ASI-150EP/CP Small Satellite Bus

ASI-150EP/CP Small Satellite Bus

FS5_PictureASI Satellite Bus Offerings:

The ASI-150EP (Electric Propulsion) and ASI-150CP (Chemical Propulsion) small satellites are highly-configurable to accommodate a wide variety of payloads, performance objectives, and mission scenarios. Several technologies employed in ASI small satellites have flight heritage as part of ASI’s Phase III small business innovative research (SBIR) program with the Air Force Research Laboratory (AFRL) including the FalconSAT series of ESPA-compliant small satellites.

ASI-150EP/CP Data Sheet:

The ASI-150EP/CP specifications and performance data shown below provides a baseline design which can be tailored to meet specific needs.

Mass
(Including Growth Margin)		 Bus (Dry) 99kg
Fuel (200 m/s delta-V) 13kg
Payload (ESPA Compliant) < 68kg
Example Inertias @ 160kg: [10.5 , 15.6 , 18.1]kg*m2
Dimensions 711 x 610 x 810 mm (Bus & Launch Adaptor)
711 x 610 x 155 mm (External Payload Volume)
618 x 490 x 328 mm (Internal Payload Volume)
Pointing & Performance
(3-Axis Stable)		 Pointing Accuracy: (Total < 0.15°)
Control < 0.1°
Attitude Determination < 0.05°
Agility Capability: (180° slew in < 90s)
Max Rates: 3-5°/s
Max Acceleration: 0.1°/s2
Orbit Determination Accuracy (w/GPS):
10m Position (RSS)
10 cm/s Velocity (RSS)
Power
(Deployed and articulating solar panel configurations available to support higher power demands)		 Two to four body-mounted panels
55 W Nominal Bus Load
80-120 W max Orbit Average Power (OAP) Collect
(Dependent upon orbit and orientation constraints)
20-50 W Payload OAP
12.5-37.5 Ah Storage Capacity
28V Nominal Bus Voltage
Communications S-Band Tx up to 1 Mbps Downlink
S-Band Rx up to 100 Kbps Uplink
Propulsion Chemical or Electric
200 to 800 m/s delta-V
Design Life > 3 years
Launch Accommodations 15” Motorized Lightband (other options available)
ESPA Compliant
Heritage on Minotaur IV
Satellite Delivery Supports schedules as short as 14 months

 

ASI150EP/CP Standard Configuration Overview:

  • 4 Reaction Wheels (25mNm, 1Nms)
  • 3 Torque Rods (15 Am2 Dual-Wound)
  • 2 Star Trackers
  • 1 Rate Sensor Assembly (3-axis)
  • 2 Sun Sensors
  • 1 Magnetometer
  • 1 GPS Receiver, 2 GPS Antenna
  • 15 Ah Lithium-Ion Battery
  • 2 Body-Mounted Solar Panels (Triple Junction Cells)
  • AiTech S950/SP0 C&DH Avionics
  • RS-422 Data Protocol, Analog, Digital, Discretes
  • S-Band Tx/Rx

FS5_Overview_CAD

ASI-150EP/CP small satellites use an integrated suite of tools developed by ASI designed to accelerate the design, integration, test, and operation of spacecraft.   Our Modular Flight Software with the Onboard Dynamic Simulation System (ODySSy) is highly-versatile and capable, supporting most hardware and mission configurations with limited software development.

ASI’s ODySSy onboard simulator greatly reduces the need for external test equipment, resulting in significant savings of time and money to the customer. Our team of engineers and technicians have the expertise to configure and build a space vehicle appropriate to meet the objectives of your mission.

  • Low-Risk Full Featured Heritage Flight Software
    • Modular Autonomous Flight Software can be targeted and adapted to a wide variety of spacecraft designs, payloads, and requirements
    • Mature high-performance Object-Oriented C++ code base
    • Includes the On-Board Dynamic Simulation System (ODySSy) to provide full life-cycle Built-In Simulation/Test for rapid spacecraft I&T
  • Commonality of the Ground and Space Segments Reduces Risk and Increases Responsiveness While Reducing Operational Cost
    • STK SOLIS spacecraft simulation uses the same ODySSy-based flight software
    • Provides a unified tool chain from initial mission design through on-board systems and operations

 
ASI-150EP/CP Bus Dimension Details:

FS_Dimensions 

 

Small Satellite Assembly, Test, and Launch Operations:

 FS5_AIT_Pictures