Bir İtki Vektör Kontrol (İVK) Test Sistemi Tasarımı ve Uygulaması
Roket motorları, üretilen itki kuvvetine bağlı olarak performanslarının değerlendirilmesi için statik olarak test edilmektedir. Roket motoru statik test değerlendirmesinin en önemli parametrelerinden biri motorun ürettiği itki değeridir. Üretilen itki, yük hücreleri ile donatılmış bir yapısal eleman olan İtki Vektör Kontrol (İVK) Ölçüm Sistemi kullanılarak ölçülür. Bu çalışmada, katı yakıtlı roket motorunun itki performansını ölçmek için bir yük sensörü sistemi tasarlanmıştır. Test sisteminde, altı serbestlik derecesine göre roket motorunun ateşleme boyunca üretmiş olduğu kuvvetler ve momentler ölçülmüştür. Elde edilen deneysel sonuçların ve analiz sonuçlarının birbiriyle uyumlu olduğu görülmektedir. Tasarlanan stand, 50 [kN]'a kadar eksenel itki üreten roket motorların eksenel itkisini, yanal (yanlış hizalanmış) itki bileşenlerini ve yuvarlanma momentini ölçebilmektedir.
Design and Implementation of a Thrust Vector Control (TVC) Test System
The rocket engines are tested statically to evaluate the performance of engine based upon thrust produced. One of the most important parameters of the rocket engine static testing evaluation is to measure the thrust produced by the engine. The thrust produced is measured using a Thrust Vector Control (TVC) test system which is a structural element equipped with load cells. In this study, a load sensor system was designed to measure the propulsion performance of a solid propellant rocket motor. The forces and moments of the rocket motor with respect to the six degrees of freedom of the test system were measured during firing. It is seen that the obtained experimental results and the analysis results are compatible with each other. The designed stand is capable of measuring axial thrust and lateral (misaligned) thrust components, and the rolling moment for rocket motors producing axial thrust up to 50 [kN].
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- Runyan R.B., Rynd J.P., Seely J.F., “Thrust stand design
principles”, AIAA 17th Aerospace Ground Testing
Conference, July 6-8, Nashville, TN, USA, (1992).
- Turner M.J.L., Rocket and spacecraft propulsion.
Principles, Practice and new development (Third edition),
Springer-Praxis Publishing Co., U.K, (2009).
- Mattingly J.D., Elements of propulsion: Gas turbines and
rockets, AIAA Publishing Inc., Virginia, USA, (2006).
- Brimhall Z.N., Atkinson J.P., Kirk D.R., Peebles H.G.,
“Design of a novel six degree of freedom solid rocket
motor
test
stand”,
AIAA
2007-5331
43rd
AIAA/ASME/SAE/ASEE Joint Propulsion Conference
& Exhibit, July 8-11, Cincinnati, OHI, USA, (2007).
- Brimhall Z.N., Divitotawela N., Atkinson J.P., Kirk D.R.,
Peebles H.G., “Design of a novel six degree of freedom
solid rocket motor test stand”, AIAA 2007-5331 44th
IAA/ASME/SAE/ASEE Joint Propulsion Conference &
Exhibit, July 21-23, Hartford, CT, USA, (2008).
- Gligorijevic N., Zivkovic S., Subotic S., Kozomara S.,
Nikolic M., Citakovic S., “Side force determination in the
rocket motor thrust vector control system”, Scientific
Technical Review, 63(1): 27-38, (2013).
- Wekerle T., Barbosa E.G., Batagini C.M., Costa
L.E.V.L., Trabasso L.G., “Closed-loop actuator
identification for Brazilian Thrust Vector Control
development”, IFAC-PapersOnLine, 49(17): 468–473,
(2016).
- Milos P., Davidovic N., Jojic B., Milos M., Todic I., “A
novel 6 DOF thrust vector control test stand”, Tehnicki
Vjesnik-Technical Gazette, 22(5): 1247-1254, (2015).
- Prince E.R., Krishnamoorthy S., Ravlich I., Kotine A.,
Fickes A.C., Fidalgo A.I., Freeman K., Anderson K.,
Gerson D., “Design, analysis, fabrication, ground-test,
and flight of a two-stage hybrid and solid rocket”, AIAA
49th Joint Propulsion Conference, July 14-17, San Jose,
CA, USA, (2013).
- Wright A.M., Wright A.B., Born T., Strickland R., “A six
degree-of-freedom thrust sensor for a labscale hybrid
rocket”, Meas. Sci. Technol, 24: 125104 (10 pp), (2013).
DOI:10.1088/0957-0233/24/12/125104.
- Wang A., Wu H., Tang H., Liu Y., Liang X.,
“Development and testing of a new thrust stand for micro-
thrust measurement in vacuum conditions”, Vacuum, 91:
35-40, (2013).
- Lugini C., Romano M., “A ballistic-pendulum test stand
to characterize small cold-gas thruster nozzles”, Acta
Astronautica, 64: 615-625, (2009).
-
Smiley M., Veno M., Bell R., “Commercial crew
development—round one, milestone 3: Overview of
Sierra Nevada Corporation’s hybrid motor ground test”,
AIAA 47th AIAA/ASME/SAE/ASEE Joint Propulsion
Conference & Exhibit, 31 July-03 August, San Diego,
CA, USA, (2011).
- Sunakawa H., Kobayashi T., Okita K., “Development
status of electrical valve control system for LE-9 engine”,
AIAA Propulsion and Energy Forum, 10-12 July,
Atlanta, GA, USA, (2017).
- Alwayse Engineering Ball Transfer Unit Catalogue,
https://www.alwayse.co.uk/brochures/CAT14August201
5Revisions.pdf., website visit date: 15.08.2015.
- Granta-mi, Material Library,
https://www.grantadesign.com/products/mi/index.htm,
website visit date: 03.07.2016.