Medzinárodný časopis zameraný na výskum Marsu | ISSN 2453-8760 | Aktuálne číslo: 4 Ročník 4

Slingshot based space rocket launcher

Abstract: In space research, rockets are used to explore the space and also rockets uses fuel to travel in space. Here the proposed Slingshot mechanism can be used in space research and to travel without fuel. The comparison of basic model of rocket and slingshot mechanism is made in this paper. Rocket uses fuel to go into the space. Whereas slingshot based space rocket launcher is an advance technology used to explore in space without using fuel. This mechanism can be used to send satellites and capsules to the planets.

Introduction

Figure 1: Basic Model of the Rocket.

Figure 1: Basic Model of the Rocket.

Thrust is been produced by burning fuel in the Rocket. In most of the rocket engines changes the burnt fuel into a hot gas. This hot gas is pushed out from the back of the engine which makes the rocket move forward.

Mainly there are two types of rocket engines. Liquid fuel is been used in some of the rockets. Even the main space shuttle orbiter engines also use liquid fuel. Even the other rocket uses solid fuels. Two solid white rocket boosters are placed on the side of the space shuttles. These are solid fuels. Solid fuels are even used to fly fireworks and model rockets.

The fuel is been burn by a chemical type called as oxidizer. Most type of the burning on this earth uses Oxygen as it’s widespread on this atmosphere. However, in space there is no atmosphere to provide oxygen or other oxidizers so rockets need to carry up their own oxidizers. Usually the fuel and the oxidizer are carried in different tanks and they are released in proper proportion with the fuel whenever rocket is fired.

The Basic working principal of the Rocket is based on Sir Isaac Newton’s third law (every action has an equal and opposite reaction). Thus in order to move rocket in forward, something has even rush backwards. That thing is the propellant. The propellant is a material that spews out of the back of the spacecraft giving it thrust, or a push forward.

A very large volume of very hot gas is produced when propellant kind of fuel is burnt with an oxidizer. These gasses expand until they rush out of the back of the rocket, making thrust. If propellant is not burnt completely and pushed directly out of the spacecraft, making thrust through the nozzle.

Problem Statement

  • Saving of fuel in space is the main problem listed in today’s space rocket technology.
  • Propellants can be in the form of a solid, liquid or gas
  • Fuel consumption in the air-breathing jet engines is inversely proportional with the speed. Which means the fuel consumed per kilometer or per mile can be a more appropriate comparison for aircraft that travels at very different speeds? So, it can save the fuel for further space travel.
  • So I came up with an idea to use a basic technology that can be implemented to the rockets which can be used for the further long distance space travel like mars mission, Jupiter mission, etc.
  • Saving of fuel and increasing the efficiency of rocket has become the biggest research in today’s space technology.
  • For moving in space, a high specific impulse is the desired quality, but propellants with high specific impulse will not produce sufficient thrust to get into space from Earth’s surface.
  • This is actually due to the larger fuel tanks that contain a lower density propellant and the atmospheric drag that acts on the tanks when the rocket moves against the Earth’s gravity.
  • The other ease propellant consideration is ignition, stability combustion, stability, reliability, temperature, cost and availability.
  • As a result, different propellants are used for different missions and differ among the stages of any given rocket.

Literature Survey

Thеrе arе several papers reporting the Space Rocket launcher algorithms and much methods. Lіtеraturе survеy discussing about thе papеrs whіch arе rеfеrrеd for dеvеlopіng projеct. Thе hіghlіghts of еach papеr and also thе drawback іn іt and ovеrcomе of projеct іs dіscussеd.

As per the author [1] rocket launching may cause temperature changes in atmosphere, high pressure and many poisonous gases, which is harmful for the instruments and operators in the launching site. Thus a mathemadical model has been developed for the electromagnetic launcher

  1. Robson [3], technology of “The need for space”, has historically undervalued the space industry, having abandoned the launcher technology and has given us the major input view pints on space rocket launcher.

As per the [3] author the parameters to be tested are the combustion principle, the composition of the propellant, the ignition principle, and the geometry of the combustion chamber and the nozzle placment for the development of the Space Rocket launcher.

Proposed Research work

Figure 2: The sling shot toy which is used as a basic mechanism and is sane applied for rocket design.

Figure 2: The sling shot toy which is used as a basic mechanism and is sane applied for rocket design.

Aim: The main aim of the rocket is to travel faster, farer with low fuel consumption.

Figure 3: Shows the payload is under tension the strings which are held between the rockets shown in figure.

Figure 3: Shows the payload is under tension the strings which are held between the rockets shown in figure.

Arrangement of payloads inside the rockets: As shown in figure 4, initially the main rocket with thrusters is taken which has to be escaped from the Earth’s gravity. There is a payload inside which is less in size when compared to the outer rocket. It is hold by a high tension wire let it be called stage 1. Inside it there is another stage 2 and this is also under tension by stage 1 and stage 3 due to the tension in stage 2. So the each stage has another stage in it with the tension in it.

Figure 4: Shows the schematic arrangement of rocket by keeping each stage under tension.

Figure 4: Shows the schematic arrangement of rocket by keeping each stage under tension.

Working: when the rocket takes off from the earth with some thrusters and then escapes from the earth’s gravity. The rocket opens the dome now the stage 1 having stage 2 and stage 3 in it. Stage 1 under high tension when released goes off with high speed after some distance the dome of stage 1 is removed which has stage 2 with high tension in it. The already stage 1 which is under high velocity after a long distance when thrusters are started (Newton’s third law) when released the stage 2 gains more velocity compared to the stage 1 and so on, going with stage 3.

Comparison: Imagine a bowler in cricket runs from a very far distance to give the ball the initial velocity. And he throws the bowl with high speed. The bowler can be compared to the stage 1 and stage 2 and stage 3 can be compared to the ball.

The figure 2 shows a slingshot toy at level 1, when the wire is not under tension and the object is under rest so at level 2 the string is under tension and the object is also ready to fly. At level 3 when the string has left the object and this takes its own trajectory path as shown in level 3 figure.

Here the figure 2 shows the rocket designed. That is arrangement of payload in the rocket which is under tension here the payload is compared to the object and launch vehicle is compared to the wooden piece which holds the strings.

The figure 4 shows how the rocket should be arranged in order to achieve high fuel saving efficiency the payload is deep inside the rocket. The stage 1 is a launch vehicle which helps to go into space after it reaches the stage one goes off and stage 2 which was under tension by stage 1 is released and goes on the same thing with stage 3 also and ultimate the payload is released where ever required.

Conclusion

Instead of using centripetal force which thus creates artificial gravity for travelling in space we can use this technology so that we can send satellites to father distance without using fuel in space.

Acknowledgements:

I would like to thank all my friends and family for their support. I would like to thank our beloved principal Dr. Badarinarayan K.S. I would like to thank Dr. Cyril Prasanna Raj P, Professor and Dean, MSEC Bangalore.  I would like to thank all the R&D department of MSEC, Bangalore.

Author:

Name: Tejas G Naik1, Chetan Naik J2, Abhilasha A3

Affiliation:  1Final Year B.E (Mech), 2Assistant Professor, 3Embedded Engineer.

E-mail: 1tejasgnaik076@gmail.com, 2chetanmassand@gmail.com, 3abhiappaji1991@gmail.com

Keywords:

Sling Shot, Space Rocket, Space application.

References:

[1] K. Wang, H. Xiang and Z. Li, “Dynamic simulation and anlysis of rocket electromagnetic launcher,” Electrical and Control Engineering (ICECE), 2011 International Conference on, Yichang, 2011, pp. 3014-3016.

[2] J. Fragola, J. D. Baum, D. Sauvageau and S. J. Horowitz, “Reliability and crew safety assessment for a solid rocket booster/J-2S launcher,” RAMS ’06. Annual Reliability and Maintainability Symposium, 2006., Newport Beach, CA, 2006, pp. 545-550.

[3] D. Robson, “Satellites – The need for space,” in Communications Engineer, vol. 4, no. 6, pp. 26-29, Dec.-Jan. 2006.

[4] T. Neff, M. Rehberger and A. Meroth, “Thrust test bench for student rocket engines,” 2016 11th France-Japan & 9th Europe-Asia Congress on Mechatronics (MECATRONICS) /17th International Conference on Research and Education in Mechatronics (REM), Compiegne, 2016, pp. 141-145.

Bibliography and publishing information:

Science & Mars Journal: Volume 4, Issue 2

Editorial review

In this paper author proposes a new method for rocket technology, called space slingshot. The article describes the use and implementation of the slingshot in the rocket technology and describes the advantages of use of this system. Author proposes to use the system for future planetary and space exploration. Article creates an interesting base for future study and research of this technology in the rocket engineering. Editor’s note: The text was published as original manuscript sent by its author. The style and grammar was not checked by reviewer.

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