Stability Analysis and Flight Trials of a Clipped Wrap Around Fin Configuration

Morote, Jesús; Liaño, Gabriel

doi:10.2514/6.2004-5055

Cited by 8 publications

(7 citation statements)

References 1 publication

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“…Isto tako, pri napadnom uglu javlja se bočni moment koji je sličan Magnusovom momentu, ali ne za-visi od ugaone brzine valjanja. Njegov uticaj na stabilnost kretanja analiziran je u radovima [3] i [4], pri čemu je uzrok nestabilnog i neregularnog leta pripisan bočnom momentu indukovanom napadnim uglom, uz zanemarivanje Magnusovog momenta.…”

Section: Uvodunclassified

“…Druga specifičnost olučastih krila jeste pojava bočne sile i momenta pri postojanju napadnog ugla i nultoj vrednosti ugaone brzine valjanja. Numerička simulacija strujnog polja i aerodinamička ispitivanja [6], [7], [3] pokazala su da za konfiguraciju na sl. 1 nastaje bočna sila nalevo, posmatrano u pravcu leta i bočni moment koji je usmeren u pozitivnom smeru ose Oz.…”

Section: Sl 8 -Uticaj Asimetrije Olučastih Krila Na Ugaonu Brzinu Vaunclassified

“…U zavisnosti od vitkosti konfiguracije, a na osnovu aerodinamičkih eksperimentalnih i numeričkih rezultata o bočnom momentu [7], [3], procenjuju se vrednosti derivativa bočnog momenta po napadnom uglu:…”

Section: Sl 8 -Uticaj Asimetrije Olučastih Krila Na Ugaonu Brzinu Vaunclassified

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Influence of range extension on dynamic stability for artillery rockets with wrap around fins

Ćuk¹

2007

Vojnotehni?ki glasnik

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Vojnotehničkog instituta, BeogradRezime: U radu su prikazani efekti povećanja dometa artiljerijske rakete sa olučastim krilima na njenu dinamičku stabilnost. Totalni impuls raketnog motora, uvećan za 50% i let rakete kroz slojeve atmosfere sa malom gustinom vazduha povećavaju domet rakete za više od 75% od nominalnog dometa. Međutim, let rakete kroz razređeni vazduh proizvodi teškoće koje se odnose na dinamičku stabilnost. Male promene bočnog momenta indukovanog napadnim uglom i Magnusovog momenta mogu proizvesti nestabilnost kretanja i nedozvoljeni rast napadnog ugla. Određene su tolerancije bočnog momenta za osnovnu i poboljšanu varijantu rakete radi sprečavanja nestabilnog leta. Analiziran je, takođe, uticaj povećanja dometa na verovatna odstupanja rakete po dometu i pravcu. Ključne reči: nevođena raketa, putanja, dinamička stabilnost, rasturanje, olučasta krila. Summary:This paper presents the effects of the range extension of an artillery rocket with wrap around fins on its dynamic stability. The increased total impulse of the rocket engine for 50% and flight through the atmosphere layers with low air density extend the range for more than 75% of the nominal range. However, the flight of the unguided rocket through the rarefied air produces difficulties related to the dynamic stability. The small changes in the side moment which is induced by the angle of attack and Magnus moment of the improved rocket can produce instabilities in flight and increasement the angle of attack. The tolerances of the side moment were determined for both basic and improved type of the rocket in order to prevent instable flight. The influence of the range extension on the probable errors in range and cross-range was analyzed as well.

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Section: Uvodunclassified

Section: Sl 8 -Uticaj Asimetrije Olučastih Krila Na Ugaonu Brzinu Vaunclassified

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Influence of range extension on dynamic stability for artillery rockets with wrap around fins

Ćuk¹

2007

Vojnotehni?ki glasnik

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“…Yi and Wang [7] proposed that the coning motion can be overcome by means of an internal moving mass. Morote and Liano [5] noticed the effects of cord and span of WAF on the dynamic stability of 140 mm rockets and concluded that clipping the span of WAF can mitigate the coning motion. Livshits [8] has studied the influence of aeroelasticity on the dynamic stability of the rocket and concluded that thrust misalignment and dynamic imbalance are important factors to the dynamic stability of the rocket.…”

Section: Introductionmentioning

confidence: 98%

“…For example, in the US, unstable coning motion was detected 20 times out of 50 flight experiments for Nitehawk Rocket [3] , and this motion also appeared in the subsonic and supersonic wind tunnel experiments for 2.75″ rockets [4] . In Spain, catastrophic coning motion made the velocity reduce 60% in just 1.5 seconds in the flight trials of a 140 mm artillery rocket [5] . In China, serious coning motion has been detected in the experiments for several kinds of unguided rockets [6] .…”

Section: Introductionmentioning

confidence: 99%

Coning motion stability of wrap around fin rockets

Mao

Yang

2007

SCI CHINA SER E

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Both the asymptotical stability criterion and the bounded stability criterion of the coning motion for wrap around fin (WAF) rockets are proposed through the analysis of coning motion equations, which can be easily used to determine the existence of the coning motion during the rocket design. The correctness of the criterions is verified by mathematical simulation examples of a WAF rocket with different setting angles. It is also found that the setting angle of WAF has great effects on the rolling moment and side moment of the rocket.coning motion, wrap around fins, setting angle, dynamic stability

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