linear actuator catalog - aviorcontrols.com€¦ ·...

LINEAR ACTUATOR PRODUCT CATALOGand Design Guidelines

Innovative Solutions, Quality Hardware, Unpara!eled Service

! 1

Avior Control Technologies, Inc -‐ www.AviorControls.com / [email protected] / (T) +1-‐303-‐882-‐0521 CAGE: 6GST1 © 2012, Avior Control Technologies, Inc All Rights Reserved

http://www.AviorControls.com


mailto:[email protected]


! 2


Introduc)on Avior Control Technologies, Inc is a full service custom motor and moNon control house, specifically servicing space, high vacuum, ex-‐treme temperature and high reliability industries.

This catalog details the characterisNc performance and mechanical consideraNons for linear translaNon actuators. This design guide is formaSed to guide the proper sizing and integraNon of these prod-‐ucts into the next higher assembly.

With over three decades in the Aerospace MoNon Control business, Avior’s engineers have introduced a line of motors, sensors and gear-‐ing that have evolved beyond other products available in this market. Materials, processes and design concepts are standardized for ex-‐treme vacuum space environment. Available contract services in-‐clude detailed dimensional worst case analysis for each product, So-‐lidWorks 3D model, detailed project Schedule, statused weekly and communicated to the customer two Nmes a month. Structural and thermal modeling reports are also available deliverables.

In addiNon to the state-‐of-‐the-‐art products and services, Avior engi-‐neers are recognized a leaders in the industry in innovaNve moNon control concepts and new technologies. Currently under develop-‐ment are drive control techniques that significantly increase per-‐formance, power output and efficiency of convenNonal stepper drive systems. Contact Avior’s engineering department for more informa-‐

Non about our innovaNve developments or for a detailed technical proposal for your linear actuaNon requirements.

Using this Design Guide: SelecNng a proper linear actuator to ac-‐commodate all the system requirements is an iteraNve process. De-‐termining the force, velocity and the rotary component performance requirements of a high reliability actuator is not a trivial exercise. The design engineer must consider translaNon efficiencies as well as mass moments when designing and specifying an actuator. This de-‐sign guide walks the responsible engineer through the process of sys-‐tem level requirements, and working the design backwards to the high speed motor. Motor selecNon and performance consideraNons are also important to the overall design. Working iteraNvely with Av-‐ior’s Stepper Motor Catalog and Housed Brushless DC Motor Catalog, the responsible engineer has all the tools necessary to iniNally size a linear actuator for their system.

With opNonal “closed frame” linear components with custom mount-‐ing and interface configuraNons, Avior may provide linear actuators at a higher level than described herein.





Using This Design Guide: Step 1: Determine Force and Power Output Requirements From system force and velocity requirements, calculate requirements of Linear Force, Velocity, Mechanical Power Output Requirements using Table 1 equaNons:

TABLE 1 -‐ LINEAR CONVERSION EQUATIONSTABLE 1 -‐ LINEAR CONVERSION EQUATIONSTABLE 1 -‐ LINEAR CONVERSION EQUATIONSTABLE 1 -‐ LINEAR CONVERSION EQUATIONSTABLE 1 -‐ LINEAR CONVERSION EQUATIONS

PARAMETER SYMBOL UNITS EQUATION COMMENT

Mechanical Power Output of Linear Actuator Po WattsPo= (FL * VL) * 0.113 Imperial -‐ FL in Lbf, VL in inches per second

Mechanical Power Output of Linear Actuator Po WattsPo = (FL * VL) System International -‐ FL in N, VL in meters per second

Load Inertia Reflected to the Rotary Output JLRO Lb-‐In-‐sec2 or kgm2 JLRO = (WL /g) / (2πP)2Where:

WL= weight of load in Lbm or Ng = gravity constant (386 in/sec2 or 9.8 m/s2)

Velocity of linear output VL in/sec or mm/sec VL = ωRO /(P*60)

Velocity at Rotary Output ωRO RPM ωRO = 60 * VL * P

Force at the Load FL Lbf or N FL = TRO * (2πP ηbs)

Torque at the Rotary Output TRO Lbf-‐In or Nm TRO = FL / (2πP ηbs)

ROTARY MECHANICAL OUTPUT EQUATIONSROTARY MECHANICAL OUTPUT EQUATIONSROTARY MECHANICAL OUTPUT EQUATIONSROTARY MECHANICAL OUTPUT EQUATIONSROTARY MECHANICAL OUTPUT EQUATIONS

Mechanical Power Output Po WattsPo = (TL * ωL ) / 807.3 Imperial -‐ TL in Lbf-‐In, ωL in rad/sec (note 1 rad/sec ≈ 9.554 RPM)

Mechanical Power Output Po WattsPo = TL * ωL System International -‐ TL in Nm, ωL rad per second

Torque at the Rotary Output TO Lbf-‐In or Nm TO = (JL αL +JM N2 αL+BL ωL+KL θL+ MgL) Inertia acceleration considerations included here

Angular Velocity for Frequency Response ωo rad/sec ωMAX = θMAX (2πfMAX)where fMAX = (2πf)-‐1(αMAX/θMAX)0.5Angular Acceleration for Frequency Re-‐sponse αo

rad/sec2 αo = θMAX (2πfMAX)2 = ωLMAX(2πfMAX)where fMAX = (2πf)-‐1(αMAX/θMAX)0.5

Natural Circular Resonant Frequency fn Hz fn = (2π)-‐1 (KG (JL+JMN2)/(JL JMN2))0.5

Where:JL = Load Inertia (In Lb-‐in-‐sec2 or kgm2)BL = Viscous Losses at the Load (Lbf-‐In or Nm)ωM = Motor Velocity (in rad/sec)JM = Motor Inertia (In Lb-‐in-‐sec2 or kgm2)

KL = Spring Constant of the Load (In Lbf-‐in/rad or Nm/rad)FC = Coulomb Friction Torque (Lbf-‐In or Nm)ωL = Load Angular Velocity (in rad/sec) KG = Gearing Spring Constant (In Lbf-‐in/rad or Nm/rad)θL = Angular Rotation at the Load (In radians)

MgL = Mass Imbalance at Load (Lbf-‐In or Nm)P = Pitch of the Ballscrew or Ball Nut (Revolutions per Inch) Note: Lead = 1/ Pitchηbs = Ball Screw Efficiency (Typically 95%)ηbn = Ball Nut Efficiency (Typically 35%)

! 3






Using This Design Guide Step 2: Determine Gearbox Module Requirement:

Once the Torque at the Rotary Output (TRO) has been determined, the required Planetary Gearbox must be determined, considering peak and conNnuous torque capaciNes of the gearbox. Table 2 is a tabulated reference of Avior’s standard modular Epicyclic Planetary Gearboxes.

TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA TABLE 2 -‐ PLANETARY GEARBOX MODULE PERFORMANCE DATA

GEARBOX DESIGNA-‐

TION

DIAMETERDIAMETER MASS (PER MODULE)MASS (PER MODULE) MAX INTERMITTENT TORQUE

MAX INTERMITTENT TORQUE TORSIONAL STIFFNESSTORSIONAL STIFFNESS BACKLASHGEARBOX

DESIGNA-‐TION INCHES MM LBM KG LBF-‐IN NM LBF-‐IN/RAD NM/RAD ARC-‐MIN

8 0.75 19.05 0.09 0.04 20 2.3 6.00E+03 680 ±7

10 1.00 2.03 0.19 0.09 75 8.5 1.50E+04 1,700 ±3

13 1.25 31.75 0.34 0.16 180 20 2.00E+04 2,250 ±3

15 1.50 38.10 0.56 0.26 400 45 4.00E+04 4,500 ±3

18 1.75 44.45 1.00 0.41 750 85 5.50E+04 6,250 ±2

20 2.00 50.80 1.25 0.57 1,500 170 7.00E+04 8,000 ±2

25 2.50 63.5 1.56 0.71 3,000 340 1.50E+05 17,000 ±2

30 3.00 76.20 1.88 0.85 6,000 675 3.00E+05 34,000 ±2

40 4.00 101.6 5.00 2.27 12,000 1,350 3.00E+06 3.40E+04 ±2

Notes: 1. ConNnuous torque raNngs dependent on gear raNo, lubricaNon system, output velociNes, operaNng condiNons and life requirements. For iniNal esNmates of conNnu-‐

ous torque raNngs, 50% of the intermiSent raNng is reasonable iniNal assumpNon. Contact Avior’s engineering department for a detailed conNnuous torque raNng assessment.

2. Torsional sNffness dependent on output sha{ configuraNon and gear raNo. 3. OperaNng efficiencies approximately 95% per stage of gearing. OperaNonal velocity and torque levels have an affect on efficiency. 4. Tighter backlash opNon is available. 5. In-‐line or right angle drives are available in each gearbox frame size. Contact Avior’s Engineering Department for Right-‐Angle Drive ICD informaNon. 6. Dry-‐film lubricaNon available for temperature extreme applicaNons. 7. Gearbox data is approximate. Data subject to change without noNce.

! 4






Linear Transla)on ModulesFor reliable and Aerospace standards compliant linear translaNon, it is important to integrate a Linear TranslaNon Module (LTM) that isolates the linear thrust forces

from the output of the epicyclic planetary gearbox. Avior has developed a line of

complementary LTMs that provide reliable and accurate rotary to linear translaNon. These ruggedized modules may be configured with numerous output ball-‐screw

configuraNons, depending on applicaNon requirements.

Precision)Threaded)Interface)to)Planetary)Module)

Input)to)LTM)Eliminates)Thrust)Loading)on)Planetary)Module))

Internally)Preloaded)Thrust)Bearings)Support)all)Linear)Thrust)Loading))

Internally)Preloaded)Duplex)Bearings)Achieves)Concentric)Alignment))and)High)Radial)Load)Capacity)Numerous)Linear)Conversion)

Screws)Available.))OpHonal)Internal)Ball)Return)Available)

Standard)Low)Outgassing)Wet)LubricaHon)or)Dry)Film)LubricaHon)Available)

Linear)Ram)ConfiguraHons)with)AnHLRotaHon)OpHons))Available)(Not)Shown)))

High)Grade)Stainless)Steel)ConstrucHon))

No)Thrust)Bearing)Retaining)Rings)or)Snap)Rings))

Linear TranslaNon Module Design Features

Custom LTMs and complete linear actuator assemblies may be designed per your

applicaNon requirements. The materials, processes, design concepts and assembly

techniques of the reliable modular configuraNon remain standard while providing custom end-‐item performance.

Table 3 tabulates some standard modular LTMs, with some standard ball screw

configuraNons. Again we iterate that the number of configuraNons and opNons are

too numerous to include in a catalog format. It is recommended that the design engineer contact Avior directly to review requirements and opNon limitaNons be-‐

fore designing a system. This catalog is useful, however, in showing the standard LTMs available with some opNonal Ball-‐Screw configuraNons.

Unlike some compeNtor’s designs, Avior’s LTMs do not uNlize any retaining rings or snap rings in the design. This is important because it is not desired to have any

thrust loading imposed on snap rings. AddiNonally, the Preloaded Duplex Bearings that achieve concentric alignment of the linear ball-‐screw to the rotary Planetary

Gearbox also provides high radial load capacity of the ball-‐screw. This is important

to endure resonant loads in a vibraNon environment.

With matched coefficient of expansion materials and dry film lubricaNon opNon, these linear translaNons can operate from -‐269º C to +300ºC. Higher temperatures

are available with speciality materials. Standard low-‐outgassing wet lubricants can

operate down to -‐70º C, in a high vacuum environment.

! 5






Notes: 1. Peak force ratings determined by ball-‐screw configuration. 2. Other ball-‐screw options available on request. 3. Continuous force ratings dependent on thermal considerations, lubrication

system, output velocities, operating conditions and life requirements. For initial estimates of continuous torque ratings, 50% of the intermittent rat-‐ing is reasonable initial assumption. Contact Avior’s engineering depart-‐ment for a detailed continuous torque rating assessment.

4. Radial load capacity and stiffness dependent on output shaft configuration and length.

5. Operating efficiencies approximately 95%. 6. Tighter backlash option is available. 7. In-‐line or right angle drives are available in each LTM frame size. Contact

Avior’s Engineering Department for Right-‐Angle Drive ICD information. 8. Dry-‐film lubrication available for temperature extreme applications. 9. LTM data is approximate. Data subject to change without notice. 10.Output shaft configuration is customized for each application.

Using This Design Guide: Step 3: Determine Linear Translation Module Requirement:

Table 3 tabulates Avior’s standard Linear Translation Module (LTM) stages, along with some example Ball Screw options. Note: If the LTM modular size is smaller in diameter than the required motor gearbox, the square flange mounting dimensions of the rotary actuator assembly will apply to the LTM for Dimensions A, B, C and F dimensions. Other dimensions per Table 3, Below. Contact Avior’s engineering department is there are any questions regarding the mounting dimensions.

TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)TABLE 3 -‐ L INEAR TRANSLAT ION MODULE MECHAN ICAL D IMENS IONS (WITH EXAMPLE BAL L SCREWS)

T Y P EP E A K F O R C E

BA L L S C R EW L E A D ( 1 / P )

A B C D E F G H J K T T Y P EL B F I N /R E V

A B C D E F G H J K T

LTM08-‐1 300 0.125 0.960 0.728 0.129 0.7500 0.156 0.188 0.675 1.00 0.750 0.750 0.664-‐32 UNS-‐2A

LTM10-‐1 300 0.125 1.100 0.862 0.129 1.0000 0.188 0.250 0.675 1.00 1.000 0.750 0.664-‐32 UNS-‐2A

LTM10-‐2 500 0.125 1.100 0.862 0.129 1.0000 0.188 0.250 1.30 1.88 1.000 0.750 0.664-‐32 UNS-‐2A

LTM15-‐1 1000 0.200 1.500 1.250 0.149 1.3750 0.250 0.313 1.40 1.75 1.500 1.130 0.9375-‐16 UNS-‐2A

LTM20-‐1 2500 0.250 2.000 1.670 0.177 1.8750 0.313 0.375 1.50 2.35 1.750 1.625 1.536-‐18 UNS-‐2A

.010 M A B

B Typical

A

4x C+-.005.001

UNLESS OTHERWISE SPECIFIED:

PROHIBITED.

D

C

B

AA

B

C

D

12345678

8 7 6 5 4 3 2

INTERPRET GEOMETRIC

FOUR PLACE DECIMAL

SHEET 1 OF 1

.003.01

Description Appr.

Lafayette, CO

DO NOT SCALE DRAWING

THREE PLACE DECIMAL

Linear Translation Module Dimensions

1

TOLERANCING PER: ASME Y14.5

MATERIAL

FINISH

DRAWN

CHECKED

ENG APPR.

MFG APPR.

Q.A.

COMMENTS:

DATENAME

TITLE:

SIZE

BDWG. NO.

.0005

Issue

TWO PLACE DECIMAL 1 Deg.

REV

DIMENSIONS ARE IN INCHESTOLERANCES:ANGULAR: MACH

PROPRIETARY AND CONFIDENTIALTHE INFORMATION CONTAINED IN THIS DRAWING IS THE SOLE PROPERTY OFAVIOR CONTROL TECHNOLOGIES, INC. ANY REPRODUCTION IN PART OR AS A WHOLEWITHOUT THE WRITTEN PERMISSION OF AVIOR CONTROL TECHNOLOGIES, INC IS

CAGE 6GST1

A

"T" Thread

.0005

AM.0005

B

As Required

E

J

.0005

K Max.

G

Added Length

F

D+-.0000

H

! 6






! 7


Using This Design Guide: Step 5: Select a Motor Gearbox

From the calculaNons in Step 1, a motor-‐gearbox combinaNon must be se-‐lected. The gearbox sizing exercise in Step 2 is for reference purposes. The design engineer must determine whether a Brushless DC Actuator or a Step-‐per Motor Actuator is preferred for each applicaNon. ConsideraNons of me-‐chanical power output and reflected load inerNa are important considera-‐Nons.

Generally speaking, if the mechanical Power Output (Po) is low (less than 5 waSs), then a Stepper Motor may saNsfy the torque at speed requirements for the rotary porNon of the linear actuator. If the Po is higher than 5 waSs, than a Brushless DC Actuator would be preferred.

We refer the design engineer to each of Stepper Motor Actuator and Housed Brushless DC Actuator Product Design Catalogs for the selecNon of the best modular design. This will be an iteraNve process of translaNng the load iner-‐Na to the motor and verifying motor performance.

Example: For a mechanism release applicaNon, a linear actuator must pull a force of 80 Lbf for 0.75” under 30 seconds. The mass of the load is 20 Lbm. The remain-‐ing force requirement os due to force margins, fricNon and preload. Redun-‐dant motor windings is required.

Step 1: Calculate System Requirements. (iniNally assume 8 Pitch Ball Screw) Po= (FL * VL) * 0.113 Po= 80 * (0.75/30) * .113 = 0.23 WaSs

JLRO = (WL /g) *(2πP)-‐2 JLRO = (20/386) * (2*3.1415*8)-‐2 = 2.05E-‐05 Lb-‐In-‐sec2

ωRO = 60 * VL * P ωRO = 60* (0.75/30) * 8 = 12 RPM

TRO = FL / (2πP ηbs)

TRO = 80 /(2*3.1415*8*.95) = 1.68 Lbf-‐In

Step 2 & 3: Avior’s size 10 gearbox would easily handle the torque requirements of the applica-‐tion. Likewise, the LTM10-‐1 Linear Translation Module would accommodate the force re-‐quirements with significant margin.

Since the mechanical power output is low (< 5 watts), a stepper motor is likely to satisfy the requirements of this actuator. We are looking for a geared stepper actuator that meets the requirements defined above. Looking through Avior’s Stepper Motor Actuator Catalog, we find the C62R-‐10N36-‐10 will satisfy the requirements, including driving the required load iner-‐tia. I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&I N S T R U M E N T & A C T U A T O R & < & T Y P E & C 6 2 < 1 0 N 3 6 & ( D A T A & A T & + 2 5 º C )&

P A R A M E T E R U N I T S

1 0 & W A T T S & S T A L L&P O W E R






P A R A M E T E R U N I T S

S I M P L E X R E D U N D A N T S I M P L E X R E D U N D A N T S I M P L E X R E D U N D A N T

Avior&Product&Code 3 C62S310N36310 C62R310N36310 C62S310N36320 C62R310N36320 C62S310N36330 C62R310N36330

ICD&Dimensions See&Table&2 C1032C1032 C1032C1032 C1032C1032

Number&of&Phases 3 22 22 22

Number&of&Poles 3 66 66 66

Gear&RaKo 3 3636 3636 3636

Step&Size& Degrees 0.83330.8333 0.83330.8333 0.83330.8333

DCR&Per&Phase Ohms 115.2115.2 57.657.6 38.438.4

Torque&Constant Lb3In/Amp 36.520 27.824 25.823 19.675 21.085 16.064

Response&Rate&with&Rated&Load&InerKa

Pules&Per&Second 201 212 285 300 349 368Response&Rate&with&Rated&Load&InerKa RPM 28 29 40 42 48 51

Holding&Torque& Lbf3In& 10.758 8.197 15.214 11.592 18.634 14.197

Torque&at&Low&Pulse&Rate Lbf3In 6.053 4.424 8.889 6.584 11.065 8.242

Dynamic&RatePules&Per&Second 101 106 142 150 174 184

Dynamic&RateRPM 14 15 20 21 24 26

Pull3In&Torque&at&Dynamic&Rate& Lbf3In 3.027 2.212 4.444 3.292 5.532 4.121

Rated&Load&InerKa Lb3In3sec2 2.85E3032.85E303 2.85E3032.85E303 2.85E3032.85E303

Stall&Power&at&24&VDC WaWs& 10.010.0 20.020.0 30.030.0

! 19

Avior&Control&Technologies,&Inc&3&www.AviorControls.com&/&[email protected]&/&(T)&+13303388230521&&CAGE:&6GST1&©&2012,&Avior&Control&Technologies,&Inc&&All&Rights&Reserved&





Electric Motors• Stepper (Up to 50 VDC)• Brushless DC (Up to 270 VDC)• AC Induction (up to 200 VAC)• Housed• Frameless / Pancake / Cog-less

Precision Gearing Transmission Drives

• Low Backlash Planetary Gearboxes • Differential• Harmonic • Right Angle Drives

Linear Translation• Ball Screw • Planetary Roller Screw• Lead Screw

Custom Actuators• Rotary and Linear Actuators using a combination of

products described herein. Eddy Current Damper Characterization Test

Kinematic TransducersPosition Transducers

• Resolvers (Housed and frameless) • Variable Reluctance• Rotary Variable Differential Transducers • Single Speed / Multi-Speed

Velocity Transducers

• Permanent Magnet Alternators • AC Tachometers

Acceleration Transducers• DC Angular Accelerometers

Alternators / Generators• AC Power Alternators

Energy Absorption• Eddy Current Dampers• DC Controlled Hysteresis Brakes• Friction Brakes and Clutches • Synchronous Deployment Control• Passive and Active Damping Control

! 8


December 2012, V2.0





linear actuator catalog - aviorcontrols.com€¦ ·...

Documents