Low-thrust jet propulsion systems
Low-thrust jetpropulsion systems
LIQUID-PROPELLANT LOW-THRUST THRUSTERS
LIQUID-PROPELLANT
LOW-THRUST THRUSTERS
THRUST 30 N AND 100 N
DESCRIPTION
Liquid-propellant thrusters are incorporated in liquid-propellant jet propulsion systems and generate thrust by propellant exhaust through a supersonic nozzle.
BASIC SPECIFICATIONS
| Parameter | Cyclone-4 thruster | Cyclone-3 thruster | Cyclone-3 thruster | Okean-O thruster |
| Propellants: | ||||
| – oxidizer | Nitrogen Tetroxide | |||
| – fuel | Unsymmetrical Dimethylhydrazine | |||
| Nominal thrust, N | 30 | 100 | 30 | 30 |
| Specific impulse in continuous running at nominal propellant inlet pressure, m/s | 2000 | 2600 | 2600 | 2600 |
| Chamber pressure, MPa | 0.1 | 0.7 | 0.7 | 0.7 |
| Nominal propellant inlet pressure, MPa | Oxidizer 0.53 Fuel 0.25 | 1.35 | 1.35 | 1.35 |
| Nominal mixture ratio | 1.85 | 1.6 | 1.3 | 1.6 |
| Guaranteed number of ignitions | 30000 | 1300 | 1300 | 50000 |
| Total running time, s | 5600 | 200 | 200 | 3600 |
| Duration of a single ignition, s | 0.21 / 2000 | 0.21 / 165 | 0.21 / 165 | 0.21 / 600 |
| Supply voltage, V | 28 | 28 | 28 | 28 |
| Mass, kg | 1.16 | 1.45 | 1.3 | 1.3 |
TESTS
All engine qualification tests were successfully completed. The qualification tests included:
• climatic tests;
• mechanical tests;
• firing tests;
• firing endurance tests.
30N thrust producing jet engines have been used for spacecraft orientation and orbiting over a period of the Ocean-O mission. 100N and 30N thrust producing engines have been used for attitude and stabilization control of the Cyclone-3 Upper Stage, with more than 100 successful launches. New 30N thrust producing engines with lower inlet pressure will be installed on Cyclone-4 and Cyclone-4M upper stages.
CYCLONE-4 ROCKET 30-NEWTON THRUSTER
CYCLONE-3 ROCKET 100-NEWTON THRUSTER
CYCLONE-3 ROCKET 30-NEWTON THRUSTER
OKEAN-O SPACECRAFT 30-NEWTON THRUSTER
Low-thrust jet propulsion systems
LIQUID-PROPELLANT LOW-THRUST THRUSTERS
LIQUID-PROPELLANT
LOW-THRUST THRUSTERS
THRUST 30 N AND 100 N
CYCLONE-4 ROCKET 30-NEWTON THRUSTER
DESCRIPTION
Liquid-propellant thrusters are incorporated in liquid-propellant jet propulsion systems and generate thrust by propellant exhaust through a supersonic nozzle.
TESTS
All engine qualification tests were successfully completed. The qualification tests included:
• climatic tests;
• mechanical tests;
• firing tests;
• firing endurance tests.
30N thrust producing jet engines have been used for spacecraft orientation and orbiting over a period of the Ocean-O mission. 100N and 30N thrust producing engines have been used for attitude and stabilization control of the Cyclone-3 Upper Stage, with more than 100 successful launches. New 30N thrust producing engines with lower inlet pressure will be installed on Cyclone-4 and Cyclone-4M upper stages.
CYCLONE-4 ROCKET 30-NEWTON THRUSTER
BASIC SPECIFICATIONS
| Parameter | Cyclone-4 thruster |
| Propellants: | |
| – oxidizer | Nitrogen Tetroxide |
| – fuel | Unsymmetrical Dimethylhydrazine |
| Nominal thrust, N | 30 |
| Specific impulse in continuous running at nominal propellant inlet pressure, m/s | 2000 |
| Chamber pressure, MPa | 0.1 |
| Nominal propellant inlet pressure, MPa | Oxidizer 0.53 Fuel 0.25 |
| Nominal mixture ratio | 1.85 |
| Guaranteed number of ignitions | 30000 |
| Total running time, s | 5600 |
| Duration of a single ignition, s | 0.21 / 2000 |
| Supply voltage, V | 28 |
| Mass, kg | 1.16 |
CYCLONE-3 ROCKET 100-NEWTON THRUSTER
BASIC SPECIFICATIONS
| Parameter | Cyclone-3 thruster |
| Propellants: | |
| oxidizer | Nitrogen Tetroxide |
| fuel | Unsymmetrical Dimethylhydrazine |
| Nominal thrust, N | 30 |
| Specific impulse in continuous running at nominal propellant inlet pressure, m/s | 2600 |
| Chamber pressure, MPa | 0.7 |
| Nominal propellant inlet pressure, MPa | 1.35 |
| Nominal mixture ratio | 1.3 |
| Guaranteed number of ignitions | 1300 |
| Total running time, s | 200 |
| Duration of a single ignition, s | 0.21 / 165 |
| Supply voltage, V | 28 |
| Mass, kg | 1.3 |
CYCLONE-3 ROCKET 30-NEWTON THRUSTER
BASIC SPECIFICATIONS
| Parameter | Cyclone-3 thruster |
| Propellants: | |
| oxidizer | Nitrogen Tetroxide |
| fuel | Unsymmetrical Dimethylhydrazine |
| Nominal thrust, N | 30 |
| Specific impulse in continuous running at nominal propellant inlet pressure, m/s | 2600 |
| Chamber pressure, MPa | 0.7 |
| Nominal propellant inlet pressure, MPa | 1.35 |
| Nominal mixture ratio | 1.3 |
| Guaranteed number of ignitions | 1300 |
| Total running time, s | 200 |
| Duration of a single ignition, s | 0.21 / 165 |
| Supply voltage, V | 28 |
| Mass, kg | 1.3 |
CYCLONE-3 ROCKET 30-NEWTON THRUSTER
OKEAN-O SPACECRAFT 30-NEWTON THRUSTER
BASIC SPECIFICATIONS
| Parameter | Okean-O thruster |
| Propellants: | |
| oxidizer | Nitrogen Tetroxide |
| fuel | Unsymmetrical Dimethylhydrazine |
| Nominal thrust, N | 30 |
| Specific impulse in continuous running at nominal propellant inlet pressure, m/s | 2600 |
| Chamber pressure, MPa | 0.7 |
| Nominal propellant inlet pressure, MPa | 1.35 |
| Nominal mixture ratio | 1.6 |
| Guaranteed number of ignitions | 50000 |
| Total running time, s | 3600 |
| Duration of a single ignition, s | 0.21 / 600 |
| Supply voltage, V | 28 |
| Mass, kg | 1.3 |
GAS-JET PROPULSION SYSTEMS
GJPS
GAS-JET PROPULSION SYSTEMS
DESCRIPTION
Gas jet propulsion systems (GJPS) damp spacecraft’s initial post-separation disturbances and provide attitude control, orbit correction, and spacecraft spin about any axis.
BASIC SPECIFICATIONS
| Working medium – air, nitrogen, argon | |
| Maximum bottle pressure at 20°С, MPa | 23 |
| Nominal gas pressure upstream engines, MPa | 0.3 |
| Total thrust impulse, N·s | 250 – 7000 |
| Nominal engine thrust, N | 0.1; 0.2; 8.5 – 55 |
| Thrust excursion in all operating environments, % | ±25 |
| Specific impulse in 20°C air, m/s | 710 |
TESTS
Gas-jet propulsion systems have passed the whole scope of qualification tests. The qualification tests included:
• leakage test;
• strength test;
• climatic tests;
• mechanical tests;
• endurance test.
GAS-JET PROPULSION SYSTEMS
GJPS
GAS-JET PROPULSION SYSTEMS
DESCRIPTION
Gas jet propulsion systems (GJPS) damp spacecraft’s initial post-separation disturbances and provide attitude control, orbit correction, and spacecraft spin about any axis.
BASIC SPECIFICATIONS
| Working medium – air, nitrogen, argon | |
| Maximum bottle pressure at 20°С, MPa | 23 |
| Nominal gas pressure upstream engines, MPa | 0.3 |
| Total thrust impulse, N·s | 250 – 7000 |
| Nominal engine thrust, N | 0.1; 0.2; 8.5 – 55 |
| Thrust excursion in all operating environments, % | ±25 |
| Specific impulse in 20°C air, m/s | 710 |
TESTS
Gas-jet propulsion systems have passed the whole scope of qualification tests. The qualification tests included:
• leakage test;
• strength test;
• climatic tests;
• mechanical tests;
• endurance test.
SPACECRAFT PROPULSION SYSTEMS
SPACECRAFT PROPULSION SYSTEMS
HALL-ENGINE-BASED ELECTRIC JET PROPULSION SYSTEM
HALL-ENGINE-BASED ELECTRIC
JET PROPULSION SYSTEM
SPACECRAFT PROPULSION SYSTEMS
DESCRIPTION
The Hall-engine-based Electric Jet Propulsion System (EJPS) is designed for spacecraft orbit correction, stabilization, and interplanetary flights.
BASIC SPECIFICATIONS
| Working medium – xenon | |
| Maximum bottle pressure at 50°С, MPa | 13 |
| Total thrust impulse, kN·s | 50 – 1000 |
| Nominal Hall engine thrust, mN | 1 – 66 |
| Thrust excursion in all operating environments, % | 15 |
| Specific impulse of Hall engines in continuous running mode in nominal environment, m/s | 2200 -22000 |
| Engine thrust-to-power ratio, W/mN | 16-20 |
HALL-ENGINE-BASED ELECTRIC JET PROPULSION SYSTEM
HALL-ENGINE-BASED ELECTRIC
JET PROPULSION SYSTEM
SPACECRAFT PROPULSION SYSTEMS
DESCRIPTION
The Hall-engine-based Electric Jet Propulsion System (EJPS) is designed for spacecraft orbit correction, stabilization, and interplanetary flights.
BASIC SPECIFICATIONS
| Working medium – xenon | |
| Maximum bottle pressure at 50°С, MPa | 13 |
| Total thrust impulse, kN·s | 50 – 1000 |
| Nominal Hall engine thrust, mN | 1 – 66 |
| Thrust excursion in all operating environments, % | 15 |
| Specific impulse of Hall engines in continuous running mode in nominal environment, m/s | 2200 -22000 |
| Engine thrust-to-power ratio, W/mN | 16-20 |
GREEN MONOPROPELLANT PROPULSION SYSTEMS
GREEN MONOPROPELLANT
PROPULSION SYSTEMS
SPACECRAFT PROPULSION SYSTEMS
DESCRIPTION
Green monopropellant propulsion system is intended for generation of thrust impulse bits with purpose to increase SC lifetime.
BASIC SPECIFICATIONS
| Working medium – HAN based | |
| Pressurant – isobutane | |
| Total thrust impulse, kN·s | 0.32 |
| Total thrust impulse in one work cycle, N·s | not less than 1.0 |
| Monopropellant mass, kg | 0.15 |
| Total power consumption for single actuation, W·h | not more than 13.0 |
| Thrust, N | 0.153 |
| Active existence period, year | not less than 1.0 |
| Mass, kg | 1.1 max |
| Overall dimensions, mm | 100х100х135 |
TESTS
Propulsion system and its components have passed whole scope of autonomous tests:
• climatic tests;
• mechanical tests;
• firing tests.
The propulsion system will be installed on the CubeSat GS-1 satellite.
GREEN MONOPROPELLANT PROPULSION SYSTEMS
GREEN MONOPROPELLANT
PROPULSION SYSTEMS
SPACECRAFT PROPULSION SYSTEMS
DESCRIPTION
Green monopropellant propulsion system is intended for generation of thrust impulse bits with purpose to increase SC lifetime.
BASIC SPECIFICATIONS
| Working medium – HAN based | |
| Pressurant – isobutane | |
| Total thrust impulse, kN·s | 0.32 |
| Total thrust impulse in one work cycle, N·s | not less than 1.0 |
| Monopropellant mass, kg | 0.15 |
| Total power consumption for single actuation, W·h | not more than 13.0 |
| Thrust, N | 0.153 |
| Active existence period, year | not less than 1.0 |
| Mass, kg | 1.1 max |
| Overall dimensions, mm | 100х100х135 |
TESTS
Propulsion system and its components have passed whole scope of autonomous tests:
• climatic tests;
• mechanical tests;
• firing tests.
The propulsion system will be installed on the CubeSat GS-1 satellite.
ABLATION JET ENGINE
ABLATION JET ENGINE
SPACECRAFT PROPULSION SYSTEMS
DESCRIPTION
The jet propulsion system of ablation type is intended for changing and maintaining nanosatellite’s relative orbital position during active lifetime, including nanosatellite stabilization.
BASIC SPECIFICATIONS
| Working medium | fluoroplastic |
| Thrust, mN | 0.1 |
| Specific impulse, m/s | 20 000 |
| Total impulse, N·s | 200 |
| Maximum power consumption, W | 20 |
| Dimensions of engine, mm | 90х21х32 |
| Dimensions of power and control unit, mm | 100х100х30 |
ADVANTAGES
• compact size and little weight;
• low power consumption;
• high specific impulse;
• simple design;
• ready for operation whenever possible;
• extremely little inertia and almost zero afteraction pulse;
• no use of dangerous working mediums and pressurized gases;
• long service life;
• easy operation.
ABLATION JET ENGINE
ABLATION JET ENGINE
SPACECRAFT PROPULSION SYSTEMS
DESCRIPTION
The jet propulsion system of ablation type is intended for changing and maintaining nanosatellite’s relative orbital position during active lifetime, including nanosatellite stabilization.
BASIC SPECIFICATIONS
| Working medium | fluoroplastic |
| Thrust, mN | 0.1 |
| Specific impulse, m/s | 20 000 |
| Total impulse, N·s | 200 |
| Maximum power consumption, W | 20 |
| Dimensions of engine, mm | 90х21х32 |
| Dimensions of power and control unit, mm | 100х100х30 |
ADVANTAGES
Propulsion system and its components have passed whole scope of autonomous tests:
• climatic tests;
• mechanical tests;
• firing tests.
The propulsion system will be installed on the CubeSat GS-1 satellite.
AMMONIA JET PROPULSION SYSTEMS
AMMONIA JET PROPULSION SYSTEMS
AMMONIA PROPULSION SYSTEM FOR MicroSat-M SC
AMMONIA PROPULSION SYSTEM
FOR MicroSat-M SC
AMMONIA JET PROPULSION SYSTEMS
DESCRIPTION
The ammonia propulsion system (APS) is designed for correction of SC injection error in orbital period and orbital period keeping during active lifetime.
BASIC SPECIFICATIONS
| Total thrust pulse, N·s (kgf·s): | |
| – in hot mode | 7000 (714) |
| – in cold mode | 2500 (255) |
| One engine thrust in hot and cold modes, N (gf) | 0.049 (5) |
| Thrust deviation from nominal value, %: | |
| – in hot mode | ±15 |
| – in cold mode | ±22 |
| Number of APS firings during ALT | up to 500 |
| Number of engines, pcs | 2 |
| Duration of one firing, min | 15, no more |
| – in hot mode | 2500 (255) |
| – in cold mode | 882 (90) |
| Direct-current power voltage, V | 24 to 34 |
| Maximum power consumption of APS at nominal power voltage of 28 V, W | 375 |
| APS mass (dry), kg | 24 |
TESTS
All qualification testing of ammonia propulsion systems, installed on the MicroSat-M satellite, was successfully completed. The qualification tests included:
• climatic tests;
• mechanical tests;
• firing tests;
• firing endurance tests.
AMMONIA PROPULSION SYSTEM FOR MicroSat-M SC
AMMONIA PROPULSION SYSTEM
FOR MicroSat-M SC
AMMONIA JET PROPULSION SYSTEMS
DESCRIPTION
The ammonia propulsion system (APS) is designed for correction of SC injection error in orbital period and orbital period keeping during active lifetime.
BASIC SPECIFICATIONS
| Total thrust pulse, N·s (kgf·s): | |
| – in hot mode | 7000 (714) |
| – in cold mode | 2500 (255) |
| One engine thrust in hot and cold modes, N (gf) | 0.049 (5) |
| Thrust deviation from nominal value, %: | |
| – in hot mode | ±15 |
| – in cold mode | ±22 |
| Number of APS firings during ALT | up to 500 |
| Number of engines, pcs | 2 |
| Duration of one firing, min | 15, no more |
| – in hot mode | 2500 (255) |
| – in cold mode | 882 (90) |
| Direct-current power voltage, V | 24 to 34 |
| Maximum power consumption of APS at nominal power voltage of 28 V, W | 375 |
| APS mass (dry), kg | 24 |
TESTS
All qualification testing of ammonia propulsion systems, installed on the MicroSat-M satellite, was successfully completed. The qualification tests included:
• climatic tests;
• mechanical tests;
• firing tests;
• firing endurance tests.