Eagle Functional Requirements Rev 1.0

The Eagle satellite is being built to support the AMSAT vision statement and will be designed to carry a set of payloads that will support the primary needs of the worldwide AMSAT community while providing both the builders and the users challenging, exciting, and valuable new features and technologies. The payloads will be carried by a modified version of the structure designed by Dick Jansson WD4FAB.

The requirements are summarized in the following outline.

1.0 Payloads

1.1 Transmitters
  1.1.1 V band using SDR techniques (bandwidth configurable not to exceed 50 khZ)
  1.1.2 Two S Band
    1.1.2.1 100KHz bandwidth
  1.1.3 C band wideband digital which includes telemetry
  1.1.4 All bands should be capable of being operated simultaneously

1.2 Receivers
  1.2.1 U band 100KHz bandwidth
  1.2.2 L band 100KHz bandwidth
  1.2.3 C band wideband digital
1.2.4 Command uplink on U and L receiver

1.3 GPS (NASA)

1.4 CEDEX (Surrey Satellite Technology)

1.5 Cameras
  1.5.1 Narrow FOV on +Z axis
  1.5.2 Wide FOV on -Z axis
  1.5.3 Cameras should survive all beta angles.

1.6 Telemetry beacons active on all transmitters
    1.6.1 The IHU will provide digital data and clock to the transmitter. The transmitter itself is responsible for
             data delivery.

1.7 Command uplinks on the U and L receivers
  1.7.1 Demodulation to baseband audio is in the receiver

2.0 Structure and Physical Properties

2.1 Mass
  2.1.1 100Kg or less

2.2 Size
  2.2.1 Compatible with the launcher.envelope constraints

2.3 Stabilization
  2.3.1 Spin stabilized ( + Z Nadir pointing at apogee) 1-15RPM

2.4 Orbit
  2.4.1 High apogee elliptical

2.5 Attitude Control
  2.5.1 Magnetorquers and nutation dampers
  2.5.2 Sensors
    2.5.2.1 The Sun sensors will measure the sun at all angles and attitudes
    2.5.2.2 The Earth sensor will measure the attitude of the spacecraft with respect to the Earth while its distance is
                within two radii of the Earth's surface.
  2.5.3 The satellite will stabilize to the desired attitude in 72 hours.

2.6 Propulsion
  2.6.1 The simplest system that will accomplish a desirable orbit and is acceptable to the launch agency. Initial
            estimate is 60 meters per second delta velocity.
  2.6.2 The propulsion system should be modular

2.7 Structure
  2.7.1 Structure as necessary to meet mission package
  2.7.2 Separation interface is located on the on -Z side, and is launcher dependent.
  2.7.3 Accommodate the possibility of side mounting

2.8 Magnetic Environment
  2.8.1 Magnetically clean as practically achievable

3.0 Thermal Control

3.1 IF batteries are flown, battery temperature should not exceed a -15 to +15C range.

3.2 Under all conditions, electronics module temperature should remain from -25 to +40C

4.0 Power Generation

4.1 Two fixed and four deployable solar panels with omni coverage.

4.2 Fault tolerant BCR and battery system that fails in an operational mode.

4.3 Buss voltage is 10 to 14 volts nominal.

5.0 Housekeeping

5.1 IHU-3

5.2 CAN-Do! Information buss

6.0 Antennas

6.1 High Gain +Z
  6.1.1 U (435MHz), L (1.2GHz), S (2.4GHz) and C (5.6GHz)

6.2 Omni Antennas, -Z (functional in all attitudes)
  6.2.1 V (145MHz), U, L and S

6.3 Omni Antennas +Z
  6.3.1 U, L and S