Orbital Hingelock TEE Deployer Model 9843 - Manual

Hingelock
TEE Deployer
Model 9843 Hingelock
TEE Deployer
Model 9843
Typical Technical Specifications:
Introduction
Hingelock deployer Model 9843 was originally
developed for the International Solar Terrestrial Physics
(ISTP) program WIND satellite. Two such mechanisms,
located at 180° apart, are used to form a dipole
antenna along the Z-axis as part of a 3-axis WAVES
experiment. This motorized mechanism is capable of
extending and retracting a 1.12 inch (2.86 cm)
diameter Tubular Extendible Element (TEE). The deployer
features electrical stops at both full-extension and -retraction. A potentiometer, driven by the moving
element, provides a continuous indication of deployed
length. To ensure minimal distortion due to thermal
gradients in a space environment, thermal control
coatings are applied on both the inside and outside TEE
surfaces. This deployment mechanism is designed to meet
the requirements of document MIL-A-083577A (USAF)
General Specification for Moving Mechanical
Assemblies for Space and Launch Vehicles. This unit can
be deployed or retracted in orbit.
Antenna Element
Deployed Length: Up to 32.8 ft
(10 meters)
Diameter: 1.12 in (2.86 cm)
Configuration: Hingelock
Material: Beryllium Copper
0.0045 in
(0.1143 mm) thick
Thermal Control Silver &
Coating: Perforations with
Kapton or Teflon
(if required)
Weight
(with coatings):
31.43 gr.ft
(103.12 gr/m)
Deployer
Height: 8.23 in (20.9 cm)
Length: 20.06 in
(50.95 cm)
Width: 7.1 in (18.03 cm)
Total Unit Weight: 14.33 lbs (6.5 kg)
Drive Motor: Brushless D.C.
Power: 14 Watts maximum
Voltage: 24-32 Vdc
Deployment Rate: Approximately 1.2
in/sec (3 cm/sec)
Operating
Temperature Range: -10°C to +50°C
Qualification
Temperature Range: -20°C to +65°C
Survival
Temperature Range: -25°C to+65°C