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 - 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.

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 integratedinto 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 anunstable and unpredictable flight trajectory.

The team shall use suitable building materials, through-the-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 ring failure Unstable shift in stability margin; Damage to all subsystems; separation of fin can

Proper centering ring 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 orover 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 orover stable.

The team shall adjust weight so that center of gravity is 1-2 calibers ahead of center ofpressure.

Motor Selection and Justification

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.

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 VerificationRequirement Design Feature Verification by

The launch vehicle shall carry the SMD and/or a scientific payload

Visual Hazard Analysis payload Inspection 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 PerfectFlite Inspection 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

Vehicle VerificationRequirement 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

Drawings/Discussion

Upper Chute Housing(b)

Retainer Ring

Dispersion Insert/Chute support

(d)

To Scientific payload in nosecone

To Scientific payload in body

(a)

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)

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

120ᵒ

Fins

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)

First Stage(f)

v v

120ᵒ

Fins

Motor Mounts

Engine Retainer

Parachute connector ring

(h)To First stage recovery chute

Parachutes

Parachutes (CONT.)

Parachutes (CONT.)

Payload Design

Payload Design

Electronics used in payload:

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

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”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

Payload Test Plan

• Hardware and Software Integrationo Check Camera's compatibility with software.

• Ground Testingo Software tested for performance in completed its needed tasks

• Computer Based Testingo 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