200N HPGP Thruster
Bradford ECAPS's 200N HPGP Thruster is designed for launch vehicle upper-stage reaction control and potential defense applications, such as missile defense. Much of the work into the 200N HPGP has been to investigate potential uses on various launch vehicle upper stage programs, including the Ariane 5ME, and for various spacecraft orbit-raising applications. This thruster is currently in development and looking for partners to bring the prior work into fruition.
- Propellant loading is simple, fast and avoids the cost associated with loading hydrazine. Allows the operator to spend less time on ground operations and more time on space operations.
- ‘Fuel at the factory’ – be ready for launch vehicle integration upon arrival at the launch pad. Eliminates significant time and cost from lengthy pre-launch campaigns.
- Non-toxic propellant is suitable for a new class of responsive small satellite launchers, where handling hazardous hydrazine may impede operations or where fully equipped hydrazine processing facilities may be non-existent at the launch site.
- Higher performance over hydrazine allows for more payload or longer mission durations.
- Allows for more agile mission profiles than electric propulsion. Spacecraft take significantly less time to execute maneuvers and orbit changes.
Specifications Table
| Thruster Type | HPGP | HPGP |
| Propellant | LMP-103S | LMP-103S |
| Thrust Class | 200 N | 200 N |
| Primary Operational Mode | RCS | Δ ∨ |
| Inlet Pressure Range | 5 - 26 Bar | 5 - 26 Bar |
| Thrust Range | 50 - 200 N | 55 - 220 N |
| Nozzle Expansion Ratio | 30:1 | 150:1 |
| Steady State ISP (vacuum) Typical | 2020 - 2300 Ns/Kg (206 -234 s) |
2385 - 2500 Ns/Kg (243 -255 s) |
| Density Impulse (vacuum) | 2050 - 2852 Ns/L | 2957 - 3100 Ns/L |
| Minimum Impulse Bit | ≤ 9 Ns | N/A |
| Overall Length | 280 mm | 390 mm |
| Mass | 5.7 kg | 6 kg |
| FCV Type | Solenoid | Solenoid |
| - No of Seats | Single Seat | Single Seat |
| - Pull-in Voltage | 28 ± 4 VDC | 28 ± 4 VDC |
| - Holding Voltage | 10 ± 1 VCD | 10 ± 1 VCD |
| - Coil Resistance (each coil) | 27 Ω | 27 Ω |
| Nominal Reactor Pre-heating Voltage | 55 VDC | 55 VDC |
| Regulated Reactor Ore-heating Power | 150 - 250 W TBC | 150 - 250 W |
| Target Life - Qual. Level | ||
| Pulses | 2,000 | 10 |
| Propellant Throughput | 150 kg | 25 kg |
| Longest Continues Firing | 10 minutes | 200 s |
| Accumulated Firing Time | 40 minutes | 400 s |
| Firing Sequences | 100 | 10 |
| Demonstrated Life | ||
| Pulses | 1,500 | 1,500 |
| Propellant Throughput | 24 kg | 24 kg |
| Longest Continues Firing Time | 20 seconds | 20 seconds |
| Accumulated Firing Time | 7.7 minutes | 7.7 minutes |
| Firing Sequences | 100 | 100 |
| Maturation Level | TRL 5 | TRL 3 |
| Current Status | ||
| Ariane 5 ME Demonstrator Hot Fired | Orbit Raiser Phase A Development |
