provide the pipe with its stick/slip behavior during bending, thereby enabling a longer fatigue life in harsh ocean environments. With these helically wound armor layers presenting a repetitive contact topology, contact surfaces can be constructed and tracked enabling the friction logic to operate resulting in the friction hysteretic moment-curvature plot provided in Figure 1 (top). 

Flexible pipe used in subsea industry; moment-curvature of the flexible pipe using reduced-order dynamic math models for surface contact
Flexible pipe used in subsea industry; moment-curvature of the flexible pipe using reduced-order dynamic math models for surface contact 

As seen from Figure 1, the pipe was subjected to many bending cycles and executed in essentially a real-time computation. A single bending cycle of the same pipe in full finite element model (FEM) resolution (i.e., no use of DMMs) would require 48 hours of computation on 36 central processing units (CPUs) running in parallel given the very large order of the FEM.   

What about utilizing DMMs for computationally efficient nonlinear dynamics involving large displacements and rotations? Before addressing this question, the residual flexibility mixed boundary transformation (RFMB1) must be defined. The RFMB coordinate transformation is given as follows: 

The RFMB transformation connects physical and modal degrees of freedom (DoFs) to a reduced set of generalized coordinates

The transformation is a mix of the following submatrices: constraint modes (ψ) due to unit displacements on the b-set boundary degrees of freedom (DoFs) that remain fixed during the eigenvalue problem, residual flexibility (g) due to unit forces at the c-set boundary DoFs that remain free during the eigenvalue problem, and a truncated set of normal modes (φ) computed with the b-set DoFs constrained. It can be shown that the transformation retains full flexibility at the DMM physical DoFs and retains the full dynamics of the FEM up to the user-selected truncation frequency for the normal modes. The reduction of DoFs, and hence the computational efficiency, arises from the number of kept modes (k) being significantly less than the number of interior FEM DoFs. 

Cantilever beam model composed of 20 DMMs
Cantilever beam model composed of 20 DMMs
Cantilever beam rolled up using the 20 NDS DMMs
Cantilever beam rolled up using the 20 NDS DMMs
Same beam bent into “catenary-like” configuration by turning on gravity
Same beam bent into “catenary-like” configuration by turning on gravity

To enable DMM large displacements/rotations, four coordinates are added to the above RFMB to track large rotations. These quaternions replace the rigid-body modes that are only valid for infinitesimal rotations. With this process, the RFMB is transformed into a nonlinear dynamic substructure (NDS). Solution algorithms need to be modified accordingly as well to allow for equilibrium iterations since the problem now is highly nonlinear. As an example, consider the undeformed cantilever beam model (Figure 2) composed of 20 DMMs (single DMM of a beam composed of 5 CBAR elements repeated 20x).   

A moment is applied at the free end (right end) of Figure 2. While small displacement theory is limited and breaks down after a few degrees of rotation, the cantilever beam can be completely rolled up using NDS (see Figure 3) in a highly nonlinear dynamic simulation. Also note that the entire nonlinear dynamic simulation was executed in seconds on a laptop and included all dynamic effects. Similarly, the beam can be bent into a “catenary-like2” shape by turning on gravity and enforcing displacements at each end to the required coupling location (see Figure 4). 

One application for this large displacement/rotation NDS capability has been to include umbilical models in the coupled loads analysis (CLA) framework. Figure 5 shows the Interim Cryogenic Propulsion Stage (ICPS) umbilical that was integrated into the Space Launch System (SLS) CLA. The SLS CLA is an integrated assembly of various component DMMs (boosters, core stage, mobile launcher (ML), upper stage, etc.) to which the ICPS umbilical (ICPSU) and its hoses as NDS DMMs can now be added. For each hose, one end connects to the SLS vehicle and the other end to the ML structure. As an example, Figure 6 shows the evolution of the deformations of the forward vent hose (modeled with 20 NDS DMMs) as it goes from the undeformed geometry (straight line) into its prelaunch geometry during the initial condition setup in the CLA. 

As the timed command for umbilical separation is given, the vehicle-side ground plate separates (using the Henkel-Mar contact/separation algorithm) and the ML gantry rotates the separating umbilical away from the already lifting vehicle (the gantry was brought into the CLA as a NDS capable of large rotations). Figure 7 captures the post-separation forward vent hose dynamics (extracted from the CLA). From this, 100  ICPSU hose clearances to the lifting vehicle can be computed. 

The power of the reduced-order models does not end with linear dynamics. It is possible to introduce large displacements and rotations into reduced-order models to enable seamless integration into large substructured integrated system dynamic analyses such as a CLA. For the specific case of the SLS, this capability allowed us to integrate umbilicals into the CLA to more accurately capture the impact of system flexibilities, dynamic response to forcing functions, pad separation “twang” effects, ML dynamics, and gantry/umbilical timings on clearances.  

For information, contact Dr. Dexter Johnson.  dexter.johnson@nasa.gov 

ICPSU model integratedinto the SLS CLA
ICPSU model integratedinto the SLS CLA
ICPSU forward vent hose evolution of deformations from undeformed (straight line) to prelaunch configuration (locking in preloads) during the CLA initial conditions setup (extracted from the CLA)
ICPSU forward vent hose evolution of deformations from undeformed (straight line) to prelaunch configuration (locking in preloads) during the CLA initial conditions setup (extracted from the CLA)
Forward vent hose post-separation dynamics (extracted from the CLA)
Forward vent hose post-separation dynamics (extracted from the CLA)

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Meagan Chappell