1. 5/17/2017

2. Work Party Status Task Summary: Repair torch Fabricate Yaw probe
Fabricate main engine Ignitors
Install Servo power supply in housing
Fin sample layup
Avionics system test
Mix fuel

3. SE:
CG Model Dev.
4/29-30
4/29-30
SE:
Composite Layup
GSE:
Torch Rebuild
4/29-30
PL:
Probe Fab
PL:
Probe Design
PL:
Payload Mass Est.
SE:
Fin Sizing
SE:
Fin Fab
EVERYONE:
Rocket Assembly
PL:
Payload Procedure Dev.
SE:
Dynamic Flt Characteristics
PL:
Pduce Selection
PL:
Probe Elec Design & Fab
PL:
Payload Checkout
TBD
GSE:
Refurbish & checkout Ground Support Equipment
GSE:
Rocket Install Procedure Dev
GSE:
Launch Procedure Review
EVERYONE:
Launch Rehearsal
AV/GSE:
Integrate Servo Pwr Supply
Prop/AV:
Checkout Servo PWR supply with Servo
Prop:
Upgrade Servo Valve
Prop:
Install new servo
Prop:
Leak Check System
Prop:
Fueling Procedure Dev.
AV:
TLM System Familiarization
AV:
TLM System Procedure Dev.
Prop:
Finalize Solid Ignitor design
4/29-30
Prop:
Fab Liquid Eng. Ignitors
PM:
Complete COA Application
PM:
Establish Launch Date
PM:
Organize Equipment List
PM:
Parent Meeting
PM:
Manage Travel & Launch Logistics
ACTIONS:
Order Oxidizer (LOX), 50 PSI Relief Valve
Phone
Fire Dept Notification
PM:
Letter to Mansfield Mayor
Prop:
Prepare Fuel

4. Action Items (Rev 5/17/2017) Page 1 of 2 No. Status Description
Due Date
POC 1
OPEN
Probe transducer selection (part number and supplier)
5/10
Ved 2
Probe data acquisition system selection 3
Payload battery sizing
Gregory 4
Payload mass estimate and CG location
5/17 5
CLOSED
Fin Sizing
Ben 6
Prepare parent meeting briefing for review
PM / Ann 7
Order ground anchors
Mr. Charles 8
Order helium valve servo 9
TLM system Familiarization
Stevie 10
Draft Procedure Review
5/17 (class next week)
ALL / Mr. Charles 11
Draft answers to FAA COA question
PM Team / Ann 12
Draft Equipment list
ALL 13
Aerojet Grant Request Submission
5/5
Mr Saxby 14
Finalize CG Model
Maheck / Kevin 15
Finalize Solid motor ignitor
5/24?
Mr. Charles 16
Identify owner equipment list
PM Team? 17
Put Equipment list on website
Mr. Saxby 18
Order pressure transducers
5/18
Mr. Masse 20
Order payload avionics 21
Schedule parent meeting
Carolyn 22
Place Action Item file where we can access each week 23
Get main engine ignitor transformer
Charles 24
Purchase more carbon fiber
5/31/17
B.O.P. 25
Print 10 copies of procedures used for Mansfield launch 26
Coordinate Mansfield fire dept. support for launch
Before Parent Meeting PM 27
Trip to Aerojet
Sometime

5. Action Items (Rev 5/17/2017) DRAFT
Page 1 of 1
No.
Status
Description
Due Date
POC 1
OPEN
Probe transducer selection (part number and supplier) 2
Probe data acquisition system selection 3
Payload battery sizing 4
Payload mass estimate and CG location 5
Fin Sizing 6
Prepare parent meeting briefing for review
PM / Ann 7
Order ground anchors 8
Order helium valve servo 9
TLM system Familiarization 10
Draft Procedure Review
5/17 (class next week)
ALL / Charles 11
Draft answers to FAA COA question
PM Team / Ann 12
Draft Equipment list
5/10
ALL 13
CLOSED
Aerojet Grant Request Submission
5/5
Mr Saxby 14
Finalize CG Model
? / Kevin 15
Finalize Solid motor ignitor
/ Charles 16
Identify owner equipment list 17
Order pressure transducers 18
Order payload avionics 20
Schedule parent meeting 21
Place Action Item file where we can access each week 22
Get main engine ignitor transformer
Charles 23 24 25

6. Tasks Today SRM ignitors fab Mix Fuel (water / alcohol)
Check fin sample for proper thickness (0.125”)
Define Max Fin Size
Parent coordination meeting brief
Probe mounting structure profile
Document battery requirements for Payload
Avionics checkout
Integrated Avionics / Ignitor checkout?
Launch team assignments
Launch control box checkout
Open Action Items from last week

7. Launch Assignments (1 of 2)
POC
CONTACT INFO
LAUNCH DIRECTOR
Primary
Backup
RANGE SAFETY
RECOVERY TEAM LEAD
PAYLOAD OPERATIONS LEAD
TELEMETRY / AVIONICS LEAD
GROUND SUPPORT EQUIP LEAD
ROCKET INSTALLATION LEAD 
SRM LOADING 
MAIN ENGINE IGNITOR

8. Launch Assignments (2 of 2)
POC
CONTACT INFO
 FUEL LOADING LEAD
Primary
Backup
GHE / LOX LOADING
LAUNCH CONSOLE
Main Engine Observer
PHOTOGRAPHY
SPECTATOR COORDINATION
COA COORDINATOR
AIRCRAFT OBSERVERS (4)
Primary (4)
Backup (2)
ROAD TRAFFIC OBSERVER (2)
Primary (2)
Backup (1)

9. Fuel Properties

10. P-reg (REG1) Set Point

11. MANSFIELD LAUNCH OPERATIONS REFERENCE BOOK
LAST YEARS LAUNCH PROCEDURE BOOK
Rev: Org Date: 8/11/2016

12. Launch Tower Setup

13. Launch Rail Setup Notes:
Reference azimuth orientation on next slide
Use tool to spread rail adjacent to fastener holes during tightening of fasteners

14. Orientation North 50 ft radius keep out zone
400 lbs nominal pull required
Track Side
Tower Base
50 ft radius keep out zone
North

15. Command System

16. Prop Valve Power supply
Launch Control System
To GHe Valve To
SRM #1 & #2
To Ignitor Valve
To Prop Valve
Ignition Transformer
Gas Solenoid Valves
Launch Control Box
Propellant valve (open/close, on/off)
GHe valve (open/close, on/off
SRM ignition
SRM shunt
Igniter (on/off)
Gas (on/off)
Launch Pad Box
400 FEET
Pad Control Box
Prop Valve Power supply
GHe Valve Power Supply
120 VAC Generator
SRM Power Supply
120 VAC Generator

20. Launch Procedures

21. Launch Procedures Rocket Installation on Rail Procedure
Rocket Checkout & Fuel / SRM Loading Procedure
LOX Loading Procedure
Launch Ready Procedure
Launch Script

22. Rocket Install On Rail Configuration
Ladder
Dewer
Table 400ft away from Launch Rail

23. Rocket Installation on Rail Procedure
Verify Shunt Recovery Shunt Plug Installed
Verify TLM computer operational
Verify bottom 5 feet of aluminum guide rail fasteners are remover from one side of rail
Verify SRM carriage is installed on launch rail
Place rocket in horizontal position
Power up TLM system and confirm operation
Install nose cone
Gently place rocket on rail
Install guide rail fasteners
Verify TLM system status
Start Generator – for ignitor checkout
Set gas flow on Main Engine ignitor and install in engine

24. Launch Procedures Rocket Installation on Rail Procedure
Rocket Checkout & Fuel / SRM Loading Procedure
LOX Loading Procedure
Launch Ready Procedure
Launch Script

25. Rocket Checkout & Fuel / SRM Loading Config.
Ladder
Dewer
Tower Base
Table 400ft away from Launch Rail

26. Rocket Checkout & Fuel / SRM Loading Procedure
Verify Generator ON (needed for prop vale actuation & ignitor setup)
Verify fuel bucket bracket installed on launch rail – (support for GHe line)
Open propellant loading access door
Install GHe valve motor power connector
Verify GHe motor direction
Hook up GHe line to rocket
Open (MV1) LOX tank pressurization Isolation Valve
Purge system (25 PSI) through injector for ~ 1 min (manual operation of prop valves)
Shut off GHe supply
Close Prop Valve (manual operation)
Verify prop valve direction is correct (electrical operation of prop valve) and mark on plume shield
Remove fuel fill port plugs
Put thread sealant on fuel port plugs
Load Fuel
Load SRMs (verify both SRM shunts installed prior to handling ignitors)

27. Launch Procedures Rocket Installation on Rail Procedure
Rocket Checkout & Fuel / SRM Loading Procedure
LOX Loading Procedure
Launch Ready Procedure
Launch Script

28. LOX Loading Configuration
Ladder
Dewer
Tower Base
Control Box
Table 400ft away from Launch Rail
MOVE CONTROL BOX

30. LOX Loading Procedure Move Launch Control Box to Launch Control Site
Verify Ignitor Arc operation (on for 1 sec & verify by listening)
Contact ATC for launch clearance (45 min to launch)
Verify LOX tank cooling jacket installed
Install transfill line
Close (MV1) LOX Tank Pressurization Isolation Valve
Install LOX overflow tube
Begin LOX flow
Approximate 30 min chill-in required

31. Launch Procedures Rocket Installation on Rail Procedure
Rocket Checkout & Fuel / SRM Loading Procedure
LOX Loading Procedure
Launch Ready Procedure
Launch Script

32. Launch Ready Procedure
Confirm Participants are in proper location (all together, at assigned location)
Confirm Avionics – Go
Confirm that Range is GO - (Aircraft & Traffic Spotters)
Confirm Launch Control Box SRM Shunt INSTALLED
Disconnect GHe fill line
Disconnect LOX transfill line
Open (MV1) LOX tank pressurization Isolation Valve (inside access door)
Install propellant loading Access Door
Remove LOX cooling jacket
Verify GHe Valve Electrical Connector installed
Verify Prop Valve power supply - ON & Set to correct voltage
Move LOX Dewer
START cameras
Close LOX Vent
Remove Recovery Shunt Plug
Remove SRM Shunt at Launch Rail box
Move to control area

33. Launch Procedures Rocket Installation on Rail Procedure
Rocket Checkout & Fuel / SRM Loading Procedure
LOX Loading Procedure
Launch Ready Procedure
Launch Script

34. Launch Script Confirm Range - GO (Traffic & Aircraft Spotters)
Move to Launch Control Area
Following actions Must occur in rapid succession or LOX tank pressure will increase to point that relief valve will start venting LOX tank
Confirm Range - GO (Traffic & Aircraft Spotters)
Confirm Avionics - GO
GHE Pressurization Valve - OPEN
Ignitor - ON
Ignitor Gas Flow - ON
Verify Avionics - Go
Prop Valve Open – Ignition
Verify (observation/sound) - Go
SRM Shunt Removal
Fire SRM

35. Contingency Procedures

36. Example “Recovery” tasks that get inserted into specific Procedures
Preflight Checkout Procedure - Recovery System:
Need to verify Avionics is working correctly (battery charge level, …)
Main chute packing procedure
Verify squib resistance
What position is rocket in when performing above
 Disarm after hang-fire, no recycle (no future flight planned):
PPE - Safety glasses, gloves, hearing protection
Obtain approval from Safety that its "safe to approach the rocket and conduct the Recovery pyro safing operation
Install the pyro shunt – never get in line of sight of pilot chute chamber
{do we remove the rocket from the stand at this point?}
Verify Recovery pyro shut plug installed
Remove nosecone
Unplug pyro connector
Remove recover section from rocket
Place recover section containing pyro charges in storage container
 Disarm after nominal flight (intact rocket, main canopy deployed):
PPE - Safety glasses, gloves, hearing protection, three people recover team
Secure main chute, have one person continue to hold chute so does not inflate due to wind
Photo documentation
Approach / reposition rocket so pilot chute chamber is facing perpendicular to line of sight
Install Recovery shunt plug
Remove payload section from pilot chute section
Disconnect parachute bridle from pilot chute section
Provide to designate mentor to verify status of pyro charges
Disarm after off-nominal flight (Main canopy/pilot chute did NOT deploy):
PPE - Safety glasses with side protection, gloves for all personal performing recovery operation.
Safety glasses with side protection for all observers within 25ft.
Extract remaining recover components - we must recover the cable cutter which should remain intact / verify status of pyro charges

37. Flight Feed System

38. Flight Feed System GHe Fuel Tank LOX Tank P1 Vent SV3 Relief Valve BV2
REG1
SV1
Relief Valve
(600 psid)
RV1
MV1
Fill Port
Vent
Fill
BV1
BV2
SV4
SV5
SV3
SV2
CV1
CV2
Fuel Tank
LOX Tank

39. LOX Load (Rev Org 6/1)
LOX Vent Tube
LOX DEWAR

40. Propellant Data

41. Fuel Properties

42. LOX Properties Table 1: Liquid Oxygen Physical and Chemical Properties
Molecular Formula O2
Molecular Weight
Boiling 1 atm –297.4°F (–183.0°C)
Freezing 1 atm –361.9°F (–218.8°C)
Critical Temperature –181.8°F (–118.4°C)
Critical Pressure psia (49.6 atm)
Density, BP, 1 atm lb/scf (1141 kg/m3)
Density, 68°F (20°C), 1 atm lb/scf (1.33 kg/m3)
Specific Gravity, Gas 68°F (20°C), 1 atm 1.11
Specific Gravity, Liquid 68°F (20°C), 1 atm 1.14
Specific 68°F (20°C), 1 atm scf/lb (0.754 m3/Kg)
Latent Heat of Vaporization at BP 91.7 Btu/lb (213 Kj/Kg)
Expansion Ratio, Liquid to Gas, BP to 68°F (20°C) 1 to 860
Solubility in 77°F (25°C), 1 atm 3.16% by volume

43. LOX Info

44. Injector Data

45. P-reg (REG1) Set Point
P-reg = = 395 psig

46. LOX Injector Water Flow Test Data

47. LOX Injector Water Flow Test Data

48. Fuel Injector Water Flow Test Data

49. Fuel Injector Water Flow Test Data

50. Fuel Trim Valve Set Data – (used 25/75 fuel mix)

51. Fuel Trim Valve Set Data – (used 25/75 fuel mix)

52. Injector Design Data