PRELIMINARY DESIGN REVIEW 2015 NASA STUDENT LAUNCH FLORIDA - - PowerPoint PPT Presentation

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PRELIMINARY DESIGN REVIEW 2015 NASA STUDENT LAUNCH FLORIDA - - PowerPoint PPT Presentation

Dec 31, 2023 117 likes •435 views

PRELIMINARY DESIGN REVIEW 2015 NASA STUDENT LAUNCH FLORIDA INTERNATIONAL UNIVERSITY (FIU-ASME) MAXI-MAV TEAM ORGANIZATION T eam Leader: Giancarlo Lombardi NAR Level 1 certified Safety Officer: Maryel Gonzalez NAR

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SLIDE 1

PRELIMINARY DESIGN REVIEW 2015 NASA STUDENT LAUNCH

FLORIDA INTERNATIONAL UNIVERSITY (FIU-ASME) MAXI-MAV

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SLIDE 2

TEAM ORGANIZATION

T eam Leader: Giancarlo Lombardi

NAR – Level 1 certified

Safety Officer: Maryel Gonzalez

NAR – Level 1 certified

Lead Designer: Christopher Hayes

Mentor: Joseph Coverston

TRA – Level 2 certified

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SLIDE 3

MISSION STATEMENT

FIU ASME will design and build Autonomous Ground Support Equipment (AGSE) that will be capable of performing on-pad

  • perations to prepare a high-powered rocket for launch that will

be capable of reaching altitudes no greater than 3000 ft above ground level. In addition, the AGSE will recover a payload located

  • utside the rocket’s mold line and insert the payload into the

rocket’s payload bay.

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SLIDE 4

CHANGES SINCE PROPOSAL

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SLIDE 5

VEHICLE CHANGES

Material: Carbon Fiber -----> Fiberglass

issues with carbon fiber blocking radio transmissions from the internal GPS units.

Recovery: T wo ----->Three parchutes

Initial design: drogue doubled as our main after payload separation (high decent rates.)

The payload bay and upper airframe will now have a dedicated main parachute.

Fins: Four -----> Three trapezoidal fins.

better center of pressure and overall rocket stability in our simulations.

Motor: K2045 -----> J1520

projected altitude of 3155 feet (previously 4453 feet.)

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SLIDE 6

AGSE CHANGES

No changes

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SLIDE 7

PROJECT PLAN CHANGES

 NEW Safety Officer: Maryel Gonzalez (NAR – Level 1 Certified)

 Carmela

Vallalta (previous Safety Officer) received a Spring 2015 internship with NASA Dryden Flight Research Center

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SLIDE 8

VEHICLE CRITERIA

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SLIDE 9

MISSION SUCCESS CRITERIA

The vehicle’s mission will be considered to be a success if the following criteria are met:

The vehicle’s apogee does not exceed 5000 ft above ground level.

The payload is ejected at 1000 ft.

The vehicle’s descent is controlled and does not result in damage to itself, property, or people.

No safety violations occur.

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SLIDE 10

LAUNCH VEHICLE SUMMARY

 Length: 117 inches  Inner Diameter: 3.9 inches  Unloaded: 13 lbs; Loaded: 15.2 lbs  Motor: J1520, Pro 54mm – 3G  Dual-Deployment

 Drogue deploys at apogee, mains deploy at 1000 ft.

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SLIDE 11

DESIGN AT SYSTEM LEVEL

Airframe materials:

3.9” Phenolic tubing

Fiberglass

Three independent sections:

Lower Airframe

Payload Bay

Nosecone & Upper Airframe

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SLIDE 12

AIRFRAME

Airframe Material PML Phenolic Fiberglassed PML Phenolic Giant Leap Fiberglass Tubes

Property

Weighing Factor Unit of measure Value Score T

  • tal

Value Score T

  • tal

Value Score T

  • tal

Strength

4 High Med Low low 3 12 High 10 40 High 10 40

Cost

4 $ $23.50 10 40 $35.0 9 36 $97.28 4 16

Manufacturability

2 Easy-Hard Easy 10 20 Hard 4 8 Easy 10 20

Weight

1

  • z

20.4oz 10 10 40oz 5 5 30oz 7 7 T

  • tal 82

T

  • tal 89

T

  • tal 83
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SLIDE 13

NOSECONE

Nose Cone Material PML Plastic Intellicone Nosecone Fiberglassed PML Plastic Nosecone Shockwave Rocketry Fiberglass Nosecone

Property

Weighing Factor Unit of measure Value Score T

  • tal

Value Score T

  • tal

Value Score T

  • tal

Strength

6 High Med Low Low 2 12 High 10 60 High 10 60

Cost

4 $ $25.0 10 40 $30.0 8 32 $56.0 5 20

Manufacturability 2

Easy-Hard Easy 10 40 Medium 5 10 Hard

Weight

1

  • z

10oz 10 10 25oz 5 5 15.1oz 7 7

Contains interior Payload bay

3 Y/N Yes 10 30 Yes 10 30 No T

  • tal 132

T

  • tal 137

T

  • tal

87

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SLIDE 14

NOSECONE – UPPER ELECTRONICS BAY

Intellicone was chosen for nosecone

Decided to incorporate electronics bay in order to decrease overall rocket length

Altimeter: Perfectflite Stratologger

GPS unit: TK102

Buzzers will be present to perform audible beeps for easy retrieval

Middle bulkhead ensures altimeter is physically separated from all

  • ther components
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SLIDE 15

PAYLOAD BAY

Rail system

Bay opens to accept payload insertion

Payload reception tube made out of 3” cut-out airframe

Stepper motor located on bottom bulkhead of sliding plate drives the translation

Powered externally by AGSE

Quick-release power cable will be used – it will be pulled off the face of the vehicle when the rail is lifted

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SLIDE 16

LOWER ELECTRONICS BAY

Contains:

Altimeter: Perfectflite Stratologger (x2 units - redundancy)

GPS: TK102

PVC cleanout plug will be used for its strength

Subjected to high axial forces – ejection and deployment – through the eyebolt

Bolts extend through PVC supporting electronics

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SLIDE 17

LOWER AIRFRAME / BOOSTER SECTION

Motor choice: Cesaroni Pro54 - J1520 3G

Three trapezoidal fins

Root chord length: 4 in

Tip chord length: 1.75 in

Thickness: 0.063 in

Sweep angle: 14.3 degrees

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SLIDE 18

RECOVERY SYSTEM

Drogue deployed at apogee (3000 ft.)

Dual main deployment at 1000 ft

T

  • p section is jettisoned containing the payload bay

Lower airframe descends on 44” main parachute

Upper airframe descends on 12” drogue and 54” parachute

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SLIDE 19

RECOVERY ELECTRICAL SCHEMATICS

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SLIDE 20

AGSE CRITERIA

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SLIDE 21

AGSE SCHEMATIC

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SLIDE 22

RAIL LIFT

Rail: 8 ft. 1” 80/20 rail

Linear Actuator: 180 lbs thrust

Retracted length: 18inches

Travel: 12 inches

1” foot is located below launch rail to counteract moment produced by the rail and the rocket sitting on the rail

Also serves to mount the linear actuator and push up on the rail

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SLIDE 23

ROBOT ARM

Single beam arm with robotic claw will rotate to pick up the payload from the ground.

The arm will follow its circular arc path to drop the payload into the rocket

The robot arm will be mounted on a platform offset by one arm length from the rocket’s payload bay

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SLIDE 24

IGNITER INSERT

Igniter will be placed on a rod attached to a rack

The igniter will initially start below the thrust plate to increase pad safety

The rack will be pushed upwards (towards the rocket’s motor) through the rotational motion of a pinion

Once the igniter has been inserted, a clamp will hold the igniter in place

The rod will be retracted downwards to decrease damage from motor ignition

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SLIDE 25

AGSE ELECTRICAL SCHEMATIC

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SLIDE 26

PROJECT PLAN

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SLIDE 27

RISK ANALYSIS

Risk Likelihood Impact Mitigation Late completion of Reports and Presentations Medium High Simultaneously design rocket and write report to keep updated documentation at all times. Late completion of rocket and/or AGSE construction Medium High Order parts and test components early to identify potential problems and allow for time to rectify them. Team member decides not to continue working

  • n project

High Medium Continuously recruit and educate students who are interested in rocketry and the NASA Student Launch competition Required budget is not met Medium High Set fundraising goals higher than necessary to account for any possible setbacks we may encounter Full scale rocket test failure Low Medium Follow mission performance criteria checklist prior to launch AGSE system fails to perform required function Low High Perform extensive testing of AGSE before final launch

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SLIDE 28

TIMELINE

November 5 Preliminary Design Review (PDR) report due 6 Start ordering parts for subscale vehicle 10 Begin fundraising efforts by contacting company sponsors 14 Start constructing AGSE components 19 PDR video teleconference 21 Begin constructing subscale vehicle 29 Ground ejection test December 3 Begin constructing full scale rocket 13 Subscale flight test January 6 AGSE testing 16 Critical Design Review (CDR) report due 21-31 CDR video teleconferences February 1-4 CDR video teleconferences March 7 Full-scale flight test 16 Flight Readiness Review (FRR) report due 18 FRR video teleconferences April 7 Team travels to Huntsville, AL 7 Launch Readiness Reviews (LRR) 8 LRR’s and safety briefing 12 Backup launch day 29 Post-Launch Assessment Review (PLAR) posted

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SLIDE 29

EDUCATIONAL ENGAGEMENT

Partnered with FIU ‘Engineers On Wheels’

provides local K-12 students with fun and interactive presentations on varying fields of engineering

Plan to reach out to 250 middle school-aged students

Will produce basics of aerodynamics and principles of rocketry presentation

Powerpoint with live demonstrations of actual high-powered rockets (owned by team members)

Water

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SLIDE 30

Questions?