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2012, vol. 60, br. 1, str. 115-135
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Novi zakon vođenja za taktičku raketu zemlja-zemlja
A new guidance law for a tactical surface-to-surface missile
aUniverzitet u Beogradu, Mašinski fakultet, Srbija bUniversity of Azawia, Faculty of Engineering, Aeronautical Department, Azawia, Libya cVojnotehnički institut - VTI, Beograd, Srbija
e-adresa: cukd@eunet.rs
Sažetak
Savremene rakete zemlja-zemlja, opremljene besplatformnim sistemom inercijalne navigacije, postižu veoma dobru tačnost u poređenju sa nevođenim raketama. Verovatno odstupanje po dometu zavisi uglavnom od instrumentalnih grešaka i poremećaja u pravcu uzdužne ose rakete kao što su devijacija totalnog impulsa raketnog motora, razlike u procenjenim i stvarnim vrednostima aksijalne sile i čeoni vetar. Ovaj rad daje proširenje koncepta korelisane brzine na rakete zemlja- zemlja koje nemaju mehanizam za prekid rada raketnog motora. Sračunati parametri korelisane brzine smešteni su u memoriju kompjutera za vođenje na raketi. Na osnovu koncepta korelisane brzine, predložena je modifikacija proporcionalne navigacije koja obuhvata podešavanje vremena do susreta rakete i cilja. Pokazano je da novi zakon vođenja može uspešno da kompenzira uzdužne poremećaje različitog nivoa. Efikasnost predložene metode vođenja potvrđena je preko sračunatih verovatnih odstupanja po dometu i pravcu za očekujuće poremećaje u sistemu vođenja.
Abstract
Modern tactical surface-to-surface missiles, equipped with strapdown inertial navigation systems, achieve very good accuracy compared with free-flight rockets. The probable range dispersion mainly depends on instruments errors and longitudinal disturbances such as rocket motor total-impulse deviation as well as differences between the estimated and actual values of the axial force and head wind. This paper gives an extension of the correlated velocity concept for surface-to-surface missiles without a thrust-terminating mechanism. The calculated parameters of the correlated velocity are stored into the memory of an onboard guidance computer. On the basis of the correlated velocity concept, the modified proportional navigation with the adjustment of the time-to-go of the missile to the target was proposed. It is shown that the new guidance law can compensate for the longitudinal disturbances of different levels successfully. The effectiveness of the proposed guidance method was confirmed by means of the calculated probable range and lateral dispersion for the anticipated disturbances in the guidance system.
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Reference
|
|
|
Ćuk, D. (2007) The program guided missile trajectory calculation by using 6 DOF model (GMTC6DOF) and the method correlated velocity proportional navigation guidance (CV PNG)
|
|
1   
|
Ćuk, D. (2008) Izbor faktora rotacije vektora potiska za balističku raketu sa Lambertovim vođenjem. Vojnotehnički glasnik, vol. 56, br. 2, str. 133-146
|
|
|
Ćuk, D. (2007) Influence of range extension on dynamic stability for artillery rockets with wrap around fins. Vojnotehnički glasnik, vol. 55, br. 3, str. 296-307
|
|
|
Ćuk, D.V. (2010) Trajectory correction of gyroscopic stabilized projectile using proportional navigation. Vojnotehnički glasnik, vol. 58, br. 1, str. 13-32
|
|
|
Ćuk, D.V., Mandić, S.D. (2011) Comparison of different lateral acceleration autopilots for a surface-to-surface missile. Vojnotehnički glasnik, vol. 59, br. 3, str. 7-28
|
|
1
|
Gamble, A.E., Jenkins, P.N. (2001) Low cost guidance for the multiple launch rocket system (MLRS) artillery rocket. IEEE AES System Magazine, Jan
|
|
2
|
Gernel, P. (1980) Guided weapon system. New York: Pergamon Press
|
|
2
|
Gregoriou, G. (1988) CEP calculation for a rocket with different control system. J. Guidance, May-June vol. 11, br. 3, pp. 193-198
|
|
1
|
Jitpraphai, T., Costello, M. (2001) Dispersion Reduction of a Direct Fire Rocket Using Lateral Pulse Jets. Journal of Spacecraft and Rockets, 38(6): 929-936
|
|
|
Jitraphai, T., Burchett, B., Costello, M. (2002) A comparison of different guidance schemes for a direct fire rocket with a pulse jet control mechanism. Corvallis: Oregon State University
|
|
1
|
Morrison, Ph.H., Ambertson, D.S. (1977) Guidance and control of a Cannon-Launched guided projectile. J. Spacecraft, Vol. 14, No. 6, pp. 328-334
|
|
1
|
Nesline, F.W., Zarchan, P. (1981) A new look at classical VS modern homing missile guidance. J. Guidance and Control, Vol. 4, No. 1, pp. 78-85
|
|
1
|
Nesline, F.W., Nesline, M.L. (1984) How autopilot requirements constrain the aerodynamic design of homing missiles. u: American Control Conference Proceedings, June, pp. 716-730
|
|
3
|
Siouris, M.G. (2004) Missile guidance and control systems. New York: Springer-Verlag
|
|
|
Zhao, H., Wang, F., Lin, Q. (2005) The investigation about using different guidance laws on improving impact point deviation of a rocket. u: International Symposium on Ballistics (XXII), Vancouver BC, Canada: National Defense Industrial Association USA - International Ballistics Committee, vol. 1, str. 81-87
|
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