SARA 21 Satellite Antenna Rotary Actuator
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1 SARA 21 Satellite Antenna Rotary Actuator RUAG Space Schaffhauserstrasse 580 CH-8052 Zurich Switzerland Phone
2 GENERAL DESCRIPTION The SARA 21 Satellite Antenna Rotary Actuator (SARA) is designed to drive any type of space borne mechanism, while also transmitting a position signal to the onboard electronic. It is used to activate a mechanism operating in one of several rotational axes. Typical uses include antenna pointing, solar array deployment and customized applications. The large range of applications on satellites in LEO, MEO and GEO orbit for scientific or a telecommunications purpose allows using a standard product to minimise costs at system level. The SARA is fully space qualified and consists of: an actuator; two potentiometers for coarse - and two potentiometers for fine position feedback. Within the qualification program, fine pointings in orbit have been achieved and the SARA 21 has over 45 years of accumulated of flight heritage since The main function of the SARA 21 is to fine point antennas on orbit in forward or reverse direction. The SARA 21 has a very precise rotational resolution (step size) of and a maximum speed of 30 /min (one rotation per 12 minutes). The position of the SARA is measured using four (two coarse and two fine) redundant potentiometers delivering an accuracy of 0.50 (coarse) and 0.01 (fine). The position feedback of the potentiometer is an analogue 0 V to 5 V signal. The deadband of the coarse and the fine potentiometer is 1%. The potentiometers have a total resistance of 10 k 10%. Figure 2: SARA 21Coarse Potentiometer The SARA is powered using a two phase hybrid stepper motor with redundant windings giving stable (un-powered) positions of the output shaft over one revolution. The SARA 21 shall be powered directly with a dual phase sinusoidal 23.4 V to 28.6 V input with a maximum current of 400 ma. ESD The SARA 21 is an ESD (electrostatic discharge) sensitive device. Electrostatic charge as high as 4000 V readily accumulate on the human body and can discharge through the test equipment without detection. Although the SARA features proprietary ESD protection circuitry, permanent damage may occur on devices subjected to high energy electrostatic discharges. Therefore, proper ESD precautions are recommended to avoid performance degradation or loss of functionality. VIBRATION LEVEL For SARA 21 the qualification and acceptance tests the acceleration levels for X- and Y-axis, parallel to mounting plate, for random vibration levels is given as follow: Random vibration levels for acceleration on Z-axis correspond with the following diagram: Figure 1: SARA 21Fine potentiometers 2 Satellite Antenna Rotary Actuator
3 PACKAGING AND STORAGE The SARA 21 is delivered by RUAG SPACE mounted on a handling tool equipped with shock detectors. The SARA 21 must be kept in a clean room class 8 (100000) environment and shall be protected from direct UV light. If moved out of a clean environment, it has to be double bagged and sealed in antistatic protective foil (ESD) under dry nitrogen. OPTIONS The SARA 21 is available with or without the fine potentiometers for position feedback. DELIVERABLES - FM or PFM-Units - Transport and Handling Jigs (temporary only) - EIDP (CD-ROM): Certificate of Conformity CIDL & ABCL Logbook Interface Control Document User s Manual RfD s / RfW s NCR s Minutes of Meetings Acceptance Test Plan Acceptance Test Report DESIGN CHARACTERISTICS Mechanism Drive direction Speed range Maximum rotation speed Forward and reverse rotation (endless rotation) 0 to 1 rev / 12 min 0.5 /s 1 revolution steps 1 step Qualified life span 15 years in orbit + 5 year storage (2 years integrated on Satellite) Revolutions performance 500 orbital rotations or fine pointings ( 0.5 ) Motor Winding resistance 76 Ω 10% Number of steps per revolution of motor 360 Stabile positions (motor is unpowered) 360 Holding torque (unpowered motor ) Holding torque (powered motor) Nominal torque (powered motor) 7 Nm 30 Nm 25 Nm Position Measurement (coarse) Potentiometer resistance 10.0 k 10% Potentiometer accuracy 0.5 Potentiometer linearity 0.5% Position Measurement (fine) Potentiometer resistance 10.0 k 10% Potentiometer accuracy 0.01 Potentiometer linearity 0.5% 3 Satellite Antenna Rotary Actuator
4 Dimensions External diameter Total length Mass 120 mm 89 mm M 2.0 kg Fixation PF interface See Figure 3 to 6 SA interface See Figure 3 to 6 Power Consumption V BUS Total Power Maximum conditions 23.4 V V 17 W Temperature Specification T min T Ambient T max Ground Storage + 10 C +22 C + 40 C In orbit non operational C C Cold start-up limit - 65 C In orbit operational - 50 C +22 C + 85 C Environment conditions during operation Orbits LEO MEO GEO Radiation Total Dose No EEE parts SARA Connector D-SUB Connector DCMA37P Radiative Interface Motor housing Rear cap External finish (nature) Black paint Alodine 1200 Emissivity ( ) Absorption ( ) 0.08 Conductive interface Case 1 Case 2 Axial load (F z ) N 0 N Radial load (F xy ) 0 N N Bending moment (M xy ) 0 Nm 200 Nm 4 Satellite Antenna Rotary Actuator
5 Stiffnesses Axial stiffness (K z ) Radial stiffness (K xy ) Torsion angular stiffnes (K z ) Bending angular stiffness (K xy ) 21*10 6 N/m 35*10 6 N/m Nm/rad Nm/rad Environment conditions during launch High level sine vibration: Frequency (Hz) MOUNTING PLANE // MOUNTING PLANE 5 to 22 ± 10.0 mm ± 10.0 mm 22 to g 20 g sweep rate 2oct / min Random vibration: Frequency (Hz) MOUNTING PLANE // MOUNTING PLANE db/oct +6 db/oct g²/hz g²/hz g²/hz -20 db/oct g²/hz -96 db/oct g²/hz g²/hz g²/hz g²/hz g²/hz +95 db/oct g²/hz g²/hz db/oct g²/hz db/oct g²/hz g²/hz g²/hz db/oct g²/hz g²/hz g²/hz db/oct -6 db/oct l Global g rms g rms Shock levels for each axes (X, Y, Z): Frequency (Hz) Shock input levels g g g FLIGHT MODEL (FM) ACCEPTANCE PROGRAMME The flight model acceptance programme normally includes the following tests: - Inspection and control - Mass measurement - Functional characteristics measurement - Vibration tests (FM-level) - Thermal vacuum cycling with performance tests 5 Satellite Antenna Rotary Actuator
6 DIMENSIONS AND MECHANICAL INTERFACES FOR SARA 21 Figure 3: SARA 21 plan view Figure 4: SARA 21-D Antenna Interface side view Figure 4: SARA 21 Antenna Interface side view Figure 5: SARA 21-D rear view 6 Satellite Antenna Rotary Actuator
7 ELECTRICAL INTERFACES FOR SARA 21 Figure 6: SARA 21 electrical interface Information furnished by RUAG Space is believed to be accurate and reliable. However, no responsibility is assumed by RUAG Space for its use, nor for any infringements of patents or other rights of third parties that may result from its use. No license is granted by implication or otherwise under any patent or patent rights of RUAG Space. 7 Satellite Antenna Rotary Actuator
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