Hugh Alan Bruck
Research Subjects
Research Interests
Hugh Alan Bruck has a total of 301 co-authors. Here are the top co-authors by number of shared publications:
- Avraham Rasooly
National Cancer Institute, National Institutes of Health
23 shared publications Satyandra K. Gupta
University of Southern California
21 shared publicationsJoshua Balsam
Center for Devices and Radiological Health, FDA
13 shared publicationsS. K. Gupta
Department of Aerospace and Mechanical Engineering, University of Southern California, Los Angeles, USA
11 shared publications- Sandip Haldar
School of Mechanical Sciences, Indian Institute of Technology Goa, Farmagudi, Goa, 403401, India
11 shared publications - Satyandra K. Gupta
University of Southern California
11 shared publications
Latest Publications
- 31 October 2025
- Published by Elsevier in Applied Thermal Engineering
- Vol. 282
A novel air-cooled heat sink for high-powered cylindrical heat sources
- 31 October 2025
- Published by Elsevier in Applied Thermal Engineering
- Vol. 282
A novel air-cooled heat sink for high-powered cylindrical heat sources
- 1 October 2025
- Published by Springer Nature
- p. 93-101
Layered Jamming of Bistable Carbon Fiber Composites for Lightweight Morphing Structures
- 1 October 2025
- Published by Springer Nature
- p. 93-101
Layered Jamming of Bistable Carbon Fiber Composites for Lightweight Morphing Structures
- 29 March 2024
- Published by Springer Nature
- p. 97-103
Layered Jamming Functional Polymer-Based Composite Structures
- 29 March 2024
- Published by Springer Nature
- p. 97-103
Layered Jamming Functional Polymer-Based Composite Structures
- Open Access
- 12 October 2023
- Published by MDPI AG in Biomimetics
- Vol. 8 (6) , 485
A Retrospective of Project Robo Raven: Developing New Capabilities for Enhancing the Performance of Flapping Wing Aerial Vehicles
Flapping Wing Air Vehicles (FWAVs) have proven to be attractive alternatives to fixed wing and rotary air vehicles at low speeds because of their bio-inspired ability to hover and maneuver. However, in the past, they have not been able to reach their full potential due to limitations in wing control and payload capacity, which also has limited endurance. Many previous FWAVs used a single actuator that couples and synchronizes motions of the wings to flap both wings, resulting in only variable rate flapping control at a constant amplitude. Independent wing control is achieved using two servo actuators that enable wing motions for FWAVs by programming positions and velocities to achieve desired wing shapes and associated aerodynamic forces. However, having two actuators integrated into the flying platform significantly increases its weight and makes it more challenging to achieve flight than a single actuator. This article presents a retrospective overview of five different designs from the “Robo Raven” family based on our previously published work. The first FWAVs utilize two servo motors to achieve independent wing control. The basic platform is capable of successfully performing dives, flips, and button hook turns, which demonstrates the potential maneuverability afforded by the independently actuated and controlled wings. Subsequent designs in the Robo Raven family were able to use multifunctional wings to harvest solar energy to overcome limitations on endurance, use on-board decision-making capabilities to perform maneuvers autonomously, and use mixed-mode propulsion to increase payload capacity by exploiting the benefits of fixed and flapping wing flight. This article elucidates how each successive version of the Robo Raven platform built upon the findings from previous generations. The Robo Raven family collectively addresses requirements related to control autonomy, energy autonomy, and maneuverability. We conclude this article by identifying new opportunities for research in avian-scale flapping wing aerial vehicles.
- 12 October 2023
- Published by MDPI AG in Biomimetics
- Vol. 8 (6) , 485
Open AccessA Retrospective of Project Robo Raven: Developing New Capabilities for Enhancing the Performance of Flapping Wing Aerial Vehicles
Flapping Wing Air Vehicles (FWAVs) have proven to be attractive alternatives to fixed wing and rotary air vehicles at low speeds because of their bio-inspired ability to hover and maneuver. However, in the past, they have not been able to reach their full potential due to limitations in wing control and payload capacity, which also has limited endurance. Many previous FWAVs used a single actuator that couples and synchronizes motions of the wings to flap both wings, resulting in only variable rate flapping control at a constant amplitude. Independent wing control is achieved using two servo actuators that enable wing motions for FWAVs by programming positions and velocities to achieve desired wing shapes and associated aerodynamic forces. However, having two actuators integrated into the flying platform significantly increases its weight and makes it more challenging to achieve flight than a single actuator. This article presents a retrospective overview of five different designs from the “Robo Raven” family based on our previously published work. The first FWAVs utilize two servo motors to achieve independent wing control. The basic platform is capable of successfully performing dives, flips, and button hook turns, which demonstrates the potential maneuverability afforded by the independently actuated and controlled wings. Subsequent designs in the Robo Raven family were able to use multifunctional wings to harvest solar energy to overcome limitations on endurance, use on-board decision-making capabilities to perform maneuvers autonomously, and use mixed-mode propulsion to increase payload capacity by exploiting the benefits of fixed and flapping wing flight. This article elucidates how each successive version of the Robo Raven platform built upon the findings from previous generations. The Robo Raven family collectively addresses requirements related to control autonomy, energy autonomy, and maneuverability. We conclude this article by identifying new opportunities for research in avian-scale flapping wing aerial vehicles.
- 3 June 2022
- Published by Springer Nature in Experimental Techniques
- Vol. 47 (3) , 679-688
New Method for Fatigue Characterization via Cyclical Instrumented Indentation Testing
- 3 June 2022
- Published by Springer Nature in Experimental Techniques
- Vol. 47 (3) , 679-688
New Method for Fatigue Characterization via Cyclical Instrumented Indentation Testing
- 7 January 2022
- Published by Springer Nature in The International Journal of Advanced Manufacturing Technology
- Vol. 119 (5-6) , 3545-3570
Automated process planning for conformal wire arc additive manufacturing
- 7 January 2022
- Published by Springer Nature in The International Journal of Advanced Manufacturing Technology
- Vol. 119 (5-6) , 3545-3570
Automated process planning for conformal wire arc additive manufacturing
- 1 January 2022
- Published by Springer Nature
- p. 93-98
Cyclical Instrumented Indentation Testing for Fatigue Characterization of Metals
- 1 January 2022
- Published by Springer Nature
- p. 93-98
Cyclical Instrumented Indentation Testing for Fatigue Characterization of Metals
- 1 October 2021
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Thermophysics and Heat Transfer
- Vol. 35 (4) , 800-813
Development of Magnetohydrodynamic Avionics Cooling Using Complex Structures Realized Through Additive Manufacturing
As electronics get smaller and faster, novel thermal management systems are needed that are capable of dissipating higher heat fluxes. Additive manufacturing and advanced materials, such as liquid metals and synthetic ceramic, offer new opportunities to realize thermal systems. This paper investigates the use of additive manufacturing to develop thermal structures designed around liquid metals to provide active magnetohydrodynamic cooling by obviating the need for moving parts and addressing the corrosive issue of liquid metal. Optimized components for the magnetohydrodynamic cooling prototype have been conceptualized, modeled, simulated, and fabricated to enhance flow and thermal transport efficiency, magnetic flux intensity, material compatibility, and manufacturing feasibility. Prototype systems were used to determine electrical and magnetic saturation thresholds of electrodes and electromagnets under direct current and alternating current. Additionally, the effect of electroplated Hartmann wall on flow rate and pressure drop was determined. The magnetohydrodynamic cooling prototype was shown to reach volumetric flow rates of up to and generated pressure due to Lorentz forces of up to 230 Pa, resulting in heat transfer improvement relative to passive prototype of 1.054. Magnetohydrodynamic cooling was also compared with alternative liquid metal cooling techniques to prove its benefits.- 1 October 2021
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Thermophysics and Heat Transfer
- Vol. 35 (4) , 800-813
Development of Magnetohydrodynamic Avionics Cooling Using Complex Structures Realized Through Additive Manufacturing
As electronics get smaller and faster, novel thermal management systems are needed that are capable of dissipating higher heat fluxes. Additive manufacturing and advanced materials, such as liquid metals and synthetic ceramic, offer new opportunities to realize thermal systems. This paper investigates the use of additive manufacturing to develop thermal structures designed around liquid metals to provide active magnetohydrodynamic cooling by obviating the need for moving parts and addressing the corrosive issue of liquid metal. Optimized components for the magnetohydrodynamic cooling prototype have been conceptualized, modeled, simulated, and fabricated to enhance flow and thermal transport efficiency, magnetic flux intensity, material compatibility, and manufacturing feasibility. Prototype systems were used to determine electrical and magnetic saturation thresholds of electrodes and electromagnets under direct current and alternating current. Additionally, the effect of electroplated Hartmann wall on flow rate and pressure drop was determined. The magnetohydrodynamic cooling prototype was shown to reach volumetric flow rates of up to and generated pressure due to Lorentz forces of up to 230 Pa, resulting in heat transfer improvement relative to passive prototype of 1.054. Magnetohydrodynamic cooling was also compared with alternative liquid metal cooling techniques to prove its benefits.- 27 March 2021
- Published by Springer Nature
- p. 7-18
Characterization of High Frequency Pulse Loading on Fatigue of Metals
- 27 March 2021
- Published by Springer Nature
- p. 7-18
Characterization of High Frequency Pulse Loading on Fatigue of Metals