Official name POLAR BEAR
Alternative name Polar BEAR
Cospar ID 1986-088A
Norad ID 17070
Launch date 1986-11-14
Launch site AFWTR
Launch vehicle Scout-G1
Country/Organization USA
Type application Experimental
Operator US Air Force (USAF) STP (Space Test Program)
RCS size LARGE
Decay date ON ORBIT
Period (min) 104.72
Inclination (deg) 89.61
Perigee (km) 951
Apogee (km) 1012
Eccentricity 0.0310748853795211
Mean motion (revs. per day) 13.7509549274255
Semi-Major axis (km) 7359.635
Raan (deg) 207.316
Arg of perigee (deg) 75.8935
Shape Oct Cyl + 4 Pan + 1 Ant
Mass (kg) 123.89
Diameter (m) 0.46
Height (m) 0.25
Contractors JHU/APL
Equipment Auroral Imaging Remote Sensor, Beacon Experiment
Propulsion ?
Configuration Transit-Bus
Power 4 deployable solar arrays, batteries

Polar Bear (Polar Beacon and Research), also known as STP P87-1, was a military mission designed to study communications interference caused by solar flares and increased auroral activity.

It was to continuie the mission of its predecessor, HILAT. The spacecraft was built on the Transit-O 17 navigational satellite that was retrieved from the Smithsonian's National Air & Space Museum, where it had been on display for 8 years.

Polar bear was gravity gradient stabilized by deployable boom with tip mass and was powered by 4 small deployable solar arrays.

The payload consisted of:

  • Auroral Imaging Remote Sensor for aurora borealis imaging
  • Beacon Experiment to monitor ionospheric propagation over the poles

In November 1986, the satellite was launched on a Scout-G1 into orbit to measure the properties of the near-Earth plasma. However, as it entered its first period of fully sunlit orbit in February 1987, its attitude degraded significantly. The roll, pitch, and yaw angles began oscillating until the satellite finally inverted in May 1987. Consequently, several attempts to re-invert the satellite were undertaken. The third attempt proved to be successful when the momentum wheel was allowed to despin for an orbit before spinning it back to its maximum spin rate. The torque from the wheel in combination with the pitch rate induced from the despinning wheel inverted the satellite and captured it in the desired orientation.

Satellite COSPAR Date LS Launch Vehicle Remarks
POLAR BEAR 1986-088A 1986-11-14 AFWTR Scout-G1 mod. Transit-O 17