PEREGRINE LUNAR LANDER PAYLOAD USER’S GUIDE
Version 2.1 May 2017
2515 Liberty Avenue
Pittsburgh, PA 15222
Phone | 412.682.3282
www.astrobotic.com [email protected]
TABLE OF CONTENTS
ABOUT US 3-9
11-19 PEREGRINE
PAYLOAD INTERFACES 21-27
29-33 MISSION ONE
M1 ENVIRONMENTS 35-41
43-45 GLOSSARY
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ABOUT US
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ASTROBOTIC MISSION
INTERNATIONAL PAYLOAD DELIVERY Astrobotic provides an end-to-end delivery service for payloads to the Moon.
On each delivery mission to the Moon, payloads are integrated onto a single Peregrine Lunar Lander and then launched on a commercially procured launch vehicle.
The lander safely delivers payloads to lunar orbit and the lunar surface.
Upon landing, Peregrine transitions to a local utility supporting payload operations with power and communication.
Astrobotic provides comprehensive support to the payload customer from contract signature to end of mission. The Payload Care Program equips the payload customer with the latest information on the mission and facilitates technical exchanges with Astrobotic engineers to ensure payload compatibility with the Peregrine Lunar Lander and overall mission success.
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ASTROBOTIC LUNAR SER VICES
COMPANIES, GOVERNMENTS, UNIVERSITIES, NON-PROFITS, AND INDIVIDUALS can send payloads to the Moon at an industry defining price of $1.2M per kilogram of payload.
Standard payload delivery options include deployment in lunar orbit prior to descent as well as to the lunar surface where payloads may remain attached to the lander, deploy from the lander for an independent mission, or hitch a ride on an Astrobotic-provided lunar rover.
LUNAR ORBIT OR LUNAR SURFACE $1,200,000 / kg DELIVERY ON ROVER $2,000,000 / kg
For every kilogram of payload, Peregrine provides:
0.5 Watt 2.8 kbps POWER BANDWIDTH
Additional power Additional bandwidth can be purchased at can be purchased at $225,000 per W. $30,000 per kbps.
NOTE: Payloads less than 1 kg may be subject to integration fees.
NOTE: Can’t afford a payload? Check out our MoonBox service on Astrobotic’s website. Prices start at $460.
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PEREGRINE MISSIONS
PEREGRINE IS A LUNAR LANDER PRODUCT LINE that will deliver payloads for Astrobotic’s first five missions.
MISSION M1 M2 M3 M4 M5
NUMBER OF LANDERS
NOMINAL MISSION 35 kg 175 kg 265 kg 588 kg 588 kg CAPACITY
LAUNCH LEO LEO LEO TLI TLI ORBIT
LAUNCH Secondary Secondary Secondary Primary Primary CONFIG Payload Payload Payload Payload Payload
Following M1, Astrobotic anticipates a flight rate of at least one mission every two years.
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PEREGRINE PARTNERS
LUNAR CATALYST PROGRAM PARTNER
OFFICIAL LOGISTICS PROVIDER TO THE MOON
TECHNICAL DESIGN PARTNER
PROPELLANT TANK PROVIDER
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PAYLOAD EXPERIENCE
SERVICES AGREEMENT
TECHNICAL SUPPORT
1 2
Following contract signature, an Interface Control Document is developed and agreed to by Astrobotic supports the payload Astrobotic and the payload customer by participating in customer. payload design cycle reviews and facilitating payload testing with simulated spacecraft interfaces.
INTEGRATION
MISSION
3 4
The payload is sent to Astrobotic using DHL Logistics. The integrated Peregrine Lunar Astrobotic accepts the payload Lander is launched and and integrates it onto Peregrine. commences its mission. The Astrobotic Mission Control Center connects the customer to their payload.
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PAYLOAD CARE PROGRAM
ASTROBOTIC IS HERE TO SUPPORT THE SUCCESS OF YOUR PAYLOAD MISSION.
Astrobotic provides a Payload Care Program to guide the customer through contract to a smooth integration of the payload with the Peregrine Lunar Lander. The following services are included within the program:
Availability for general and technical inquiries
Quarterly presentation of Astrobotic business and mission updates
Optional monthly technical exchanges with Astrobotic mission engineers
Access to library of Astrobotic payload design references and standards
Technical feedback through payload milestone design reviews
Facilitation of lander-payload interface compatibility testing
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PEREGRINE
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PEREGRINE LUNAR LAND ER
ONE LANDER — ANY MISSION
The Peregrine Lunar Lander precisely and safely delivers payloads to lunar orbit and the lunar surface on every mission.
Peregrine’s flexible payload mounting accommodates a variety of payload types for science, exploration, marketing, resources, and commemoration.
Following landing, Peregrine provides payloads with power as well as communication to and from Earth.
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LANDER SYSTEMS
Avionics Four Decks
Solar Panel Four Tanks
Four Legs
Attitude Thrusters Five Main Engines
Landing Launch Sensor Vehicle Adapter
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STRUCTURE
THE PEREGRINE LUNAR LANDER’S STRUCTURE is stout, stiff, and simple for survivability during launch and landing. A releasable clamp band mates Peregrine to the launch vehicle and allows for separation prior to cruise to the Moon. Four landing legs are designed to absorb shock and stabilize the craft on touchdown. The lander features four light and sturdy aluminum decks for payload as well as avionics and electronics mounting. Payloads can attach to the topside or underside of the deck panel. The The use of a release mechanism to deploy a Peregrine payload from the lander is possible in lunar orbit or Lunar Lander on the lunar surface. The entire structure is scalable to accommodate various payload capacities up to 265 kg.
M1 Lander Dimensions: 2.5 m Diameter, 1.8 m Height
M1 Payload Capacity: 35 kg
M1 Dry Mass: 284.5 kg
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PROPULSION
THE PEREGRINE LUNAR LANDER uses a propulsion system featuring next generation space engine technology to power payloads to the Moon.
Five engines, with 440 N thrust each, serve as the spacecraft’s main engines for all major maneuvers including trans-lunar injection, trajectory correction, lunar orbit insertion, and powered descent.
Twelve thrusters, with 20 N thrust each, make up the Attitude Control System (ACS) to Image courtesy of maintain spacecraft orientation throughout the Aerojet mission. The system uses a MMH/MON-25 fuel and Rocketdyne oxidizer combination.
Main Engine Thrust: 440 N
ACS Engine Thrust: 20 N
Fuel & Oxidizer: MMH & MON-25
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POWER
THE PEREGRINE LUNAR LANDER IS DESIGNED TO BE A POWER-POSITIVE SYSTEM, allowing it to generate more power than it consumes during nominal mission operations. The spacecraft draws power from the 29.6 V Range Safety certified lithium-ion battery using 18650 cell technology. This feeds into a 28 V power rail from which power is distributed to all subsystems by the lander. The battery is utilized during
UTJ engine burns and attitude maneuvers. The solar cell solar panel array provides battery charge and assembly maintains surface operations. The GaInP/GaAs/Ge triple junction material has heritage in orbital and deep space missions.
M1 Battery Capacity: 840 Wh
M1 Solar Panel Power: 480 W
M1 Solar Panel Size: 1.8 m2
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AVIONICS
PEREGRINE’S FLIGHT COMPUTER consists of a high performance safety microcontroller with dual CPUs running in Lockstep for error and fault checking. A rad-hard watchdog timer serves as an additional fault check and error prevention. The computer has been tested in radiation, temperature, shock, and vacuum conditions to ensure the functionality remains nominal for the longest projected mission timeline. The primary flight computer performs all command and data handling of the spacecraft. It gathers input from the GNC flight sensors and issues corresponding commands Astrobotic to the propulsion control units. Additionally, it designed and cooperates with the payload controller to ensure safe developed operation of the payloads throughout the mission. flight computer prototype board
Payload CPU Design: 32-bit RISC
Programmable Payload IO Channels: 64
Payload CPU Clock Speed: 330 MHz
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COMMUNICATION
PEREGRINE SERVES AS THE PRIMARY COMMUNICATIONS NODE relaying data between the payload customer and their payloads on the Moon. The lander-to-Earth connection is provided by a high-powered and flight- qualified transponder employing X-Band downlink and S-Band uplink satellite communications connecting the payload customer with Peregrine. The selection of several Swedish Space Corporation (SSC) ground stations maintains 100% coverage around Earth. The lander-to-payload connection is SSC provided via Serial RS-422 within the ground electrical connector for wired communication antenna throughout the mission timeline. During surface operations, a 2.4 GHz IEEE 802.11n compliant Wi-Fi modem enables wireless communication between the lander and deployed payloads.
Wired Protocol: Serial RS-422
Wireless Protocol: 802.11n Wi-Fi
Wireless Frequency: 2.4 GHz
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GUIDANCE, NAVIGATION, & CONTROL
PEREGRINE’S GNC SYSTEM orients the spacecraft throughout the mission to facilitate operations. Input from the star tracker, sun sensors, and rate gyros aid the Attitude Determination and Control System (ADCS) in maintaining cruise operations with the solar array pointed towards the Sun. Earth-based ranging informs position and velocity state estimates for orbital and trajectory correction maneuvers. During powered descent and landing, a radar altimeter provides velocity information that guides the spacecraft to a Astrobotic-built safe landing. Peregrine’s flight software is built on landing sensor NASA’s core flight software and tested in the NASA prototype TRICK/JEOD simulation suite.
Descent Orbit: 15 km
Powered Descent Duration: 600 s
Maximum Landing Velocity: 2.5 m/s
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PAYLOAD INTERFACES
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MECHANICAL INTERFACE
PEREGRINE ACCOMMODATES A WIDE RANGE OF PAYLOAD TYPES INCLUDING LUNAR SATELLITES, ROVERS, INSTRUMENTS, AND ARTIFACTS.
Mounting locations are available above and below the aluminum lander decks. Alternate mounting locations are available as a non-standard service.
ABOVE DECK BELOW DECK
THERMAL INTERFACE
Payloads provide a thermally isolating adapter plate to the payload mounting deck. This allows the payload to effectively manage its own thermal environment through passive methods such as radiators or coatings. Peregrine will provide power throughout the mission to attached payloads, which may be utilized for internal heaters.
For availability of standard payload package sizes or the accommodation of specific payload geometries, please contact Astrobotic.
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RELEASE MECHANISM
PAYLOADS MAY DEPLOY FROM THE PEREGRINE LUNAR LANDER IN LUNAR ORBIT OR ON THE LUNAR SURFACE.
Deployable payloads are encouraged to use a Hold Down and Release Mechanism (HDRM). The selected device may not:
Be pyrotechnic,
Create excessive debris, or
Impart shocks greater than 30 g’s on the lander.
Peregrine provides power and power signal services to the electrical connector. The payload customer is responsible for integrating the release mechanism into their payload design and interfacing it correctly with these provided services.
A sample egress procedure for a deployable payload on the lunar surface is outlined below:
The payload charges its batteries with power provided by Peregrine. The payload customer performs any necessary system diagnostic checks and firmware or software updates for the payload.
The payload transitions to mission mode and powers up its onboard radios. A diagnostic check is performed by the payload customer to verify internal power sources and wireless communication.
Upon request of the payload customer, Astrobotic commands Peregrine to send a release signal to the payload. Confirmation of signal transmission to the electrical connector is provided by Astrobotic. Peregrine-provided power and wired communication are discontinued to the electrical connector.
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ELECTRICAL INTERFACE
PEREGRINE PROVIDES POWER AND BANDWIDTH SERVICES VIA A SINGLE ELECTRICAL CONNECTOR.
Static payloads employ a straight plug screw type connector.
Deployable payloads employ a zero separation force connector.
Both connector types will provide the same standard pin configuration:
Power Return
Power
Power Signal
Data
Not Connected
Additional points of contact, of the payload structural and conductive elements as well as the payload’s electrical circuit common ground, are required for effective grounding to the spacecraft chassis.
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POWER INTERFACE
THE PEREGRINE LUNAR LANDER SUPPORTS PAYLOAD OPERATIONS WITH POWER SERVICES.
Peregrine provides nominal power services throughout the cruise to the Moon and on the lunar surface.
Power services are only available via the electrical connector while the payload is attached to the lander. Deployable payloads will take full control of their own power consumption and generation after release from the lander.
The Peregrine Lunar Lander maintains control of all power lines to ultimately ensure spacecraft and mission safety. The main features of the power interface are:
0.5 W per kilogram of payload nominal power
Regulated and switched 28 ± 0.5 Vdc power line
60 second 30 W peak power signal for release mechanism actuation
For additional power needs, please contact Astrobotic.
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DATA INTERFACE
THE PEREGRINE LUNAR LANDER SUPPORTS PAYLOAD OPERATIONS WITH BANDWIDTH SERVICES.
Peregrine provides nominal bandwidth services on the lunar surface. Limited bandwidth services for “heartbeat” data will be available throughout the cruise to the Moon.
Wired bandwidth services are only available via the electrical connector while the payload is attached to the lander. Wireless bandwidth services will only be provided on the lunar surface.
The Peregrine Lunar Lander employs quality of service techniques to ensure bandwidth is maintained. Various flight-proven methods to facilitate safe and reliable transmission of payload data are implemented. The main features of the data interface are:
2.8 kbps per kilogram of payload nominal bandwidth
TCP/IP and UDP protocols supported
Serial RS-422 wired bandwidth
2.4 GHz 802.11n Wi-Fi radio wireless bandwidth
For additional bandwidth needs, please contact Astrobotic.
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COMMUNICATION CHAIN
ASTROBOTIC FACILITATES TRANSPARENT COMMUNICATION BETWEEN THE CUSTOMER AND THEIR PAYLOAD.
Communication between the customer and their payload will nominally take 5 seconds and no more than 17 seconds one way.
Peregrine Wi-Fi RS-422 Attached Deployed Payload Payload
PMCCs X-Band Downlink AMCC S-Band Uplink
SSC Ethernet
The Astrobotic Mission Control Center (AMCC) forwards customer commands and payload data between the individual Payload Mission Control Centers (PMCCs) and SSC. In addition, Astrobotic will provide the payload customer with general spacecraft telemetry and health information.
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MISSION ONE
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MISSION ONE
FOR MISSION ONE, Peregrine will launch as a secondary payload on a commercial launch vehicle. This enables a low-cost first mission carrying 35 kg of payload.
Target Launch Orbit: LEO
Target Lunar Orbit: Stable Elliptical Orbit
Target Landing Site: Lacus Mortis, 45°N 25°E
Lacus Mortis is a basaltic plain in the northeastern region of the Moon. A plateau there serves as the target landing site.
Local Landing Time: 55-110 Hours After Sunrise
A Lunar day, from sunrise to sunset on the Moon, is equivalent to 354 Earth hours or approximately 14 Earth days.
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M1 TRAJECTORY
LEO
LOI TLI
Cruise
Descent
Launch to LEO
Separation from launch vehicle
Earth orbit hold between 6 and 33 days
TLI maneuver
5-day cruise to the Moon
LOI into stable elliptical orbit
Lunar orbit hold up to 10 days
Autonomous powered descent
Landing at Lacus Mortis
8 Earth days nominal surface operations
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ORBIT & DESCENT
DESCENT IS INITIATED by an orbit-lowering main engine burn.
UNPOWERED POWERED DESCENT DESCENT BRAKING APPROACH TERMINAL DESCENT
Peregrine descends vertically at constant velocity.
Peregrine coasts after an orbit- lowering Powered descent maneuver, using commences and only attitude main engines are thrusters to pulsed The altimeter and maintain continuously to star tracker inform orientation. slow down targeted guidance Peregrine. activity to the landing site.
100 km 15 km 1 km 100 m to to to to 15 km 1 km 100 m Touchdown
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SURFACE OPERATIONS
1
SYSTEM CHECK 2 Following a successful touchdown, the Peregrine Lunar PAYLOAD CHECK Lander transitions to surface operational mode. The craft establishes communication with Peregrine provides payloads Earth and performs a system with power and communication. check. Excess propellant is Software/firmware updates and vented as a precaution. diagnostic system checks may be performed by the payload.
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MISSION SUPPORT 4 Payload egress procedures are facilitated by the lander at this LUNAR NIGHT time. Peregrine will provide power and communication to payloads for at least 8 Earth Peregrine discontinues all days of lunar surface payload services and transitions operations. to hibernation mode at the onset of lunar night.
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M1 ENVIRONMENTS
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LAUNCH LOADS
The Peregrine Lunar Lander will encounter the greatest load environments during launch. The maximum range of axial and lateral accelerations experienced by the lander during launch are below:
A positive axial value indicates a compressive net-center of gravity acceleration whereas a negative value indicates tension.
The corresponding load environments of the payloads will depend on mounting location and are a function of the structural dynamic properties of both the lander and the payload. A coupled loads analysis determines the effect of launch loads at the payload interface. Please contact Astrobotic for further details and special payload mounting requirements.
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VIBRATIONAL
The Peregrine Lunar Lander will encounter the following maximum predicted axial and lateral sine environments during launch:
Astrobotic develops a mission specific vibration spectrum based on a coupled loads analysis using the input response from the launch provider. Astrobotic is able to generate qualification and acceptance curves. After contract, Astrobotic works with each customer to develop a payload specific sine vibration curve, which can be used for system testing prior to payload integration.
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ACOUSTIC & SHOCK
ACOUSTIC
The Peregrine Lunar Lander will encounter varying acoustic environments during Mission One. The maximum predicted acoustic environment is below:
The highest levels occur at lift-off and during transonic flight as the launch vehicle transitions to speeds greater than the speed of sound.
SHOCK
The Peregrine Lunar Lander will encounter shock events during launch and injection from the launch vehicle fairing release and separation from the launch vehicle.
FREQUENCY (Hz) SRS (g) The maximum shock levels for the clamp band release, not 100 100 accounting for variation during 1,400 2,800 flight, can be seen to the right. 10,000 2,800
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THERMAL
The Peregrine Lunar Lander will encounter the following approximate thermal environments during Mission One:
Terrestrial: 0°C to 35°C
Launch: 20°C to 80°C
Cruise: -60°C to 100°C
Descent: -120°C to 100°C
Lunar Surface: 25°C to 80°C
The large range of temperatures from cruise to the lunar surface reflect the warmth in direct sunlight and the cold in shadow. The corresponding thermal environments of the payloads will depend on mounting location and the amount of incident sunlight there throughout the mission. Please contact Astrobotic for further details and specific payload mounting requirements.
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PRESSURE & HUMIDITY
PRESSURE
The Peregrine Lunar Lander will encounter the following approximate pressure environments during Mission One:
Terrestrial: 101.3 kPa
Average atmospheric pressure at sea level
Launch: –2.5 kPa/s
Expected pressure drop during launch
Remaining Mission: 6.7×10-5 kPa
HUMIDITY
The Peregrine Lunar Lander will encounter the following approximate humidity environments during Mission One:
Terrestrial: 35% to 90%
Remaining Mission: 0%
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RADIATION & EMI
RADIATION
The Peregrine Lunar Lander will encounter the following approximate ionizing radiation environments during Mission One:
Mission: 3.8 to 59 rads
Total expected dosage
Extraplanetary: 1.1 rad/day
Average dosage per additional Earth day on Lunar surface
The lander is designed to mitigate destructive events within electronics caused by nominal radiation for a period of eight months.
EMI
The Peregrine Lunar Lander will experience electromagnetic interference during Mission One.
The spacecraft and all payloads will be designed to comply with MIL-STD-461D for conducted emissions and to meet CE102 for frequencies between 10 kHz and 10 MHz.
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GLOSSARY
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GLOSSARY OF UNITS
Unit Significance
°C degree Celsius [temperature]
dB decibel [sound pressure level referenced to 20×10-6 Pa]
g Earth gravitational acceleration [9.81 m/s2]
Hz Hertz [frequency]
kbps kilobits per second [data rate]
kg kilogram [mass]
m meter [length]
N Newton [force]
Pa Pascal [pressure]
rad rad [absorbed radiation dose]
s second [time]
V (dc) Volt (direct current) [voltage]
W Watt [power]
Wh Watt-hour [energy]
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GLOSSARY OF TERMS
Term Significance
AMCC Astrobotic Mission Control Center
CPU Central Processing Unit
EMI ElectroMagnetic Interference
GNC Guidance, Navigation, and Control
IEEE Institute of Electrical and Electronics Engineers
LEO Low Earth Orbit
LOI Lunar Orbit Insertion
MMH MonoMethylHydrazine
MON-25 Mixed Oxides of Nitrogen - 25% nitric oxide
PMCC Payload Mission Control Center
RISC Reduced Instruction Set Computing
SPL Sound Pressure Level
SRS Shock Response Spectrum
TCP/IP Transmission Control Protocol / Internet Protocol
TLI TransLunar Injection
UDP User Datagram Protocol
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