ROCKET CONTEST CONTEST TERMS AND CONDITIONS

Transcription

1 ROCKET CONTEST CONTEST TERMS AND CONDITIONS

2 Terms and Definitions: Payload: Any system circling an orbit or falling in trajectory from a specific altitude designed to complete a scientific/commercial/military task during/after the fall. A closed experiment mechanism released to fall down from an altitude of 120 km designed to observe the effects of micro-gravity in space is also defined as a Payload system. Rocket: Any transport vehicle of various sizes, running on various types of fuel and capable of carrying out a variety of tasks depending on the Payload being transported, designed to deliver Payload at a specific altitude. Rocket design limitations and criteria are specified in the document. An exemplary rocket placement layout is also available in Appendix 1. Recommendations: Any statement made by the contest committee which may be useful for a safe flight but is not necessarily considered a rule to be followed. All recommendations are available in Appendix 2. Category: Contest location options determined by the contest committee subject to specific limitations. Contest is held in 2 different categories. The reason for this is to give the contestants the opportunity design rockets with differing thrust and size specifications. Final Report: Final detailed report submitted to the contest which must include the exact specifications of the competing rocket. Ignition Wire: Wire which can ignite fuel and/or combustible material when an electrical current is passed through its open ends. Ground Station: Device which controls the ignition process of the rocket (to be supplied by the contest committee). In addition, this is used for communicating with and controlling the rocket during flight (each team must bring their own stations). Engine: Thrust unit found in thrust systems. There are 3 different types of fuel systems namely liquid, solid and hybrid fuels. Class: Rocket engines fall into different international classes depending on their thrust levels. Commercial engines competing in this contest must be smaller than M Class. Flight Computer: Main controller unit which controls the flight of the rocket and stores various readings with the sensors. Eyebolt: The intermediary component in the shape of an eye which is used for connecting the parachute with the remaining systems of the rocket. The following example illustrates this system.

3 Example of an eyebolt Commercial System: The term commercial system refers to two subsystems. These are the flight computer and thrust systems.. In this document, commercial thrust systems are referred to as Commercial Rocket Engines. This type of rocket engines are ready-to-use engines having design and production operations being carried out by the vendor. These engines are considered not to have any originality. Commercial flight computers are also sold in this manner and they are also considered not to have any originality. Integration Body: Integration body of a rocket is used to connect the two continuous bodies of a rocket which has the same outer diameter as the inner diameter of the rocket. Ramp: Launching station from which the thrust system takes off. Launching station is set at a specific angle in accordance with the terms of the contest. Static Margin: Static margin is the ratio of the distance between the centre of pressure and the centre of gravity of the rocket to its diameter. Stable State: State where the static margin of the rocket is between 1.5 and 3. Reusable Rocket: A rocket is considered reusable if it can be used for consecutive flights after post-flight recovery and control operations are carried out and only by simply replacing its fuel. Reusability of a rocket depends on the damage inflicted on its body, flight computer and engine parts before, during and after the flight and their reusability status. The rocket may be prepared for another flight once the necessary damage evaluation, repair work and inspection is done. This requires a high level of inspection. Reusable Payload: Payload which may be prepared for another flight after landing attached to the rocket or independently, once the required inspections are completed. Reusability may depend on the damage inflicted on the Payload body and scientific components. The rocket may be prepared for another flight once the required damage inspections and repair work is done. Rail Button: This is the lead attached to the body of the rocket using mechanical parts which is used for mounting the thrust systems to be launched on the launching ramp in a linear manner. A minimum of two Rail Buttons are mounted on the rocket body. The integration of Rail Buttons with the rocket is the responsibility of the teams. The linearity of Rail Buttons is checked by the contest judges.

4 Risk Analysis: The analysis work which should be conducted by the competing teams according to the specified criteria for their respective rocket designs. A sample document of the analysis will be shared after the summons for the contest. Check List: Each team is required to have a list ready on the location of the contest area which is used to check that all the material and the entire assembly process is complete regarding their rockets. A sample check list will be shared after the summons for the contest. Staged Rocket: Staged rockets have multiple thrust systems which separate from the main system in stages during flight. Staged rocket systems are divided into parallel and serial staged systems. Open Rocket: An open source code software used for simulating the flight of rockets in altitude rocketry. Link: 1. Purpose: General Content of the Contest and Introduction The contest is organized for and open to high school, university and graduate students. The purpose of the contest is to create interest among students and to develop their capabilities in space technologies. The contest is held in 2 different categories. Categories and design requirements are described in Section 2.1 Contest categories. This document is designed to define the rules and requirements of Rocket category of TEKNOFEST ISTANBUL Aviation, Space and Technology Festival (TEKNOFEST) Technology Contest. The general content of this document consists of contest rules and design limitations. Contestants are expected to design and produce rockets which meet the design requirements and the criteria described further in this document and launch these rockets on the day of the contest. This process is not subjected to any design, size or shape limitations by the contest committee. The application form must be filled until February 28 th Applications will be made on the TEKNOFEST Technology Contest official web site ( 2. Contest Details 2.1. Contest Categories Competing teams are expected to design, produce and launch rockets capable of carrying a Payload no less than 4 kg to an altitude of 1500 to 3000 meters Commercial Rocket Engine Low Altitude Category Contestants in this category are expected to design, produce and prepare for launch a commercial engine rocket which is capable of carrying a Payload of 4 kg to an altitude of 1500 meters. The teams must also recover the rocket in a reusable manner with its subsystems and Payload intact.

5 Commercial Rocket Engine High Altitude Category Contestants in this category are expected to design, produce and prepare for launch a commercial engine rocket which is capable of carrying a Payload of 4 kg to an altitude of 3000 meters. The teams must also recover the rocket in a reusable manner with its subsystems and Payload intact. The contest is open to all fuel. Rockets fuels cannot contain toxic substances. Rocket components purchased commercially or produced by third parties are allowed. It is compulsory to use GPS or radio signal positional systems on parts which need to be recovered independently (including Payload) during recovery. A Jolly Logic AltimeterTwo or AltimeterThree will be supplied to finalist teams from the Contest Committee in order for the contest committee to evaluate the maximum altitude reached during flight. The user guide of the altimeter devices shall be provided to the teams and its usage will be the responsibility of the competitors. Teams who recover their rockets must deliver all its subsystems and the altimeter to the contest committee for evaluation. Contestants in the Commercial Engine category cannot use engines bigger than M Class Engines. Classification information about Rocket Engines and provision of engines will be announced in a detailed safety booklet which will be published after the invitations for contest. General Information: Rocket engines will be supplied by the TEKNOFEST competition committee for the teams. It is not possible to supply the motors the teams themselves. Only one motor will be given to each team (for each category). It is strictly forbidden to adhere the engine to the body or to the motor bearing, and after the shot, the engine must be removed from the rocket and launched with a new engine. Engine; outer case, insulations, fuel, nozzle, sealing equipment and covers. All these sub-components of the engine will be supplied as ready. Competing teams do not need to conduct research on the production and supply of rocket engines. Heat, gas etc. are not factors that affect your design. You do not need to design or manufacture motor or any subcomponent of the motor. The competition is about the realization of the appropriate rocket design. The propelling part, ie the engine, will be given to you in order to verify your design. The rocket engine will not be given to the teams before the competition. Engines will be given in the shooting area. The engine assembly will be presented to the competitors by TEKNOFEST competition committee. Parallel or series stepped rocket designs and multi-engine systems within the single frame called cluster are not included in the competition concept.

6 You can find details about engine types and selection process from here Scoring System and Evaluation General Scoring Points are scored according to the following criteria: Points Preliminary Design Report 50 Critical Design Report 150 Originality 100 Final Report and Design Compliance 200 Flight Performance 500 Total 1000 Preliminary Design Report, Critical Design Report, Final Report and Design Compliance scoring guidelines will be announced to teams along with report templates and their contents Originality The following criteria will be used for originality grading. Originality Grading Structural 30 Recovery 40 Electronics 30 Commercial Engine Rockets Category Flight Performance and Evaluation A total of 500 points can be scored for flight performance. The accuracy of rocket s actual orbital peak altitude in comparison to targeted peak altitude constitutes 70% (350 points) of the total value attributed to flight performance. Precision Orbital planning is important. Score is calculated using the below formula according to the values recorded by AltimeterTwo and AltimeterThree and with a tolerance of ± 20% with respect to the targeted orbital altitude of 3000 meters and 1500 meters. Points= 350 (350/Tolerance(m)) X Targeted Altitude Actual Altitude Successful recovery constitutes 30% (150 points) of flight performance points. Recovery operation is deemed to be successful only if the rocket is Reusable. Evaluating judge(s) makes a visual inspection and evaluates the launch vehicle once it has returned to the camp site.

7 Changes in Category and Its Effect on Team Points Changes in category is reflected on the total points of the team using a coefficient determined by the contest jury. 3. Contest Participation Terms and Changes in Category High school, university and graduate students may participate in the contest. High school students and university and graduate students will compete in the same category. Mixed Teams from different universities and establishments can also be formed to compete in the contest. There are no limitations regarding the number of graduate students in teams Advisor Each team has to have an advisor. Advisors of high school teams may be a teacher in technology and science from their school. The advisors of university teams should be academicians in the fields of Engineering and Natural Sciences (Research assistant, Faculty Member). Applications which do not meet the above requirements will be considered invalid Single Rocket Principle for Each Team Each team can compete with a single rocket and a single rocket is permitted for each category. Competing students can participate in different teams as long as each team has a different team leader. Reporting process specified in Article 5 will be carried out for separately for each rocket. Number of team members cannot be less than 4 or more than 30. Unless the team applied both categories; then the team has to have at least 8 members, 4 different members for each category. Each teams has to have a team leader, a member in charge of launch and a member in charge of post-flight recovery. Job definition for these responsibilities will be announced in a detailed safety booklet which will be published after the summons for contest Changes in Category Teams can change the category they have announced in the Preliminary Design Report during the contest process and no later than the Critical Design Report submittal date. Category changes are not allowed once the Critical Design Reports have been submitted

8 4. Contest Area and Team Working Area Details Teams are required to bring their own equipment. 220V AC power will be supplied in the contest area. 5. Pre-Contest: Contest Calendar Important Dates February 28 th 2019 Situation Application Deadline March 7 th 2019 Deadline for Preliminary Design Report March 29 th 2019 Announcement of Evaluation Results of Preliminary Design Report and Selected Teams May 7 th 2019 Deadline for Critical Design Report May 15 th 2019 July 14 th 2019 August 15 th 2019 August 20 th 2019 August 25 th 2019 September 1 th 2019 September 2019 (will be announced) Announcement of Finalist Teams Deadline for General Test Report Deadline for Launch Readiness Report Announcement of Eligible Teams to Launch Announcement of Transportation, Accommodation Informations and Launch Dates Deadline for Final Design Report Contest Dates

9 5.1. Preliminary Design Report Each team will submit a design report and entry form in the format determined by the contest committee after making their contest applications. Deadline for Preliminary Design Report is March 7 th, pm..ork extension Open Rocket files will also be submitted to support team reports. Preliminary Design Report (PDR) format will be made available on the contest website. In the preliminary design reports, teams are required to use any engine they choose from the motor catalogs which will be announced until the application deadline. According to evaluations of PDR, selected teams will be announced on March 29, The criteria to be considered in the preliminary design report are as follows: Pre-selection Criteria: For Low-Altitude Category, Track Speed During Launch should be at least 15 m/sec and after parachute deployment, rocket should be descended at a maximum rate of 9 m/s. Static margin of the rocket should be between 1.5 and 3. For High-Altitude Category, Track Speed During Launch should be at least 25 m/sec and after parachute deployment, rocket should be descended at a maximum rate of 9 m/s. Static margin of the rocket should be between 1.5 and 3. It is compulsory to use GPS or radio signal positional systems on parts which need to be recovered independently (including Payload) during recovery. The above mentioned criteria will be checked together with the mass, diameter and overall design of the rockets from the open rocket files collected with the preliminary design report. In addition to these criteria, by considering organization, content and originality, the designs which are regarded as inconsistent by the Contest Committee will be eliminated after PDR Critical Design Report Teams must submit their Critical Design Reports before May 7 th, 2019 at pm. Each criterion, design and detail specified in this report will be evaluated as the system to be used in the contest according to which contest committee will give feedbacks. Teams must submit supporting.ork extension Open Rocket files attached to their reports. Report contents and grading details will be announced to participants at a later date. Finalist teams will be announced on May 15 th In case they meet the cost of the rocket engine they have chosen, the motors will be supplied by the Competition Committee. Rocket engines will be delivered to all teams in Tuzgölü, Turkey on the day of the competition Final Design Report Teams must submit their Final Design Reports before the Competition date. Teams must submit supporting.ork extension Open Rocket files attached to their reports. The competition will take place on September 2019 in Tuzgölü, Aksaray.

10 5.4. Minimum Criteria Expected From Report Contents Expectations in Preliminary Design Report It is expected that they will complete the CAD design with the general outline of the rocket they are planning to produce from the teams and they will be able to explain their systems in the file through this design. They have made a comparison for the systems they plan to use and have listed these comparisons with their advantages and disadvantages and are expected to present them in the PDR. With the Open Rocket program, they must complete pre-simulations of the rocket. It is expected that all systems will be able to define the total budget in detail. We expect them to prove why they decided to use it and that they were suitable for their systems. We expect to determine the appropriate engine types Expectations in Critical Design Report Technical feedback is planned to be given to teams after PDR. In accordance with these feedback, teams are expected to finalize the design of their rockets. This means that all the strength of the rocket, which is designed, flow etc. such analyzes should be completed. Thus, the materials and production methods that have been selected can be proved in the computer environment. All Open Rocket simulations must also be completed. Since this process will be an itertive process, it is expected that the stages of the design of the rocket will be explained in the CDR along with the cause and results. Detailed CAD designs should be completed by using the CAD program. Any details written or not in the report should be shown and explained in CAD design. There should be no question left in the Evaluation Board. The assembly of the split systems must be shared with the details of the whole rocket assembly strategy. So how to connect the nose to the body, how to connect the parachute to the body, how to fix the motor to the body that can be removed later, etc. details of the installation of all systems should be explained in the presentation supported by visuals form CAD. How to produce all systems such as body, nose, electronic card and etc. with which materials should be completed. Production plan must be issued. It is expected that the test plan and all tests will be explained in detail. Prototypes of all systems intended to be used should be completed. The prototypes on which the systems work must be proved. In short, it is necessary to prove to the Evaluation Committee that the designs will be produced and their tests will be completed. The CDR Template will be shared with all competitors on (7 March 2019).

11 Expectations in the General Test Report The general test report is expected to meet 80% of the test plan, dates and test patterns specified in the CDR. In the GTR, teams are expected to report the results of all tests performed in accordance with the format. The General Test Report format will be announced on (15 May 2019) Expectations in the Launch Readiness Report 80% of all production and tests should be completed. At the same time, 80% of all production methods are expected to comply. The Launch Readiness Report format will be announced on (14 July 2019) Expectations in Final Design Report All production, tests and assembly of the rocket must be completed at least once. Final Design Report format will be announced on (14 July 2019) Risk Analysis and Check List Just before the flight, the jury committee conducts rocket control risk analysis and inspects the check lists prepared by teams for any missing items 6. Contest Rocket Sub-system Design Criteria This section contains directions for teams participating in the contest to make safer designs Thrust Systems Non-toxic Thrust Systems Launch vehicles competing in the High Altitude Category cannot contain toxic fuels. Ammonium Perchlorate Composite Propellant (APCP), Potassium Nitrate and Sugar (Sugar Propellant), Nitrogen Protoxide (Anesthetic Gas), Liquid Oxygen (LOX), Hydrogen Peroxide, Kerosene (Paraffin), Propane, Alcohol and similar fuels are considered as non-toxic gases. Toxic fuels are defined as fuels which require the using respirators, special containers, transportation infrastructure and protective equipment Ignition of Thrust Systems Thrust systems which can be ignited with one motion such as solid fuel rocket engines are considered ready-to-launch systems Controlled Ignition from Ground Station Rockets will be ignited from a ground station provided by the Contest Committee. Teams must provide their own ignition wires. Ignition wires will be connected to the ground station provided by the Contest Committee.

12 6.2. Recovery Systems Two-Stage Parachute System A Two-Stage Parachute system must be employed in each stage of the rocket. During descent, a total of two parachutes must be deployed: first a drag (primary) parachute is deployed at peak point followed by a second (secondary) parachute deployed at a certain altitude before touchdown. Thus, excessive dragging of rocket is prevented Parachute Deployment System If combustible material or hot gas is employed in the recovery system, these must be isolated from the parachute and shock absorption cables Choice of Colour for the Parachute In order for ground control staff to watch the event live, discernable, remote and bright colors must be chosen for primary and secondary parachutes. Dull colours or shades blue should not be used for parachutes Back-up Avionic System There must be two flight computers in the rocket with one main and one backup. In addition to the main flight computer, rockets must have a separate backup computer that can perform the same basic functions. This backup computer must be fed from a different power source and must be completely connected to separate cables and sensors. This backup computer does not have to be a commercial system. In the case of a non-commercial computer, it is required to perform separation receiving data from the sensor with a different operating principle than the sensor on the host computer. (For example, when receiving data from the barometric pressure sensor, the other is receiving data from the acceleration sensor) The flight computers on the rocket will open when the rocket is on the ramp Separation Systems The systems that rockets use to open the parachute systems at maximum altitudes and at other altitudes cannot work with any flammable or caustic energetic material. Separation systems must be a non-pyro system Rocket Structures Load Bearing Eyebolt Eyebolts used on rockets must be made of solid forged steel. Flexion eyebolts are disallowed.

13 Interior Integration Bodies Interior integration body lengths must be at least one and a half of body diameter Mechanical Connection of Rail Button Rail buttons will be provided by the Contest Committee. Technical drawings of the rail buttons will be shared with all teams after the contest applications are completed. Rail buttons will be shipped to the finalist teams before the competition date. Rail Buttons must be connected to structurally reinforced parts of the body. There must be at least two Rail Buttons on a rocket. The first must be situated in the engine compartment and the second in the middle of centers of gravity and pressure Validation of Rail Button Rail Buttons must be able to support the full weight of the rocket in vertical position. Contest Committee may ask the rockets to be lifted up before being carried to the launching ramp Team Numbers Team numbers (teams assigned numbers by the Contest Committee before the contest), name of the project and academic connections must be clearly visible on the vehicle body Payload and Its Recovery Payload cannot be any lighter than 4 kg. Payload doesn t need to have a scientific purpose. However, Contest Committee supports the construction of Payload built with scientific, experimental and technological application purposes. Payload cannot contain live organisms and/or radioactive materials. Payload must be separated from the rocket. It has to descend independently of the rocket. The payload must be separated immediately after the rocket has reached its peak. If the nose is to be recovered independently of the rest of the rocket, the payload and nose may be lowered together. At this point, you must realize your designs by considering the criteria that your rocket should be found after the shot. Payload must be landed no faster than 9 m/sec. If the Payload will be recovered separately, a two-stage recovery system is not necessary to be employed. It may also be recovered using a single stage parachute system. Payload is not obliged to fulfill any scientific task. Any mass can be used to represent the payload. If you carry an original payload (a designed task), an extra scoring will be performed in the criterion of authenticity.

14 6.5. Launching and Climbing Orbit Limitations Launching Angle Vehicles must be launched at an angle of 84 ±1 respective to the ground and in a directional angle specified by the contest judges. Track of the launching ramp must be 5.5 m in length Climbing Stability Launched vehicles must maintain their stability as they reach climbing orbit Contest Launching Equipment 7. Prize Contest Provisioned Launching Ramp Specifications of launching ramps provisioned by the contest committee will be announced at a later date Contest Provisioned Ignition System Contest committee will provide a control station for ignition. The open end of the wire (ignition wire) will be connected to a 12 V 15A power supply using a bolt. Prizes shown in the below table indicate the total prize to be awarded to winning teams. Individual prizes will not be awarded. The first, second and third prizes; will be divided into equal amounts according to the total number of Team Members and deposited into the bank account to be specified by each person respectively. Commercial Rocket Engine Low Altitude Category High School University and above First TRY 50,000 Second TRY 40,000 Third TRY 30,000 Commercial Rocket Engine High Altitude Category High School University and above First TRY 50,000 Second TRY 40,000 Third TRY 30, Minimum success criteria for prize ranking: To be included in the prize ranking, Contest Committee-approved rocket must perform a smooth ignition and lift off, and reach 50% of targeted altitude specified for the category. Only teams who rank in the top three positions in ranking will be awarded with the aforementioned prizes.

15 8. Safety Safety rules determined according to the contest area will be announced in a separate booklet after the summons for contest. The booklet will contain the safety responsibilities of the contestants.

16 GENERAL RULES AND REGULATIONS Teams have the right to object to the concerned judge through their team leaders. Objections can be made verbally, provided that they are submitted in writing at a later time. Verbal objections must be put in writing within 24 hours. In any case, non-written objections will not be taken into consideration. Objections will be finalized within 24 hours after having examined by the judge panel. Each contestant is responsible for taking the necessary precautions and showing the expected attention to his/her peers and the environment. Turkish Technology Team (T3) Foundation and the organisation committee reserve the right to make any amendments to the specifications in order for the contest to take place in accordance with the specified impartial criteria so that any violations may result in judicial outcomes, to better meet all sorts of requirements by the contestants, to provide necessary safety precautions and to maintain the functionality of the contest specifications. Having made the necessary evaluations following the application deadline, T3 Foundation and the organisation committee reserves the right to cancel the contest given that sufficient number of applications is not reached with the required technical knowledge and skills. TEKNOFEST Safety and Security Terms and Conditions will be communicated to all contestants, delegations and concerned parties. All competing teams are responsible for observing the safety terms and conditions specific to their respective categories specified in TEKNOFEST Safety and Security Terms and Conditions. In this regard, with the exception of security precautions contained in the aforementioned security instructions, it is the contestants responsibility to take additional precautions arising from the systems employed. T3 Foundation and the organisation committee has the right to exclude any and all teams from the contest who do not fulfill the terms and conditions of TEKNOFEST Safety and Security Terms and Conditions to provide a safe environment for holding the contest. T3 Foundation and organisation officials cannot be held responsible for damages arising from the violation of terms and conditions by the contestants, delegations and concerned parties. Regarding the competition, the competitor hereby accepts and consents to any kind of written or visual promotion, publication, social media and internet broadcasting to be made by the T3 Foundation and / or TEKNOFEST before or after the competition. In addition, the competitor agrees and submits that any and all intellectual property generated as pertains to the competition, including but not exclusive to designs, code, and manufactured products, belongs exclusively to the T3 Foundation and / or TEKNOFEST and that the competitor does not have any rights to or demands on these artifacts. T3 reserves the right to disclose all intellectual property thereby for public consumption in a manner it deems fitting. In the event that a competitor infringes upon the intellectual property rights of any product, and T3 Foundation and/or TEKNOFEST incur damages, the responsibility for such damages will be borne entirely by the relevant participant(s). All teams who qualify to compete in the contest will be given a Participation Certificate.

17 STATEMENT OF LIABILITY Turkish Technology Team Foundation and TEKNOFEST are in no way liable for any injury or damage caused by any entry, any entrant, or by the disqualification of an entry. Turkey Technology Team Foundation and TEKNOFEST at large are not responsible for ensuring teams operate their systems within the law of the Turkish Republic. The Turkish Technology Team Foundation and TEKNOFEST, and organisation officials cannot be held responsible for the damages inflicted upon third parties by the contestants. Turkish Technology Team Foundation has the right to make any amendments to this terms and conditions.

18 Appendix-1: Open Rocket Sample Document

19 Appendix 2: Recommendations Primary Parachute Deployment: Primary parachute should deploy at peak altitude. The rocket should not roll in the air. Falling speed of the rocket should be slowed down. However, in order to prevent the rocket from drifting to much in the wind, falling speed should be slowed down to 20 to 40 m/sec by deploying the primary parachute. Secondary Parachute Deployment: Secondary parachute should be deployed no earlier than 600 m and no later than 400m from the ground. It should be descended at a maximum rate of 9 m/sec and a minimum rate of 5 m/sec to prevent damage to the vehicle and its parts. Launching Stability: Vehicles should reach sufficient Track Speed During Launch to ensure that they will follow a predictable course. A rate higher than 30 m/sec guarantees that the rocket will follow a predictable course. Alternatively, teams must prove theoretically (computer simulation) or empirically (flight tests) that the rockets can maintain stability at a lower Track Speed During Launch. Track Speed During Launch will have been proven in the Open Rocket file attached to the final report submitted before the contest. Static margin is the distance between a rocket s pressure and gravity centers in terms of diameter. If the static margin of a rocket is larger than its diameter, the rocket is considered stable. If the vehicle s static margin is larger than both body tube diameters, it is considered over-stable. Overstable vehicles should be avoided. Safety: It is recommended for teams who want to carry out trial launches and thrust tests with their own means in order to base their efforts on code 1125 of the US National Fire Prevention. Link: pdf Turkish Technology Team Foundation has the right to make any amendments to this terms and conditions.