Critical Design Review - CAL POLY POMONA · PDF fileCritical Design Review ... Pomona, CA...

Critical Design Review

1/27/2017

NASA Student Launch Competition 2016-2017

California State Polytechnic University, Pomona

3801 W Temple Ave, Pomona, CA 91768

1/27/2017 California State Polytechnic University, Pomona CDR 1

Agenda

Subscale Model Overview

Final Primary Payload Overview (RIS)

Final Secondary Payload Overview (FMP)

Launch Vehicle Interfaces

Project Plan

Probability of Success

Introduction

Final Launch Vehicle Overview

Launch Vehicle Performance

Recovery Subsystem

Mission Performance Predictions

Test Plans and Procedures


Introduction





Project Plan


Introduction



Recovery Subsystem




Introduction


Advisors and Mentors

Dr. Donald L. Edberg•Faculty advisor•Professor of Aerospace Engineering

Dr. Todd Coburn•Structural mentor•Professor of Aerospace Engineering

Rick Maschek•Rocketry mentor•Tripoli Rocketry Association level 2 certification


Team WBS

• Team lead

• Deputy/systems engineer

• Safety officer

• Structures sub-team

• Aerodynamics sub-team

• Avionics sub-team

• Support sub-team


Task Force WBS







Project Plan


Introduction



Recovery Subsystem




Major Changes Since PDR


Nose Cone

• Parabolic nose cone to Elliptical nose cone

Weight and length

• Length increased from 7.3 ft. to 8.92 ft.

• Weight increased from 28.1 lb. to 48.38 lb.

Coupler size

• Increased from 7 in. to 13.5 in.

Main parachute

• Increased from 27.4 ft2 to 80 ft2

Drogue Parachute

• Decreased from 11.25 ft2 to 5 ft2

Avionics, Recovery Bay

• Redundant GPS systems in nose cone

• Recovery Avionics and Payload Electronics Sleds Redesigned

Motor Bay

• Motor changed from L1150P to L1120W-O

• Size of motor bay slightly increased to accommodate new motor

Final Launch Vehicle



1/27/2017 11California State Polytechnic University, Pomona CDR






Elliptical Nose Cone:

•Offers highest structural Integrity compared to previous Parabolic Design

•Aerodynamic blunt tip design offers low Cd

•Housed GPS sled for tracking

•3D printed using 100% fill PLA plastic

GPS Sled



Recovery Sub Systems:

• This encompasses the Main Parachute Bay, Recovery Bay, and Drogue Bay

• Recovery bay includes the flight altimeters

Main Parachute Bay Drogue Parachute Bay

Access to

Outside



Fragile Materials Protection Bay (FMP):

•Secondary payload we are testing

•The “Pill” will contain packing material for fragile object

•It will be suspended by surgical tubing within a custom frame within the body tube to dampen oscillations

•Entirely self contained, assembled outside body tube and inserted within the tube when ready for flight

The “Pill”



RIS Payload/ Observation Bay and Motor Bay:

•Most technically complex section of rocket

•Fin Integration of the rocket Including attachments

•Motor Integration and Retention for structural integrity

•RIS Payload accomplishing roll of rocket

•Observation system for visual confirmation of roll of rocket

Fin Integration

Motor

Integration

RIS Payload

Observation


Payload Dimensions


Design Features

Elliptical Nose

Cone: Greater

Structural Integrity

Piston recovery

System: Offers a

more reliable

parachute ejection

FMP Bay: Secondary payload for

more scientific data

Fins: 3D printed material with

actual NACA airfoil design for

optimum Cd and Cl

Motor Bay: Hand made

carbon fiber composite

motor tube

RIS Bay: Main payload

for roll induction using

coupled servo design

Aileron: Used to

create lift with

varied angle of

attacks


Final Motor Selection and Justification

Aerotech L1120W

Performance

• 5148 feet simulated

• 92% L motor

• Thrust-to-weight ratio: 4.60

• Rail Exit Velocity: 55.52 fps

Propellant Weight 6.08 lbm

Total Weight 10.27 lbm

Average Thrust 220.91 lbf

Peak Thrust 349.57 lbf

Total Impulse 4922.22 Ns

Burn Time 5.01 s







Project Plan


Introduction



Recovery Subsystem





Stability Analysis

OpenRocket Hand Calculations

Stability Margin 2.65 Calibers 3.00 Calibers

Center of Gravity (from Nose Cone) 66.62 in 66.98

Center of Pressure (from Nose Cone) 82.95 in 85.51

Outer Diameter 6.16 in

Total Length 107 in

Apogee: 5148

Max. velocity: 574 ft/s

Mach number= 0.52

1/27/2017California State Polytechnic University, Pomona CDR

22

Launch Vehicle Mass Statement

Mass Statement

Component Total Mass

(lbs.)

Mass

Margin %

Module 1: Nose cone, GPS 2.53 5.22%

Module 2: Main and Drogue

Parachutes, Avionic Bay,

FMP

11.55 23.85

Module 3: Payload Bay,

Observation Bay, Motor Bay34.36 70.95%

Total 48.43 100%

After Burnout 42.24 -12%


Recovery Subsystem





Project Plan


Introduction



Recovery Subsystem




Parachute OverviewMain Parachute Drogue Parachute

• Toroidal Parachute

• 80 ft2 effective area

• 400 lb paraline

• Manufactured by Fruity Chutes

• Cruciform Parachute


• 550 lb paraline

• Manufactured in-house


Parachute Sizes

Main Parachute Drogue Parachute


• 120’’ Do

• 36 oz

• 200 in3 packing volume


• 3.0’ Do

• 3.90 oz

• 14 in3 packing volume


Recovery Harnesses

Main Parachute Drogue Parachute

• 40 ft. length

• Τ1 2 ’’ Kevlar 2200 lb.

cord

• Τ1 4’’ Steel Quicklinks

at all 3 attach points

• Attaches to 3000 lb.

swivel linking to

main

• Mounted to rocket

by Τ1 3’’ Steel U-bolt

• 40 ft. length

• Τ1 2’’ Kevlar 2200 lb.

cord

• Τ1 4’’ Steel Quicklinks

at all 3 attach points

• Attaches to 1500 lb.

swivel linking to

drogue

• Mounted to rocket by

Τ1 3’’ Steel U-bolt


Recovery Avionics: GPS and Altimeters

Major components•Primary PerfectFlite stratologgerCF

•Secondary PerfectFlite StratologgerCF

•Two 1000 Mah Lipo batteries

StratologgerCF Primary Secondary

Deployment of

drogue

Apogee (5280 ft) One second post

Apogee

Deployment of

Main

700 ft 500 ft

Subscale Assembly1/27/2017 California State Polytechnic University, Pomona CDR 28


Ejection Charges- Fore Charge:

•Ejects main Parachute

•Attached to fore Bulkhead of recovery bay

- Aft Charges:

•Ejects drogue parachute

•Attached to aft bulkhead of recovery bay

- Recovery Bay EMI shielded with copper foil tape



Major components• BRB900

• Trackimo

GPS Operating

frequency

Operating range

BRB900 900 MHz 6 miles

Trackimo 850/1900MHz Indefinite (Requires cell

reception)

BRB900 Trackimo



GPS Specifications

BRB900

•850 mAh single cell LiPo

•ublox 7 GPS chipset

•XBee pro HP S3B – 900 MHz

Trackimo

•600 mAh Li-ion battery

•Quad Band frequency – In US 850 and 1900 MHz

GPS sled fitted in nose cone







Project Plan


Introduction



Recovery Subsystem




Descent Rates

•Post burn rocket weight is 42.24 lb

•Main chute area is 80 ft2

•Drogue chute are is 5 ft2

Component Max Velocity

Terminal Main

Velocity

Terminal Drogue

Velocity

(ft/s) (ft/s) (ft/s)

Nose Cone 55.0 13.5 76.6

Forward Rocket Section 21.4 13.5 76.6

Aft Rocket Section 13.5 13.5 76.6


Kinetic energy at key phases of the mission

•Main Parachute area is 80 ft2

•75 ft-lbf Max Kinetic energy of module at touch down

Component MassMax

Velocity

Terminal

Main

Velocity

Terminal

Main KE

Terminal

Drogue

Velocity

Terminal

Drogue KE

(slugs) (ft/s) (ft/s) (ft-lbf) (ft/s) (ft-lbf)

Nose Cone 0.049 55.0 13.5 4.56 76.6 145

Forward

Rocket

Section

0.329 21.4 13.5 30.2 76.6 965

Aft Rocket

Section0.814 13.5 13.5 74.7 76.6 2391


Predicted drift from the launch pad with 5, 10, 15, 20 mph wind

•Note: For the 20 mph condition Main parachute deployment at 500 ft will cause drift outside of desired zone. To keep the rocket within the 2500 ft drift limit deployment of the main has to be reduced to 325 ft.

Wind Velocity (mph) Drift Distance (ft)

0 0

5 728

10 1456

15 2184

20 2912







Project Plan


Introduction



Recovery Subsystem




Test Plan Matrix

#Test

Requirement

Fulfilled

Team

ResponsibleTest Planned Status

Actual Test

CompletedVerification Method Success Criteria

1

Subscale

Launch

VR1.2.5, VR1.4,

VR1.9, VR1.16,

VR1.16.1.

VR1.17.1,

RSR2.10

ALL 12/10/2016 Done 12/10/2016

The launch of the subscale rocket is a

holistic overview of procedures. The

subscale launch was intended to be a half-

scaled model of the full-scale launch

vehicle and was designed as such. To that

effect, the launch of the subscale is

primarily intended as a proof of concept for

the stability margin of the full-scale design.

(1) After launch, the launch will be

recoverable and reusable (2) Subscale

launch successful (3) On-board

altimeter capable of recording peak

altitude (4) recovery system functions

as designed

2

Full-scale

Launch

VR1.1, VR1.4,

VR1.17, VR1.17,

RSR2.10

ALL2/11/2017,

2/18/2017Not Done TBD

The team will run through the entire launch

procedure and analyze the resulting data

to determine what changes must be made,

if any, to the full-scale launch vehicle prior

to the competition

(1) Launch vehicle reaches an apogee

of 5,280 ft. 75 ft (2) Launch vehicle is

recoverable and usable after launch.

(3) Full scale test launch occurs prior

to FRR. (4) Recovery system functions

as designed.

3

Drogue

Parachute

Test

RSR2.1 Aerodynamics 1/28/2017 Not Done TBD

Attach a 5lb weight to the parachute and

view performance of parachute and take

measurements

(1) Inflation of Drogue (2) Matching

estimated drop test specimen descent

time

4

Main

Parachute

Test

RSR2.1 Aerodynamics 1/28/2017 Not Done TBD

Attach a 10lb weight to the parachute and

view performance of parachute and take

measurements

(1) Inflation of Drogue (2) Matching

estimated drop test specimen descent

time


Test Plan Matrix Continued

TestRequirement

Fulfilled

Team


Actual Test


5

Ejection Charge

TestRSR2.2 Avionics 1/29/2017 Not Done TBD

Ejection charge is sufficient to deploy

the recovery system

(1) The sections separate with enough energy to

break shear pins and pull the entire length of the

shock cord taunt (2) The body tube does not rip or

tear near shear pin interface or bulkhead screw

interface (3) Parachute and shock cord undamaged

from ejection charge hot gasses

6

Recovery Avionics VR1.3, RSR2.12 Avionics 1/29/2017 Not Done TBD

Recovery shielding must be capable

to blocking radio frequency

transmissions

(1) Radio frequency signals substantially reduced

within the recovery bay

7

RIS Test: Wind

Tunnel

ER3.3.1, ER3.3.1.1,

ER3.3.1.2, DR1.0ALLRIS 2/4/2017 Not Done TBD

Measure the side force and

moments experienced by the RIS at

a zero-degree deflection then at a

deflected position

(1) Accurate data for Normal force, pitching

moment, yawing moment, rolling moment, drag is

collected at different speeds and angles of attach

(2) Flow conditions are matched to subscale wind

tunnel testing

8

FMP TestER3.4.1, ER3.4.1.1,

ER3.4.1.2, ER3.4.1.6FMP 2/4/2017 Not Done TBD

Drop fragile material system from

height of 68 ft. to mimic max impulse

experienced during rocket flight.

(1) Fragile material unbroken (2) Fragile material

system re-usable

9

Body Tube

Materials

Properties Test for

Crippling

DR4.1 Structures 1/21/2017 Not Done TBD

(1) Static Load Test: load applied to

continuous section of a body tube (2)

Dynamics Drop Test: simulate same

impulse during launch on body

section

(1) The body tube will experience absolutely no

localized crippling (2) The body tube will maintain

its structural integrity with no permanent

deformations to the material (3) Fastener bulkhead

attachment point holes located on body tube will

show no signs of tearing, ripping, or shearing at

these specified locations


Test Plan Matrix Continued

TestRequirement

Fulfilled

Team


Actual Test


10

Bulkhead Shear

and Shear Tear-

Out Test

DR4.2 Structures 1/21/2017 Not Done TBD

(1) Static Load Test: load applied to

bulkhead (2) Dynamics Drop Test:

simulate same impulse during

launch on bulkhead

(1) The bulkhead will experience no shearing at fastener

locations (2) The bulkhead will maintain its structural integrity,

meaning the material the bulkhead is made from will not show

any sign of damage or material degradation (3) Fastener

bulkhead attachment point holes will show no signs of yielding

due to bearing stress thus deforming the area around the

fastener

11

PLA Shear Test DR4.3 Structures 1/21/2017 Not Done TBD

verify the impulse force caused by

the main parachute does not cause

the screws to shear through the

nosecone during midflight

(1) The PLA will experience no shearing at the fastener

locations (2) The PLA will maintain its structural integrity, with

no permanent deformation or any signs of damage to the

material

12

Water Tunnel

TestDR4.4 Aerodynamics 1/25/2017 Not Done TBD

Full scale test models of nose cone

and fins will be placed in water

tunnel

(1) Tests show flow is turbulent as is expected (2) No

separation occurs during the simulated flight envelope (3) No

vortices or other disturbances form on the rocket that degrade

performance (4) Clear and useable data can be drawn from

the tests

13

Wind Tunnel

TestDR4.5 Aerodynamics 1/23/2017 Not Done TBD

Compare theoretical data

calculated for the full-scale rocket

with experimental data from wind

tunnel; forces, moments, and drag

are reasonable

(1) Useable data is recovered from the testing (2) Data from

the test matches with models and known results

14

GPS Test DR5.3 Avionics 1/28/2017 Not Done TBD

Run the GPS and see if it performs

properly, determining the accuracy

of the coordinates and proper

transmission

(1) Both systems still transmit properly when placed next to

one another (2) Both of the transmitted coordinates received

are similar to each other.


Test Plan Matrix ContinuedTest

Requirement

Fulfilled

Team


Actual Test


15

Observation

Subsystem TestER6.1.2, DR5.2 Avionics 1/28/2017 Not Done TBD

Recording for 20 minutes, extract the

video and watch to verify camera

record video. Follow same steps but

place the camera in the rocket at an

angle to view downwards

(1) Clear video recorded (2) Video

recorded for full duration

16

Arduino MEGA

2560 TestDR5.5 Avionics 1/28/2017 Not Done TBD

After circuit and code baseline

functionality established, system will

be attached to the rotation table at a

measured radius. Data points will be

taken at (1) Constant angular

velocities (2) Changing angular

velocities (angular acceleration)

(1) MEGA outputs viable data at 10

samples per second (2) 10 DOF

acceleration/gyroscope data matches

specifications within 5% (3) Rotation

table angular velocity (4) Rotation table

angular acceleration

17

10 DOF Test DR5.1 Avionics 1/28/2017 Not Done TBD

After circuit and code baseline

functionality established, system will

be attached to the rotation table at a

measured radius. Data points will be

taken at (1) Constant angular

velocities (2) Changing angular

velocities (angular acceleration)

(1) MEGA outputs viable data at 10

samples per second (2) 10 DOF

acceleration/gyroscope data matches

specifications within 5% (3) Rotation

table angular velocity (4) Rotation table

angular acceleration

18

Xbee Pro 900HP

TestDR5.4 Avionics 1/28/2017 Not Done TBD

A 2 mile distance test for data

transmission

The Xbee transmitting data at over 2

miles


Safety Plan

Personal HazardsHazard Cause Effect Pre –

Mitigation RAC

Mitigation Post - Risk

Personnel injury when working with chemicals

Chemical spill/splash

Exposure to chemical fumes

Skin, eye, and lung irritation

Mild to serve skin burns

Lung damage or asthma

3C – Medium

MSDS will be readily available in all labs at all times. They will be reviewed prior to working with any chemicals

Gloves and safety glasses will be worn when handling hazardous chemicals

All personnel will be familiar with locations of safety equipment including chemical showers and eye wash stations

4C – Minimal


Safety Plan

Launch Vehicle Failure Modes and Effects Analysis

Hazard Cause Effect Pre –

Mitigation

RAC

Mitigation Post – Mitigation

Rocket is

pitched in an

unwanted

direction

Aileron rotating in

the same

direction

• Personnel

Hazard

• Potential hazard

to surrounding

property

2B –

High

• Number of actuated

ailerons reduced from

four to two

• Ailerons mechanically

constrained to only

induce roll

2E – Low

Divergent

oscillation

around roll

axis

Payload control

system

malfunction

• Ground hazard

• Personnel

Hazard

• Loss of rocket

2B –

High

• Open loop control

system

• Autonomous control

2E – Low


Environmental Hazards

From

Environment:

To

Environment:

Safety Plan

Hazard Cause Effect Pre –Mitigation

RAC Mitigation Post –

Mitigation

Blue Tube

Warping ● Moisture

Absorption

● Heat

● Swelling 3C - Medium

● Avoid rainy weather ● Avoid transonic

velocities

4D -

Minimal

PLA Warping ● Heat ● Part

Deformation

2D - Medium ● Avoid surrounding

heat source

● Avoid transonic

velocities

4E -

Minimal

Wood

Warping ● Moisture

Absorption

● Swelling 3D - Low ● Avoid rainy weather 4E -

Minimal

Hazard Cause Effect Pre –Mitigation

RAC Mitigation Post –

Mitigation

Ammonium

Perchlorate ● Storage

Malpractice

● Contamination

● Wildlife

development

retardation

2B - High ● Store in designated

box ● Avoid unnecessary

transportation and

contact

2E - Low

Hydrochloric

Acid

● Motor

byproduct

● Corrosion

● Toxicities in

wildlife

2B - High ● Test in desolate

areas 2E - Low







Project Plan


Introduction



Recovery Subsystem




Subscale Launch Vehicle Scaling

•Diameter of Subscale was created to be ½ scale

•Subscale had a larger stability margin, but is still within the same range and greater than 2.0

•Lengths were not scaled

•Velocity values were not scaled either

•Acceleration values were higher to try to simulate larger loads on the rocket Scale Diameter Stability

Margin

Length Velocity Acceleration

Subscale 3” 3.3 77” 460 ft/s 11.3 (g)

Full Scale 6” 2.65 107” 574 ft/s 6.40 (g)


Subscale Flight Test Results

•All flight test data came from altimeter

•Apogee – 3122 ft

•Velocity profile came from altitude data, but extrapolated acceleration data was too noisy

•Velocity profile is a little noisy, but a curve fit helps get a better idea of the velocity profile

•Max Velocity about 460 ft/s


Predicted Flight vs True

•The predicted model for subscale performance is based on data obtained from open rocket

•The Matlab predictions are based upon an average thrust approximation for the J460 engine used

•The actual flight data is based on the position and time data collected from the Strattologger CF, velocity was then calculated

•The velocity data was very noisy so a curve fit can seen in red for better approximation




Predicted Flight vs Actual Flight



Drogue Video

Descent Time 36 s

Main Video

Descent Time 29 s

Drogue Predicted

Descent Time 38 s

Main Predicted

Descent Tine 26 s

Error 5.26 % Error 10.34 %


Drag Coefficient Models

Sub-Scale Full-Scale

Open Rocket 0.46 0.52

Excel 0.73 0.44

% Error 58.70 -15.38

Matlab 0.51 0.55

% Error 10.87 5.771/27/2017 California State Polytechnic University, Pomona CDR 51

Lessons Learned

•All models assume vertical flight and don’t account for disturbances or weather cocking

•The Cd obtained from the subscale launch is higher from than the predicted models due the weather cocking experienced by the subscale

•The discrepancy shows that simplistic models are good for initial estimates but ultimately wind tunnel testing and CFD analysis are needed for accurate calculations


Lessons Learned Continued

•Hand calculations are a necessity the teams initial open rocket model underestimated the height achieved, this was later corrected

•Pointed nose cones do not handle impacts well as a result the design was changed to a blunter elliptical

• Coupler size will be increased to reduce bending moments

•PLA plastic performed well and exceeded durability expectations

•Better planning for screw locations for body







Project Plan


Introduction



Recovery Subsystem




Final Design: RIS-B

• Minimizes mass burden on the

vehicle by taking advantage of the

low altitude flight profile of our

mission

• Challenging servo-mechanical

design and execution; yet within our

capabilities

• Design features mitigate chances of

erratic trajectories


Final Design: RIS

Overall Design Features:

• “Pull-pull” servo configuration

utilizing stranded steel cables

• Single set of actuating ailerons;

±24 deflection range

• Two physically coupled servos


56

Servo Block Assembly: Design Features

• Servos receive the same electrical

signal

• Configuration constrains ailerons to

counter-rotating motion

• (2) HS-7955TG Servos: operational

redundancy and double effective

torque

• Pulleys provide cable redirection

and allow lateral movement


1/27/2017 58

Hitec HS-7955TG Servos

Specifications

Motor Type: Coreless

Bearing Type: Dual Ball Bearing

Speed (4.8V/6.0V): 0.19 / 0.15

Torque oz-in. (4.8V/6.0V): 250 / 333

Torque lbf-in. (4.8V/6.0V): 15.6 / 20.8

Weight ounces: 2.29

Weight grams: 64.92

Justification

Aileron Area 8 in2

Max. Airspeed 750 ft/s

Max. Deflection 25

Torque Needed 220 oz-in (13.8 lbf-in)1/27/2017 59

Aileron Assembly


Torque Needed Using

Method Moment of Inertia Value (lbm*ft2)

I = mr2, r = 3.0 in 2.6

I = mr2, r = 3.5 in 3.6

OpenRocket 3.7

Assumed Value 4.0

𝜏 = 𝐼𝛼

𝜃 = 𝜔0𝑡 +1

2𝛼𝑡2

𝜃 = 4𝜋;𝜔0 = 0; 𝑡 = 5𝑠,

⇒ 𝛼 = 1.0𝑟𝑎𝑑

𝑠2

∴ 𝜏 = 4.0 𝑙𝑏𝑓 ∗ 𝑓𝑡


𝑑′ = 𝑟𝑏𝑑𝑦 + 𝑑0 + 0.5𝓁

⇒ 𝑑′ = 0.5 𝑓𝑡

𝐿 = 𝐹 =𝜏

𝑑′

⇒ 𝑳 = 𝟖 𝒍𝒃𝒇

Lift Provided by Aileron


62

0-5s post-burnout Vavg = 425 ft/s

Payload Bay Electronic Systems


PBE Block Diagram Overview


64

Payload Control System (PCS)

•Small and efficient open-loop servo control

•70+ Hz sampling rate

•Offloads data points to DCS

LIS331HH Accelerometer Operating Voltage 2.16 – 3.6 V

Current Consumption < 0.25 mA (normal mode)

Detection Range ±6g/±12g/±24g

Data Output 16 bit

Survivability 10,000g shock resistance

(for 0.1ms)

Operating

Temperature Range

-40 C to 85 C


Payload Control System Schematic


Data Collection System


Observation System: Raspberry Pi Zero


60W Power Switch; Power Consumption

System Microprocessor Expected Current Draw

Payload Control System

(PCS)

Arduino Nano v3.0 100 – 200 mA

Data Collection System

(DCS)

Arduino Mega R3 2560 350 - 500 mA

Observation System

(OS)

Raspberry Pi Zero v1.3 160 – 300 mA

Expected System Power Consumption Table (Battery #1)


Payload Integration

Aileron Section

attachment to axle

Fin with Airfoil

design and

aileron section

cut out

Integration of aileron

section with fin

Servo Arm used for

actuation


Payload Integration

Aileron has the

ability to turn up to

plus or minus 24

degrees

Lubricated joints

will offer low

friction for

maneuver


Payload Integration

Fin section

integrates with

bulkheads 1

through 4

Hose clamp holds the fins

in place and allows easy

removalCut away segments

for cabling


Payload Integration

Sled Integration for

RIS Electronics

(not shown here)Mounting attachment for

sled, allowing sled to be

removable


Payload Integration

Mounting attachment for

servos pulleys and cable

attachment

Mounting occurs on the

top end of the motor

block bulkhead

Note: More detailed

Drawings of system

present in previous

sections


Payload Dimensions and Mass Statement

Items Mass (oz)

Electronics associated with

Payload and Observation 26.096RMS-75/5120 Casing w/ forward

seal disk 45.630

75 mm aft closure 2.580

75 mm Forward Closure 12.125

Aeropack 75 mm Retainer 4.225

Motor 168.000

Motor Bay + RIS/Obs Bays + Fins 251.450

Total 510.106

Items Purpose Number of items Mass (oz)

HS-7955TG Servo Servos for Roll Induction System 2 4.586

4-40 Mounting Hardware Servo cabling, mounting hardware 2 1.764

11.1V, 2200mAh LiPo Payload Bay power supplies 2 14.010

Arduino Micro Controls Roll Induction System 1 0.230

Arduino MEGA 2560 Controls Data Collection System 1 1.306

Adafruit 10 DOF IMU DCS sensor 1 0.099

XBee Pro 900HP DCS transmitter 1 0.299

High Gain Antenna For XBee (adds 15mi+ range) 1 0.458

XBee Adapter For XBee 1 0.320

SD Breakout + Card DCS local data storage 1 0.130

Raspberry Pi Zero v1.3 Controls Observation System 1 0.300

Pi Camera v2 Camera for Observation System 1 0.180

Switch Switch for entire payload system 1 0.415

Misc. mounting hardware - Approx 2.000


Primary Payload Test Plans

• Objective: Develop Cl vs AoA relationship for aileron• Low speed wind tunnel tests; scale up results

• Objective: Verify strength and determine proper diameter of stranded steel cabling• Stress, tension tests

• Objective: Ensure proper detection of motor burnout• Accelerometer and various scenario testing







Project Plan


Introduction



Recovery Subsystem




• 3D Printed Plastic Container; “Pill”

• Filled with foam• Suspended in surgical tubing

net• Secured to removable

bulkhead

Final Secondary Payload Overview

78

• Central ring changed to separate into two pieces for easy removal of pill.

• Number of surgical tubes from 24 to 10.• Coupler enlarged to 12” allowing for more room.• Frame Design

• Steel instead of plywood• Two beams instead of four

Payload Design Changes from PDR

79

• Steel U-shaped frame attached to removable bulkhead

• Bulkhead attached to body tube with bolts

• Tied to an eye-bolt, surgical tubing will suspend the pill which holds fragile material

Payload Integration

80

• Final design allows for:• Lightweight structure that doesn’t

compromise the strength.• Simple integration of pill and collar.• Maintains easy access to pill and

frame.• Increase in size of coupler allows for

more room for vertical deflection

• Dimensions • Total Bay length - 12”• Total weight - 2 lbs• Width of Pill - 4”• Height of Pill - 6.5”

FMP Operations Summary

81






Project Plan


Introduction



Recovery Subsystem




Internal Interfaces with Launch Vehicle

GPS System Parachute

Charges

Recovery Bay Payload

Bay

Pulley System Ailerons

GPS System Self-Enclosed

System of

GPS/Battery

No interface No interface No interface No interface No interface

Parachute

Charges

No interface Set of dual

charges for

main/drogue

Ignites the

parachute

charges

No interface No interface No interface

Recovery Bay No interface Ignites the

parachute

charges

Altimeter/

Charge Igniter

No interface No interface No interface

Payload Bay No interface No interface No interface PCS/DCS/OS Controls the

pulley system

Controls the

ailerons

Pulley System No interface No interface No interface Controls the

pulley systemCable system

to control

ailerons

Controls the

ailerons

Ailerons No interface No interface No interface Controls the

ailerons

Controls the

ailerons

Two actuating

ailerons1/27/2017 California State Polytechnic University, Pomona CDR 83

External Interfaces with Launch Vehicle

Ailerons

• Generate CL and rotate rocket post burnout and interfaces with RIS

Payload

Launch Lug

• Connects launch rail to launch lug

Launch Rail

• Slides over the launch lug to guide rocket

Igniter

• Interfaces with motor to initiate launch

Rotary Key

• Interfaces with recovery avionics

12 V Battery

• Interfaces with igniter for direct launch1/27/2017 California State Polytechnic University, Pomona CDR 84

Project Plan





Project Plan


Introduction



Recovery Subsystem




Educational Engagement•Charter Oaks Elementary

•iPoly High School

•Country Springs Elementary

•Tustin High School

•Almondale Elementary

1/27/2017 86

Requirements Status

Requirement Verified In Progress Not Verified

Vehicle 27 4 7

Recovery System 5 13 0

Experiment 4 12 0

Safety 4 11 2

General 7 6 1

Derived 2 24 0


Timeline


Timeline Continued

Current

Team

Focused

Milestones


Timeline Continued







Project Plan


Introduction



Recovery Subsystem





Leading Design

Subscale Manufacturing

TestingSubscale Launch

Evaluation Final Design


2016-2017 CPP NSL Team CDR Presentation

Thank You!

Questions?1/27/2017 California State Polytechnic University, Pomona CDR 93

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