ADN Micro Propulsion System 13066300-01 The VACCO / ECAPS CubeSat ADN Delta-V Propulsion System is a high performance micro propulsion system (MiPS) specifically designed for CubeSats. The ADN Delta-V MiPS is a self-contained subsystem that can be scaled from 0.5U to >1U. Four high-thrust, high specific impulse (I sp ) ADN thrusters deliver 1,828 N-Sec of total impulse using only integral propellant. The smart feed system can independently throttle each thruster to provide thrust vector control during delta-v burns. Reliability is ensured through simplicity of design, welded titanium construction and frictionless valve technology. SPACE Features Smart, self-contained propulsion system 1,828 N-Sec total impulse / 697 M-Sec delta-v assuming 3 kg CubeSat Four throttlable 100 mn ECAPS ADN thrusters Thrusters canted for thrust vector control Low Power: <15 watts during hot-fire <0.055 watts in standby mode Reliable, frictionless valves Operating Parameters Max Operating Pressure...244 psia Proof Pressure...366 psia Burst Pressure...610 psia Total Thrust...400 mn Internal Leakage...3.0 scc/hr External Leakage...1.0 x 10-6 scch Operating Temperature... 0 C to +50 C Non-Operating Temperature... -10 C to +60 C Vibration...23 Grms Cycle Life...900,000 firings Total Impulse... 1,808 N-Sec Minimum Impulse Bit... 2 mn-sec Operating Voltage...9 to 12.6 vdc Dry Mass... 909 grams Propellant Mass... 720 grams Total Mass... 1,800 grams Performance characteristics are based on customer requirements. As such, they are not representative of component capabilities or limitations.
Envelope Drawing 13066300-01 Electrical Schematic
MEPSI Micro Propulsion System XV0E10889-01 The MEMS PicoSat Inspector (MEPSI) Micro-Propulsion System (MiPS) is a cold gas propulsion system designed for 1U CubeSats. Using Chemically Etched Micro System (ChEMS ) technology, VACCO has produced a complete propulsion system including propellant storage, pressurization, distribution and thrusters. This simple, highly integrated design uses a selfpressurizing liquid propellant that is expelled as a gas. Capable of 23 N-Sec of total impulse with up to 43,000 firings, MiPS brings true propulsion capabilities to micro-spacecraft for formation flying, attitude control and velocity change (delta-v). SPACE Features Five thrusters for pitch, yaw, roll and delta-v 53 mn thrust Up to 43,000 minimum impulse firings Redundant, frictionless valves All-welded titanium construction Dry mass: 456 grams Integral pressure & temperature sensors Operating Parameters Max Operating Pressure...150 psia Proof Pressure...225 psia Burst Pressure...375 psia Thrust... 53 mn @ 20ºC Internal Leakage...3.6 scc/hr GN2 @ 20ºC External Leakage...1.0 x 10-6 scc/hr GN2 @ 20ºC Operating Temperature... 0 C to +60 C Vibration...16 Grms Cycle Life... 80,000 cycles Minimum Impulse Bit... 0.53 mn-sec Operating Voltage...4.0 to 6.0 vdc Tank Pressure Sensor Output...0.5 to 3.5 vdc Gas Tank Pressure Sensor Output...0.5 to 3.5 vdc Coil Resistance...5.3 +/- 0.5 coil Pull-in Voltage... 3.5 vdc max @ 20 C Drop Out Voltage... 1.0 vdc min @ 20 C Mass... 456 grams (dry) Performance characteristics are based on customer requirements. As such, they are not representative of component capabilities or limitations.
Envelope Drawing XV0E10889-01 Performance Characteristics Maneuver +Yaw (+X -Yaw (-X) +Pitch (+Y) -Pitch (-Y) CW Roll CCW Roll Delta V (+Z) Delta V (-Z) Thrusters AB CD Roll 90 CW, then CD Roll 90 CW, then AB AD CB ABCD E System Schematic
Palomar Micro Propulsion System XS0E10220-01 The Palomar Propulsion System is a fully integrated CubeSat micro propulsion system that includes a propellant tank, plenum and eight thrusters. The Palmomar MiPS is designed to occupy the center of a 3U CubeSat. This smart system is designed to interface with the spacecraft through an I 2 C data bus for command and control. The Palomar MiPS is primarily a reaction control system with thrusters arranged so that use of all six degrees of freedom (DoF) in rotation and translation are possible. Additional propellant is available by stretching the tank lobes, allowing for a custom propulsion system mass and volume based on specific mission needs. SPACE Upgrades to other propellants available. Features Over 200,000 thruster firings in a simulated space environment Ten frictionless valves for thrust, plenum pressure regulation, and filling Eight independent thrusters Simple command protocol for operation and health monitoring Liquid isobutane propellant provides high storage density; other propellants available Complete propulsion system in one monolithic package 5V power supply and I 2 C serial data interface Operating Parameters Max Operating Pressure...150 psia Proof Pressure...225 psia Burst Pressure...375 psia Thrust...35 mn Internal Leakage...3.0 scc/hr External Leakage...1.0 x 10-6 scch Operating Temperature... 0 C to +50 C Non-Operating Temperature... -10 C to +60 C Vibration...23 Grms Cycle Life...120,000 firings Total Impulse... 85 N-Sec Minimum Impulse Bit... 0.75 mn-sec Operating Voltage...4.75 to 5.25 vdc Peak Power...<5 watts (two thrusters) Dry Mass... 890 grams Propellant Mass... 173 grams Total Mass... 1,063 grams Performance characteristics are based on customer requirements. As such, they are not representative of component capabilities or limitations.
Envelope Drawing XS0E10220-01 End Views Side View Flow Schematic