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Peregrine Mission 1 (TO2-AB)

NSSDCA ID: PEREGRN-1

Description

Launch of Peregrine Mission 1 is no longer targeted for its planned May 4 date due to anomalies found in tests of the Vulcan Centaur launch vehicle. A new launch date will be announced once the launch vehicle investigation is completed.

Peregrine Mission 1 (TO2-AB), or the Peregrine Lunar Lander, carrying scientific and other payloads to the Moon, is planned to touch down on the lunar surface on Sinus Viscositatis. The scientific objectives of the mission are to study the lunar exosphere, thermal properties and hydrogen abundance of the lunar regolith, magnetic fields, and the radiation environment. It will also test advanced solar arrays. Peregrine Mission 1 was selected through NASA's Commercial Lunar Payload Services (CLPS) initiative, in which NASA contracts with a commercial partner, in this case Astrobotic, that provides the launch and lander.

Spacecraft and Subsystems

Peregrine Mission 1 is about 1.9 m high and roughly 2.5 m across. It is a box-shaped main body sitting on four landing legs. The main structural landing bus is composed of aluminum isogrid shear panels and aluminum honeycomb mounting surfaces with one primary deck divided into four parts. Propulsion is provided by five ISE-100 667-N thrusters mounted on the bottom of the lander. They use a hypergolic system of Mono-Methyl Hydrazine (MMH) fuel and dinitrogen tetroxide/nitrogen dioxide, 25% Mixed Oxides of Nitrogen (MON-25) oxidizer. Four sets of three 45-N attitude control thrusters maintain orientation. Attitude knowledge is provided by Sun and star trackers, inertial measurement, and Doppler radio and LIDAR, with the landing sensors mounted on the bottom of the bus.

Power (at 28 V, max. 480 W) is generated by GaInP/GaAs/Ge triple junction solar cells mounted on the top of the lander on a 1.8 square meter panel, and is stored in lithium-ion batteries with a capacity of 840 Whr. Communications (X-band downlink, S-band uplink) are via a medium gain, low-gain, and WLAN antennas. Thermal control is achieved by radiators and multi-layer insulation blankets.

The mission will carry about 10 payloads of various types, the lander has a payload mass capacity of 90 kg. The scientific payload includes the Laser Retro-Reflector Array (LRA), Linear Energy Transfer Spectrometer (LETS), Near-Infrared Volatile Spectrometer System (NIRVSS), PROSPECT Ion-Trap Mass Spectrometer (PITMS), and Neutron Spectrometer System (NSS). Five other science payloads were originally planned for Peregrine Mission 1, but are being reallocated to other future lunar delivery missions. These are: Photovoltaic Investigation on Lunar Surface (PILS), Mass Spectrometer Observing Lunar Operations (MSolo), and Neutron Measurements at the Lunar Surface (NMLS), Fluxgate Magnetometer (MAG), and Surface Exosphere Alterations by Landers (SEAL).

Mission Profile

Launch will take place from Cape Canaveral, Florida on a United Launch Alliance Vulcan Centaur rocket in the VC2S configuration, with 2 GEM-63XL solid boosters, a standard short faring, and two RL10 engines in the Centaur upper stage. The launch was scheduled for 4 May, but has been delayed while an investigation into anomalies found during testing of the launch vehicle are being investigated. After a 3 to 33 day Earth orbit and cruise to the Moon, followed by a 4 to 25 day lunar orbit phase, it will descend and land in Sinus Viscositatis (Bay of Stickiness) adjacent to the Gruitheisen Domes on the northeast border of Oceanus Procellarum (Ocean of Storms). It is planned to land 55-110 hours after local sunrise and to operate for about 192 hours.

For more on NASA's CLPS initiative and missions, see:

https://science.nasa.gov/lunar-discovery/deliveries

Image credit: Astrobotic Technology

Alternate Names

  • PeregrineMission1
  • Peregrine Lunar Lander 1
  • TO2-AB
  • CLPS TO2-AB
  • Peregrine 1

Facts in Brief

Launch Date: 
Launch Vehicle: VC2S
Launch Site: Cape Canaveral, United States

Funding Agency

  • Unknown (United States)

Discipline

  • Planetary Science

Additional Information

Questions and comments about this spacecraft can be directed to: Dr. David R. Williams

 

Personnel

NameRoleOriginal AffiliationE-mail
Dr. Sharad BhaskaranMission Directorsharad.bhaskaran@astrobotic.com
Dr. Paul NilesProject ScientistNASA Johnson Space Centerpaul.b.niles@nasa.gov
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