Electric Helicopter Rotor Hub Development
Location: Sydney, NSW
Duration: 5 months
Proposed start date: April/May 2019
Please note: Due to the sensitivity and security of this project, students must have Australian Citizenship to apply. Students also need to be enrolled in one of the following universities; Macquarie University, The University of Newcastle, The University of New South Wales, The University of Sydney, University of Technology Sydney, University of Wollongong or Western Sydney University. Any applicants not meeting this requirement will automatically be deemed ineligible for this project.
This research internship is funded in partnership with New South Wales Defence Innovation Network.
Hyper Q Aerospace is developing a hybrid electric rotorcraft. The rotorcraft will use electric axial flux motors to rotate the rotorhead and attached rotor blades. This configuration will eliminate the need for gearboxes, transmissions and drive shafts as they exist in conventional helicopter design. Using an electric drive will offer a far more responsive RPM control of the rotorhead, and when combined with the solution of an allied project will allow Hyper Q Aerospace plans to build the first pure electric drive rotorcraft in the world.
The project is fundamental to the existence of the company. Hyper Q Aerospace intends producing a range of unmanned rotorcrafts based on the technology derived from this project. The primary outcome of this project will be to create a hybrid electric rotorcraft that will improve speed and carry greater payload than any comparable platform. By developing an electric rotorhead Hyper Q Aerospace can take advantage of alternative power supplies, as new electric storage systems come into being. This might include battery, fuel cell, electric umbilical or possibly and more efficient liquid fuel powered engines. As the Hyper Q Aerospace rotorcraft models are fully scalable they will significantly disrupt the entire market place, enabling cost effective implementation of any size model from a couple of metres of rotor disk diameter up to sizes well in excess of 15m.
Research to be Conducted
Objective 1. Create a CFD analysis according to the theorem to be provided by Hyper Q Aerospace.
Objective 2. Create the algorithms by way of a simulation environment such as Matlab, Altair or similar to represent the solution of the proof.
Objective 3. Provide data analysis by way of a simulation environment such as Matlab, Altair or similar to prove the theorem.
Objective 4. Create a functional physical prototype which will demonstrate the proof of the theorem.
Objective 5. Integrate the solution with the Hyper Q Aerospace Virtual Swashplate project.
We are looking for a PhD student with the following:
- EQ – Communication; focus on a practical outcome; not bound by conventional thinking, respect of others, independent, responsible, a willingness to learn.
- IQ – CFD, helicopter aerodynamics, Matlab or Altair or similar, mechatronics, Solidworks or similar
- electronic communication systems, sensor capture and analysis, optical and laser capture and analysis, hybrid electric systems
Hyper Q Aerospace will drive a disruptive change in the understanding of helicopter aerodynamics and its implementation.
The methodology and theorem will be described in detail to the successful candidate. As a guide, the Hyper Q Aerospace theorem is based on a relationship between environmental conditions and the rpm of a coaxial rotorhead rotorcraft.
There is no requirement to develop a comprehensive mathematical description of the proof. The project requires sufficient mathematics only to provide the control code to fly the rotorcraft throughout the entire flight envelope.
The candidate may use existing library data such as lookup tables from existing and standard rotor blade design. This might include NACA 0012, NACA 0015 or other known blade types. Should a mathematical derivation to obtain this data be seen to be advantageous, that method will be considered an acceptable outcome.
Calculation performance ie. iteration time interval will be a measured output of the project. Processing intervals exceeding 35Hz are required. Should library data be used it must be capable of being encapsulated into the physical on-board control system to be managed airborne.
Input control will be that of an autopilot (digital or electro-mechanical) or direct linkage control from a manned aircraft. The completed system will operate seamlessly between the control input (autopilot or direct linkage) and resultant lift and thrust forces created to fly the rotorcraft throughout the entire flight envelop. Hyper Q Aerospace believes however that new ways of flying rotorcraft may become evident once the practical prototype has been completed.
The successful candidate will be required to work in collaboration to integrate the solution for the Hyper Q Aerospace Virtual Swashplate project. Ultimately the two projects will combine as a set of algorithms which enable the rotorcraft to fly at speeds well above the speed of any conventional helicopter.
In doing so, Hyper Q Aerospace requires a comprehensive stepwise approach to achieve a practical outcome. The goal of the project is to fly a completely functional prototype within 12 months.
The intern will receive $3,000 per month of the internship, usually in the form of stipend payments.
It is expected that the intern will primarily undertake this research project during regular business hours, spending at least 80% of their time on-site with the industry partner. The intern will be expected to maintain contact with their academic mentor throughout the internship either through face-to-face or phone meetings as appropriate.
The intern and their academic mentor will have the opportunity to negotiate the project’s scope, milestones and timeline during the project planning stage.
01 May 2019
APR – 0907