Thermokinetic Analysis and Performance Evaluation of Guanidinium Azotetrazolate Based Gas Generating Composition for Testing of Solid Rocket Motor Nozzle Closures

2018 ◽  
Vol 43 (10) ◽  
pp. 1006-1012 ◽  
Author(s):  
Erezhath Shani Harikrishnan ◽  
Bodagala Hariharanath ◽  
Gayathri Muraleedharanpillai Vineeth ◽  
Pokkan Purushothaman
Keyword(s):  
Performance Evaluation ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Thermokinetic Analysis ◽  
And Performance ◽  
Solid Rocket ◽  
Guanidinium Azotetrazolate

scholarly journals A New Erosive Burning Model of Solid Propellant Based on Heat Transfer Equilibrium at Propellant Surface

2020 ◽  
Vol 2020 ◽  
pp. 1-9
Author(s):  
Yanjie Ma ◽  
Futing Bao ◽  
Lin Sun ◽  
Yang Liu ◽  
Weihua Hui
Keyword(s):  
Heat Transfer ◽  
Heat Flux ◽  
Burning Rate ◽  
Rocket Motor ◽  
Solid Rocket Motor ◽  
Erosive Burning ◽  
Computational Data ◽  
And Performance ◽  
Solid Rocket ◽  
Propellant Surface

Erosive burning refers to the augmentation of propellant burning rate appears when the velocity of combustion gas flowing parallel to the propellant surface is relatively high. Erosive burning can influence the total burning rate of propellant and performance of solid rocket motors dramatically. There have been many different models to evaluate erosive burning rate for now. Yet, due to the complication processes involving in propellant and solid rocket motor combustion, unknown constants often exist in these models. To use these models, trial-and-error procedure must be implemented to determine the unknown constants firstly. This makes many models difficult to estimate erosive burning before plenty of experiments. In this paper, a new erosive burning rate model is proposed based on the assumption that the erosive burning rate is proportional to the heat flux at the propellant surface. With entrance effect, roughness, and transpiration considered, convective heat transfer coefficient correlation proposed in recent years is used to compute the heat flux. This allows the release of unknown constants, making the model universal and easy to implement. The computational data of the model are compared with different experimental and computational data from different models. Results show that good accuracy (10%) with experiments can be achieved by this model. It is concluded that the present model could be used universally for erosive burning rate evaluation of propellant and performance prediction of solid rocket motor as well.

Design of an Air-Launched Tactical Missile for Three Different Propulsion Systems: ATR, Rocket and Turbojet

2007 ◽  
Author(s):  
Henrik Edefur ◽  
Fredrik Haglind ◽  
Stefan Olsson
Keyword(s):  
Fuel Efficiency ◽  
Engine Performance ◽  
Rocket Motor ◽  
Point Of View ◽  
Load Factor ◽  
Solid Rocket Motor ◽  
Final Size ◽  
Large Maximum ◽  
And Performance ◽  
Solid Rocket

The objective of this paper is to assess the feasibility of a solid propellant Air Turbo Rocket (ATR), in comparison with a conventional turbojet engine or a solid rocket motor, as power source for a medium range tactical air-launched missile from an overall system point of view. A sizing method for missiles is developed, which together with flight performance calculations and engine performance data determines the final size and weight of the missile and its engine. The results suggest that an ATR engine is more favourable than a jet engine when the ratio between maximum (manoeuvre) thrust and minimum (cruise) thrust is large; for example for a mission including a cruise segment and a high load factor manoeuvre made at constant speed. For the missile range investigated in this paper no breakpoint in distance has been found beyond which the ATR engine becomes impractical. The rocket motor can produce a huge amount of thrust, thus giving it a very large maximum to minimum thrust ratio. However, it has a disadvantage in its low fuel efficiency and high combustion temperature, making it impracticable for missions requiring any longer duration. Altogether the choice of propulsion system has a large impact on maximum take-off weight, size and performance of the missile.

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