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Power Final Design and Review(.pdf format)

TEAM MEMBERS:

David Groch - Team Lead
Anthony
Tunde Akinpelu

OVERVIEW

The purpose of the Electrical Power Subsystem group is to design and develop the circuitry of the Spartnik satellite and all the wiring needed to integrate the subsystems. Spartnik is powered by 10 Gallium Arsenide solar panels integrated on the sides, top and bottom, of the satellite. Each panel, contain, 48 cells, divided into 4 strings of 12 cells producing a total power of 20 W in sunlight. the net power is stored in 12 Nickel Cadium rechargeable batteries. All the Power components are placed in the middle section of the satellite, called "The Power Tray."

Electrical Power Subsystem is in-charged of:

1. Designing the self-activation of the satellite
2. Antenna deployment mechanism
3. Power Controller
4. Umbilical chord
5. Wiring of the satellite
6. Batteries; 2 Battery Boxes
7. Solar array wiring

Currently, the group is working on the antenna deployment mechanism. The antennas of the satellite are initially rolled into a Spring Activated Deployment Mechanism SADM (i.e. housing). When the satellite ejects from the launch vehicle, the solar panels will charge the batteries and the power will then be used to activate the SADM, thus releasing the antenna.

The team has just finished designing the microswitch placement on the satellite. The function of the microswitch is to disconnect power to the satellite as long as the satellite is in the launch vehicle. Once the satellite leaves the Launch Vehicle Adapter, the microswitches close the circuit and current is allowed to flow through the spacecraft.

System Status: October 2000

The power team currently is in process of desigining the power control unit.
The power team is also in process of designing the wiring diagram.
Another objective is to finish the battery testing.

System Status: July 2000

The summer team is currently creating FFDs (Functional Flow Diagram) and FRDs (Functional Requirements Documents) for Power Subsystem.

Batteries have being acquired and vacuum tested (the batteries did not out gas or leak). A test procedure for the batteries is in process.

Part list for the Solar Panel wiring have been researched and parts are in process of acquisition. The wiring of the satellite will begin within 2 weeks.

System Status: March 2000

Currently, the team is acquiring NiCd batteries for the satellite. These batteries will be vacuum tested to verify the survivability in space. Concurrently, Robbie is designing the inter-cell connectors for the battery box. The battery box have already been designed, therefore the connectors should satisfy the design constraints.

System Status: Spring 1999

Currently, the group is working on the antenna deployment mechanism. The antennas of the satellite are initially rolled into a Spring Activated Deployment Mechanism SADM (i.e. housing). When the satellite ejects from the launch vehicle, the solar panels charge the battery and power is used to activate the SADM, thus releasing the antenna.

The team has just finished designing the microswitch placement on the satellite. The function of the microswitch is to disconnect power to the satellite as long as the satellite is in the launch vehicle. Once the satellite leaves the Launch Vehicle Adapter, the microswitches close the circuit and current is allowed to flow through the spacecraft.

SELF ACTIVATION OF THE SATELLITE

The satellite will use Umbilical Connector as the means to detect its separation from the launch vehicle. When the umbilical chord is disconnected to the satellite, the computer detects its absences and initiates a relay, which in-turn passes power to the muscle wires on the Antenna Deployment Mechanism (ADM). The muscle wires contracts thus pulling the latch of the Locking Mechanism. When the latch is pulled the levels open thus releasing the stowed antennas. The adjacent picture illustrates the latching system (actuator) of the ADM.