|HyShot I Launch 30 October 2001
||HyShot II launch 30 July 2002
||HyShot III launch 25 March 2006
||HyShot IV launch 30 March 2006
|| HyCAUSE launch 15 June 2007
The HyShot Flight Program is an experiment designed to develop a correlation between pressure measurements made of supersonic combustion in The University of Queensland's T4 shock tunnel, and that which is observed in flight. For university press releases about HyShot and other UQ hypersonics news, click here. For news about the HyCAUSE launch, click here.
This correlation is being developed with a scramjet configuration that retains the essential components for supersonic combustion.
Five flights were made
- HyShot I was launched on 30 October 2001
- HyShot II was launched on 30 July 2002
- HyShot III was launched on 25 March 2006
- HyShot IV was launched on 30 March 2006
- HyCAUSE was launched on 15 June 2007
Supersonic combustion was achieved in the HyShot II and III flights. Analysis of results from the 2007 HyCAUSE launch is ongoing.
The HyShot launches used a two stage Terrier-Orion Mk70 rocket to boost the payload and the empty Orion motor (the Orion motor remains attached to the payload) to an apogee of approximately 330 km. As the spent motor and its attached payload falls back to Earth, they gather speed. The trajectory is designed so that between 35 km and 23 km, they are traveling at Mach 7.6. It is during this part of the trajectory that the measurements of supersonic combustion are made. HyCause used a Talos-Castor launcher with a target Mach number of 10. All flights were launched from the Woomera Test Facility in South Australia.
Pressure measurements are the primary means for obtaining the correlation. In the HyShot I and II launches, approximately 40 measurements were made in and around the engine.
Gaseous Hydrogen is used as the fuel. As the combustion process in the scramjet is dependent on the ambient pressure, a highly parabolic trajectory with a near vertical decent during the test time was chosen, so that a correlation could be developed over an envelope of ambient pressures. In addition to the scientific merits, a vertical trajectory is also more cost efficient and there are less structural difficulties resulting from the lower heat and dynamic loads.
The approach being taken by The University of Queensland is new and has opened a new era in flight testing hypersonic air-breathing engines.
The Mission begins with the rockets pointing to the sky in a near vertical position. The payload is shrouded beneath a nose cone to protect it during the ascent through the atmosphere.
If suitable atmospheric conditions prevail, the launch sequence begins. A final check is made of all the operational equipment using the on-board telemetry system. The arm button is then activated to start the computer running. At T=0, the Terrier motor is fired.
As the rocket leaves the launch pad, it pulls away the fuel lines and an umbilical cord which has enabled the scientists and engineers to control the payload systems whilst on the ground. The computer now has to control the experiment for the next 10 minutes by itself. With an acceleration of 22 g (22 times the acceleration due to the Earth's gravity) the Terrier motor propels the system to 4000 km/h after just 6 s. This motor is then jettisoned and the Orion motor and its payload coast for 9 s. The Orion motor is then fired and boosts the payload in 26 s to a speed in excess of eight times that of sound (8300 km/h) and to an altitude of 56 km, approaching the edge of the atmosphere. Five seconds later the nose cone is blown off with compressed nitrogen. During the next 400 s, the rocket is manoeuvered to point downwards, in readiness to re-enter the atmosphere. This is achieved by using a cold gas thruster which provides pulses of compressed nitrogen to gently nudge the spent Orion motor and the experiment into the correct orientation.
As the rocket and the experiment re-enter the atmosphere, the altitude is monitored using a Pitot probe. When it descends to 35 km, hydrogen is supplied to the scramjet and the supersonic combustion experiment begins. Measurements of pressure and temperature in the combustor are transmitted back to three ground stations to be stored for later analysis. The flow of fuel is maintained for the next 5 s as the experiment descends to an altitude of 23 km. At this point the experiment is complete.
The first two HyShot flight experiments used a two-dimensional supersonic combustion ramjet with a back to back configuration. It included boundary layer bleeds on the intake and constant area combustors. The configuration was not designed to produce a net thrust, as the objectives of the experiments are to measure the pressures in the combustor and on the thrust surface and correlate these with the shock tunnel data. Hence, simplicity of the flow field was a high priority in the design of the experiment and this resulted in an 'engine' with poor performance. Developing an engine with net positive thrust is the subject of future flight trials.
Ground Experiments on the 'engine' that was flown were made in the T4 shock tunnel, located in UQ's Centre for Hypersonics (Smart et al., 2006; Frost et al., 2009). These experiments showed that supersonic combustion could be achieved at angles of attack up to four degrees. Experiments were also made at different yaw angles. Again, it was shown that four degrees of yaw could be tolerated. It is important that the engine operates at non-zero angles of attack because the HyShot payloads spin and cone on re-entry, providing a continuous change in angle of attack and yaw.
This is advantageous to the experiment because it provides additional data for the correlation purposes. These data can also clearly be used for testing computational analyses also. It is important that the design of the pressure sensors ensures sufficient response time so that these changes can be detected.
The Vertical Trajectory has one difficulty in that only small aerodynamic forces act on the motor and its payload during re-entry to the atmosphere. If the payload and the Orion motor are not pointing downwards before re-entering the atmosphere, this lack of air makes it difficult to turn the payload into the downwards direction before reaching the altitude at which the experiment begins. To alleviate this problem, the payload is rotated so that it is correctly oriented before it re-enters the atmosphere. This is quite a difficult maneuver to perform as the payload and its attached spent rocket motor are spinning at between 4 and 6 Hertz. This coupled with the fact that the system weighs close to 600 kg provides for a very large angular momentum vector, which must be rotated through approximately 160 degrees. The method chosen to perform this maneuver is called a "Bang-Bang" maneuver.
A Bang-Bang Manoeuver is one where an impulse is provided to a spinning object. This allows the object to nutate. After it has nutated through 180 degrees, another impulse is provided. This stops the nutation, but the whole system has changed its angular position. The HyShot system undergoes approximately 50 Bang-Bang manoeuvers to complete its re-orientation. The procedure to re-orient the payload has to be done without any intervention from the ground as only a telemetry downlink is provided. Hence, on-board sensors are provided to determine the orientation. These include two sun-sensors and a three-component magnetometer.
Grounding Testing of the payload is an important part of the HyShot Flight Program. With this testing, confidence is obtained in the computer programs and the equipment that has been specially manufactured for the flight. The ground test program includes testing the response times of transducers, the structural integrity of individual components, vibration testing, shock load testing, vacuum testing and source code evaluation. The source code and the algorithms which have been implemented were checked by using a three-axis gimbal system developed at The University of Queensland, especially for the HyShot Program and with "hardware-in-the-loop" experiments.
The gimbal that was constructed rotated a quarter scale model of the spent Orion motor and its payload at speeds up to 6 Hz. The orientation of the system was monitored using a three-axis magnetometer and two sun sensors, as is done in flight.
When the Terrier motor initially starts there are accelerations approaching 60 g experienced by all the components. This acceleration is only short lived and dies away to less than 30 g after half a second, but unless the equipment on board can withstand this initial shock, the experiment will fail in the first second of the flight. Hence, a vibration rig, which is essentially a stiff beam, was built to simulate this environment. Different pieces of equipment can be bolted to the vibration rig and tested to see if they can withstand the vibrations. Up to 30 kg at a time can be placed on the rig. This allows complete testing of much of the experimental structure at the one time.
Ground testing also includes aerodynamic testing to determine if the experiment will be stable as it re-enters the atmosphere. Testing was been done at QINETIQ's Farnborough facilities. Extensive tests were performed to determine the orientation that the experiment should have relative to the tail fins to ensure the greatest aerodynamic stability. This contribution provided valuable information which was fed back into the designs to optimise the chances of a successful mission.
The Electrical Layout of the payload is also an important issue which must be addressed for a successful mission. Components must be chosen which can operate under testing operating conditions. A large effort was made to make the circuitry as simple as possible. This leads to reduced costs and weight and a higher chance of success.
The Fuel System was also designed using the same philosophy. Two separate systems are used. One for the hydrogen supplied to the scramjet during the experiment and the other is used to supply the nitrogen to the cold gas thruster during the maneuver.
Sponsorship for the HyShot Flight Program has been obtained from, The University of Queensland, Astrotech Space Operations, Defence Evaluation and Research Agency (DERA, UK), National Aeronautics and Space Agency (NASA, USA), Defence, Science and Technology Organisation (DSTO, Australia), Dept. of Defence (Australia), Dept. of Industry Science and Resources (Australia), The German Aerospace Centre (DLR, Germany), Seoul, National University (Korea), The Australian Research Council, Australian Space Research Institute (ASRI), Alesi Technologies (Australia), National Aerospace Laboratories (NAL, Japan), NQEA (Australia), Australian Research and Development Unit (ARDU, Australia), the Air Force Office of Scientific Research (AFOSR, USA) and Luxfer, Australia.
The HyCAUSE flight was performed through a collaborative effort between the United States’ Defense Advanced Research Projects Agency (DARPA) and DSTO, also representing the research collaborators in the Australian Hypersonics Initiative (AHI).
Smart, M. K., Hass, N. E. and Paull, A. (2006) "Flight data analysis of the HyShot 2 scramjet flight experiment" AIAA JOURNAL, Vol. 44, No.10: 2366-2375.
Smart, M. (2007) "Scramjets" AERONAUTICAL JOURNAL Volume: 111 Issue: 1124 Pages: 605-619
Frost, M. A., Gangurde, D. Y., Paull, A. and Mee, D. J. 2009 "Boundary layer separation due to combustion-induced pressure rise in a supersonic flow," AIAA Journal, Vol. 47, No. 4: 1050-1053.
Ho, Sook-Ying; Paull, Allan (2006) "Coupled thermal, structural and vibrational analysis of a hypersonic engine for flight test" AEROSPACE SCIENCE AND TECHNOLOGY Volume: 10 Issue: 5 Pages: 420-426
Fureby, C.; Chapuis, M.; Fedina, E.; et al. (2011) "CFD analysis of the HyShot II scramjet combustor" PROCEEDINGS OF THE COMBUSTION INSTITUTE Volume: 33 Pages: 2399-2405.
Keistler, P. G.; Hassan, H. A.; Xiao, X. (2009) "Simulation of Supersonic Combustion in Three-Dimensional Configurations" JOURNAL OF PROPULSION AND POWER Volume: 25 Issue: 6 Pages: 1233-1239.
The Hypersonic International Flight Research Experimentation (HIFiRE) program is investigating the fundamental science of hypersonics technology and its potential for next generation aeronautical systems and will involve up to ten flights. HIFiRE has been jointly established by DSTO and the US Air Force Research Laboratory (AFRL).
UQ is involved in three flights in the HIFiRE program. These tests will also be known as HyShot, V, VI and VII.
The flights are planned to for launch at Woomera in South Australia.
The three flights are funded by a $8.5 million Smart State National and International Research Alliances partnership announced last year between UQ, the Queensland Government, Boeing and DSTO (Defence Science and Technology Organisation). This international collaboration allows UQ to build advanced scramjet prototypes and undertake prolonged flight tests at speeds of more than Mach 8.
• HyShot V — A free-flying hypersonic glider
HyShot V will be a hypersonic waverider designed to fly at Mach 8 (8000 km/hr). It will separate from its rocket booster in space and perform controlled manoeuvres as it enters the atmosphere. This flight will not have a scramjet attached. It is about learning how to fly a hypersonic vehicle at high altitude. Both an up-and-down trajectory similar to HyShot I-IV, and a more horizontal “depressed” trajectory are being considered for the flight.
• HyShot VI — A free-flying Mach 8 scramjet
HyShot VI will use an up-and-down trajectory similar to HyShot flights 1-IV, but the scramjet engine will separate from the rocket and enter the atmosphere on its own at about Mach 8. It will be a payload of around 250 kg (twice the size of the scramjet engines in the HyShot I-IV flight series). The HyShot team will then measure actual thrust levels of the scramjet over about five seconds of scramjet engine operation. The scramjet will be one of the new breed of three-dimensional engines designed by UQ.
• HyShot VII - Sustained Mach 8 Scramjet Powered Flight
HyShot VII is the culmination of the other two flights. It will be a scramjet-powered waverider vehicle and its design will make use of the information learned from HyShot V and VI. A depressed trajectory will be used for this flight and the HyShot team plans to fly the scramjet-powered vehicle horizontally for up to a minute at Mach 8. This compares with the brief experimental window of about 5 seconds for HyShot I-IV and VI.
| HIFiRE 0 launch from Woomera 7 May 2009
|| HIFIRE 1 launch from Woomera 22 March 2010
||HIFiRE launch from Hawaii May 2012
||HIFiRE launch from Andoya September 2012