PAYLOAD USER S GUIDE

Transcription

1 PEREGRINE LUNAR LANDER PAYLOAD USER S GUIDE Version 2.4 May 2018

2 2515 Liberty Avenue Pittsburgh, PA Phone

3 T A B L E O F C O N T E N T S ABOUT US PEREGRINE PAYLOAD INTERFACES MISSION ONE M1 ENVIRONMENTS GLOSSARY 1

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5 ABOUT US 3

6 W H A T W E D O 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

7 A S T R O B O T I C L U N A R S E R V I C E S 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 $300,000 / kg LUNAR SURFACE $1,200,000 / kg DELIVERY ON ROVER $2,000,000 / kg For every kilogram of payload, Peregrine provides: 0.5 Watt POWER Additional power can be purchased at $225,000 per W. 2.8 kbps BANDWIDTH 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

8 P A Y L O A D C A R E P R O G R A M 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 6

9 P A Y L O A D E X P E R I E N C E 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. 7

10 P E R E G R I N E M I S S I O N S 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 530 kg 530 kg CAPACITY LAUNCH ORBIT LEO LEO LEO TLI TLI LAUNCH CONFIG Secondary Payload Secondary Payload Secondary Payload Primary Payload Primary Payload Following M1, Astrobotic anticipates a flight rate of at least one mission every two years. 8

11 P E R E G R I N E P A R T N E R S LUNAR CATALYST PROGRAM PARTNER TECHNICAL DESIGN PARTNER LAUNCH PARTNER PREMIUM COMMUNICATIONS PARTNER SPONSORS OFFICIAL LOGISTICS PROVIDER TO THE MOON 9

12 P E R E G R I N E S U P P L I E R S HONEYWELL RADAR ALTIMETER ORBITAL ATK PROPELLANT TANKS SSC GROUND STATIONS AGI STK SOFTWARE ALTIUM ALTIUM SOFTWARE C&R TECHNOLOGY THERMAL DESKTOP SOFTWARE DASSAULT SYSTÈMES SOLIDWORKS SOFTWARE SIEMENS NX NASTRAN SOFTWARE 10

13 PEREGRINE 11

14 P E R E G R I N E L U N A R L A N D 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. 12

15 L A N D E R S Y S T E M S Four Decks Avionics Four Tanks Solar Panel Four Legs Attitude Thrusters Five Main Engines Landing Sensor Launch Vehicle Adapter 13

16 S T R U C T U R E The Peregrine Lunar Lander 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 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, 1.9 m Height M1 Payload Capacity: 35 kg M1 Dry Mass: 325 kg 14

17 P R O P U L S I O N THE PEREGRINE LUNAR LANDER uses a propulsion system featuring next generation space engine technology to power payloads to the Moon. Five engines, with 667 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 45 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 Model of one of five main engines oxidizer combination. Main Engine Thrust: 667 N ACS Engine Thrust: 45 N Fuel & Oxidizer: MMH & MON-25 15

18 P O W E R 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 stores energy on a flight h e r i tage 28 V l i thium - i on space-grade battery. This feeds into a 28 V power rail from which power is distributed to all subsystems by the lander. The battery is utilized during engine burns XTJ solar cell assembly 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: 540 W M1 Solar Panel Size: 1.9 m 2 16

19 A V I O N I C S PEREGRINE S FLIGHT COMPUTER consists of a 32-bit high-performance dual-core microprocessor with an advanced 7-stage pipeline, 1.4 DMIPS/ MHz, 1.8 CoreMark/MHz, and EDAC protection employing a Reed-Solomon memory interface. The processor is accompanied with high-speed external NOR-Flash and SRAM. The computer employs radiationhardened integrated circuits and fault-tolerant and SEU-proof characteristics. 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. Q7 board, housing the payload CPU Payload CPU Design: Xilinx Zync-7020 Payload CPU Clock Speed: 766 MHz Payload CPU Safety Features: EDAC, TMR, Watchdogs 17

20 C O M M U N I C A T I O N SSC ground antenna 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 maintains 100% coverage around Earth. The lander-to-payload connection is provided via Serial RS-422 within the electrical connector for wired communication throughout the mission timeline. During surface operations, a 2.4 GHz IEEE n compliant Wi-Fi modem enables wireless communication between the lander and deployed payloads. Wired Protocol: Serial RS-422 Wireless Protocol: n Wi-Fi Wireless Frequency: 2.4 GHz 18

21 G U I D A N C E, N A V I G A T I O N, & C O N T R O L 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 safe landing. Peregrine s flight software is built on NASA s core flight software and tested in the NASA TRICK/JEOD simulation suite. Honeywell radar altimeter array prototype Descent Orbit: 15 km Powered Descent Duration: 600 s Maximum Landing Velocity: 2.5 m/s 19

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23 PAYLOAD INTERFACES 21

24 M E C H A N I C A L I N T E R F A C E 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 To ensure safe and simple accommodation for every payload, Astrobotic provides the following features: Standard bolt pattern grid for simplified payload mounting Defined payload envelope for safe stowage during flight and sufficient ground clearance at landing Standard payload package sizing and placement guidelines For availability of standard payload package sizes or the accommodation of specific payload geometries, please contact Astrobotic. 22

25 P A Y L O A D M O U N T I N G P R O P E R T I E S T H E R M A L Payloads are thermally isolated from the spacecraft. This allows the payload to more effectively manage its own thermal environment using passive methods, such as radiators and coatings, or active methods, such as internal heaters. Peregrine provides power throughout the mission to attached payloads, which may be utilized for active thermal control. Astrobotic recommends the use of an adaptor plate to provide the required payload mounting properties such as thermal isolation and allow for a more independent development of the payload and mounting solution designs. G R O U N D I N G, B O N D I N G, A N D I S O L A T I O N The spacecraft will operate with one common ground. Payloads must conform to this approach by employing proper grounding, bonding, and isolation schemes within their own payload design and providing contact points for the payload structural and conductive elements as well as internal electrical circuit common ground which Astrobotic will connect to the spacecraft chassis for grounding. 23

26 R E L E A S E M E C H A N I S M PAYLOADS MAY DEPLOY FROM THE PEREGRINE LUNAR LANDER IN LUNAR ORBIT OR ON THE LUNAR SURFACE. Deployable payloads will require a release mechanism to detach from the lander. The payload customer may select the mechanism most suited to the payload design as Astrobotic does not mandate a specific model to be implemented; however, the selected device must: Be non-pyrotechnic, Create minimal debris, and Impart no shocks greater than 30 g s on the lander upon actuation. Deployable payloads are encouraged to use Hold Down and Release Mechanism (HDRM) style devices to satisfy these requirements. Peregrine provides power and power release signal services to the electrical connector. The payload customer is responsible for integrating the release mechanism into their payload design such that it correctly interfaces with these provided services and employs the appropriate safe, arm, and fire techniques to satisfy Range Safety requirements. Astrobotic provides guidance in navigating and designing to Range Safety requirements. 24

27 P A Y L O A D E G R E S S L U N A R O R B I T E G R E S S The orbit egress procedure is similar to the surface egress procedure (example provided below. It is important to note that following separation, orbit deployable payloads are responsible not only for providing independent power management but also independent communications to and from Earth. Several lunar orbits will be available for orbital payload deployment dependent on the specific mission trajectory. Some of these orbits may be less stable than others; please contact Astrobotic for specific orbital parameters and potential constraints for safe operations in unstable orbits. L U N A R S U R F A C E E G R E S S 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. 25

28 E L E C T R I C A L I N T E R F A C E 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 are available in a regular and small size, each with a standard pin configuration: Power Return Power Power Signal Data Not Connected Regular Size Small Size Access to premium laser communication services will require a supplementary optional high-speed data connector for static payloads. Deployable payloads will access premium laser communication services through the wireless interface. 26

29 P O W E R I N T E R F A C E 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. 27

30 D A T A I N T E R F A C E THE PEREGRINE LUNAR LANDER SUPPORTS PAYLOAD OPERATIONS WITH BANDWIDTH SERVICES. Peregrine provides nominal bandwidth services on the lunar surface as well as offering access to high-speed data premium communication services. 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 Serial RS-422 wired communication using HDLC Ethernet high-speed data wired communication using TCP/IP 2.4 GHz n Wi-Fi radio wireless communication using TCP/IP For additional bandwidth needs, please contact Astrobotic. 28

31 C O M M U N I C A T I O N C H A I N ASTROBOTIC FACILITATES TRANSPARENT COMMUNICATION BETWEEN THE CUSTOMER AND THEIR PAYLOAD. 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. Communication between the customer and their payload will nominally take approximately 3 seconds one-way. Attached Payload Peregrine RS-422 Wi-Fi Deployed Payload PMCCs AMCC S-Band Uplink X-Band Downlink Ethernet SSC Premium laser communication services will be directed through an alternate communication chain utilizing the Atlas Space Operations laser communications terminal on board the Peregrine Lunar Lander and ground stations on Earth. 29

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33 MISSION ONE 31

34 M I S S I O N O N E FOR MISSION ONE, Peregrine will launch as a secondary payload on a ULA Atlas V launch vehicle. This enables a low-cost first mission carrying 35 kg of payload. Target Launch Orbit: LEO Target Lunar Orbit: Inclination LOI 1 LOI 2 LOI km 8700 km 100 km 800 km 100 km 100 km Lunar Ecliptic Inclination reference frame 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: Hours After Sunrise A Lunar day, from sunrise to sunset on the Moon, is equivalent to 354 Earth hours or approximately 14 Earth days. 32

35 M 1 T R A J E C T O R Y LEO LOI TLI Cruise Descent Launch to LEO Separation from launch vehicle Earth orbit hold TLI maneuver Cruise to the Moon LOI into stable elliptical orbit Lunar orbit hold Autonomous powered descent Landing at Lacus Mortis 8 Earth days nominal surface operations 33

36 O R B I T & D E S C E N T DESCENT IS INITIATED by an orbit-lowering main engine burn. UNPOWERED POWERED TERMINAL TERMINAL DESCENT DESCENT DESCENT DESCENT NADIR Peregrine descends vertically and decelerates to constant velocity at 30 m altitude. Peregrine coasts after an orbit-lowering maneuver, using only attitude thrusters to maintain orientation. 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. 100 km to 15 km 15 km to 2 km 2 km to 300 m 300 m to Touchdown 34

37 S U R F A C E O P E R A T I O N S 1 SYSTEM CHECK 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. 2 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 Payload egress procedures are facilitated by the lander at this time. Peregrine will provide power and communication to payloads for approximately 8 Earth days of lunar surface operations. 4 LUNAR NIGHT Peregrine discontinues all payload services and transitions to hibernation mode before the onset of lunar night. 35

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39 M1 ENVIRONMENTS 37

40 L A U N C H L O A D S 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. 38

41 V I B R A T I O N A L 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. 39

42 A C O U S T I C & S H O C K A C O U S T I C 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. S H O C K 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. FREQUENCY (Hz) SRS (g) ,400 2,800 10,000 2,800 40

43 T H E R M A L The Peregrine Lunar Lander will encounter the following approximate thermal environments during Mission One: Terrestrial: 0 C to 27 C Launch: 0 C to 27 C Cruise: -60 C to 100 C Descent: -120 C to 100 C Lunar Surface: -30 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. 41

44 P R E S S U R E & H U M I D I T Y P R E S S U R E The Peregrine Lunar Lander will encounter the following approximate pressure environments during Mission One: Terrestrial: kpa Average atmospheric pressure at sea level Launch: 2.5 kpa/s Expected pressure drop during launch Remaining Mission: kpa H U M I D I T Y The Peregrine Lunar Lander will encounter the following approximate humidity environments during Mission One: Terrestrial: 35% to 90% Remaining Mission: 0% 42

45 R A D I A T I O N & E M I R A D I A T I O N The Peregrine Lunar Lander will encounter the following approximate ionizing radiation environments during Mission One: Near-Earth: 17 rads/ day Expected ionizing dosage per Earth day in near-earth environment Interplanetary: 1 rad/day Expected ionizing dosage per Earth day in interplanetary environment The total ionizing dosage for M1 is not expected to exceed 1 krad. 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. 43

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47 GLOSSARY 45

48 G L O S S A R Y O F U N I T S Unit Significance C degree Celsius [temperature] db DMIPS decibel [sound pressure level referenced to Pa] Dhrystone million instructions per second [computer performance] g Earth gravitational acceleration [9.81 m/s 2 ] Hz kbps kg m N Pa rad s V (dc) W Wh Hertz [frequency] kilobits per second [data rate] kilogram [mass] meter [length] Newton [force] Pascal [pressure] rad [absorbed radiation dose] second [time] Volt (direct current) [voltage] Watt [power] Watt-hour [energy] 46

49 G L O S S A R Y O F T E R M S Term AMCC CPU EDAC EMI GNC HDLC IEEE LEO LOI M1 MMH MON-25 PMCC SPL SRS TCP/IP TLI TMR Significance Astrobotic Mission Control Center Central Processing Unit Error Detection And Correction ElectroMagnetic Interference Guidance, Navigation, and Control High-level Data Link Control Institute of Electrical and Electronics Engineers Low Earth Orbit Lunar Orbit Insertion Mission One MonoMethylHydrazine Mixed Oxides of Nitrogen - 25% nitric oxide Payload Mission Control Center Sound Pressure Level Shock Response Spectrum Transmission Control Protocol / Internet Protocol Trans-Lunar Injection Triple Mode Redundancy 47