As a ‘wind-tunnel in the sky’ this is a means of conducting rapid and inexpensive
sub-orbital re-entry experiments in support of novel probe design, flight dynamics,
control system development, and instrument and sensor verification.
SOAREX (Sub-Orbital Aerodynamic Re-entry EXperiments)
It is of great importance to the exploration program to have a capability of testing
a variety of different technologies for future flight application. The advantages
of the sounding rocket platform include elimination of crew safety concerns (e.g.,
STS and ISS) and a rapidity with which new experiments can be incorporated. A
very high altitude sounding rocket may provide as much as 40 minutes of microgravity,
and atmospheric entry velocities approaching that of earth orbit entry.
Image right: Superstable probe: Initial flight verification for SCRAMP configuration.
For entry applications, the potential utility is as follows:
- this would include the initial testing of attached
and trailing ballutes as well as other concepts (deployed flexible decelerators;
linear aerobrake designs)
- Integrated Vehicle Health Management systems for both ascent and
Advanced control methodologies
- for improving the landing footprint of
CEVs, Mars and other planetary probes.
- an initial flight experiment with a ‘Busemann duct’
was conducted with some success, suggesting focused experiments in duct flow physics
with fuel injection are possible.
Advanced probe design
- for the development of dynamically stable re-entry
systems (e.g., SCRAMP). This is particularly important for future SAMPLE RETURN
Our in-house expertise draws upon a diverse, multi-disciplinary team of psychologists
and engineers. We apply a variety of task analytic, experimental, and modeling
techniques to characterize interface requirements and test potential solutions.
Right: Image from waverider aft-camera at apogee (image of terminator from pre-dawn launch).
Recent research and development projects include:
- Haptic Interfaces for Teleoperations
We are developing human factors guidelines for effective haptic (force reflecting)
manual interfaces for multi-sensory virtual simulation and teleoperation displays.
Major program goals include: 1) the design of a novel, very high performance,
3 DOF force reflecting manual interface device; and 2) examination of operator
perception and manual task mechanical linkage.
- Spatial Auditory Displays
We have developed and validated technologies to synthesize spatially localized
sounds. By applying real-time transformation, any acoustic source (voice, warning
tones) can be localized to a point in 3D space. Sounds can be displayed via speakers
or headphones. These technologies have been tested in a number of aerospace environments
(including ATC, aircraft flight deck, and mission control). We have demonstrated
consistent improvements in situational awareness and speech intelligibility with
these advanced acoustic displays. Several patents have been awarded or are pending.
- Space Perception in Virtual Environments
We are assessing the acquisition of situational awareness via immersive (virtual
environment) and non-immersive (desktop) interface displays, and are developing
a model to predict the degree of interface fidelity required for specific visualization
tasks. Our findings have been published in PRESENCE, the journal of virtual environment
The flight series was born of the perceived difficulty of performing small scale
flight experiments. It was intended to complement ground facilities such as ballistic
ranges (this was conceived as an ‘atmospheric scale’ ballistic range), arc-jets,
and more traditional hypersonic test facilities.
Image right: Hypersonic waverider flight test development article.
By using the stable of NASA sounding rockets, and developing a simple means of
deploying multiple experiments above the atmosphere, Mach 8-12 may be readily
Three flights have been conducted with over 15 independent re-entry experiments.
Experiments have ranged from advanced low L/D probes
(‘super’ stable configurations;
transpiration cooling systems testing, deployed drag devices) to high L/D flight
(simple waveriders; control systems development for future planetary
Flight using a land range, radial ejection of 11 experiments and autonomous on-board
data-storage. performance via psychophysical and target acquisition experiment.
A patent has been award for our 3 DOF parallel All experiments were recovered
using unique retrieval systems.
Flight using a water range, first design of multiple-axial experiment ejection,
linear aerobrake system test.
: Comprehensive Success
First waverider system test, redundant IMU sensors, use of multiple cameras on
payload to confirm ejection and subsequent stabilization.
Launch in late 2004
Multiple high L/D test articles; first test of deployable aerobrake technology,
water recovery system test.
SOAREX Launch systems:
Multiple Reentry Experiments
Altitude vs. velocity plots show different ballistic and lifting entry trajectories
compared to a typical STS trajectory. Sounding rocket platforms can provide very
high altitude ejection of experiments, and 10-30 minutes of microgravity during
Experimental modular data system packages have been developed which help to efficiently
incorporate future experiments. The high L/D test articles (waveriders) have been
equipped with redundant IMU sensors, video cameras, pressure and temperature sensors
(for boundary layer transition flight data). There are both terrestrial and planetary