Our adaptable generic LEO Bus is a capable solution for your needs.

Leopard

  • 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.

  • 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

  • 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 spacecraftn text goes here

    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