Information Pack for Mid Power Rockets

Information Pack for Mid Power Rockets www.qldrocketry.com Table of Contents 1. Introduction... 2 2. Terminology... 3 3. Rocket Flight Phases... 4 4. Igniters... 5 5. Motors... 6 5.1 Key Components... 6 5.2 Impulse... 7 5.3 Motor Identification... 8 5.4 Single Use and Reloadable Motors... 8 6. Deployment... 13 6.1 Delay Element... 13 6.2 Electronic Deployment... 13 6.3 Deployment Methods... 14 7. Recovery Systems... 16 8. Rocket Design Considerations... 17 8.1 Rocket Stability... 17 8.2 Pressure Relief Holes... 17 9. Flight Records and other Data... 18 10. TRA Certification... 19 11. Helpful Websites and Resources... 21 Appendix A Typical Reloadable Motor System... 22 Appendix B Typical Motor Designation... 23 QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 1 of 23

1. Introduction This information pack is to help rocketeers who are wishing to progress from low power rockets into the mid power range and beyond. It contains detailed information about the advanced aspects of rocketry including the construction, launch reparation and launching of rockets in this power range. Whilst the construction and preparation for flight can be a detailed and lengthy process, the actual launch and recovery of the rocket are over very quickly. The success of the flight is dependent on all of the preparatory phases being completed successfully. Rockets can be designed and built from scratch, or made from commercial kits. Design software programs are available to aid with the design of rockets. This design process results in the determination of the fin and nose cone shape, location of the on-board components (e.g. A/V bays) and will ultimately determine the centre of gravity and centre of pressure (These will determine if the rocket s flight will be stable or not). Flights can also be simulated to determine the rocket s performance for various motors and weather conditions. A great deal of time, effort and attention-to-detail will be required to ensure that your rocket is constructed to withstand the rigours of the more arduous flights associated with mid and highpowered rockets. Adhesives, fin orientation, parachute selection, electronic components will all be important considerations. The launch preparation will also require greater scrutiny. With the more elaborate high power rockets, some rocketeers will prepare a checklist for use during preparation to ensure that nothing is overlooked. The contents of this information pack will assist with some of these considerations. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 2 of 23

2. Terminology Term Airframe Apogee Avionics Bay (A/V) Centre of Gravity Centre of Pressure Drogue Ejection Fillets Impulse Launch lugs Launch rod Launch Control Officer (LCO) Motor Motor CATO Natural Resources and Mines QRS Range Safety Officer (RSO) Recovery System Scratchbuilt TRA Wadding Description The main section of the rocket. It contains the motor, parachute, A/V bay. The point at which, after launching the rocket, the flight path changes from ascending to descending i.e. the highest point of ascent. The section of the rocket that contains the electronics e.g. altimeter, GPS (usually only for high powered rockets). The point of a rocket at which the weight is evenly distributed i.e.balance point along the rocket s length. The point of a rocket at which the aerodynamic lift of the rocket is centred. It is determined by the shape and length of the rocket, the shape and size of the nose cone, the number, size and shape of the fins. Smaller parachute typically deployed at apogee that will slow the rocket s descent until the main parachute is deployed at a lower altitude. Used to reduce the amount of drift experienced by a high power rocket. The act of separating the rocket components during flight, thus deploying the recovery system from the rocket body. The glued part of the rocket that secures the rocket frame to the fins. The change in momentum per unit mass of propellant of a propulsion system. Measured in Newton.seconds (N.s). The devices fastened to the external frame of the rocket that hold the rocket in place on the launch rod prior to launching. The vertically mounted assembly that aims the rocket upwards before launch. The person at the launch site who has the responsibility and duty to: Ensure that the ignition system is working correctly, and; The rocket ignition leads are connected correctly, and; Control the countdown, and; Ensure the safety and continuity of rocket launches. A part of the rocket that provides propulsion. A failure of the motor causing termination of the flight. Queensland Government Department responsible for the issue of explosives licences in Queensland. Queensland Rocketry Society Inc. - the association responsible for the development of the hobby of rocketry in Queensland. The person at the launch site who has the responsibility and duty to: ensure that any rocket presented for launch is fit for flight, and; ensure that the TRA safety rules are being followed. The device that is deployed at the highest point of the launch that will then bring the rocket back to the ground at a controlled speed thus reducing the possibility of damage or injury. A rocket can be designed and constructed by the owner using kit and non-kit components. Tripoli Rocketry Association Inc. - the international organisation responsible for organising the sport worldwide. Insulated material inserted into the airframe between the recovery assembly and the ejection charge to prevent burning of the recovery assembly QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 3 of 23

3. Rocket Flight Phases The rocket flight has five distinct phases as shown in the table below. Flight Phases Ignition Thrust (Powered flight) Coast (Unpowered flight) Deployment Descent Description This stage involves applying a heat source to the rocket motor sufficient to cause the ignition of the motor propellant. Igniters are used for this purpose and consist of two wires with a small amount of material that will burn when a high enough current is supplied. This confers heat to the motor sufficient to cause ignition. At ignition, pressure builds rapidly inside the motor and superheated gases exit the exhaust nozzle. The rocket is propelled upward until all of the propellant in the motor is burnt. it accelerates to a velocity determined by the motor impulse, rocket weight and body tube cross-section area. Powered flight may last from as little as a fraction of a second to many seconds for high power motors. The rocket reaches its maximum speed just before the end of the thrust phase. This is the phase during which the rocket momentum continues to carry rocket upwards until all speed is lost. This is the phase where the rocket is decelerating due to gravity and air resistance and will eventually cease its upward motion. It can be much longer than the powered segment. Most of the altitude is gained during this phase. Ideally, deployment will occur at the instant the rocket has ceased its upward motion and has begun falling back toward the ground. The ejection charge pushes the rocket sections apart to enable the recovery system (parachute or streamer) to deploy. If packed correctly, the recovery system will open completely. Once the recovery system is deployed, the rocket begins a controlled descent. The downward motion is generally arrested by the deployment of a recovery device such as parachutes or streamers. If the recovery system fails e.g. separates from the rocket or fails to open, it is almost certain that the rocket will be damaged when it impacts the ground. Uncontrolled descents pose a hazard to any persons in the vicinity. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 4 of 23

4. Igniters Igniters, as the name implies, are used to ignite the propellant. They consist of a thin wire element secured across the two igniter wires with terminals. When a battery voltage is applied to the wire terminals, the thin wire element heats up and commences the thermal reaction in the propellant. The terminals are connected to the battery via the launch control box. For low power rockets, the igniter can be installed into the rocket in the prep area. For high powered motors, the igniter must be inserted into the rocket only after it has been positioned on the launch pad and the AV bay components have been activated. Three typical types of igniters available are listed in the table below. Igniter Description Example Copperhead First fire e-match Igniter has strips of a thin copper foil on either side of an insulating medium. The two copper strips act as the positive and negative leads for the battery. An igniter head on the ignition leads is completes the circuit. A special launch lead assembly is required to connect the igniter to the battery. These are used for G and below motors. These have a similar ignition head but are connected by traditional insulated copper wires. There are two types: First Fire and First Fire Junior. The First Fire is used for high power motors. The First Fire Junior is used for G and below motors and should not be used for deployment ejection charges. These are similar to the First Fire and are used more commonly to ignite black powder ejection charges for altimeter-initiated deployment. They can also be used for the ignition of black powder and some other motors. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 5 of 23

5. Motors Motors are the generic term for the component of the rocket that provides the propulsion (thrust). A wide variety of motors can be inserted into the rocket prior to launching providing high speed or high altitude launches. They come in various sizes and shapes depending on the impulse range and manufacturer. Rockets are designed to accommodate the desired motor s physical size and impulse range. There are two main motor types available in model rocketry; solid propellant and hybrid. Hybrid motors typically use a liquid oxidiser (such as nitrous oxide) along with a solid fuel (typically a type of plastic). In this document we will only cover solid propellant motors. 5.1 Key Components The key components of a propulsion system are as follows: Component Description Propellant This provides the thrust for the motor. This is the main part of the motor occupying the greatest space. Propellant can be black powder or Ammonium Perchlorate based. Delay element This has three purposes Ejection charge It provides the time delay between when the propellant is exhausted and when the ejection charge is ignited. The delay can be adjusted in some motors by drilling out a small amount of the charge. It burns producing a trail of white smoke in the sky as it coasts to apogee. This assists with tracking the progress of the rocket. It also ignites the ejection charge. When the delay element combustible material has burnt through, there is enough heat to ignite the ejection charge. This provides a small explosive charge that forces the nose cone to separate from the airframe allowing the recovery system (parachute or streamer) to deploy. This should occur at apogee. For the low and medium powered power single-use and some reloadable motors, the three components are combined into a single unit. For higher powered motors, separate components are assembled to fill a more specific role e.g. ejection charges can be designed, prepared and installed in purpose built sections of the rocket separate to the motor. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 6 of 23

5.2 Impulse Motors are categorised in impulse size (Newton seconds) using an alphabetical listing e.g. A motors are the most basic with the lowest impulse. The motor impulse then increases by factors of two through the alphabet e.g. an H motor has twice the impulse of a G motor. At the time of writing, the O motor is the largest motor available for hobby purposes. The larger hobby motors have certain restrictions in relation to their possession, storage and transportation of motor propellant. In general terms, rocketeers must acquire a Queensland Explosives licence to use motors with impulse H and greater. The table below shows the range of motors available and the rocketeer s required certification level to use them. (Source: USA National Association of Rocketry). Hobby Rocket Motor Information Classification Impulse Range Impulse Limit (N.sec) Category Model Rocket High Power 1/4A 0.625 1/2A 1.25 A 2.5 B 5 C 10 D 20 E 40 F 80 G 160 H 320 I 640 J 1280 K 2560 L 5120 M 10240 N 20480 O 40960 Low Power Mid Power Level 1 Level 2 Level 3 Note that the impulse limit listed is the maximum for the range e.g. an H motor can have an impulse range between 160 320 N.secs even though it is listed as a fixed figure of 320 N.secs. Rocketeers must check the manufacturer s specifications to determine the actual impulse for a particular motor. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 7 of 23

This can be used to determine the timing of the thrust phase and the maximum height that the rocket can achieve. 5.3 Motor Identification Rocket motors are identified with a three-part code that gives the rocketeer some basic information about the motor's power and behaviour as follows: A letter specifying the total impulse e.g. C ; A number specifying the average thrust in Newtons e.g. 6; A number specifying the time delay between burnout and recovery ejection e.g. 3. Hence a C6-3 motor is in the C impulse range, has an average thrust of six Newtons over the motor burn time and a delay time to ejection of three seconds. With the larger motors, there is an additional letter relating to the colour of the exhaust. Refer to Appendices A and B. 5.4 Single Use and Reloadable Motors Motors can be categorised as single-use or reloadable. They also come in various sizes. The appropriate sized motor must be selected to fit into the motor mount of the rocket. Motor standard sizes for mid to high power rockets include 29mm, 34mm, 54mm, 78mm and 98mm diameter. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 8 of 23

Refer to the table below for details of typical motor types. (Source: Aerotech Consumer Aerospace Catalogue). Motor Description Typical Example Single use It is used only once and is then discarded. Comes in 1/4A, 1/2A and A E sizes. Reloadable The reloadable motor can be used many times. The reloadable motor consists of a metal cylinder (casing) with threaded closures at both ends. Reload kits of various impulses and thrusts can be used with the reloadable motor. They come in a variety of lengths and diameters to suit the rocket construction and the desired performance. Reload kits contain propellant, delay elements, ejection charges, washers, O rings and nozzles. They are assembled and then installed into the rocket. After the launch, the motor components are discarded but the motor casing is kept for further use. Single use motors contain propellant, delay elements and ejection charges. The casing consists of multiple layers of tightly wound paper. It is wound into a cylindrical shape and the propellant, delay element, nozzle and ejection charge are sealed inside by clay retainer caps. The assembly is easily inserted into the motor mount and held in place by the retaining hook. It is important to ensure that the motor is held in place inside the rocket. If not, it can be ejected when the ejection charge ignites (the force of the ejection charge popping the nose cone can also propel the motor out the back of the rocket if it is not constrained). For higher powered rockets, the motor is generally held in place by screwed motor retaining assemblies. The diagram below shows a typical single-use rocket motor assembly. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 9 of 23

(Source: Phil Entwistle) Reloadable motors can accommodate a variety of motor reload kits. The kits present a variety of impulses, thrust and propellant types. The kits contain propellant, washers, O rings, spacers, nozzles, delay and ejection charges, igniters and instructions. The components of the kits are assembled into the motor. The instructions must be followed completely. If any parts are installed incorrectly or left out, then the motor may not perform correctly with catastrophic effect e.g. the ejection charges may ignite early causing the parachute to deploy early, the motor casing may be damaged and the rocket may experience motor cato. Instructions are available with all kits. It is important that the rocketeer follow the instructions precisely to ensure all components are incorporated and assembled in the correct order. If any components are inserted incorrectly or omitted, the motor could fail. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 10 of 23

Shown below is a typical reload kit. In this case, it is an Aertotech G64-10 for a 29mm diameter, 120mm long motor. (Source: Jeff Cheales) Motor Casing forward closure Instructions Liner tubes containing propellant grain Ejection charge Forward insulator Delay spacer Motor Casing aft closure Delay Insulator Delay element Forward and Aft O-rings Copperhead igniter Delay O-ring QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 11 of 23

The diagram below shows a typical mid power rocket motor assembly (in this case, the Aerotech kit described above). (Source: Phil Entwistle) The kit is assembled by the rocketeer. Assembled kits cannot be transported with the igniter inserted. This must be done at the launch pad. The motor impulse can be increased with the number of propellant grains that are incorporated. These are billets of propellant that are inserted into the motor casing - the more grains, the greater the impulse. The limitation for this is the dimension of the motor casing. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 12 of 23

6. Deployment In this phase, the recovery system deployment mechanism is triggered. A small charge is exploded within the rocket ejecting the nose cone (or other parts of the rocket if dual-deployment is used). It is accepted that the best approach is that the recovery system is deployed at or near apogee. This ensures that the recovery system (parachute/streamer) and rocket structure will suffer little effects from the upward or downward mechanical forces due to rocket momentum as it deploys. There are two basic mechanisms that can initiate deployment: delay element and electronic. 6.1 Delay Element A delay element is a small container of combustible material mounted on top of the motor propellant within the motor. When the motor s propellant has been exhausted, the delay element ignites and slowly burns. Depending on the length and volume of the combustible material, it will burn for a designated time (usually a few seconds) as specified in the manufacturer s instructions supplied with the reload kit. Ideally, it will burn for the duration of the coast period. When the delay element has completely burned, it will ignite the ejection charge thus deploying the recovery system. With single use motors, the delay element is fixed in place and the delay timing cannot be altered. However, with reloadable motors, the delay element timing can be changed by drilling out an appropriate amount of the combustible material. Of course, this means that the time can only be reduced, it cannot be extended. If the correct delay period has been chosen, the ejection charge will be ignited and deployment will occur at, or near, apogee. This is the cheapest and most popular means of deployment for low power rockets. It does, however, have its disadvantages. This method is effective only if the correct delay time has been calculated. If the ejection/deployment charge is ignited too early or too late, then the rocket may be travelling at high speed (either on the up or downward phase of the flight. The recovery system will be subjected to large forces and this may cause damage to the recovery system or rocket. Simulation software can assist with determining the best delay timing. However, it is only an approximation given the many variables that can affect these calculations e.g. coefficient of drag. Trial and error with the various motors and delay charges will determine the correct delay element timing for a particular rocket. 6.2 Electronic Deployment The more sophisticated deployment technique is to utilise on-board electronic devices such as altimeters. These devices have the advantage of: Detecting apogee and deploying the recovery system at that time Allowing for a second deployment at an altitude closer to the ground Recording the rocket s altitude for later performance evaluation These devices are used in conjunction with separate black powder ejection charges. These charges will be fired by the electronic device and will deploy the recovery systems. Electronic devices are QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 13 of 23

more expensive than the single-use delay element devices. However, they have the advantage of virtually guaranteeing deployment at apogee. They will also record basic flight details for later downloading and analysis. Many mid to high power rockets will utilise motors that will launch to much higher altitudes. As such, they will experience a greater drift when using normal parachutes. In these cases, dual-deploy recovery systems are advised. A smaller parachute, called a drogue, will deploy at apogee. This will create a controlled descent at a rate of about 8 10 meters / second. This allows the rocket to descend at a faster, controlled rate that prevents excessive drift. When the rocket descends to a pre-set altitude (determined by the on-board altimeter), the second, larger or main parachute is deployed. This will reduce the rate of descent to that required for a safe landing. Some electronic devices will also have capability for tracking the rocket and location using GPS. In many cases, rocket designers will allow for two on-board electronic devices with one as a back-up. 6.3 Deployment Methods When the ejection charge ignites, it creates a large volume of heated gas within the rocket. This generates a large force that is designed to separate the nose cone (or other body components) thus allowing the deployment of the recovery system. The heated gas can cause damage to the recovery system. Hence, it is important to shield the recovery system e.g. parachutes, streamers from the heat. We have already seen how the use of wadding and heat resistant material can be used as a buffer between the ejection charge and the fragile parachutes/streamers for low power rockets. For mid to high power rockets, the ejection charges are more substantial and can cause greater damage. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 14 of 23

For this level of rocketry, there are two basic deployment methods used - piston and straight deployment with optional fire (blast) blanket. Igniter Description Example Piston Fire blanket The piston is a tight fitting in-line solid component of the recovery system It usually takes the shape of an openended cylinder made of phenolic, cardboard or similar material. It sits between the ejection charge and the deployment device inside the body of the rocket. The open end faces towards the ejection charge. The force of the ejection charge pushes the piston and the parachute out of the rocket and the recovery device is deployed. The piston protects the recovery device from heat damage from the hot gases. One end of the piston is connected to the motor mount. The other end is connected to the deployment device. The fire blanket is made from a heat resistant material. It is attached to the shock cord of the deployment device. It is located between the ejection charge and the deployment device within the rocket. It is large enough that it can completely shield the deployment device from the hot gases of the ejection charge. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 15 of 23

7. Recovery Systems The recovery system is the combination of the electronics used for deploying the recovery device and the recovery device itself. The purpose of the recovery device is to provide a controlled descent of the rocket. This will reduce the possibility of damage to the rocket or property. It will also contribute to the safety of personnel on the ground. The recovery device may consist of streamers and/or parachutes. The ideal descent rate for a rocket is about five metres/second. Some recovery devices/methods are listed below. Mode Tumble Description Suitable only for small models. At deployment, the nose cone is ejected. This spoils the aerodynamic profile of the model causing a slower descent. Streamer Parachute Dual Deploy A streamer is used in place of a parachute. Suitable for smaller models. The most popular mode of recovery. The size of the parachute is selected to provide a descent rate of approximately 15 feet/second (4.6 m/s) or less. Uses two parachutes. A drogue chute deployed at apogee allows a more rapid descent (25 30 feet/second) to reduce drift. The main chute is deployed at a user defined height (around a few hundred feet). Only possible with a dual deploy capable altimeter and a suitably designed rocket. The recovery device consists of a parachute/streamer, shock cord attachments and swivels. Parachutes are available in various sizes. The selected size for a particular rocket will depend on the weight of the rocket the more the weight, the bigger the parachute. The following table provides an indication of the variety of controlled descent devices available (Source: Public Missiles Ltd) Device Spill Hole Rocket Weight Parachute Size Diameter (oz) (kg) (inch) (mm) (inch) (mm) Parachute 0-16 0 0.45 6-18 150 450 0-1 0 25 Main Streamer 16 60 0.45 1.7 Drogue/Main 16 120 0.45 3.4 18 450 4 100 Drogue 12 26 0.34 0.74 24 600 5 125 24 34 0.68 0.96 30 30 5 125 30 42 0.85 1.20 36 36 8 205 36 54 1.0 1.5 48 48 8 205 Parachute 50 90 1.4 2.5 54 54 10 255 90 160 2.5 4.5 60 60 12 305 Main 160 220 4.5 6.2 72 72 14 355 200 260 5.7 7.4 84 84 16 405 250 320 7.1 9.1 96 96 16 405 416-880 11.8 25.0 120 120 20 510 Use QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 16 of 23

Spill holes are incorporated into the parachute to provide stability in the descent. Swivels incorporated between the parachute and the shock cord allow the parachute to deploy effectively and reduce the possibility of the shroud lines from becoming tangled. 8. Rocket Design Considerations 8.1 Rocket Stability The centre of gravity (Cg) and centre of pressure (Cp) and the relationship between them are key aspects in determining the stability of the rocket during flight. It is important to know where the two points are located on the rocket. The centre of gravity is the point on the rocket at which the weight of the individual components (called the gross lift-off weight or G.L.O.W) is balanced. The centre of pressure is the centre of aerodynamic lift. This can be determined considering the geometric layout of the rocket e.g. rocket length and shape/size/number of fins, shape of nose cone. These can be determined using rocket design software. Alternatively, it can be calculated using spreadsheets. The Cp and the Cg must be marked on the rocket. As a general rule, the Cg must be at least one rocket diameter (called the static margin) forward of the Cp i.e. the Cg must be closer to the rocket s nose than the Cp (generally by at least one rocket diameter) as shown below. If the separation is closer than the rocket diameter, it could become unstable in flight and start to tumble. This can be corrected by moving the Cg forward e.g.by adding weight to the nose cone) or by moving the Cp backwards (by redesigning the rocket to add more or different shaped fins). Cg Cp d Where d = diameter of the rocket This distance d 8.2 Pressure Relief Holes Medium and high power rockets fly higher than the low power counterparts. Because of this, the rocket will experience changes in atmosphere pressure as it rises to the greater altitude i.e. the outside pressure reduces. If the pressure inside the rocket is not equalised with that of the outside atmosphere, the nose cone can be ejected earlier than planned. This can happen when the rocket is travelling at high speed. The parachute can deploy early thus causing the rocket to turn sideways. Extensive damage can occur to the rocket body, parachute, fins etc. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 17 of 23

It is also important that the altimeters in the AV bay to be exposed to the correct external air pressure for them to work effectively when used for deployment purposes. This is particularly apparent with rockets with larger diameters e.g. 100mm and above. To reduce the effect of the pressure variation, small holes can be drilled into the upper airframe below the nose cone to equalise the internal pressure as the rocket ascends. The number and diameter depends on the volume of air inside the rocket cavity. As a rule of thumb allow ¼ hole for every 100 cu in of internal air space. Pressure relief hole drilled into the upper airframe Small holes can also be drilled into the AV bays to prevent similar pressure differential. Pressure relief hole drilled into the AV bay 9. Flight Records and other Data Rocketeers are encouraged to keep; A folder containing all of the relevant information about the rocket/s. (This is helpful when filling out flight cards.) Simulation data that will assist in determining the expected height for the rocket launch given the weight and motor thrust and impulse details A log of their launches including weather conditions, rocket performance (launch, flight, deployment), delay timing performance, recommendations for future QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 18 of 23

It would also be appropriate to develop and utilise a checklist to assist in the process of prepping the rocket for launch. This will assist in ensuring that the flight is successful e.g. all components have been incorporated/assembled, the electronics are armed, batteries are charged and connected. 10. TRA Certification For the beginner rocketeer, it is important to understand that there is a pathway through the levels of rocketry from beginner through to advanced. It could be considered as a career path. In general, rocketeers progress through three different stages of rocketry: low-power, mid-power and high power. Many rocketeers are happy to stay with low or mid-power rocketry for their careers and that is OK. There is no pressure to progress through more advanced stages. However, for those interested in advancing through the various classifications, there is a well-developed support structure available both informally through the AusRocketry forum and mentor scheme as well as formally through the TRA guidelines and certifications. For high power rocketry, TRA have developed a three level system to facilitate a structured progression from beginner through to advanced rocketeer. Level 1 is the basic level with level 3 the highest level. This system is recognised internationally. At each stage, the rocketeer must undertake evaluations and pass an assessment process administered by the TRA prefect. For each level attempted, the rocketeer must complete an application form and submit to the TRA prefect before evaluation can commence. The QRS has adopted this system of certification. QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 19 of 23

The three certification levels for high power are described in the table below in general terms. Power Level Description Rocket Motors Other Requirements Low - Low powered rockets A D Use green launch cards at QRS launches Mid - Mid powered rockets E - G Use yellow launch cards at QRS launches High 1 Motor impulse up to 640 N.sec H I Obtain Qld Explosives Rocket built by flyer (kit or scratch built) licence from Natural Certification flight observed by TRA prefect or TAP member Resources and Mines Join Tripoli Rocketry Electronics not required Association Recovery system deployment must operate Use yellow launch Rocket must be recovered without major damage cards at QRS launches High 2 As for Level 1 except: Motor impulse up to 5120 N.sec Must complete a written test High 3 As for Level 2 except: Motor impulse greater than 5120 N.sec Electronic device as primary means of recovery Rocket design approved by 2 TAP members o Pre-flight data capture form o Rocket drawings showing rocket components o Parts listing o Electronics wiring diagram o Pre-flight check list detailing assembly J - L M + As for Level1 except: Obtain Qld Explosives licence alter Maintain log book for explosives licence justification Encouraged to obtain RSO/LCO accreditation Act as RSO/LCO at scheduled launches QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 20 of 23

11. Helpful Websites and Resources Listed below are some helpful websites. There many others. These are just a selection. Aerotech http://www.aerotech-rocketry.com/ US based manufacturer Apogee http://www.apogeerockets.com/ US based manufacturer Educational newsletters AusRocketry forum http://ausrocketry.com/forum/ Australian based forum AusRocketry Shop http://ausrocketry.com/shop/ Australian based distributor Estes Rockets http://www.estesrockets.com/ US based manufacturer LOC / Precision http://www.locprecision.com/ US based manufacturer Public Missiles Ltd http://www.publicmissiles.com/ US based manufacturer Queensland Rocketry http://www.qldrocketry.com QRS web site Qld Rocketry Society Forum http://www.ausrocketry.com/forum/viewforum.php?f=13 Tripoli Rocketry Association http://www.tripoli.org/ US rocketry organisation Wildman Rocketry http://www.wildmanrocketry.com US based manufacturer Vern s Rocketry Web Site http://www.vernk.com/ US based Rocketeer Wikipedia UK Rocketry Handbook http://en.wikipedia.org/wiki/mainpage Internet encyclopaedia http://www.ukra.org.uk/docs/youth/rocketryhandbookv1.2.pdf The Wikipedia site can be used for research issues relating to rocketry e.g. aerodynamics, drag coefficient, model rockets, nose cone design There are two model rocketry simulation software programs available as follows: Rocksim Open Rocket Apogee Rockets (may be purchased after a free trial period) (free to download and use) - Available from http://openrocket.sourceforge.net/ QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 21 of 23

Appendix A Typical Reloadable Motor System (Source: Aerotech Consumer Aerospace Catalogue). QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 22 of 23

Appendix B Typical Motor Designation (Source: Aerotech Consumer Aerospace Catalogue). QINFO-002 Mid Power Info Pack (Ver 1.2) 14 June 2013 Page 23 of 23