1. FAMU PDR Presentation

2. 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

3. Vehicle Dimensions, Materials, and Justifications

4. Vehicle dimensions, materials, and justifications Airframe: Always Ready Rocketry - BT20-139A - 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.

5. Vehicle dimensions, materials, and justifications

6. Static Stability Margin

7. Concept used to characterize the static stability and controllability of aircraft and missiles Stability Margin: 1.71 cal

8. Vehicle Safety verification and testing

9. Vehicle Safety/Failure Mitigation Potential Failure ModeEffects of Potential FailurePrevention 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 heavyRocket 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, through- the-wall fin mounting, and ample application of epoxy adhesive and fillets

10. 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.

11. 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 ring failureUnstable shift in stability margin; Damage to all subsystems; separation of fin can Proper centering ring diameter; proper construction techniques Bulkhead failureUnstable flight; damage to subsystems; unstable shift in stability margin Proper bulkhead diameter; proper construction techniques

12. 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.

13. Motor Selection and Justification

14. Motor Loki L930 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 L930. Our rocket design is similar to last years and based on the weight of the rocket we chose the L930. Lead plates will be added to the rocket to keep the rocket from exceeding a 10240 ft.

15. Thrust-to-Weight Ratio and Rail Exit Velocity

16. 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

17. Launch Vehicle Verification and Test Plan

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

19. Vehicle Verification RequirementDesign FeatureVerification 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

20. Vehicle Verification RequirementDesign FeatureVerification by The recovery system electronics shall have each altimeter armed by a dedicated arming switch Each altimeter has a separate switchInspection The recovery system electronics shall have a dedicated battery for each altimeter Each altimeter has a separate batteryInspection 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

21. Drawings/Discussion

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

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

26. Secondary Stage (d) v v Parachute connector ring (e) To drogue chute Motor Mounts (g) (g) is inserted in base of (f) secondary stage 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. v 120 ᵒ Fins

27. Stage Two Rocket Engine Ignition System (e) Hollow Tube Electrical wiring for ignition cap Altimeters for ignition and parachute Solid Tube Ignition cap and Flammable material Black powder and cap 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. (h)

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

29. Parachutes

30. Parachutes (CONT.)

32. Payload Design

33. Electronics used in payload:

34. Payload Design Raven 3 altimeter → Flight Counter Fit-PC2 miniature computer → Data acquisition HackHD Camera → Video & still frames – faces tail of rocket 5.8G 8ch 2w Wireless Camera Video AV Audio Transmitter & Receiver → Provides USB interface between computer and video devices with component outputs

35. 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

36. Payload Integration/Test Plans

37. Payload Integration Mounted on 5.5”x9.25” Board in electronics bay above motor mount 2 - Fit-PC2, powered by LiPo s 2 – 5.8G 8ch 2w Wireless Camera Video AV Audio Transmitter & Receiver 3 - Raven 3 altimeter, powered by built-in 9v battery In separate bay adjacent to motor mount HackHD camera, powered by LiPo battery

38. Payload Test Plan Hardware and Software Integration o Check Camera's compatibility with software. Ground Testing o Software tested for performance in completed its needed tasks Computer Based Testing o 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

39. 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.

40. Questions