Planetary Flight Vehicles (PFV): Technology Development Plans for New Robotic Explorers [invited]

Rhew, Ray D.; Guynn, Mark D.; Yetter, J. A.; Levine, Joel S.; Young, Larry A.

doi:10.2514/6.2005-7132

Cited by 6 publications

(5 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Currently, in the field of rotary-wing Mars UAV research, numerous scholars have conducted extensive investigations into the following aspects: (i) the feasibility of rotarywing Mars UAVs' flight; (ii) the vertical-takeoff-and-landing (VTOL) capabilities of rotarywing Mars UAVs; (iii) the development of prototypes for rotary-wing Mars UAVs. This section provides a summary of the state of research on rotary-wing Mars UAV technologies conducted by various research institutions [34,35], as depicted in Figure 3.…”

Section: Development Of Rotary-wing Mars Uavsmentioning

confidence: 99%

“…In the same year, the ARC collaborated with the Langley Research Center to develop a series of deployment strategies for UAVs on Mars. Extensive research was conducted on various aspects of Martian UAVs, including maximum lift, total mass, power source, mechanical efficiency, autonomous flight capability, reliability, and hover performance, among others [34].…”

Section: The Ames Research Centermentioning

confidence: 99%

See 1 more Smart Citation

Review of Key Technologies of Rotary-Wing Mars UAVs for Mars Exploration

Zhao,

Li,

et al. 2023

Inventions

View full text Add to dashboard Cite

The sparse atmosphere on the surface of Mars provides the necessary flight conditions for Mars unmanned aerial vehicles (UAVs) to perform low-altitude flights. This work presents a comprehensive overview of key technologies in the development of Mars UAVs, with a specific focus on rotary-wing Mars UAVs. It summarizes prototypes of rotary-wing Mars UAVs developed by various global research institutions. It reviews essential technologies in rotary-wing Mars UAV research, including the Mars near-surface atmospheric environment, aerodynamic characteristics, and principles of low-pressure flight control. This work also summarizes various experimental setups and ground test results for rotary-wing Mars UAVs. Furthermore, it discusses the future development trends of rotary-wing Mars UAVs.

show abstract

Section: Development Of Rotary-wing Mars Uavsmentioning

confidence: 99%

Section: The Ames Research Centermentioning

confidence: 99%

Review of Key Technologies of Rotary-Wing Mars UAVs for Mars Exploration

Zhao,

Li,

et al. 2023

Inventions

View full text Add to dashboard Cite

show abstract

“…[16][17][18][19] They recognize their limitations proposing aircraft or rotorcraft configurations as feasible stand-alone platforms. Autonomous vehicles are able to freely explore, which is an improvement in extraterrestrial scientific research techniques, as Rhew states in his Mars PFVs study 20 and Young outlines in relation to VTOL vehicles. 21 Miralles 22 also analyzed possible scenarios for planetary gliders.…”

Section: Uav Projectsmentioning

confidence: 99%

“…23 At present, the project has reached wind tunnel tests and high altitude flight tests stage. 7,20 The project implementation is due in 2018. 24 Regarding Titan, numerous projects of atmospheric flight vehicles have been proposed 3,10,11,[25][26][27] but the most developed one is the AVIATR (Aerial Vehicle of In-Situ and Airborne Titan Reconnaissance) project developed by Barnes with the objective of studying Titan's geography and atmosphere.…”

Section: Uav Projectsmentioning

confidence: 99%

Optimizing multidisciplinary scaled tests in terrestrial atmosphere for extraterrestrial unmanned aerial vehicle missions

Moreno

Jarzabek

González

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

View full text Add to dashboard Cite

Unmanned aerial vehicles are a valid tool for exploring celestial objects that have atmosphere. The design process of these vehicles includes numerical analysis phase, which is then followed by an experimental flight test campaign in order to validate and refine the design. In terrestrial conditions, it is impossible to use the full size prototype and recreate all the conditions of extraterrestrial flight. The only option is to use a scaled model maintaining certain similarity parameters to the prototype. This would, however, not reproduce the global multidisciplinary behavior in terrestrial conditions. Alternatively, relaxing similarity constraints enables reproducing the global multidisciplinary behavior but introduces known and measurable similarity differences. The objective of this study is to provide a methodology for designing a relaxed similarity scaled model for terrestrial multidisciplinary tests for any extraterrestrial unmanned aerial vehicle. The methodology is then applied to a case scenario in order to verify its validity.

show abstract

“…In this context, many researchers are trying to use fuel cell systems as primary and secondary sources of power [3][4][5][6]. The NASA Aerial, RegionalScale Environmental, Survey of Mars (ARES) UAV platform is another example of a technology demonstrator [7][8][9]. It is designed to fly in the Martian atmosphere while analyzing Mars's crustal magnetism and the atmosphere boundary layer composition.…”

Section: Armentioning

confidence: 99%

Variable Fidelity Conceptual Design Environment for Revolutionary Unmanned Aerial Vehicles

Dufresne

Johnson

Mavris

2008

Journal of Aircraft

View full text Add to dashboard Cite

This paper describes the development of an unmanned aerial vehicle's conceptual design environment. A review of current unmanned aerial vehicle design challenges is conducted, which leads to the description of the desired capabilities for the environment. The key characteristics of the design environment include the capability of integrating variable fidelity, modular, and flexible disciplinary analysis tools. The environment is tested against available data from the AeroVironment Pathfinder Plus vehicle. In addition to the Pathfinder Plus mission analysis, aerodynamics, propulsion, and structures performance results are discussed and then applied to a hurricane-tracker mission. This case study demonstrates the environment's capability to perform and explore new types of missions. A further exploration of the Pathfinder Plus design space is conducted using response surface methodology. This investigation provides valuable information regarding design tradeoffs, which are essential for the selection of a final vehicle architecture. Nomenclature AR= wing aspect ratioairfoil maximum lift coefficient D = vehicle drag, N ezV = electrolyzer voltage, V E ez = solar energy consumed to power the electrolyzer, W E ez = energy consumed by the electrolyzer per mass of hydrogen, W=kg E fc = total fuel cell energy production, W E fc = energy produced by the fuel cell per mass of hydrogen, W=kg E solar = solar energy consumed to power the vehicle, W E total = total energy consumed to power the vehicle, W fcV = fuel cell voltage, V Kv = voltage constant kgH2 = mass of hydrogen, kg m prop = total propulsion system mass, kg n days = number of days the vehicle flew S = wing planform area, m 2 sa eff = solar cell efficiency T A = thrust available, N R = response of the response surface equation V = vehicle velocity, m=s W i = vehicle actual weight, N Wpld = payload mass, kg x i = design variable of the response surface equation = coefficients of the response surface equation ez = electrolyzer efficiency

show abstract

Planetary Flight Vehicles (PFV): Technology Development Plans for New Robotic Explorers [invited]

Cited by 6 publications

References 3 publications

Review of Key Technologies of Rotary-Wing Mars UAVs for Mars Exploration

Review of Key Technologies of Rotary-Wing Mars UAVs for Mars Exploration

Optimizing multidisciplinary scaled tests in terrestrial atmosphere for extraterrestrial unmanned aerial vehicle missions

Variable Fidelity Conceptual Design Environment for Revolutionary Unmanned Aerial Vehicles

Contact Info

Product

Resources

About