Our adaptable generic LEO Bus is a capable solution for your needs.
Leopard
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Specifications
Mass
Payload Capacity: Up to 100 kg (higher limits possible depending on launch vehicle)
Spacecraft Bus Mass: 95 kg
Power
Payload Output: Up to 30 W (with 20% margin using 2 solar panels); up to 240 W (with 20% margin using 4 solar panels)
Dimensions
Customizable dimensions depending on mission requirements
Interface & Data Handling
Launch Vehicle Interface
Compatible with F9 Full or XL Plate, and Electron launch vehicles
Data Interface
Native: Gigabit Ethernet (ground only), RS-422, and RS-485
Expansion Options: CAN, Gigabit Ethernet (in-space), SpaceWire, CameraLink, LVDS
Storage
Capacity: Ranges from 8 GB to 256 GB
TT&C (Telemetry, Tracking & Command)
S-band with omnidirectional Rx and Tx capability at 1 Mbps
Performance
Propulsion
Chemical: ~70 kNs or larger
Electric Propulsion (EP): ~50 kNs Hall Effect Thruster
Attitude Control (ACS) Modes
Modes: Inertial, solar inertial, Nadir/Earth-referenced
Environmental Testing & Reliability
Bus Class
C/D as per NASA NPR 8705.4A standards
Additional Features
High-bandwidth downlink, optical bench, expanded storage options, and more
LYNX
Our LEO ESPA standard class 6-DOF spacecraft for SSA LEO characterization missions.
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Specifications
Mass
Payload Capacity: Up to 48.7 kg (higher limits possible depending on launch vehicle)
Spacecraft Bus Mass: 139.9 kg
Power
Payload Output: Up to 50 W (with 20% margin using 2 solar panels)
Interface & Data Handling
Launch Vehicle Interface
Compatible with F9 Full or XL Plate, and Electron launch vehicles
Data Interface
Native: Gigabit Ethernet (ground only), RS-422, and RS-485
Expansion Options: CAN, Gigabit Ethernet (in-space), SpaceWire, CameraLink, LVDS
Storage
Capacity: Ranges from 8 GB to 256 GB
TT&C (Telemetry, Tracking & Command)
S-band with omnidirectional Rx and Tx capability at 1 Mbps
Performance
Propulsion
Chemical Propulsion: ~70 kNs
Attitude Control (ACS) Modes
Modes: RPO (Rendezvous and Proximity Operations), Inertial, solar inertial, Nadir/Earth-referenced
Guidance, Navigation, and Control (GN&C)
RPO and 6-DOF control with ΔV capacity of ~325 m/s
Environmental Testing & Reliability
Bus Class
C/D as per NASA NPR 8705.4A standards
Additional Features
High-bandwidth downlink, optical bench, expanded storage options, and more
A price-conscious visible band sensor with superior performance.
CARACAL
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Specifications
Mass
Telescope Mass: 10 kg
Power
Power Consumption: 8 W at 12 VDC
Dimensions
Telescope Assembly: 68 cm x 41 cm (diameter)
Camera/Focuser Electronics: Approximately 13.4 cm (diameter) x 22 cm
Special Requirements: Requires a cut-out in mounting plate
Interface & Data Handling
Launch Vehicle Interface
Compatible with standard spacecraft mounting and power supply (28V and 12V)
Data Interface
Native: 4 GB LPDDR4 RAM (ECC), 2 x 256 MB QSPI Flash (NOR), and 2 x 128 GB eMMC for over 1000 images
Storage
Image Capacity: Over 1000 images store
TT&C (Telemetry, Tracking & Command)
N/A for standalone telescope; integrates with host spacecraft
Performance
Optical Parameters
Aperture Diameter: 35 cm
Focal Ratio: F/10 with a 3.5 m focal length
Bandpass Filter: 450 to 900 nm
Resolution: ~1.3 cm at 10 km
Resolving Power: 0.27 arcseconds
Field of View: 0.71 degrees
Sensor
Resolution: 29 MP (6600 x 4400 PAN)
Dynamic Range: 64 dB with 20,000 e- full well
Features: Binning, Time-Delay Integration (TDI), Automatic Gain Control (AGC), Automatic Exposure Control (AEC), and Area of Interest (AOI)
Environmental Testing & Reliability
Environmental Testing
Vibration Testing: Meets GEVS Protoflight standards
Thermal Vacuum (TVAC) Testing: Range from -20°C to +60°C
Target Operating Temperature: 0°C to +40°C
Additional Features
Edge computing for onboard image processing, storage, and interfacing options
JAGUAR
