going beyond traditional rideshare using an orbital...
TRANSCRIPT
Going Beyond Traditional Rideshare using an Orbital Maneuvering Vehicle
February 3, 2016
Chris Loghry Space Systems Engineer
Contact Info: [email protected]
This document, including all enclosed slides, consists of general capabilities information that is not defined as controlled technical data under ITAR Part 120.10 or EAR Part 772.
Introduction
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• The potential data value from small sat payloads will continue to increase as capability evolves at an exponential rate
• However, this can only be truly exploited (be it commercially or scientifically) if the payloads are in the optimal orbit
• There are several established ways of getting to orbit and these all come with limitations and costs
• An Orbital maneuvering vehicle (OMV) provides an option for desired orbit access
Customer Focused Space Organization
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Moog Space leverages the unique experience from acquisitions to include all perspectives in the Space market Schaeffer Magnetics, CSA Engineering, Bradford Engineering, Bell/ARC/AMPAC In-Space Propulsion, Broad Reach Engineering
Operating Sites
Launch Vehicle Systems and Components Strategic Missiles and Missile Defense
Integrated Space Systems Structures and Analysis
Spacecraft Mechanisms Rocket Engines
Propulsion Systems, Valves and Components Satellite Avionics and Software
Attitude and Orbit Control Components
Spacecraft Controls
Space Access & Integrated Systems
Chatsworth, CA Cheltenham, UK East Aurora, NY Heerle,
The Netherlands Niagara Falls, NY Westcott, UK Tempe, AZ
Albuquerque, NM Dublin, Ireland East Aurora, NY
Golden, CO Mountain View, CA
~$2.5B, 11,000 Employees, 27 Countries, 5 Operating Groups• Space and Defense Group
• ~$380M, 6 Countries, 24 locations
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Getting SmallSats into Orbit
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Dedicated rideshare (no
primary)Rideshare
Space Station Dedicated launcher
PROS CONSRideshare Established and developing
infrastructureOrbits tied to primary sat; primary imposes other constraints
Rideshare (Dedicated / No Primary)
More control over orbits, Upper Stage restart capability
Costs could be higher, large constellations with many different payloads are difficult for launch providers
ISS Deployment Low cost and subsidized Low, restricted and limited life orbits, payload limitations
Dedicated Launch Complete control over orbit
Not much market capacity (yet)
What Is an Orbital Maneuvering Vehicle? • An OMV is an intermediate vehicle somewhere between a Launch Vehicle and a
Satellite - a close cousin to Upper Stages – Utilizes the EELV Secondary Payload Adapter (ESPA) ring as the primary structure – Provides delta-v & maneuvering within space, typically within Earth’s orbit but not always
• An OMV’s capabilities can address the limitations of other launch options for getting small satellites in to their desired orbits
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OMVLaunch Vehicle
Upper Stage
Satellite
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Moog Orbital Maneuvering Vehicle (OMV) Family
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Secondary Adapter
Spacecraft Structure Spacecraft
Tug
The OMV family of applications requires the use of scalable subsystem capability
Not mutually exclusive
• The OMV gives the capability (even with a rideshare launch) to put small satellites in their optimal obit to maximize their value rather than in 'opportunity' orbits
• An OMV can facilitate and/or directly support a small satellite mission as part
of the platform
• Mission/spacecraft design can be
streamlined through the elimination/simplification of on-board propulsion
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OMV: Taking Advantage of Moog Vertical Integration
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Moog prefers to work closely with customers from the mission concept phase to co-develop the optimal OMV configuration and can work at any level from component supplier to system integrator
• Core structure – Moog ESPA • Moog Integrated Avionics Unit (IAU)
– Flight computer – Command and Data Handling (C&DH) – Power conditioning and switching – Precision Orbit Determination (POD)
• Chemical propulsion systems • Flight software • ACS actuators and sensors • Solar array / antenna pointing • EGSE & mission simulation software
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OMV Subsystem Overview • Over the past 4 months Moog has progressed
the OMV design using internal resources while taking into account a wide range of potential requirements and customers – Established a high fidelity baseline architecture
that is both modular and scalable – Developed detailed CONOPs: short duration
upper stage mission scenario – ADCS analyses, including sensor/actuator
selection and thruster sizing – Power trades and analyses; Battery-only
configuration vs. solar array powered system – Detailed propulsion system layout and
component trades – Analysis of composite structures
• Internal Design Review Completed: 10Dec2015 • Notional flight readiness: Q3 2018
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OMV Structure: ESPA Ring • Multi-payload adapter for a large primary spacecraft
and six auxiliary spacecraft (up to 180 kg/400 lb) – 24-inch port enables 320 kg/700lb (ESPA “Grande”)
• Multiple ring heights and increased carrying capability are also options for alternate launch configurations
• Multiple mounting options – Standard or custom ESPA ports – External brackets – Internal mounting features – Multiple deployment devices per port
• Heritage: – STP-1 (2007) – NASA’s LRO/LCROSS (2009) – ORBCOMM OG2 Mission 1 Constellation (2014) – AFSPC-4 (2014) – OG2 Mission 2 – Launched Dec. 21, 2015
• Upcoming missions: – Spaceflight SHERPA, AFRL’s DSX, U.S. Air Force’s EAGLE, AFSPC-6
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The OG2 Constellation of eight spacecraft utilized two stacked ESPA rings with SoftRide vibration
isolation on a SpaceX Falcon 9 (By permission from Sierra Nevada Corporation and ORBCOMM)
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GNC & Power Subsystems • Moog’s attitude control simulations
influenced the thruster placement and confirmed thruster sizing
• Detailed CONOPs and power modeling over the mission duration influence the battery-only vs. solar array + battery trade space
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100.00
150.00
200.00
250.00
300.00
0 4000 8000 12000 16000
OAPPo
werDem
and[W
]
MissionTimeline[s]
OMVMission-PowerTimeHistory
Heater Power Draw
Delta-V Th.
ACS Th.
6 x RCS Thrusters
4 x delta-V Thrusters Internal composite
structure4 x Tanks
Typical OMV Block Diagram
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Each OMV is specifically tailored for the mission requirements.
AJEET (BRE440)
AJEET Daughter Board
SACISolar Array and Charge
InterfacePAPI-1
Propulsion and Switching
PAPI-2Propulsion and Switching
Solar Array
Heaters MLIThermistors
ReceiverTransmitter
STRUCTURE
Propulsion Platform Structure
ESPA Ring
PAYLOADS
COMMUNICATIONS COMMAND & DATA HANDLING
ELECTRICAL POWER SYSTEM
Integrated Avionics Unit
THERMAL
Patch
SEPIA Module
Battery
ESPA-Class Auxiliary Payloads
2 x Startrackers
2 x NAV440 (3-axis IMU + GPS)
GUIDANCE, NAVIGATION &
CONTROL
Wheels, Torque Rods, Sun Sensors
Patch
Payload Deployment Sequencer
Low gain Antenna
Separation Ring
Customer Furnished Equipment
Baseline Components
He Pressurant
Fuel Tanks
RCS Thrusters
Delta-V Thrusters
PROPULSION
Tailored Solution
Example Rideshare Configurations
• Primary Spacecraft + OMV to GTO – Throw mass more likely to constrain auxiliary
payloads than volume – Launch to GTO could offer a staging orbit for an
OMV’s interplanetary or lunar trajectory
• Multiple OMVs to LEO – Three Example OMVs:
• Lunar Tug • Smallsat Constellation • Passive ESPA Ring
– Total Mass: 3,264 kg
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Lunar CubeSat Tug
Smallsat ConstellationPassive ESPA Ring
Accelerated LEO Constellation Deployment
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12 S/C Constellation Deployment using 2 OMVs
Deployments & Maneuvers OMV Delta-V
OMV Fuel Required
Deploy S/C 1 & 2 (S/C boost to 800 km) 0 m/s 0 kg
Deploy S/C 3 & 4 0 m/s 0 kgDecrease OMV Inclination to 67 deg. 664 m/s 224.7 kgIncrease Inclination to 72 deg. 664 m/s 171.35 kgDeploy S/C 5 & 6 (S/C boost to 800 km) 0 m/s 0 kg
S/C 3 & 4 boost to 800 km 0 m/s 0 kg
TOTAL 1328 m/s 396 kg
• An OMV can be utilized to dramatically speed up the dispersion of a smallsat constellation in LEO – Strategically changing the altitude and inclination with respect to
the final orbit allows the OMV to drop satellites off at the desired LTAN in pairs
– A single propulsion system on the OMV replaces and/or simplifies the propulsion system requirements for the small satellites
Earth Observation CubeSat Constellation • Baseline parameters:
– OMV delivers 48 CubeSats to two orbits from a single secondary launch • Deploy 24 CubeSats per orbit, dropped at 90° intervals around each orbital plane
• OMV Configuration: – 3 standardized deployment devices (16 CubeSats each)
• FANTM-RiDE concept in conjunction TriSept Corporation – HPGP Blowdown System
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• CONOPS – OMV drops-off 24 CubeSats in initial
orbit ! Multiple drop-offs around plane – OMV makes a 1° inclination change
and 100 km altitude change to increase precession rate wrt to initial plane
– OMV returns to initial inclination and altitude after RAAN precesses 15° ! Multiple drop-offs to release remaining 24 CubeSats around plane
– Total Time: 97 days
Hosted Payload to Earth/Sun L1
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Deployments & Maneuvers OMV Delta-V
OMV Fuel Required
Perigee Raising Maneuver 1 250 91.75 kg Perigee Raising Maneuver 2 250 82.3 kg L1 Transfer Orbit Injection Maneuver 250 73.9 kg
Trajectory Correction Maneuver 10 2.8 kg
L1 Halo Orbit Insertion 50 13.8 kg
Station keeping (15m/s per year) 75 20.1 kg TOTAL 885 m/s 284.6 kg
Margin 8.5% on delta-V (Total capability = 987 m/s)
Secondary Payload to Earth/Sun L1 & 5 year Hosted Payload at L1
• An ESPA ring is the basis for a low-cost rideshare mission to GTO, and then on to the Earth-Sun L1 point
• The standard ports allow hosted payloads or rideshare passengers to deploy in GTO or at L1
• The avionics, communications and propulsion system are spec’d for a 5-year mission to support the science payloads
Hosted Payload to Earth/Sun L1: Video
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Ferry to Low Lunar Orbit for Small Payload
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• Shared Launch Configuration – OMV Dropped in GTO with Small Sat (or CubeSat) Payloads – Translunar Orbit Injection = Three Maneuvers + Lunar Capture
• Options utilizing weak stability boundary orbits are also under consideration depending on mission time constraints & excess launch vehicle capacity
Example secondary launch configuration Reference: Biesbroek, R. and Janin, G. “Ways to the Moon.” ESA Bulletin 103, August 2000.
Deployments & Maneuvers OMV Delta-V
OMV Fuel Required
Duration after
LaunchOMV dropped in GTO 0 m/s 0 kgTranslunar Orbit Injection (1) 240 m/s 102.2 kg Day 1Translunar Orbit Injection (2) 240 m/s 92.7 kg Day 2Translunar Orbit Injection (3) 240 m/s 84.1 kg Day 4Mid-course Maneuver 50 m/s 16.5 kgLunar Capture (at 200 km) 810 m/s 225.3 kg Day 8
TOTAL 520.8 kg 8 days
• Mass Summary – Payload Mass: 100 kg – Platform Dry Mass: 471.9 kg – HPGP (LMP-103S) Propellant Mass: 446.4 kg – Wet Mass: 918.3 kg
Sun Synchronous Multi-Manifest/Multi-Stack
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• Assessed OMV design compatibility for a Multi-Manifest/Multi-Stack tug
• Deployment of a large number of payloads at various altitudes/inclinations in SSO
• OMV/ESPA capacity of 4500 kg payload – 15x300 kg payloads, each dedicated port – 30x150 kg payloads, using split port adapters
• Same Baseline OMV design can be used
2x Passive ESPAs
1x OMV
Conclusions • The OMV can offer small, rideshare payloads:
– Orbit Optimization – Accelerated Constellation Deployment – Non-standard Orbits
• An advantage of this propulsive ESPA concept is the vertical integration Moog can leverage. Sourcing components in-house creates a number of benefits, including: – Reduction in programmatic costs, lead time and risk – Heritage – Scalability for numerous applications
• The diverse and growing number of rideshare payloads can take advantage of a greater number of launch opportunities with the flexibility provided by an OMV
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