Mass production using proven processes minimizes cost and schedule
Spacecraft Bus
Design
High heritage design (BCP-Small spacecraft w/ FSW reuse >90%)
Externally mounted components for easy AI&T
High pointing accuracy <15 arcsec (Pitch/Yaw, 3σ)
S-band Omni to MGS and NSN-SR
On-board transient event detection and alert to ground
Rapid response to Targets of Opportunity
XRT Focal Plane Assembly
Design
Four Charge-Coupled Device (CCD) chips
Large Focal Plane Coverage: 100 mm × 100 mm (16.8 MegaPixels)
Back-illuminated CCD chips provide low energy response
Straightforward thermal design: TECs and passive cooling maintain focal plane at -70°C
Warm contamination control filter
UVT
Design
33 cm C.A. Ritchey-Chretien telescope for complementary UV imaging
50 mm sealed MCP detector
High sensitivity with ≤ 5" HPD PSF averaged across FOV
Mission Requirements
Orbit: 5° inclination, 600 km, circular Transient Event Alert: Within 5 mins of on-board detection, through NSN-SR (90% of the time) Response to ToO: ≤ 120 mins of receipt (80% of the time) Slew and Repoint: 120° in less than 9 mins; 0.5° in 26 sec Astrometric Knowledge: 2.8 arcsec (3σ) Observing Efficiency: > 73% Launch Readiness Date: July 2028
Instrument Requirements
X-ray Telescope Assembly
Energy Band: 0.2-6 keV Field of View: 1.0 deg2 Point spread function: 2.5 arcsec half-power diameter on-axis, ≤6 arcsec FOV-averaged Spectral Resolution (FWHM) (eV): ≤100 (1 keV), ≤150 (3 keV) Sensitivity in 10 ks (5σ; erg cm-2s-1): <8 x 10-14 (0.5-2 keV)
UV Telescope Assembly
Energy Band: 165-300 nm Field of View: 0.8 deg2 Point spread function: ≤ 5.0 arcsec FOV-averaged Filters: ≥3 (180 nm, 225 nm, and 275 nm)