FAMU PDR Presentation Table of Contents Vehicle dimensions

FAMU PDR Presentation

Table of Contents • Vehicle dimensions, materials, and justifications • Static stability margin • Plan for vehicle safety verification and testing • Baseline motor selection and justification • Thrust-to-weight ratio and rail exit velocity • Launch vehicle verification and test plan overview • Drawing/Discussion of each major component and subsystem, especially the recovery subsystem • Baseline payload design • Payload verification and test plan overview • Questions

Vehicle Dimensions, Materials, and Justifications

Vehicle dimensions, materials, and justifications • Airframe: Always Ready Rocketry - BT 20 -139 A - 5. 5 in Blue Tube 2. 0 • Fins: 3/16 Aircraft Plywood • Length: 123 in. • Mass: 718. 92 ounces (44. 932 lbs. ) • Outside Diameter: 5. 50 in. • Inside Diameter: 5. 35 in.

Vehicle dimensions, materials, and justifications

Static Stability Margin

Static Stability Margin Concept used to characterize the static stability and controllability of aircraft and missiles Stability Margin: 1. 71 cal

Vehicle Safety verification and testing

Vehicle Safety/Failure Mitigation Potential Failure Mode Effects of Potential Failure Prevention Electronics package is too large to fit inside rocket Payload cannot be integrated into rocket Redesign payload to fit proper body tube size Nose section too heavy Rocket may not have enough power for stable flight Redesign rocket to reduce weight The fins fail during flight due to shear forces or inadequate use of adhesive. The rocket will experience an unstable and unpredictable flight trajectory. The team shall use suitable building materials, throughthe-wall fin mounting, and ample application of epoxy adhesive and fillets

Vehicle Safety/Failure Mitigation The interior of the rocket catches on fire due to internal heat. The interior of the rocket is destroyed. The team shall use proper spacing and bulkheads to prevent the transfer of heat. The rocket experiences drag separation during flight. The rocket will prematurely separate, leading to early parachute deployment and a mission failure. The team shall ensure that all joints are secure and shall drill a hole in the body tube to equalize pressure between the interior of the rocket and the atmosphere. A bulkhead detaches from the interior of the body tube. Shock cords become no longer attached, causing a ballistic recovery. The team shall apply ample amounts of adhesive, such as epoxy. Rocket components are lost or damaged during transport to launch site. The team risks not launching the rocket unless repairs can be made. The team shall pack components safely and securely for transport and have replacement components and needed tools available at the launch site.

Vehicle Safety/Failure Mitigation Fin(s) break off during flight/landing Unstable flight; possible damage of engine mount Adequate materials and construction techniques Fin-can failure due to high temperatures Unstable flight; Fin-can separation during flight Proper mounting material and hardware Centering failure Unstable shift in stability margin; Damage to all subsystems; separation of fin can Proper centering diameter; proper construction techniques Bulkhead failure Unstable flight; damage to subsystems; unstable shift in stability margin Proper bulkhead diameter; proper construction techniques

Vehicle Safety/Failure Mitigation The center of pressure is too high or too low. The rocket will be unstable or over stable. The team shall adjust fin sizing and position so that the center of pressure is 1 -2 calibers behind the center of gravity. The center of gravity is too high or too low. The rocket will be unstable or over stable. The team shall adjust weight so that center of gravity is 1 -2 calibers ahead of center of pressure.

Motor Selection and Justification

Motor • Loki L 930 • Motor Type: reloadable • Total Weight: 3538. 0200 g • Peak Thrust: 1136. 70 N • Total Impulse: 3587. 2 Ns • Justification: We currently have the motor house for the L 930. Our rocket design is similar to last years and based on the weight of the rocket we chose the L 930. Lead plates will be added to the rocket to keep the rocket from exceeding a 10240 ft.

Thrust-to-Weight Ratio and Rail Exit Velocity

Thrust to weight /Rail Exit Velocity • Rail Size: 1. 5 in. • Rail Exit Length: 96 in. • Rail Exit Velocity : 67. 99 ft/s • Thrust to Weight Ratio: 5. 62 N

Launch Vehicle Verification and Test Plan

Vehicle Verification Launch Vehicle Requirement Design Feature Verification by The launch vehicle shall carry the SMD and/or Visual Hazard Analysis payload a scientific payload Inspection and testing The launch vehicle shall deliver the payload to Correct selection of motor, Rocksim 10, 240 ft. simulations. Analysis and testing The launch vehicle shall carry one Perfect. Flite Electronics bay includes a Perfect. Flite altimeter Inspection and testing The recovery system electronics shall be designed to be armed on the pad Push button switches are accessible from the Testing outside of the vehicle by holes

Vehicle Verification Requirement Design Feature Verification by The recovery system electronics shall be completely independent of the payload electronics The recovery electronics and payload electronics will be in separate bays. Inspection and design The recovery system electronics shall contain redundant altimeters There are two separate altimeters in the electronics bay. They are powered by two separate batteries for complete redundancy Inspection and testing

Vehicle Verification Requirement Design Feature Verification by The recovery system electronics shall have each altimeter armed by a dedicated arming switch Each altimeter has a separate switch Inspection The recovery system electronics shall have a dedicated battery for each altimeter Each altimeter has a separate battery Inspection The recovery system electronics shall have each arming switch accessible from the exterior of the rocket frame There are holes in the frame of the rocket that reaches the push button switches Inspection

Drawings/Discussion

(a) Upper Chute Housing (b) To Scientific payload in nosecone Retainer Ring Dispersion Insert/Chute support (d) To Scientific payload in body

Scientific Payload (c) Internal layout of scientific payload TBD by dimensions of equipment. Black powder wells Equipment Camera (s) Sensor board Transmitter GPS Retainer Ring(s) Batteries Altimeter (s) External Center Ring

Secondary Stage (d) To drogue chute (e) Parachute connector ring Motor Mounts Mounting of secondary will be recessed from the bottom of the tube to insert engine ignition system to ensure stability of rocket and proper ignition. Fins v (g) is inserted in base of (f) secondary stage v 120ᵒ (g)

Stage Two Rocket Engine Ignition System (e) Ignition cap and Flammable material Electrical wiring for ignition cap Solid Tube Black powder and cap Hollow Tube Altimeters for ignition and parachute Parachute connector Position of Altimeter (s) are TBD do to battery size (not shown). Also, the length of the ignition tube will depend on the depth of engine and material used for ignition. Altimeter for Ignition will be set to ignite engine when altitude of rocket is still straight and adequate velocity TBD.

First Stage (f) To First stage recovery chute (h) Parachute connector ring Motor Mounts Fins v Engine Retainer v 120ᵒ

Parachutes

Parachutes (CONT. )

Payload Design

Payload Design Electronics used in payload:

Payload Design • Raven 3 altimeter → Flight Counter • Fit-PC 2 miniature computer → Data acquisition • Hack. HD Camera → Video & still frames – faces tail of rocket • 5. 8 G 8 ch 2 w Wireless Camera Video AV Audio Transmitter & Receiver → Provides USB interface between computer and video devices with component outputs

Payload Design • The team aim to implement and test a Hazard classification system with its scientific payload. • Two computers mounted in the electronics bay, one connected to altimeter, will determine altitude intervals on which video will be analyzed • Analysis tasks shared between the 2 payload computers

Payload Integration/Test Plans

Payload Integration • Mounted on 5. 5”x 9. 25” Board in electronics bay above motor mount • 2 - Fit-PC 2, powered by Li. Po s • 2 – 5. 8 G 8 ch 2 w Wireless Camera Video AV Audio Transmitter & Receiver • • 3 - Raven 3 altimeter, powered by built-in 9 v battery In separate bay adjacent to motor mount • Hack. HD camera, powered by Li. Po battery

Payload Test Plan • Hardware and Software Integration o • Ground Testing o • Software tested for performance in completed its needed tasks Computer Based Testing o • Check Camera's compatibility with software. Testing data transmission between payload electronics and a computer based device(s). Full-Scale launch o Encapsulates every previous test; all systems tested in context of a rocket launch

Payload Experiment Criteria • The team aim to implement and test a Hazard classification system with its scientific payload. Hazard classification is a general term for methods used to derive descriptions of the physical characteristics of an area that is in harmful distance from the rocket, such as whether the Hazard in question is people, cars, or other heavy machinery Determining the nature of an area’s Hazard is useful in the area of autonomous robotics. • Florida A&M University’s scientific we will Execute Hazard Detections, be recoverable, and execute triple deployment. • Also, the electronics bay is required to be reusable and recoverable in order for the mission to succeed.

Questions