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High Performance Green Propulsion (HPGP):
A Flight-Proven Capability and Cost Game-Changer
for Small and Secondary Satellites
Aaron Dinardi
26th AIAA/USU Small
Satellite Conference
14 August 2012
1. HPGP Overview
2. PRISMA Two-Year Update
3. Benefits to Small Satellite Missions
Outline
• IMPROVED PERFORMANCE
- Storable liquid monopropellant
- Higher Specific Impulse and Density Impulse
Why Green Propulsion?
Higher performance than
monopropellant Hydrazine
Reduced tank volume
or Extended mission
+
• INCREASED SAFETY
- Low Sensitivity - Low Toxicity
- Non-Carcinogenic
- Environmentally Benign
=
• LOWER MISSION COSTS - Simplified handling and transportation
- Reduced cost for fueling operations
- Compatible with available COTS hardware Much less toxic than Hydrazine
Reduced fueling cost
HPGP Characteristics (as compared to hydrazine)
Comparison Parameter Hydrazine HPGP (LMP-103S)
Specific Impulse Reference ≥ 6% higher than hydrazine
Density Reference 24% higher than hydrazine
Stability Unstable (reactivity) Stable > 20 yrs (STANAG 4582)
Toxicity Highly Toxic Low Toxicity (due to methanol)
Carcinogenic Yes No
Corrosive Yes No
Flammable Vapors Yes No
Environmental Hazard Yes No
Sensitive to Air & Humidity Yes No
SCAPE Required for Handling Yes No
Storable Yes Yes (> 6.5 yrs, end-to-end test is ongoing)
Freezing Point 1°C -90°C (-7°C saturation)
Boiling Point 114°C 120°C
Qualified Operating Temp Range 10°C to 50°C 10°C to 50°C
(allows use of COTS hydrazine components)
Operating Temp Range
Capability
10°C to 50°C -5°C to 60°C
Typical Blow-Down Ratio 4:1 4:1
Exhaust Gases Ammonia, nitrogen, hydrogen H20 (50%), N2 (23%), H2 (16%), CO (6%),
CO2 (5%)
Radiation Tolerance Reference Insensitive up to 100 kRad (Cobalt 60)
Shipping Class 8 / UN2029
(Forbidden on commercial aircraft)
UN / DOT 1.4S
(Permitted on commercial passenger aircraft)
Air Transport of LMP-103S Transport Classified as UN / US DOT 1.4S
1. 21 Aug 2009: Stockholm Kiruna (via commercial passenger aircraft)
2. 17 May 2010: Örebro Orsk (via cargo aircraft with the PRISMA satellites)
3. 11 Aug 2011: Stockholm Zurich London (via commercial passenger aircraft)
4. 6 Jun 2012: Göteborg Stockholm New York (via commercial passenger aircraft)
Tango
• 3-axis stabilized
• Solar Magnetic control
• No orbit control
• 40 kg launch mass
Mango
• 3-axis stabilized
• Attitude Independent Orbit
Control
• 100 m/s Delta-V
• 145 kg launch mass
• 2.6 m “wing-span”
• 3 propulsion systems
• 4 RF systems
(Artists Impression – Courtesy of DLR)
HPGP has been flight-proven to outperform
hydrazine on the PRISMA mission
HPGP In-Space Comparison with Hydrazine as seen during 2 years on PRISMA
Specific Impulse and Density Impulse Comparison
Steady-State Firing: Isp for last 10 s of 60 s firings
6-12 % Higher Isp than hydrazine
30-39 % Higher Density Impulse than hydrazine
Single Pulse Firing: Ton: 50 ms – 60 s
First half of the mission
10-20 % Higher Isp than hydrazine
36-49 % Higher Density Impulse than hydrazine
Pulse Mode Firing: Ton: 50 ms – 30 s
Duty Factor: 0.1 – 97%
0-12 % Higher Isp than hydrazine
24-39 % Higher Density Impulse than hydrazine
Mission Average improvement with HPGP compared to hydrazine:
- Isp + 8% - Density Impulse + 32%
Benefits to Small Satellite Missions:
1) Increased Performance 2) Simplified Handling & Transportation
4) Fewer Secondary/Rideshare Restrictions 3) Reduced Mission Costs
≥ 30% higher performance allows:
Longer mission lifetime (with same tank), or
Smaller tank (for same ∆V)
o Waterfall mass reductions
o Better utilization of limited volume & mass
Efficient orbit raising and/or de-orbit
Reduced propellant toxicity allows:
Handling in facilities not rated for hydrazine o Launch sites o Universities and SMEs
Air transport (commercial/passenger aircraft) o Shipment to launch site with s/c & GSE
Fueling without SCAPE suits Increased responsiveness
o Shorter launch campaigns
o Shipment of pre-fueled satellites
Significant life-cycle cost reductions, due to:
All of the blue highlighted items on this slide
Non-Hazardous fueling operations allow:
Reduced physical risk to primary satellites
Parallel processing at launch site
o Reduced schedule risk to primary satellites
More launch opportunities
Benefit #1: Increased Performance
Longer Mission Lifetime Astrium Space Transportation analyzed replacing hydrazine
with HPGP on their existing Myriade platform (100 - 200 kg),
and concluded that for the same tank size:
• Up to 28% higher total impulse is achievable, resulting in
• 24% more ∆V (blow-down dependent)
Myriade
LRO mass savings with HPGP
Smaller Tank NASA GSFC analyzed the mass savings which would have
been achieved on the Lunar Reconnaissance Orbiter (1,882 kg)
if it had implemented HPGP instead of hydrazine, and
concluded that:
• A 39% smaller tank (volume) and 26% less propellant (mass) could have been used, resulting in “waterfall” mass savings
of 18.7% of the entire spacecraft’s mass
Orbit Raising and/or De-orbit Small satellites are often injected into sub-optimal orbits (due to
being launched as secondary payloads), resulting in: • Reduced mission lifetime (if injected too low), or • If injected too high, and orbit decay timeframe exceeding the 25
year post-mission requirement
Including a small COTS-based HPGP system can provide an
effective way for small satellites to raise and/or lower their perigee
Benefit #2: Simplified Handling & Transportation
Loading PRISMA with Hydrazine
Loading PRISMA with LMP-103S For the PRIMSA launch campaign:
• The LMP-103S propellant was transported as air cargo,
together with the satellites and associated GSE
o Hydrazine was shipped separately, by rail/boat/truck
Hydrazine HPGP
470 kg toxic waste 3 kg non-toxic waste
29 kg propellant waste 1 kg propellant waste
• HPGP fueling operations required only 3 working days (leak
checks, fueling & pressurization, decontamination)
• All HPGP handling (loading & decontamination) was
declared “non-hazardous operations” by Range Safety
o HPGP loading did not require SCAPE operations
o Only limited decontamination of the HPGP loading cart was
required at the launch site:
• The costs for propellant, transportation and fueling of
hydrazine were 3 times higher than those for HPGP
Benefit #3: Reduced Life-Cycle Costs
A “Non-Space”
Case Study
42% - 88% higher up-front costs than
heritage technology
options are offset by
significant savings in
other areas
Source: Demonstration Assessment of Light-Emitting Diode (LED) Parking Lot Lighting, Prepared for the US Dept. of Energy by the Pacific Northwest National Laboratory, May 2011
Conclusions:
1) Significant savings are achievable, even before all cost areas are accounted for.
2) Analyses must be performed on a mission-by-mission basis in order to determine if the
transportation & launch processing cost savings are able to offset the higher material costs.
(*Note: Positive values indicate HPGP cost savings over a hydrazine-based system) Consideration Factors:
HPGP vs. Hydrazine Cost Comparison
Analysis includes: flight hardware, propellant (excluding transport) and satellite fueling (excluding waste disposal)
Greater savings are able to be achieved from smaller tanks, propellant transportation and waste disposal
Mission #1:
1a 1b 1c
Mission #2:
2a 2b 2c
Missions #3&4:
3a 4a
Missions #3&4:
4b 3b
Example HPGP Cost Savings (vs. a comparable hydrazine system)
HPGP eliminates or reduces the concerns
which often preclude the inclusion of a liquid
propulsion system on small satellite missions;
thus enabling small satellites to achieve
increased scientific utility
The combined benefits of higher performance
& simplified transportation/handling provided
by HPGP allow satellite mass reductions and
significantly reduced mission life-cycle costs
(as compared with hydrazine-based systems of
similar performance)
When taken together, the many flight-proven
benefits make HPGP a “game changer” for
both increasing the capabilities and reducing
the costs of small satellite missions
Conclusions Increased
Performance
Simplified Handling
& Transportation
Reduced
Mission Costs Fewer Rideshare
Restrictions
Benefits to Small Satellites:
Ammonium DiNitrimide (ADN)
in liquid monopropellants
Solvent
Water
Fuel
Alcohols,
acetone,
ammonia
The family of ADN propellants was
invented in 1997 by the Swedish Space Corporation (SSC) and the Swedish Defence Research Agency (FOI).
ADN Energetic Material
Highly Soluble
Oxidizer
LMP-103S
monopropellant:
ADN 60-65 % Methanol 15-20 % Ammonia 3-6 %
Water balance (by weight)
HPGP
High Performance
Green Propellant
* Delivered steady-state vacuum specific impulse at MEOP and ε = 150:1
** Predicted steady-state vacuum specific impulse at MEOP and ε = 150:1
1 N 5 N 22 N 50 N 220 N
ECAPS High Performance Green Propulsion
1 N 5 N 22 N 50 N 220 N
ECAPS High Performance Green Propulsion
Thrust 0.5 N 1 N 5 N 22 N 50 N 220 N
Propellant LMP-103S LMP-103S LMP-103S LMP-103S LMP-103S LMP-103
Isp (Ns/kg) 2210*
(~ 225 sec)
2310*
(~ 235 sec)
2450*
(~ 250 sec)
2500*
(~ 255 sec)
2515**
(~ 255 sec)
2800**
(~ 255 - 285 sec)
Density
Impulse (Ns/L)
2730
2860
2900
3030
3120
3580
Status TRL 5 TRL 9
flight proven
TRL 5 TRL 5 TRL 3 TRL 4/5
The PRISMA Mission
Objective and Background: • Demonstration of technologies related to Formation Flying (FF)
and Rendezvous in space
− Main satellite “Mango” and Target satellite “Tango”
• Demonstration of High Performance Green Propulsion (HPGP) system
HPGP Flight Objectives: • Demonstration of non-hazardous fueling operations and
reduced fueling lead time of a high performance monopropellant
• First in-space demonstration of a high performance storable
“green” monopropellant
• Deliver ΔV to the PRISMA mission
• Redundant propulsion system to hydrazine
• Perform Back-to-Back performance comparison with hydrazine
Status: • Launched clamped together on 15 Jun 2010
• Tango separated from Mango on 11 Aug 2010
• Nominal mission completed by mid-Aug 2011
• Mission extended into 2012 (still operational)
HPGP propulsion system:
Two 1N thrusters
• Specific HPGP experiments
• Formation flying maneuvers
• Co-operations with hydrazine
PRISMA (Mango) Propulsion Systems
Hydrazine propulsion system:
Six 1N thrusters
• Autonomous formation flying
• Autonomous rendezvous
• Homing
• Proximity operations
LMP-103S
GHe
TS TS
Propellant Service
Valve Orifice
Filter Latch Valve
Thrusters
Pressurant Service
Valve
Pressure
Transducer
*Hydrazine based Commercial Off The Shelf components
Additional Consideration: “Hidden” Hydrazine Costs
Hydrazine Disposal
Cost Analysis
Note: The cumulative “disposal charge”
translates to ~$29/pound of hydrazine. However, when categories 5 & 6 are
combined, the cost can grow to more
than 3x that…