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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.

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Page 1: Going Beyond Traditional Rideshare using an Orbital ...schd.ws/hosted_files/canadiansmallsatsymposium2016/7d/Chris Loghry...Going Beyond Traditional Rideshare using an Orbital Maneuvering

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.

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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

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Customer Focused Space Organization

3

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

Canadian SmallSat Symposium 2016

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Getting SmallSats into Orbit

4 Canadian SmallSat Symposium 2016

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)

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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

5

OMVLaunch Vehicle

Upper Stage

Satellite

Canadian SmallSat Symposium 2016

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Moog Orbital Maneuvering Vehicle (OMV) Family

6

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

Canadian SmallSat Symposium 2016

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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

Canadian SmallSat Symposium 2016

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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

8 Canadian SmallSat Symposium 2016

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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)

Canadian SmallSat Symposium 2016

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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

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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

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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

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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

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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

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Hosted Payload to Earth/Sun L1

15 Canadian SmallSat Symposium 2016

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

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Hosted Payload to Earth/Sun L1: Video

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Ferry to Low Lunar Orbit for Small Payload

17 Canadian SmallSat Symposium 2016

•  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

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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

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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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