critical design review nasa university student launch initiative n.
Download
Skip this Video
Loading SlideShow in 5 Seconds..
Critical design review NASA University Student Launch Initiative PowerPoint Presentation
Download Presentation
Critical design review NASA University Student Launch Initiative

Loading in 2 Seconds...

play fullscreen
1 / 32

Critical design review NASA University Student Launch Initiative - PowerPoint PPT Presentation


  • 216 Views
  • Uploaded on

Overview. Critical design review NASA University Student Launch Initiative. January 24, 2011. Overview. V. Payload Integration Feasibility Vehicle Integration Electronics Deployment Testing VI. Test Plans and Procedures VII. Scale Model Flight Test Test No. 1 Test No. 2

loader
I am the owner, or an agent authorized to act on behalf of the owner, of the copyrighted work described.
capcha
Download Presentation

PowerPoint Slideshow about 'Critical design review NASA University Student Launch Initiative' - edric


Download Now An Image/Link below is provided (as is) to download presentation

Download Policy: Content on the Website is provided to you AS IS for your information and personal use and may not be sold / licensed / shared on other websites without getting consent from its author.While downloading, if for some reason you are not able to download a presentation, the publisher may have deleted the file from their server.


- - - - - - - - - - - - - - - - - - - - - - - - - - E N D - - - - - - - - - - - - - - - - - - - - - - - - - -
Presentation Transcript
overview
Overview
  • V. Payload Integration Feasibility
    • Vehicle Integration
    • Electronics
    • Deployment Testing
  • VI. Test Plans and Procedures
  • VII. Scale Model Flight Test
    • Test No. 1
    • Test No. 2
    • Flight Video
  • VIII. Education Engagement
    • Plan
    • Status
  • Vehicle
    • Overview
    • Static Stability Margin
  • Motor
    • Selection
    • Weight to Thrust Ratio
  • Launch Rail
  • Recovery
    • Configuration
    • Deployment Sequence
    • Parachutes
    • Testing

Preliminary Design Review

i vehicle
I. Vehicle

A. Overview: Configuration and Dimensions

46”

Nose Cone

Main Parachute Bay

36”

Recovery Avionics

174.25”

Drogue Chute -

Payload Bay

42”

Motor Bay

40”

9.5”

11.2"

18”

9.5”

3”

Preliminary Design Review

i vehicle1
I. Vehicle

A. Overview: Nosecone

  • Shape
  • Performance 1) Superior, 2) Good, 3) Fair, 4) Poor

Von Karman

Preliminary Design Review

i vehicle2
I. Vehicle

A. Overview: Airframe

  • Cardboard and Fiberglass

Preliminary Design Review

i vehicle3
I. Vehicle

A. Overview: Fins

Leading Edge

Aft

Edge

Span

Tang Edge

Original Trapezoidal Design

Fins On Motor Mount

Modified Trapezoidal Design

Preliminary Design Review

i vehicle4
I. Vehicle

B. Static Stability Margin

CG minus CP

21.94"

2.31

=

=

=

Stability Margin

Diameter of Rocket

9.48"

Preliminary Design Review

ii motor
II. Motor

A. Selection: Requirements

Preliminary Design Review

ii motor1
II. Motor

A. Selection: Thrust Curve

Avg. Thrust

Avg. Thrust = 1,953 N

Total Impulse = 9,181 N-sec

Burn time = 4.7 s

Preliminary Design Review

ii motor2
II. Motor

B. Thrust to Weight Ratio

Mass Conversion

0.02834 kg

Massrocket = 1399.68 oz. =

= 39.66 kg (loaded)

1 oz.

Thrust to Weight Ratio

Thrust

Thrust

1,953 N

=

=

=

Weight

(Mass) (Gravity)

(39.66 kg) (9.807 m/s2)

5.02 > 1

Preliminary Design Review

iii launch rail
III. Launch Rail

Exit Velocity

66.82 ft/s

Unistrut Rail

Actual Launch Pad

Preliminary Design Review

iv recovery
IV. Recovery

A. Configuration

Separation at Nose Cone

Rocket System

Main Chute with Kevlar Protector

PVC Black Powder Ejection Containers

Recovery Avionics

Payload System

CO2 Ejection Cartridges

Drogue Chute

CO2 Release Device

Main Chute (in Deployment Bag)

Drogue Chute

Advanced Retention and Release Device

Payload

Separation at Fin Can

Preliminary Design Review

iv recovery1
IV. Recovery

B. Deployment Sequence

3

CO2 (16 g)

Black Powder (2.3g)

Preliminary Design Review

iv recovery2
IV. Recovery

C. Parachutes

Payload(6-8lb load)

Rocket(71lb load)

Main

Drogue

Main

Drogue

SkyAngle

Classic II

Spherachute

Plus

SkyAngle

Classic

SkyAngle

Cert 3, XXL

Type:

17-22 ft/s

80 ft/s

17-22 ft/s

100 ft/s

Descent:

64 oz.

Weight:

5 oz.

13 oz.

.5 oz.

105"

52"

36"

18"

Preliminary Design Review

iv recovery3
IV. Recovery

D. Testing: Avionics

Changes in pressure simulate changes in altitude

Vacuum

Air Tight Bag

Inflate

Hose

Air Pump

Avionics Board

Preliminary Design Review

iv recovery4
IV. Recovery

D. Testing: Sub-scale Ejection

Preliminary Design Review

v payload integration
V. Payload Integration

A. Vehicle Integration

Preliminary Design Review

slide18

V. Payload Integration

B. Electronics: Integration

UV

Computer

Serial Port

Arduino

Micro-

Controller

Solar

Irradiance

GPS

Temp/Hum

Barometer

UV

Gyro

Preliminary Design Review

v payload integration1
V. Payload Integration

B. Electronics: Testing (Solar Irradiance Sensor)

Connect to computer

Sensor Readings (Control)

100

101

100

101

101

101

100

100

101

100

101

100

100

Constant Readings

LED verification

Preliminary Design Review

v payload integration2
V. Payload Integration

B. Electronics: Testing (Solar Irradiance Sensor)

Test Sensor

Verify Sensor Readings (Variable)

100

101

100

47

101

100

100

47

101

100

101

48

100

Reading Anomalies

Preliminary Design Review

v payload integration3
V. Payload Integration

C. Deployment Testing: Lab Verification

Lab tests verified leg mechanism worked as designed

Spring Loaded Action

Leg Mechanism Components

Preliminary Design Review

v payload integration4
V. Payload Integration

C. Deployment Testing: Field Verification

Field tests reveal flaws in design and construction

Uneven Landing

Even Landing

Preliminary Design Review

v payload integration5
V. Payload Integration

C. Deployment Testing: Conclusion

  • Fix legs after deployment
  • Add redundancy dampening system under bottom plate
  • Install carbon fiber tubes around rods, in between plates

Preliminary Design Review

vi test plan and procedures
VI. Test Plan and Procedures
  • Construction Methods
  • Pre – Subscale Launch
    • Ejection charge
    • Avionics (Vehicle and Payload)
  • Subscale Launch
    • RockSim Verification
    • Recovery
    • Payload Ejection and Recovery
  • Pre – Full Scale Launch
    • Ejection
    • Avionics (Vehicle and Payload)
    • Payload Landing
  • Full Scale Test

Preliminary Design Review

vii scale model flight test
VII. Scale Model Flight Test

A. Test No. 1

  • Purpose
  • Verify RockSim calculations
  • Systems Testing: Airframe, Avionics, Recovery
  • Plan
  • Launch without payload
  • Launch with payload

Preliminary Design Review

vii scale model flight test1
VII. Scale Model Flight Test

A. Test No. 1: Results

  • Main chute deployed early
  • Cause: Incorrect manufacturing of
  • avionics bay
  • Solution: Label and triple check
  • Second Launch Aborted
  • Cause: Unsuccessful assembly due to low temperatures and body
  • tube contraction
  • Solution: Test assembly during similar conditions prior to launch
  • make necessary adjustments

Preliminary Design Review

vii scale model flight test2
VII. Scale Model Flight Test

B. Test No. 2

  • Purpose
  • Verify RockSim calculations
  • Vehicle Tests: Avionics
  • Recovery
  • Payload Tests: Ejection
  • Deployment
  • Recovery

Preliminary Design Review

vii scale model flight test3
VII. Scale Model Flight Test

B. Test No. 2: Results

Recovery bay shock cord snapped

Fin can descended without chute

Fin can bulkhead damaged upon impact

Payload ARRD fired, but

payload main chute tangled

did not deploy

Preliminary Design Review

vii scale model flight test4
VII. Scale Model Flight Test

C. Flight Video

Preliminary Design Review

viii educational engagement
VIII. Educational Engagement

A. Plan

We strive to promote higher education in mechanical and aerospace engineering through teaching community youth about the math, science and excitement high powered rocketry.

Preliminary Design Review

viii educational engagement1
VIII. Educational Engagement

B. Status

Completed Engagements

Boys and Girls Club

Oct 15

Oct 19

YMCA – Raleigh, NC

Nov 13

Pisgah Astronomical Research Institute

Jan 14

Baileywick Elementary School

Planned Engagements

Marbles Kid's Museum

Feb 13

Baileywick Elementary School

Feb 18

YMCA – Durham, NC

Mar 02

NC Mathematics and Science

Education Network (MSEN)

Mar/Apr

Baileywick Science Expo

Mar/Apr

Preliminary Design Review