Aero-Propulsive and Propulsor Cross-Coupling Effects on a Distributed Propulsion System

2018 ◽  
Vol 55 (6) ◽  
pp. 2414-2426 ◽  
Author(s):  
Aaron T. Perry ◽  
Phillip J. Ansell ◽  
Michael F. Kerho
Keyword(s):  
Cross Coupling ◽  
Propulsion System ◽  
Coupling Effects ◽  
Distributed Propulsion

A novel hybrid aircraft propulsion based on the DEA compressor—Part A: Design

2021 ◽  
pp. 095441002110253
Author(s):  
Babak Aryana
Keyword(s):  
High Performance ◽  
Static Condition ◽  
Propulsion System ◽  
Hybrid Propulsion ◽  
Pulse Detonation ◽  
Low Emission ◽  
Wide Range ◽  
Exit Nozzle ◽  
Distributed Propulsion ◽  
Detonation Process

This two-part article introduces a novel hybrid propulsion system based on the DEA compressor. The system encompasses a Pulse Detonation TurboDEA as the master engine that supplies several full-electric ancillary thrusters called DEAThruster. The system, called the propulsion set, can be categorized as a distributed propulsion system based on the design mission and number of ancillary thrusters. Part A of this article explains the design process comprising intake, compressor, detonation process, diffuser, axial turbine, and the exit nozzle. The main target is to design a high-performance low emission propulsion system capable of serving in a wide range of altitudes and flight Mach numbers that covers altitudes up to 20,000 m and flight Mach number up to the hypersonic edge. Designing the propulsion set, the design point is considered at the static condition in the sea level. Design results show the propulsion set can satisfy all requirements necessary for its mission.

scholarly journals Aerodynamic interaction between propellers of a distributed-propulsion system in forward flight

2021 ◽  
pp. 107009
Author(s):  
Reynard de Vries ◽  
Nando van Arnhem ◽  
Tomas Sinnige ◽  
Roelof Vos ◽  
Leo L.M. Veldhuis
Keyword(s):  
Propulsion System ◽  
Forward Flight ◽  
Aerodynamic Interaction ◽  
Distributed Propulsion

LaCoste and Romberg straight‐line gravity meter

Geophysics ◽  
1983 ◽  
Vol 48 (5) ◽  
pp. 606-610 ◽  
Author(s):  
Lucien LaCoste
Keyword(s):  
Cross Coupling ◽  
Coupling Effects ◽  
New Model ◽  
Silicone Fluid ◽  
Air Damping ◽  
Straight Line ◽  
New Instrument ◽  
Spring Suspension ◽  
Fluid Damping ◽  
Rough Handling

The LaCoste and Romberg straight‐line gravity meter uses a new suspension in which the movable element moves vertically in a straight line rather than in an arc of a circle (LaCoste, 1973a). It was designed primarily for shipboard operation to avoid effects from cross coupling between various ship accelerations, thereby making it unnecessary to correct for such effects. The straight‐line suspension is a modification of the zero length spring suspension used in all LaCoste and Romberg gravity meters. The new model also uses silicone fluid damping rather than the air damping used in earlier models. Its main advantages over the older models appear to be: it is (1) free of cross‐coupling effects, (2) easier to build and adjust, (3) less subject to slight degradation in performance from rough handling, and (4) less sensitive to ship vibrations. In spite of the above advantages it is doubtful whether the new model will give substantially better accuracy than the previous models, if the previous models are kept in good operating condition by making occasional crosscorrelation analyses (LaCoste, 1973b). Valliant (1983, this issue) describes sea tests of the new instrument.

scholarly journals Yaw control torque generation for a hovering robotic hummingbird

2019 ◽  
Vol 16 (1) ◽  
pp. 172988141882396 ◽  
Author(s):  
Ali Roshanbin ◽  
André Preumont
Keyword(s):  
Control Mechanism ◽  
Cross Coupling ◽  
Parallel Mechanisms ◽  
Design Development ◽  
Control Torque ◽  
Coupling Effects ◽  
Flight Tests ◽  
Wing Kinematics ◽  
Yaw Control ◽  
Torque Generation

This study describes the design, development, and flight tests of a novel control mechanism to generate yaw control torque of a hovering robotic hummingbird (known as Colibri). The proposed method generates yaw torque by modifying the wing kinematics while minimizing its influence on roll and pitch torques. To achieve this, two different architectures of series and parallel mechanisms are investigated; they are mathematically analyzed to investigate their behavior with respect to cross-coupling effects. The analysis is verified by measuring the control torque characteristics. The efficacy of the proposed method is also explored by flight experiments.

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