Near Earth Asteroid Rendezvous (N.E.A.R) Shoemaker Spacecraft, USA
Key Data:
Launch Year
1996
Project Type
Spacecraft
Base Country
USA
Estimated investment
Unknown
Project Completion
2001
Key Players:
Sponsor & Financing
NASAs Discovery programme
Construction
Johns Hopkins Universitys Applied Physics Laboratory
Characteristics:
Mass (kg)
805 (including propellant)
Basic Design
Three-axis stabilized
Fixed solar panels
Fixed 1.50 metre high-gain antenna
Fixed instruments
Passive thermal design
Redundant critical subsystems
Fixed solar panels
Fixed 1.50 metre high-gain antenna
Fixed instruments
Passive thermal design
Redundant critical subsystems
Power
Solar Powered 1,800 Watts at 1 AU
Telemetry
X-Band link to NASA Deep Space Network
Size
1.70 square metres at the base
Data Rate
Selectable Between
9 bits/second and 26.8 kilobits/second
9 bits/second and 26.8 kilobits/second
Memory Capacity
1.7 Gigabits solid rate
Propulsion
1 x 100-lb thrusters
4 x 5-lb thrusters
7 x 1-lb thrusters
Total Delta Velocity of 1,450 metres/second
4 x 5-lb thrusters
7 x 1-lb thrusters
Total Delta Velocity of 1,450 metres/second
Mission Control Centre
Applied Physics Laboratory
Navigation Support
Jet Propulsion Laboratory
Subsystems
Flight software
Mechanical
Structure
Thermal
Command & Data Handling
Telecommunications
Propulsion
Power
Guidance & Control
Electromagnetic Compatibility
Test Equipment
Mechanical
Structure
Thermal
Command & Data Handling
Telecommunications
Propulsion
Power
Guidance & Control
Electromagnetic Compatibility
Test Equipment
