Launch Vehicle Actuators

14 Launch Vehicle Actuators for Space Applications from 2 manufacturers listed on SatNow

Launch Vehicle Actuators are high-performance electromechanical or electrohydraulic devices designed to control critical motion systems in rockets and space launch vehicles. These actuators are typically used for thrust vector control (TVC), engine gimbaling, fin actuation, stage separation mechanisms, and valve positioning. Launch Vehicle Actuators for space applications from multiple manufacturers are listed on SATNow. Use the filters to select products based on your requirement. View product details, download datasheets, compare products, get quotes and pricing for matching products. SATNow has compiled this list of products specifically for Space and Satellite Applications.

14 Launch Vehicle Actuators from 2 Manufacturers
14 Products from 2 Manufacturers
Description:25 W Non-Pyrotechnic Launch Vehicle Actuator

Product Specs

Space Heritage:
Yes
Actuator Mass:
0.025 Kg
Voltage:
22 to 36 V
Current:
0.9 A
Power Consumption:
25 W
Resistance:
31 Ohms
Stall Load:
850 lbf
Operating Temperature:
-65 to 80 Degree C
Application:
Space, Solar array and Instrument deployment, Instrument launch locks, Optic covers
more info
Description:Hydraulic Linear Actuator for Aerospace Applications

Product Specs

Actuator Type:
Hydraulic Linear Actuator
Actuator Mass:
870 g
Supply Pressure:
2000 psig
Voltage:
28 V
Current:
4 to 20 mA
Frequency Response:
5.6 Hz
Static Force:
Extension : 700 lb, Retraction : 600 lb
Operating Temperature:
-40 to 121 Degree C
Dimension:
10 x 2.13 x 3.23 Inches
more info
Description:Non-Pyrotechnic Launch Vehicle Actuator

Product Specs

Space Heritage:
Yes
Actuator Mass:
0.04 Kg
Voltage:
22 to 36 V
Current:
1.75 A
Power Consumption:
49 W
Resistance:
16 Ohms
Stall Load:
1400 lbf
Operating Temperature:
-65 to 80 Degree C
Application:
Space, Solar array and Instrument deployment, Instrument launch locks, Optic covers
more info
Description:3000 psi Launch Vehicle Actuator

Product Specs

Space Standard:
MIL-PRF-83282, MIL-H-5606
Actuator Type:
Thrust Vector Control Actuator
Actuator Mass:
5.8 Kg
Supply Pressure:
3000 psig
Frequency Response:
5.1 Hz
Static Force:
Extension : 13500 lb, Retraction : 11000 lb
Dimension:
18 x 4.5 x 14.1 Inches
more info
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Description:Non-Pyrotechnic Launch Vehicle Actuator

Product Specs

Space Heritage:
Yes
Actuator Mass:
0.055 Kg
Voltage:
22 to 36 V / 95 to 105 V
Current:
1.1 to 2.9 A
Power Consumption:
80 to 111 W
Resistance:
9.7 to 90 Ohms
Stall Load:
3400 lbf
Operating Temperature:
-65 to 80 Degree C
Application:
Space, Solar array and Instrument deployment, Instrument launch locks, Optic covers
more info
Description:3000 psi Launch Vehicle Actuator

Product Specs

Space Standard:
MIL-PRF-83282, MIL-H-5606
Actuator Type:
Thrust Vector Control Actuator
Actuator Mass:
13.2 Kg
Supply Pressure:
3000 psig
Frequency Response:
4.4 Hz
Static Force:
Extension : 32500 lb, Retraction : 27500 lb
Dimension:
10.7 x 6.3 x 22.0 Inches
more info
Description:Non-Pyrotechnic Launch Vehicle Actuator

Product Specs

Space Heritage:
Yes
Actuator Mass:
0.110 Kg
Voltage:
22 to 36 V / 95 to 105 V
Current:
1.4 to 4 A
Power Consumption:
112 to 143 W
Resistance:
7 to 70 Ohms
Stall Load:
6000 lbf
Operating Temperature:
-65 to 80 Degree C
Application:
Solar array and Instrument deployment, Instrument launch locks, Optic covers
more info
Description:1500 psi Thrust Vector Control Actuator

Product Specs

Space Standard:
MIL-PRF-7024, MIL-H-5606
Actuator Type:
Thrust Vector Control Actuator
Actuator Mass:
6.12 Kg
Supply Pressure:
1500 psig
Frequency Response:
6 Hz
Static Force:
Extension : 7100 lb, Retraction : 5000 lb
Dimension:
7.6 x 4.4 x 15.1 Inches
more info
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Description:Non-Pyrotechnic Launch Vehicle Actuator

Product Specs

Space Heritage:
Yes
Actuator Mass:
0.175 Kg
Voltage:
28 to 41 V
Current:
4.8 A
Power Consumption:
105 W
Resistance:
7.5 Ohms
Stall Load:
9600 lbf
Operating Temperature:
-65 to 80 Degree C
Application:
Space, Solar array and Instrument deployment, Instrument launch locks, Optic covers
more info
Description:2000 psi Thrust Vector Control Actuator

Product Specs

Space Standard:
MIL-PRF-7024, MIL-H-5606
Actuator Type:
Thrust Vector Control Actuator
Actuator Mass:
6.12 Kg
Supply Pressure:
2000 psig
Frequency Response:
9 Hz
Static Force:
Extension : 9460 lb, Retraction : 6660 lb
Dimension:
7.6 x 4.4 x 15.1 Inches
more info
Description:Non-Pyrotechnic Launch Vehicle Actuator

Product Specs

Space Heritage:
Yes
Actuator Mass:
0.010 Kg
Voltage:
6 to 13.5 V
Current:
0.75 to 1.25 A
Power Consumption:
9 W
Resistance:
5.5 to 16 Ohms
Stall Load:
150 lbf
Operating Temperature:
-50 to 70 Degree C
Application:
Space, Solar array and Instrument deployment, Instrument launch locks, Optic covers
more info
Description:3000 psi Thrust Vector Control Actuator

Product Specs

Space Standard:
MIL-PRF-83282, MIL-H-5606, MIL-PRF-7024
Actuator Type:
Thrust Vector Control Actuator
Actuator Mass:
6.39 Kg
Supply Pressure:
3000 psig
Frequency Response:
8 Hz
Static Force:
Extension : 13250 lb, Retraction : 10750 lb
Dimension:
7.4 x 4.4 x 17.8 Inches
more info
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Description:1800 psi Thrust Vector Control Actuator

Product Specs

Space Standard:
MIL-PRF-7024, MIL-H-5606
Actuator Type:
Thrust Vector Control Actuator
Actuator Mass:
8.98 Kg
Supply Pressure:
1800 psig
Frequency Response:
10.1 Hz
Static Force:
Extension : 15800 lb, Retraction : 15000 lb
Dimension:
11.5 x 6.0 x 16.9 Inches
more info
Description:3000 psi Thrust Vector Control Actuator

Product Specs

Space Standard:
MIL-PRF-83282, MIL-H-5606, MIL-PRF-7024
Actuator Type:
Thrust Vector Control Actuator
Actuator Mass:
6.48 Kg
Supply Pressure:
3000 psig
Frequency Response:
8 Hz
Static Force:
Extension : 13250 lb, Retraction : 10750 lb
Dimension:
7.8 x 4.4 x 17.8 Inches
more info
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What are Launch Vehicle Actuators?

Launch Vehicle Actuators are high-performance electromechanical or electrohydraulic devices designed to control critical motion systems in rockets and space launch vehicles. These actuators are typically used for thrust vector control (TVC), engine gimbaling, fin actuation, stage separation mechanisms, and valve positioning. They convert electrical or hydraulic input energy into controlled linear or rotary motion, enabling precise adjustment of propulsion direction and aerodynamic control surfaces during ascent.

Engineered to operate under extreme vibration, acceleration, pressure, and thermal conditions, launch vehicle actuators must deliver high force output, rapid dynamic response, and robust reliability within tightly constrained mass and power budgets. Their mechanical stiffness, pressure compatibility, electrical characteristics, and response bandwidth directly influence flight stability, trajectory accuracy, and mission safety. Proper actuator selection ensures compatibility with propulsion systems, control electronics, and structural interfaces throughout all flight phases.

Key specifications of launch vehicle actuator:

  • Actuator Type: Specifies the operational principle of the actuator, such as electromechanical, electrohydraulic, or pneumatic. Actuator type determines force generation mechanism, response characteristics, maintenance requirements, and integration complexity within the launch vehicle control system.
  • Actuator Mass: Indicates the total mass of the actuator assembly including motor or hydraulic components, housing, and control interfaces. Actuator mass directly affects vehicle mass fraction, structural loading, and overall performance margins.
  • Supply Pressure: Defines the hydraulic or pneumatic pressure required for operation in fluid-powered systems. Supply pressure influences force output capability, structural design, sealing requirements, and system-level plumbing integration.
  • Voltage: Specifies the electrical supply voltage required for actuator operation. Voltage compatibility must align with onboard power systems and influences motor design, insulation requirements, and control electronics architecture.
  • Current: Represents the electrical current drawn during nominal and peak actuation. Current demand impacts power distribution sizing, thermal management, and protection circuitry within the launch vehicle electrical system.
  • Resistance: Refers to the electrical resistance of actuator windings or control elements. Resistance affects current flow characteristics, efficiency, and heat dissipation during sustained operation.
  • Static Force: Defines the maximum continuous force the actuator can exert without motion. Static force capability is critical for maintaining engine or control surface position under sustained aerodynamic and thrust loads.
  • Frequency Response: Indicates the bandwidth over which the actuator can accurately follow control input signals. Frequency response determines suitability for high-dynamic thrust vector adjustments and flight stability control.
  • Stall Load: Represents the maximum load at which the actuator ceases motion under commanded input. Stall load defines structural and motor protection thresholds and influences fault management strategies.
  • Horsepower: Specifies the mechanical power output capability of the actuator. Horsepower directly relates to force and velocity performance, determining the actuator’s ability to deliver rapid and high-load movements during flight maneuvers.

The Largest Database of Launch Vehicle Actuators

SatNow has listed Launch Vehicle Actuators from the leading manufacturers and made them searchable by specification. You can enter the key parameters and the search tool will scan catalogs from the leading manufacturers to identify products that meet your spec. Once you find Launch Vehicle Actuators that meet your requirement, you can view product information, download datasheets or request quotations. Quotation requests will be routed to the manufacturer of the product who will get back to you directly. The quotation will also be routed to distributors of the product in your region.