Model Rockets Research Articles

The Effect of Moveable Fins on Trajectory and Aerodynamic Characteristics of Model Rockets

The application of the fins on the rocket are necessaryto achieveoptimal flight performance. However, the appearanceof gust wind can affectthe stability of the rocket during flight. To minimize instability, the fins are designed to be adjustable by changing the fin cant angles.This study aims to investigate the effect of different cant angles on rocket’s trajectory and aerodynamic characteristicsthrough computer simulation.The Open Rocket software is used to conduct the simulations. The range of cant angle in this study is from0°to 15°and the Clipped Delta fin design is chosen for this study. The launch condition is all the same for all the model rocketsand the launch site’slatitude and longitude wasbased on Parit Raja location. The trajectory characteristics were evaluated through simulations of altitude versus position east of launch, altitude versus position north of launch, and altitude versus lateral distance. Meanwhile, the aerodynamic characteristics were evaluated through simulations of stability margin and drag force over time. This study found thatthe maximum altitude for each model rocket is decreasing as the cant angle increases. Different fin’scant angles slightly alter the trajectory characteristic of model rockets,but they do not significantly impact the overall stability and drag characteristics during critical phases of flight. Higher cant angles resulted in shorter horizontal and lateral distances from the launch site to the apogee, suggesting a more vertical trajectory.

Investigation of Flight Performance of Notched Delta Wing Rockets on Different Types of Nose Cones

In this study, four solid fuel model rockets with conical, parabolic, power and haack series nose cones that can carry 4 kg payload at an average altitude of 3 km were designed in the OpenRocket program. Later, the notched delta fin model was mounted on these designed model rockets. The effects of this fin model on the changes in the speed, stability, acceleration, weight and altitude of the rockets were analyzed numerically in the OpenRocket program. As a result of the analysis, it was determined that the conical nose rocket showed the worst flight performance and the Haack series nose cone rocket model showed the best performance. When used with the notched delta fin of the Haack series model, it was determined that the rocket's altitude increased by 7.67%, and its speed increased by 1.83%, but decreased by 1.2% in mach number, 0.6% in weight, 0.3% in acceleration, and 4.5% in stability. As a result, it was seen that it would be beneficial to consider the nose cone and fin together when evaluating the flight performance of the rocket. The results obtained in the study have shown that the notched delta fin model can be used experimentally in defense industry and model rocket applications and the studies can be advanced.

Static stability study of a model rocket

Relevance. When designing flying models of rockets, one of the difficult tasks is to ensure the static stability of the rocket in flight along a given trajectory. Static stability refers to the ability of a model to return to an equilibrium position disturbed by external forces (wind, model asymmetry, etc.). In this case, the model must be stabilized in terms of the angle between the longitudinal axis of the model and the direction of flight (velocity vector), i.e. maintain a zero angle of attack. The condition for ensuring the static stability of the rocket model is the location of its center of gravity ahead of the center ofpressure. In this case, when the angle of attack is different from zero, the aerodynamic forces will create a stabilizing moment, which will return the model to a zero angle of attack. The purpose of the study is to develop and compare methods for determining the position of the center of pressure of a rocket and determining its static stability. A simplified method, an analytical calculation, a graphical method, and various practical approaches that can be used in rocket modeling are considered. As research methods, an analytical approach, a graphical method and finite element modeling in the SolidWorks Flow Simulation program were used. In addition, a number of approximate calculation methods were considered. The study analyzes the capabilities of the considered methods for determining the static stability of a model rocket and the error of their application. To confirm the results of the calculation, a computer experiment was carried out in the form of blowing a finite element model of a rocket using the SolidWorks Flow Simulation program. The results of computer simulation confirmed the reliability of the proposed methods for determining the static stability of a model rocket. Research results. Simplified methods for determining the static stability of a rocket are the simplest and most reliable when designing model rockets. It is advisable to use it for launching demonstration rockets with an allowable misalignment error of 15% or more. Analytical methods are useful for designing sports models of rockets with high flight requirements, for example, for international competitions. Conclusion. The proposed method for ensuring the static stability of a model rocket makes it possible to simplify the design process of both demonstration and sports models of rockets for reliable demonstration launches.

Recent Advances of Design Optimization Techniques in Solid Rocket

A solid-propellant rocket or solid rocket refers to a rocket with an engine using solid propellants. The earliest solid rockets were powered by gunpowder. It is still used today in military armaments worldwide, model rockets, solid rocket boosters and on larger applications for their simplicity and reliability. With the fast development in the complexity of rockets, the importance of optimisation where the overall performance is maximised has been shown. Engineers are routinely given design tasks to find a design meeting the stringent constraints. For instance, researchers developed different optimisation techniques to maximise the overall performance while decreasing the economic and time requirements. This paper has reviewed four types of recent advances in design optimisation techniques used in solid rockets, with all the findings and analysis summarised. In conclusion, this study provides a useful reference to people who would like to know about different types of optimisation used in the current astronautical engineering field.

Investigation on solid propellant test and time calibration for complete combustion

A solid propellant is simple and reliable rocket fuel. Once ignited, the propellant cannot be stopped since they burn until they run out. Solid fuel rockets are widely used in military applications such as missiles, model rockets, boosters for satellite launchers and so on because they can be stored for long periods of time without degrading the propellant. The primary objective of this research is to study the burnout mass of solid propellants using various propellants and catalysts. Potassium Nitrate (KNO3) was chosen as an oxidant in the experiment because of its compatibility with other ingredients and low-cost affordability. KNO3 was used as an oxidizer in a 65% ratio with 34% of the fuel and 1% of the catalyst. KNO3, fuel ingredients like Fructose, Glucose and Lactose with catalysts Copper and Aluminum were taken in powdered form. Cylindrical stainless steel with one closed end was taken to fill the cavity, and a concentric hole was made for constant burning. This propellant-filled chamber is fixed strongly in a position so that it does not propel during fuel combustion when thrust is formed. The obtained result shows that the longest burnout mass was secured by burning Glucose with Copper powder and KNO3 for 136 s when compared to the shortest burnout mass was secured by burning Lactose with Aluminum powder and KNO3 mixture to 57 s. The highest temperature of the mixture was Lactose with Copper powder and KNO3 resulted in 518 °C when compared to the lowest temperature of the mixture was Glucose with Copper powder and KNO3 was 211.75 °C.

Student firing tests and launches with commercial and self-made solid rocket motors

This paper presents work performed by students at Sapienza University of Rome regarding on-ground testing of solid rocket motors and launch of single-stage rocket models. The activities are part of a multidisciplinary project, in collaboration with the Italian Space Agency, aimed at the design, test, build, and launch of model rockets to be used as technological demonstrators and for educational purposes. Student activities included: (i) building of electronic components; (ii) designing and building of an experimental test bench; (iii) manufacturing of rocket parts and fuels; (iv) static firing tests of commercial and self-made solid rocket motors; (v) rocket launches. Self-made solid propellants were obtained as a mixture between potassium nitrate and sorbitol, yielding chamber pressures up to 20 bar and thrust up to 20 N, while commercial motors with thrust up to 90 N were tested. Additive manufacturing was employed for building specific rocket parts such as the nosecone, fins, and videocamera housing. The payload consisted in self-programmed board computers which recorded telemetry during flight. A total of four rocket launches up to 540 m have been performed.

Design & analysis of solid rocket using open rocket software

Model rockets are small sized rockets which are used to understand how a full-sized rocket along with its engine works. In this project design, analyze, fabrication and testing of a Solid Propellant Rocket Model carried out. Solid rocket motors (or SRMs) are systems with minimal moving parts. An input is amplified to the igniter, which produces hot gases. The main propellant grain is ignited by hot gases. Because the propellant comprises both fuel and oxidizer, this equipment are capable of operating in the vacuum of space. The high thermal energy of the combustion gases is transferred to kinetic energy in the exhaust, resulting in thrust.The body of the rocket designed using Open Rocket software and analyzed its flight characteristics using the same software. In this research work Dextrose used as the fuel and Potassium Nitrate used as the Oxidizer and made the solid propellant for the rocket. After that the motor is tested using a thrust stand. The body of the rocket fabricated and assembled it with the motor. Finally, tested the rocket by launching it using a launch pad.

Cold-Crafted KNSu Mechanically Pressed Burning Rate for Combustion Pressure Ranging from 0.9 to 7.7 bar

ABSTRACT Potassium nitrate/sucrose propellant (KNSu) is a common solid propellant, which can be cold or hot crafted, employed in amateur and experimental model rockets. There is limited burning rate data available for the KNSu, particularly for the cold-crafted one. In this study, KNSu composed of 65% potassium nitrate and 35% sucrose was prepared through cold crafting and by pressing with a hydraulic press. For such a particular crafting method, we did not find any experimental data on the burning rate versus combustion pressure. Therefore, we experimentally determined the cold-crafted KNSu burning rate for pressure levels ranging from 0.9 to 7.7 bar. We employed a ballistic evaluation motor with varying nozzle diameters to obtain the desired combustion pressure. We demonstrate that the cold-crafted KNSu burning rate lies in the range of available data for the hot-crafted version. The burning rate is not sensitive to combustion pressure levels lower than 2 bar, and the combustion temperature is 98.7% of the theoretical value. We also explain the estimation the combustion pressure from the thrust-plotted curve or by using the engine burning video.

Stacked-cup multiwall carbon nanotubes as components of energy-intensive suspension jet fuels

Objectives. The addition of high-density carbon materials to jet fuels can lead to a significant increase in the volumetric energy of the fuel combustion. The purpose of the current study was to thermodynamically analyze the possibility of obtaining model hydrocarbon fuels from toluene and T-1 using stacked-cup multiwall carbon nanotubes (MWCNTs). Methods. Bomb combustion calorimetry was used to define the combustion energy of the MWCNTs in the crystalline state. The temperature dependence of the MWCNTs’ heat capacity in the range 5–370 K and the fusion parameters were estimated using low-temperature adiabatic calorimetry. The physical density of MWCNTs was measured using the pycnometric method. The sedimentation stability of the mixtures of MWCNTs with liquids was determined using centrifugation at 7000 g. The calculations were carried out in MS Excel. Results. The energy and enthalpy of combustion of a technical sample of MWCNTs in the crystalline state were determined. Based on the smoothed heat capacity values, the standard thermodynamic functions (enthalpy, entropy, and Gibbs reduced energy) of MWCNTs in the crystalline state were obtained in a temperature range of 0–2000 K. The extrapolation of the MWCNTs’ heat capacity was carried out at a temperature of up to 2000 K using the heat capacity of crystalline graphite. It has been established that mixtures of MWCNTs with liquids containing more than 33 mass % of MWCNTs are stable during centrifugal sedimentation at 7000 g. For the toluene–MWCNTs and fuel T-1–MWCNTs model systems, the specific and volumetric combustion energies, the adiabatic combustion temperatures, and the conditional final maximum speed of the model rockets with fuel of various compositions were also calculated. Conclusions. The thermodynamic analysis showed that the addition of MWCNTs can significantly increase the volumetric energy intensity of traditional jet fuels, which can in turn improve the operational characteristics of drones and rockets.

The Effectiveness of Model Rocketry to Teach Science and Quantitative Content to Students in a Non-Science Majors Course at the College Level: An Example from a Planetary Geology Course

Engaging non-science majors in a college-level science course can prove challenging. In turn, this can make it difficult to effectively teach science and math content. However, topics related to planetary exploration have a unique way of capturing one’s imagination and may serve to robustly engage non-science majors. In this contribution, I 1) describe a model rocketry lab module, I have created and implemented into an introductory-level planetary geology course and 2) quantify student learning gains as a result of this module. This module builds on model rocketry lesson plans for science and math coursework at the K-12 level (e.g., [1] [2]) and involves students working in groups to 1) design and build model rockets to carry out a theoretical mission that addresses a science question the students have developed, 2) launch their rockets and collect related data, 3) synthesize and evaluate their data, and 4) report their results in both oral and written forms. The tasks of building and launching the model rocket serve as a vehicle that allows students to employ the scientific process while learning about planetary mission design and applying geologic and quantitative skills useful to answering a science-related question. Quantification of student learning gains shows that through this lab module, students significantly improved their quantitative and scientific reasoning skills. Results from student questionnaires showed a significant increase in student interest and confidence in addressing scientific questions as well as an understanding of how planetary missions are designed and conducted.

Determination of aerodynamic drag coefficients using a drop test with a wireless accelerometer and its application to model rockets

The use of drag coefficients to quantify the drag force on objects moving through air is a key concept in aerodynamics. However, gaining access to a wind tunnel, the conventionally used apparatus with which to measure drag coefficients, can be difficult for students and educators at the undergraduate level. Several methods have been proposed as alternatives to the wind tunnel, but these often suffer from experimental complexity. In this paper, we propose a straightforward method using a wireless accelerometer to eliminate several common drawbacks of previous methods, enabling a simpler and direct analysis of drag. Here, we describe the method and its validation along with an application to model rockets as a possible undergraduate laboratory experiment. We also discuss an inconsistency regarding the drag coefficient of a typical model rocket and use it as an example of not taking published results at face value.

“You Heard Me Swear but You Never Heard Me!” negotiating Agency in the pupil referral unit classroom

ABSTRACTThis study explores the exercise of student agency in an alternative educational setting in England by considering students’ verbal interactions during an art lesson in which they created masks and during an engineering lesson in which they developed model rockets. We build on pre-existing operationalisations of student agency by drawing attention to some of the more particular linguistic features that characterise the exercise of agency in immediate classroom situations. Our findings demonstrate that the participating students were responding to, renegotiating, or resisting their teacher’s agendas in subtle ways, depending on the contingencies of the moment.

Which contains the most?

When implementing STEM activities, such as model rockets blasting off or paper airplanes flying across the room, the mathematical or scientific content can get lost as we focus on the “wow factor.” However, meaningful learning experiences can be implemented anytime by employing the components of the 4E×2 instructional model. In essence, the model promotes students exploring their ideas before constructing an explanation for their concept, allowing the development of deeper understanding and connections with multiple conceptions.

モデルロケットを用いた中学生向け体験型学習の試み

This paper describes an effective learning method using model rockets for junior high school students to increase their interest in science and engineering. First, we conducted the model rocket workshops and taught how to make model rockets for junior high school students. Next, we organized the model rocket competition that the participants compete for the accuracy of a model rocket’s landing point. Almost all the students took part in the competition using their own designed model rockets. The results of the questionnaire conducted for the competition participants indicated that a lot of participants enhanced the interest in model rockets. In this paper, we report that the experience-based learning gives children the opportunities to learn proactively towards the goal.

Steering Toward Normal by Rebecca Petruck (review)

Reviewed by: Steering Toward Normal by Rebecca Petruck Thaddeus Andracki Petruck, Rebecca Steering Toward Normal. Amulet/Abrams, 2014 328p ISBN 978-1-4197-0732-2 $16.95 R* Gr. 6-10 Diggy has spent all thirteen years of his life with his father, having been left on Pop’s doorstep as a baby when Diggy’s mother famously left town riding a tractor. Diggy’s classmate Wayne—almost a year older—now finds himself in a similar situation when his mother’s death leads to his dad’s alcoholism spiraling out of control and dumping Wayne at Pop’s place in a drunken fit, with the bombshell that Pop is actually Wayne’s father. Diggy must learn to adjust to having a brother—especially one “from town”—at the height of an already stressful season for him: he’s being groomed by the reigning champion 4-H steer-raiser (on whom he also has a major crush) to take over her top slot with his calf, Joker. Meanwhile, Wayne gets a steer of his own in order to fit in better with his new family while still trying to get a handle on his grief and shifting relationships. Petruck expertly manifests the gruff ways that teenage guys—especially brothers—express vulnerability coated with a veneer of hobbies and practical joking, and she slowly draws her characters together over steer grooming and model rockets. The parallels between Diggy and Wayne’s feelings of abandonment are subtly but divergently developed; as Diggy throws himself into obtaining future goals to win approval, Wayne dives into the past, hoping that by finding Diggy’s mother, he can achieve closure on his own mother’s death. Pop is also a character in his own right, dispensing world-wise advice, learned from his flawed past. It’s the warm but difficult relationship between Diggy and Wayne that makes this one a purple ribbon (with a 4-H glossary and practical joke handbook for city folks in the back matter). Copyright © 2014 The Board of Trustees of the University of Illinois

New Capabilities and Discovered Interconnectivities for a Curriculum-Integrated Multicourse Model Rocketry Project

To provide students a more coherent and cohesive view of the mechanical engineering curriculum, we created and are delivering a multicourse curriculum-integrated engineering project that permeates and unifies five required classes within our undergraduate curriculum: 1) Freshman Design, 2) Dynamics, 3) Numerical Analysis, 4) Fluid Mechanics, and 5) Thermodynamics. Students enrolled in these Rocket Project (RP) classes design, build, flight test, and analyze model rockets through hands-on exercises. These activities challenge students to work on different aspects of the same rocket project across all four years of their degree program. Critical to the seamless collection and presentation of data and experimental/numerical techniques across five courses was the development of new laboratory, field, and simulation capabilities driven by our goal: to measure all unknown variables needed for rocket performance analysis and modeling in-house without reliance on external data. These needed capabilities included: 1) collecting acceleration and barometric altitude data from a model rocket flight, 2) simulating via computer rocket trajectories for comparison to actual measured altitudes, 3) evaluating rocket performance by numerical methods to validate modeling assumptions, 4) determining rocket drag coefficient as a function of Reynolds number for velocities relevant to a launch, and 5) measuring rocket motor thrust as a function of time as well as the energy density of the fuel used. As these capabilities were developed, additional course interconnectivities and opportunities for data sharing were discovered and exploited to further enrich the course experience for students.Â

Personal Reflections on Big Science, Small Science, or the Right Mix

Late June, 1969, at a suburban Philadelphia day camp. There was much to look forward to: color war, soccer, nature hikes, bug juice, barbecues, swimming, softball, and, of course, no school! But I paid little attention, as for me these paled compared with the upcoming big event, the much-anticipated launch of Apollo 11, the rocket that would fulfill President Kennedy’s call to land men on the moon and bring them back home. During the next few weeks, my parents and I spent hours glued to the TV; and my parents quietly endured the smell of glue emanating from model rockets and lunar modules taking form in my room. Some 20 years later, Bernadine Healy, Director of the National Institutes of Health, called for a moon shot for women’s health. The resulting Women’s Health Initiative (WHI) would be a big science effort that would invest substantial resources, enabling scientists to address questions about hormone replacement therapy, supplementation with Vitamin D and calcium, and diet as interventions that might prevent serious health conditions faced by postmenopausal women. Like National Aeronautics and Space Administration’s moon shot, the National Institutes of Health’s WHI succeeded1; a national team of top-notch scientists enrolled well over 100 000 women into several randomized trials and observational studies. The surprising findings of the relative harms of hormone replacement therapy led to sweeping changes in clinical practice and likely played a role in the past decade’s decline in breast cancer incidence. Now, 25 years later, American science and engineering face an uncertain future. Although big science projects have always generated controversy, shrinking budgets have invited only more criticism. The United States invests a lower proportion of its Gross Domestic Product into research and development than several other economically developed nations.2 Of perhaps greater concern, there has been …

This Is Rocket Science!

Using model rockets to teach physics can be an effective way to engage students in learning. In this paper, we present a curriculum developed in response to an expressed need for helping high school students review physics equations in preparation for a state-mandated exam. This required a mode of teaching that was more advanced and analytical than that offered by Estes Industries,1 but more basic than the analysis of Nelson et al.2,3 In particular, drag is neglected until the very end of the exercise, which allows the concept of conservation of energy to be shown when predicting the rocket's flight. Also, the variable mass of the rocket motor is assumed to decrease linearly during the flight (while the propulsion charge and recovery delay charge are burning) and handled simplistically by using an average mass value. These changes greatly simplify the equations needed to predict the times and heights at various stages of flight, making it more useful as a review of basic physics. Details about model rocket motors, range safety, and other supplemental information may be found online at Apogee Components4 and the National Association of Rocketry.5

Knowing the Stability of Model Rockets: A Study of Learning in Interest-Based Practices

This article adds to sociocultural theories of learning by investigating knowing and learning in the hobby of model rocketry. Hobbies are paradigmatic of interest-based, long-term pursuits and studying the tailored practices the rocketeers craft for themselves sheds further light on the relationship between the nature of practices and the learning processes that emerge in their enactment. My window into this issue is the core problem of determining the stability of model rockets, across phases of design, construction, and flying. Using ethnographic and experimental data, I catalog the various individual and collective ways of knowing rocket stability and articulate the manners in which they operate to foster and sustain the highly tailored pursuits characteristic of interest-based practices.

High-Speed Video Analysis in a Conceptual Physics Class

The use of probe ware and computers has become quite common in introductory physics classrooms.1 Video analysis is also becoming more popular and is available to a wide range of students through commercially available and/or free software.2,3 Video analysis allows for the study of motions that cannot be easily measured in the traditional lab setting and also allows real-world situations to be analyzed. Many motions are too fast to easily be captured at the standard video frame rate of 30 frames per second (fps) employed by most video cameras. This paper will discuss using a consumer camera that can record high-frame-rate video in a college-level conceptual physics class. In particular this will involve the use of model rockets to determine the acceleration during the boost period right at launch and compare it to a simple model of the expected acceleration.