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Flight Experiment of the Capsule with the Deployable Flexible Aeroshell Using a Large Scientific Balloon. Kazuhiko Yamada , Daisuke Akita, Eiiji Sato,Kojiro Suzuki (University of Tokyo) Yuuki Tsutusmi, Kazuhiko Wakatuki (Tokai University) Tomohiro Narumi, Akira Sakurai (Kyushu University)

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Presentation Transcript
slide1
Flight Experiment of the Capsule

with the Deployable Flexible Aeroshell

Using a Large Scientific Balloon

Kazuhiko Yamada, Daisuke Akita, Eiiji Sato,Kojiro Suzuki (University of Tokyo)

Yuuki Tsutusmi, Kazuhiko Wakatuki (Tokai University)

Tomohiro Narumi, Akira Sakurai (Kyushu University)

Takashi Abe, Yukihiko Matsusaka (ISAS/JAXA)

56th International Astronautical Congree

In Fukuoka JAPAN

contents
CONTENTS
  • Background

Membrane Aeroshell Concept

  • Outline of flight test
  • Flight model

Configuration

Sensors

  • Results

Behavior of membrane aeroshell

Flight trajectory

Aerodynamic Characteristics

  • Conclusions
background
Background

New Concept of Atmospheric-entry system

Conventional

Flexible Aeroshell

Withstand

high aerodynamic heating

Avoid

high aerodynamic heating

C/C material or Ablator

Large and Light Aeroshell

And Soft Landing

Parachute System

for Soft Landing

outline of project
Outline of project

Drop flight test of actual size model

of flexible membrane aeroshell

using a Balloon from at a altitude of 39km

Separation

Ascending

Free Flight

Mach number : 0.9

Dynamic pressure : 0.84kPa

Launching

objectives
Objectives
  • Development of a actual scale capsule-type vehicle with a deployable membrane aeroshell
  • Demonstration of the capability of the deployable membrane structure and the stable flight
  • Obtaining the aerodynamic characteristics and the behavior of the aeroshell in transonic and subsonic flow regimes
flight model
Flight Model

Outer Frame

  • Dodecagonal configuration
  • Material : 12 Aluminum hollow pipes
  • Weight : 2.6 kg
  • Carpenter tape hinge deployment mechanism

Membrane Aeroshell

  • Flare configuration
  • Material : ZYLON
  • Weight : 0.6 kg
  • Maximum Diameter 150cm
  • Grid pattern was printed

Capsule

  • Hemispheric configuration
  • Material : Iron
  • Weight : 102 kg
  • Diameter : 60cm
  • All device were installed
sensors
Sensors
  • CCD camera
  • Fish eye lens
  • Acceleration Sensors
  • Angular Velocity Sensors
  • Geomagnetism Sensors
  • Pressure Transducer
  • Piezo Film
  • Thermo couple
  • GPS

Attitude and motion

Trajectory

Behavior of Aeroshell

Environmental of Flight

All data were transferred to ground station by telemetry system

deployment demonstration
Deployment Demonstration

Deployed Configuration

At Ground Test

Folded Configuration

balloon flight
Balloon flight

1. Mount the flight model

2. Turn on all the sensors

3. Launching balloon

4. Separation of the flight from an altitude of 40 km

5. Data transfer to the ground during flight

6. Splash down (No recovery )

7. Balloon and gondola is recoveries.

results
Results

CCD image

  • Oscillation of the membrane aeroshell
  • Deformation of the membrane aeroshell
  • Attitude and rotation of the capsule

Horizontal Trajectory

Vertical Trajectory

  • Deceleration performance
ccd image
CCD IMAGE

Two CCD cameras are equipped

気球本体

ゴンドラ

Camera 1

カッター

外枠

膜面

Camera 2

魚眼レンズ

カプセル

membrane oscillations
Membrane Oscillations

FFT analysis

Time variation of frequency spectrum

Output of piezo film

10Hz

4Hz

Membrane Aeroshell oscillated at a frequency of 4Hz and 10Hz

membrane deformation
Membrane Deformation

determiened from CCD Image through fish-eye lens

and assumption that membrane does not stretch

In Flight

Unloaded

Membrane aeroshell deformed to concave shape due to aerodynamic force

attitude and rotation
Attitude and Rotation

Track of Sun in the CCD View

Angular Velocity around body axis

→Capsule did not inclined

→ Capsule rotated around body axis

Vehicle kept a vertical attitude with rotation during flight.

horizontal trajectory
Horizontal Trajectory

Horizontal Trajectory

Wind and Horizontal Motion

→Horizontal Motion is synchronized

with the wind

→Capsule traveled in 6km horizontally

Vehicle dropped with zero angle of attack.

vertical trajectory
Vertical Trajectory

~ Comparison with simulation

History of Vertical Acceleration

History of Vertical Velocity and Altitude

→Flight data is in good agreement with trajectory Simulation

aerodynamic characteristics
Aerodynamic Characteristics

Mach Number vs Drag Coefficient

Drag Coefficient

S=1.617m2

m=106kg

g=9.8m/s2

Comparison with Wind Tunnel test

Plot the flight data

from 5km to 35 km

→Flight data is good agreement

with Wind tunnel data

The flare-type membrane aeroshell has a reasonable deceleration performance

in free flight condition as we expected at wind tunnel test.

conclusions
Conclusions

The flight test of the capsule with flare-type membrane aeroshell was carried out using a Large scientific Balloon.

In flight test,

The flight model kept stable and vertical attitude

The flight model dropped with a zero angle of attack

The 4Hz and 10Hz oscillations were induced

in both transonic and subsonic regime

The flight path and drag coefficient is in good agreement with

the Trajectory analysis and wind tunnel test.

It is demonstrated

the flare-type membrane aeroshell has a good deceleration performance

wind tunnel test
Wind Tunnel Test

Low speed Wind Tunnel Test

Drag Coefficient vs Angle of Attack

Concave shape

Tack-like Wrinkle

Transonic Wind Tunnel Test

separation demonstration
Separation Demonstration

Set up

Main rope

Cutter

Separation

advantages
Advantages

Reference Case (Small sounding rocket )

Mass = 50kg

Altitude = 200km

Diameter = 20cm

Velocity =1000m/s

Dramatic Reduction of the Surface temperature

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