Preliminary Design Review California State University, Long Beach - - PowerPoint PPT Presentation

Preliminary Design Review

California State University, Long Beach USLI November 13th, 2017

System Overview

Launch Vehicle Dimensions

• Total Length 108in
• Airframe OD 6.17in. ID 6.00in.
• Couplers OD 5.998in. ID 5.775in.
• Motor Mount 75mm
• Centering Ring Thickness 0.2 in

Material Selection - Airframe, Nose Cone & Couplers

• Significantly stronger than

blue tube

• Much cheaper than carbon

fiber

• More environmentally

resistant than blue tube

• Low thermal and electrical

conductivity Fiberglass

Material Selection - Fins

Carbon Fiber

• Highest yield strength
• Highest strength to weight
• Great environmental

resistance

• Affordable for fins

Material Selection - Bulkheads & Centering Rings

• Stronger than wood
• Inexpensive
• Easily manufactured
• Adds stability to coupler

sections Aluminum

Material Selection - Miscellaneous

• Avionics tray will be 3D

printed using ABS material

• Epoxy for fin and centering

ring attachment is Aeropoxy Light epoxy

Motor Selection

• 75mm Cesaroni

4263-L1350-CS

• Provides sufficient thrust to

reach an apogee well over a mile

Stability

• From the tip of the nose cone
• Center of Gravity (CG)=68.73in
• Center of Pressure (CP)=85.05in
• Stability Margin=(85.05-68.73)/6.17in=2.64 cal

Flight Simulations

• Total Mass-42.0lbs
• Projected Apogee- 5467 ft
• Thrust-to-weight

ratio-7.21

• Velocity off rod -66.9ft/s

Recovery System

Altimeter Vendor Model Cost (1-5) Weight (1-5) Features (1-5) Integration (1-5) Total Eggtimer Eggtimer Quark 5 5 1 2 13 PerfectFlite Stratologger CF 4 4 3 4 15 MissileWor ks RCC2+ 4 4 3 3 14 MissileWor ks RCC3 Sport 3 2 4 4 13 Adept AltS2-50k 2 2 2 3 9 Altus Metrum Easy Mega 1 3 5 4 13

Recovery System (cont.)

GPS Unit Comparison Vendor Model Cost (1-5) Weight (1-5) Dimensions (1-5) Integration (1-5) Total Transolve BeepX 5 2 1 2 10 Eggtimer Eggfinder 4 4 1 2 11 BigRedBe e BRB900 TX/RX 3 4 3 4 14 Altus Metrum TeleMetrum 3 4 3 3 13 Altus Metrum TeleMega 2 4 1 4 11

Recovery System (cont.)

• 13” Coupler Piece
• U-Bolt - 1,075 lb Maximum

Capacity (Nylon Harness)

• Primary and Backup

Altimeters

• BRB900 GPS Tracker
• Rotary Switch

Recovery System (cont.)

Type of Parachute Parachute Size and Model Location Relative Descent Velocity (fps) Drogue Parachute 20" FC TARC Low and Mid Power Parachute Nose Cone + Payload Bay Aft End 92.99 Main Parachute 84" FC Iris Ultra Standard Parachute Propulsion Bay Forward End 17.80

Recovery System (cont.)

Wind Speed (mph) Wind Speed (fps) Drogue Drift (ft) Main Drift (ft) Total Drift (ft) 5 7.33335 376.958952 6 205.9929775 582.9519301 10 14.6667 753.917905 2 411.985955 1165.90386 15 22.00005 1130.87685 8 617.9789326 1748.85579 20 29.3334 1507.83581 823.9719101 2331.80772

Recovery System (cont.)

Kinetic Energy for Each Independent Section Upon Landing Section Weight (lb) Mass (slugs) Descent Velocity (ft/s) Kinetic Energy (lb-ft) Payload Bay 13.879 0.431373199 17.80 68.3381421 9 Avionics Bay (After Event 2) 4.769 0.148225289 17.80 23.4818502 8 Propulsion Bay 12.983 0.403524623 17.80 63.9263707 8

Recovery System (cont.)

Rover

Rover Overview

• Ground clearance
• Payload Space
• Distance
• Solar panel

Rover: Design Considerations

• Cylindrical Rover
• Stability, complexity, volume

efficiency

• Triangular
• Able to deploy in multiple
• rientations.
• More possibilities of failure.
• Rectangular
• Wheg wheels
• Simple design

Rover: Design Choice

• Triangular
• Able to deploy from any
• rientation.
• Bogie system
• Gearbox

Rover: Design Choice

• Triangular
• Maximizes available space in

rocket.

• Houses all electronics inside the

body.

Rover Controls and Electronics

• Controller
• Arduino Nano
• Motorshield
• Sensors
• Inertial Measurement Unit (IMU)
• Rangefinder
• Control
• Yaw Suppression
• Obstacle Avoidance

Rover Deployment Mechanism (RDM)

RDM Summary

Purpose: Remotely deploy the rover from the internal structure of the launch vehicle. Design Choice:

• Single motor
• One threaded rod and two non-threaded rods
• Load is driven along threaded rod through a matching

threaded nut

Mechanical/Hardware

• Rotary to linear system for load translation

○ Motor attached to threaded rod ○ Threaded nuts attached to the rover

• Bulkhead with threaded nut

Electronics/ Control

• Remotely activate the system

○ 2.4GHz Digital Transmitter/Receiver

• Motor control

○ Arduino Nano Microcontroller ○ L298N H-Bridge ○ 11.1 V LiPo Battery

• Provide motor feedback

○ rotary encoder

RDM Schematics

Remote rover deployment switch initiated Rocket lands Electric motor spins the threaded rod in the loosening direction The nose cone translates along the rod and detaches. The rover continues to translate, and pushes the nose cone away from the airframe. The rover falls off the rod and initializes the system.

Airbrake Summary

• Main Goal: Ensure that the

rocket achieves target apogee by correcting upward drift velocity after engine cutout.

• Mechanics: airbrake flaps are

deployed by use of a linear actuator.

• Control: triggering the actuation
• f the flaps to maintain target

velocity.

Airbrake mechanics

• A linear actuator with a 2” stroke

will be used to deploy the flaps from the rocket.

• The actuator will pull up causing

the linkage arms to straighten, deploying the flaps.

• 4 flaps are used to maximize drag

without compromising the structural integrity of the rocket.

Air Brake Control

• Electronics
• 2” Stroke electric linear actuator
• Arduino Nano microcontroller
• Sensors
• Pitot Tube Airspeed Sensor
• BMP280 Barometer
• 6 DOF IMU
• Control
• Correct for error in velocity
• Modeling of system to determine timing, duration, and

deflection of flaps

• Closed versus open-loop system

Significant Failure Mode - Launch Vehicle

• Tail Fins shear off during flight

○ Fins are not properly secured to airframe ○ Rocket takes unpredictable flight path ○ Ensure adhesive used is strong enough to handle force of flight. Check adhesive for cracks before launch.

• Fins not properly aligned

○ Fins not assembled correctly ○ Rocket spins uncontrollably ○ Follow proper procedure when assembling fins

• Motor centering ring fails

○ Adhesive not properly applied to centring ring ○ Motor launch through the rocket ○ Construction procedures are followed for applying adhesive

Significant Failure Mode - Recovery

• Parachute does not deploy

○ Parachute gets tangled around rocket ○ Rocket will fall to ground at high velocity ○ Parachute will be integrated in a was to reduce risk of getting tangled

• Parachute has rip

○ Parachute gets ripped while deploying ○ Rocket descend to quick and get damaged upon impact ○ Team members will be careful during packaging of parachute

• Altimeter failure

○ Faultily altimeter ○ Parachute will not deploy ○ Use two altimeter for redundancy

Significant Failure Mode - Airbrakes

• Structural damage to airbrake system during launch

○ Material of airbrake not strong enough ○ Airbrakes will not deploy or become damaged ○ Verify through testing that airbrake can handle force of flight

• Airbrakes do not deploy at desired altitude

○ Programming failure ○ Rocket will not make desired altitude ○ Test airbrakes programming during subscale launch

• Airbrake flaps fly off during flight

○ Flaps made not to handle force of launch ○ Rocket become unstable ○ Verify through testing flaps can handle force of flight

Significant Failure Mode - Rover

• Rover damaged during landing

○ Impact of landing more than expected ○ Rover becomes inoperable ○ Make sure rover is secure in place before launch and test to ensure it can handle force of landing

• Rover damaged during flight

○ Rover not secure in place ○ Rover becomes damaged and inoperable ○ Ensure rover is secure put in the rocket

• Rover gets stuck on rock

○ Rover not capable of handling terrain ○ Rover gets stuck and unable to make distance requirement ○ Design rover to handle all terrains and verify that through testing

Significant Failure Mode - RDM

• RDM does not deploy when activated

○ Programing failure ○ Rover will not deploy ○ Verify that programing will act as desired through testing

• RDM deploys during flight

○ Electronic failure ○ Nose cone opens up during flight ○ Ensure electronics work properly through testing

• RDM becomes damaged during flight

○ RDM materials cannot handle force of launch ○ RDM damaged and rover will not deploy ○ Choose strong material that can handle the force of flight

Testing

• Wind tunnel

○ Test drag force and drag coefficient of airbrake flaps

• Drop testing

○ Test strength of components to ensure they can handle forces of flight and landing

• Programing and Electronic testing

○ Test all programs and electronics to ensure that they act in the way that they are supposed to

• Shock and Impact testing

○ Test all components of launch vehicle to ensure that they can handle the shock of the flight and the impact of landing

Project Plan

Timeline

Subscale Launch in November, Full scale built by February, Full scale launch in March

Airbrake Timeline

Educational Engagement

Event Date Estimated Attendees Girls Day at the Beach (1) 3/2017 100 Aerospace Rocket Symposium 9/7/2017 200 Girls Day at the Beach (2) 9/2017 200 Introduction to Engineering Presentations 11/2017 100 MAES Latinos in Engineering Bottle Rocketry 4/2018 60 High School Engineering Presentation 12/2018 500 TOTAL 1160

Budget-Expenses

Subteam Projected Expenses RDM $178.84 Rover $553.58 Avionics $538.63 Recovery $517.10 Launch Vehicle $2,295 Airbrake $137.83 Business $8,670 Total $13,870.91

Budget-Income

Source Income

College of Engineering $4,200 AIAA - CSULB $1,500 Fundraisers $1,500 ASI Travel Grant $7,000 Sponserships $600 Total $14,800