Payload User Guide - Astrobotic

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

11-19

PEREGRINE

PAYLOAD INTERFACES

29-33

21-27

MISSION ONE

M1 ENVIRONMENTS

43-45

3-9

GLOSSARY

1

35-41

2

ABOUT US 3

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.

4

ASTROBOTIC LUNAR SERVICES

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 POWER

2.8 kbps BANDWIDTH

Additional power can be purchased at $225,000 per W.

Additional bandwidth can be purchased at $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.

5

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

35 kg

175 kg

265 kg

588 kg

588 kg

LEO

LEO

LEO

TLI

TLI

Secondary Payload

Secondary Payload

Secondary Payload

Primary Payload

Primary Payload

NUMBER OF LANDERS

NOMINAL MISSION CAPACITY

LAUNCH ORBIT

LAUNCH CONFIG

Following M1, Astrobotic anticipates a flight rate of at least one mission every two years.

6

PEREGRINE PARTNERS

LUNAR CATALYST PROGRAM PARTNER

OFFICIAL LOGISTICS PROVIDER TO THE MOON

TECHNICAL DESIGN PARTNER

PROPELLANT TANK PROVIDER

7

PAYLOAD EXPERIENCE

SERVICES AGREEMENT TECHNICAL SUPPORT

1 2 Following contract signature, an Interface Control Document is developed and agreed to by Astrobotic and the payload customer.

Astrobotic supports the payload customer by participating in 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. Astrobotic accepts the payload and integrates it onto Peregrine.

The integrated Peregrine Lunar Lander is launched and commences its mission. The Astrobotic Mission Control Center connects the customer to their payload.

8

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 Astrobotic mission engineers

exchanges

with

Access to library of Astrobotic payload design references and standards

Technical feedback through payload milestone design reviews

Facilitation of lander-payload compatibility testing

9

interface

10

PEREGRINE 11

PEREGRINE LUNAR LANDER

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.

12

LANDER SYSTEMS

Avionics Four Decks

Solar Panel Four Tanks Four Legs

Attitude Thrusters

Five Main Engines

Landing Sensor

Launch Vehicle Adapter

13

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 Peregrine Lunar Lander

The use of a release mechanism to deploy a payload from the lander is possible in lunar orbit or 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

14

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

trajectory

correction,

insertion,

and

injection, lunar

powered

orbit

descent.

Twelve thrusters, with 20 N thrust each, make up the Attitude Control System (ACS) to maintain

spacecraft

orientation

throughout

the

mission. The system uses a MMH/MON-25 fuel and

Image courtesy of Aerojet Rocketdyne

oxidizer combination.

Main Engine Thrust:

440 N

ACS Engine Thrust:

20 N

Fuel & Oxidizer:

MMH & MON-25

15

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 solar cell assembly

engine burns and attitude maneuvers. The

solar panel array provides battery charge and 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

16

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 to

the

propulsion

control

units.

Additionally,

it

cooperates with the payload controller to ensure safe operation of the payloads throughout the mission.

Payload CPU Design:

Astrobotic designed and developed flight computer prototype board

32-bit RISC

Programmable Payload IO Channels:

Payload CPU Clock Speed:

64

330 MHz

17

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 flightqualified

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

c o v e r ag e

around

lander-to-payload

SSC ground antenna

provided

via

maintains

Serial

100%

Earth. connection

RS-422

within

The is the

electrical connector for wired communication 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

18

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

t o w a r ds

Earth-based

the

ranging

Sun. 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 safe landing. Peregrine’s flight software is built on NASA’s core flight software and tested in the NASA

Astrobotic-built landing sensor prototype

TRICK/JEOD simulation suite.

Descent Orbit:

15 km

Powered Descent Duration:

600 s

Maximum Landing Velocity:

2.5 m/s

19

20

PAYLOAD INTERFACES 21

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.

22

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.

23

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.

24

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.

25

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 bandwidth

nominal

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.

26

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 Payload

Deployed Payload

PMCCs X-Band Downlink AMCC

Ethernet

S-Band Uplink

SSC

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.

27

28

MISSION ONE 29

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.

30

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

31

ORBIT & DESCENT

DESCENT IS INITIATED by an orbit-lowering main engine burn.

UNPOWERED DESCENT

POWERED DESCENT BRAKING

APPROACH

TERMINAL

DESCENT

Peregrine descends vertically at constant velocity. Peregrine coasts after an orbitlowering maneuver, using only attitude thrusters to maintain orientation.

100 km to 15 km

Powered descent commences and main engines are pulsed continuously to slow down Peregrine.

The altimeter and star tracker inform targeted guidance activity to the landing site.

15 km to 1 km

1 km to 100 m

32

100 m to Touchdown

SURFACE OPERATIONS

1 SYSTEM CHECK

2 Following a successful touchdown, the Peregrine Lunar Lander transitions to surface operational mode. The craft establishes communication with Earth and performs a system check. Excess propellant is vented as a precaution.

PAYLOAD CHECK

Peregrine provides payloads with power and communication. Software/firmware updates and diagnostic system checks may be performed by the payload.

3 MISSION SUPPORT

4 Payload egress procedures are facilitated by the lander at this time. Peregrine will provide power and communication to payloads for at least 8 Earth days of lunar surface operations.

LUNAR NIGHT

Peregrine discontinues all payload services and transitions to hibernation mode at the onset of lunar night.

33

34

M1 ENVIRONMENTS 35

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.

36

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.

37

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.

The maximum shock levels for the clamp band release, not accounting for variation during flight, can be seen to the right.

38

FREQUENCY (Hz)

SRS (g)

100

100

1,400

2,800

10,000

2,800

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.

39

PRESSURE & HUMIDITY

PRESSURE

The Peregrine Lunar Lander will encounter the following approximate pressure environments during Mission One:

101.3 kPa

Terrestrial: Average atmospheric pressure at sea level

Launch:

–2.5 kPa/s Expected pressure drop during launch

6.7×10-5 kPa

Remaining Mission:

HUMIDITY

The Peregrine Lunar Lander will encounter the following approximate humidity environments during Mission One:

Terrestrial:

35% to 90%

Remaining Mission:

0%

40

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.

41

42

GLOSSARY 43

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 V (dc)

second [time] Volt (direct current) [voltage]

W

Watt [power]

Wh

Watt-hour [energy]

44

GLOSSARY OF TERMS

Term AMCC

Significance 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 MON-25

MonoMethylHydrazine 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 TLI UDP

Transmission Control Protocol / Internet Protocol TransLunar Injection User Datagram Protocol

45