Initial Development of an Earth-Based Prototype for a Lunar Hopper Exploration System

Cunio, Phillip M.; Babuscia, Alessandra; Bailey, Zach; Cohanim, Babak E.; Hoffman, Jeffrey A.; Miller, David W.; Chaurasia, Hemant Kumar; Timmons, Eric; Selva, Daniel; Aliakbargolkar, Alessandro; Goel, Rahul

doi:10.2514/6.2009-6713

Cited by 5 publications

(4 citation statements)

References 1 publication

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“…The CGSE has three main functions: (1) to lift the hopper"s lunar weight, i.e. 1/6 of its Earth weight; (2) to propel the hopper horizontally; and (3) to provide attitude control.…”

Section: Design Of the Cold Gas Spacecraft Emulatormentioning

confidence: 99%

“…1,2 The flight profile for TALARIS, called a hover hop, is composed of a vertical takeoff, a horizontal transit at constant altitude and attitude, and a controlled vertical descent. Maneuvers of this type could enable unique contributions to many different planetary exploration objectives, 3 but TALARIS has specifically been designed to support the participation of MIT and Draper Laboratory…”

Section: Introductionmentioning

confidence: 99%

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Verification and Validation of a Cold Gas Propulsion System for the TALARIS Hopper Testbed

Morrow

Nothnagel

Cunio

et al. 2011

AIAA SPACE 2011 Conference &Amp; Exposition

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The TALARIS (Terrestrial Artificial Lunar And Reduced gravIty Simulator) hopper is a small prototype vehicle currently being flight tested as an Earth-based testbed for guidance, navigation, and control algorithms that will be used to explore lunar and other planetary surfaces remotely. It has two propulsion systems: (1) a system of four electric ducted fans to offset 5/6 of the Earth's gravitational force, and (2) a cold gas propulsion system which uses compressed nitrogen propellant to impulsively emulate the lunar propulsion system and flies in an environment dynamically similar to that of the Moon. This paper is a follow-up to the SPACE 2010 paper entitled "Development of a Cold Gas Spacecraft Emulator [CGSE] System for the TALARIS Hopper." It focuses on the second of the aforementioned propulsion systems. This paper reviews the history and design of the CGSE, describes the testing characterization process, compares actual and predicted results, and discusses the CGSE performance in the context of closed-loop vehicle control. Special focus is given to emergent behaviors. NomenclatureA e = exit area of a converging-diverging nozzle, m 2 A t = throat area of a converging-diverging nozzle, m 2 F = thruster force, N γ = ratio of specific heats m  = mass flow, kg/sec P b = back pressure in a converging-diverging nozzle, Pa P c = chamber pressure in a converging-diverging nozzle, Pa P e = exit pressure in a converging-diverging nozzle, Pa R = specific gas constant, J/(kg-K) T c = chamber temperature in a converging-diverging nozzle, K V e = exit velocity in a converging-diverging nozzle, m/sec V i = entrance velocity in a converging-diverging nozzle, m/sec

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“…The CGSE has three main functions: (1) to lift the hopper"s lunar weight, i.e. 1/6 of its Earth weight; (2) to propel the hopper horizontally; and (3) to provide attitude control.…”

Section: Design Of the Cold Gas Spacecraft Emulatormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Verification and Validation of a Cold Gas Propulsion System for the TALARIS Hopper Testbed

Morrow

Nothnagel

Cunio

et al. 2011

AIAA SPACE 2011 Conference &Amp; Exposition

Self Cite

View full text Add to dashboard Cite

show abstract

“…Accordingly, a design for a lightweight landing gear system that could withstand crash loads and be traceable 1 …”

Section: Introductionmentioning

confidence: 99%

“…HE TALARIS (Terrestrial Artificial Lunar And Reduced gravIty Simulator) hopper is a small prototype hopping vehicle currently being developed as an Earth-based testbed for guidance, navigation, and control (GNC) algorithms that will be used to explore lunar and other planetary surfaces remotely 1 . The TALARIS prototype hopper uses dual propulsion systems (air-breathing Electric Ducted Fans, or EDFs), and compressed nitrogen fired through cold-gas thruster valves.…”

Section: Introductionmentioning

confidence: 99%

Conceptual Design and Testing of a Landing Gear System for the TALARIS Lunar and Planetary Surface Exploration Hopper Prototype

Shafa

Cunio

Hoffman

et al. 2011

AIAA SPACE 2011 Conference &Amp; Exposition

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The TALARIS (Terrestrial Artificial Lunar And Reduced gravIty Simulator) lunar hopper prototype vehicle, which conducts test flights in Earth gravity, may undergo significant impacts upon landing. Accordingly, a concept was developed for landing gear to mitigate the effects of these impacts. This concept was then developed and prototyped, and initial tests for actuation capability and deceleration capability were conducted on the prototype. Initial results indicate that the selected concept, a foam-compressing piston design, performs well. Further testing to measure peak acceleration of the payload atop the landing gear and to develop the concept with lightweight materials is also recommended.

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Mars reconnaissance lander: Vehicle and mission design

Williams

Bridges

Ambrosi

et al. 2011

Planetary and Space Science

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Initial Development of an Earth-Based Prototype for a Lunar Hopper Exploration System

Cited by 5 publications

References 1 publication

Verification and Validation of a Cold Gas Propulsion System for the TALARIS Hopper Testbed

Verification and Validation of a Cold Gas Propulsion System for the TALARIS Hopper Testbed

Conceptual Design and Testing of a Landing Gear System for the TALARIS Lunar and Planetary Surface Exploration Hopper Prototype

Mars reconnaissance lander: Vehicle and mission design

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