A study of the suitabiiity of ground-based faciiities for simulating the iiow and combustion in scramjets has been carried out. A wind tunnei model was developed for the HEG from the HyShot flight test model, which recreated the internal geometry at a scale of 1: 1. The model was split into two engines, which were instrumented with pressure transducers and thermocouples. A fuei injection. The HyShot™ IV experimental scramjet test has been conducted today at the Woomera range, 500km north of Adelaide, South Australia at about 1.10pm local time (CDT). “The rocket launch looked as expected. We had another clean liftoff,” Associate Professor Michael Smart of the UQ HyShot team said.

HyShot is a research project of The University of Queensland, Australia Centre for Hypersonics, to demonstrate the possibility of supersonic combustion under flight conditions using two scramjet engines, one designed by The University of Queensland and one designed by QinetiQ (formerly the MOD's Defence Evaluation & Research Agency).

The Hypersonic International Flight Research Experimentation (HIFiRE) program investigated the fundamental science of hypersonics technology and its potential for next generation aeronautical systems. It was to designed to involve up to ten flights. HIFiRE was jointly established by DSTO and the US Air Force Research Laboratory (AFRL).

Hyshot Scramjet

UQ was involved in three flights in the HIFiRE program. These tests wera also known as HyShot, V, VI and VII. The flights were planned for launch at Woomera in South Australia, or an alternative range in Andoya, Norway. The three flights were funded by a $8.5 million Smart State National and International Research Alliances partnership between UQ, the Queensland Government, Boeing and DSTO (2007-2017) . This international collaboration allowed UQ to build advanced scramjet prototypes and undertake prolonged flight tests at speeds of more than Mach 8.

Casino beach live cam webcam. HyShot V (HIFiRE 4)— A free-flying hypersonic glider

HyShot V was a hypersonic waverider designed to fly at Mach 8 (8000 km/hr). It was designed to separate from its rocket booster in space and perform controlled manoeuvres as it entered the atmosphere. This flight did not have a scramjet attached. It was about learning how to fly a hypersonic vehicle at high altitude.

This test flight was successfully completed in July 2017. Read the full story here

HyShot VI (HIFiRE 7) — A free-flying Mach 8 scramjet

HyShot VI flew on 30 March 2015. It used an up-and-down trajectory similar to HyShot flights 1-IV, but the scramjet engine separated from the rocket and entered the atmosphere on its own at about Mach 8. The scramjet was one of the new breed of three-dimensional engines designed by UQ. The HIFiRE team collected data for the flight until the payload was re-entering the atmosphere at 65 km, when telemetry was lost. Unfortunately no scramjet engine data was able to be collected.

HyShot VII (HIFiRE 8) - Sustained Mach 8 Scramjet Powered Flight

So-dimm slots. HyShot VII was to be the culmination of the other two flights. It was to be a scramjet-powered waverider vehicle and its design made use of the information learned from HyShot V and VI. A depressed trajectory was to be used for this flight and the HyShot team planned 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. The HIFiRE program ended before the vehicle could be flown.

HIFiRE 7 payload
HIFiRE 8 payload

HIFire 7 on the launch pad

Hyshot Scramjet

Gardner, Anthony Donald (2007)HyShot scramjet testing in the HEG. Dissertation, University of Queensland, Australia.

Full text not available from this repository.

Abstract

In this study, CFD and shock tunnel experiments have been performed, these then being compared with the flight test data from the HyShot II flight. Two new conditions for the HEG were designed analytically and refined using the one-dimensional Lagrangian code L1D and experimentally-determined efficiency coefficients, allowing the definition of a new condition with a maximum of two tests in the HEG. A new Mach 7.8 contoured nozzle was calibrated and a new piston with a braking system to prevent reverse movement after diaphragm burst was designed and tested. A wind tunnel model was developed for the HEG from the HyShot flight test model, which recreated the internal geometry at a scale of 1:1. The model was split into two engines, which were instrumented with pressure transducers and thermocouples. A fuel injection system injected cold gaseous hydrogen into the flow through portholes in the wall of one combustion chamber. Poker room sables d olonne. The model was tested at various angles of attack and equivalence ratios and testing with a nitrogen freestream was used to quantify the effect of fuel injection without combustion.

Item URL in elib:

https://elib.dlr.de/51689/

Document Type:

Thesis (Dissertation)

Title:

HyShot scramjet testing in the HEG

Authors:

Authors	Institution or Email of Authors	Authors ORCID iD
Gardner, Anthony Donald	UNSPECIFIED	UNSPECIFIED

Date:

2007

Refereed publication:

Yes

Open Access:

Gold Open Access:

In SCOPUS:

In ISI Web of Science:

Number of Pages:

294

Status:

Unpublished

Keywords:

scramjet, HEG, TAU, hypersonic, shock tube, flight test, combustion, hydrogen

Institution:

University of Queensland, Australia

HGF - Research field:

Aeronautics, Space and Transport (old)

HGF - Program:

Space (old)

HGF - Program Themes:

W - no assignment

DLR - Research area:

Space

DLR - Program:

W - no assignment

DLR - Research theme (Project):

W - no assignment (old)

Location:

Göttingen

Institutes and Institutions:

Institute of Aerodynamics and Flow Technology > Spacecraft
Institute of Aerodynamics and Flow Technology > High Speed Configurations

Deposited By:

Gardner, Dr.habil. Anthony

Deposited On:

30 Nov 2007

Last Modified:

27 Apr 2009 14:27

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