ECHIPAMENTE DE BORD

DINAMICA ZBORULUI

BOEING 737-300

I. Prezentare Generala:

Scurt istoric:

La inceputul anului 1980 compania "BOEING" incepe sa lucreze la o noua varianta de Boeing 737 cu scopul de a mari numarul de locuri pentru pasageri si spatial alocat bagajelor. Aceasta noua varianta de Boeing 737-300 urma sa aiba fuselajul marit si sa fie echipata cu o noua generatie de motoare turbofan, care aveau un consum de combustibil mult redus si un nivel de zgomot mai mic in comparative cu varianta precedenta (737-200).

Proiectul a fost dat mai departe pentru productie in martie 1981, iar in vara anului 1982 a inceput constructia avionului. Prototipul 737-300 a facut primul zbor pe data de 24 februarie 1984. Certificarea acestui tip de avion a fost facuta pe 14 noiembrie 1984. Primul avion care a fost pus in serviciu de catre compania "SOWTHWEST AIRLINES" pe data de 7 decembrie 1984.

Pana in aprilie 1989 au fost in total peste 790 de comenzi si 540 de livrari catre companii din toata lumea.

Modelele Boeing 737 au fost al treilea tip de avioane care au ajuns la vanmzari de peste 1000 bucati iar in iunie 1987 a devenit cel mai bine vandut avion commercial cand comenzile pentru toate tipurile au depasit recordul anterior de 1831 avioane stability de Boeing 727. S-a deposit cifra de 2000 de avioane vandute pe 3 martie 1988.

Modelul 737-300 este o versiune "alungita" din familia de aeronave 737 dispunanad de o lungime de 33.04 m (109 ft 7 in) . Are fuselajul asemanator cu 737-200 numai ca varianta 300 are doua sectiuni adaugate: o parte de fuselaj de 44 inches (1.12 m) in fata aripilor si o alta parte de 60 inches (1.52 m) in spatele aripilor. De asemenea au fost marite si ampenajele. Modelul 737-300 are o aerodinamica noua si motoare noi pentru a imbunatati raza de actiune si a reduce consumul.

Performante:

Viteza de croaziera: 0.745 Mach, 495 mph, 797 km-h

Viteza maxima: 0.84 Mach

Raza de actiune: - 2595 (4175 km)

Plafon de zbor: 11250 m

Caracteristici tehnice:

Greutatea: -la livrare 63048 kg

-operationala 51710 kg

-maxima de decolare68040 kg

Tractiune: 2*95KN CFMInternational CFM 56-3C-1

Turbofans

Consum specific: 2440 kg/h

Dimensiuni generale:

Anvergura: 30.18 m

Lungime fuselaj: 32.23 m

Inaltimea cozii: 11.1 m

III Prezentarea pachetului de calcul

Pachetul de calcul pentru determinarea performantelor contine patru module de calcul:

1.    modulul proiectare, dispus in directorul AFPAER

2.    modulul de analiza liniara, care preluand caracteristicile de aerodinamica si de masa realizeaza calculul derivatelor de stabilitate

3.    modulul de performante permite calculul principalelor performante de zbor

4.    modulul de simulare a zborului permite simularea zborului autonom dupa un program impus, in diferite coditii de vant sau zgomot de la senzori

1. Modulul de proiectare

Modulul de proiectare contine urmatoarele rutine: AER- programul principal de calcul aerodinamic care asambleaza suprafetele aerodinamice cu fuzelajul tinand cont de interferentele suprafata fuzelaj si asigura iesirea prin fisierul DCOEFA.REZ ce contine derivatele de translatie ale coeficientilor aerodinamici cu marimi de referinta conform standardului [XI] intru-un triedru cu originea in varful configuratiei, cu axa x orientata in spate. In paralel este generat si fisierul DCOFAM.REZ ce contine derivatele de translatie ale coeficientilor aerodinamici cu marimi de referinta conform standardului [X2], intr-un triedru cu originea in centrul de masa, cu axa x orientata in fata. GEO.DAT furnizeaza sintetic principalele marimi geometrice care vor fi utilizate ulterior pentru simularea zborului si la analiza indicilor de calitate. Totodata programul furnizeaza caracteristicile masice ale aparatului care sunt grupate in fisierul MEC.DAT. Datele de intrare, reprezentand marimile geometrice ale elementelor izolate si ale ansamblului sunt continute in fisierele cu extensia GEO, cum ar fi: ARIPA.GEO, FUSELAJ.GEO, ANS.GEO, AMPENAJO.GEO, AMPENAJV.GEO. Numerele Mach la care se efectueaza calculul sunt continute in fisierul MACH.INP.

2. Modulul de analiza

Modulul este continut in directorul ANA si contine pe langa programul principal care asambleaza rutinele de calcul si asigura iesirea prin fisierul ANA.REZ, rutine de calcul a derivatelor de stabilitate si a indicilor de calitate a zborului definiti conform prevederilor standardului [X4]. Fisierele de intrare utilizate sunt: DCOEFA.REZ - continand caracteristicile aerodinamice; MEC.DAT continand caracteristicile mecanice, GEO.DAT continand principalele marimi geometrice ale produsului, AERPAR.DAT. Modulul are trei variante de lucru. Prima realizeaza un calcul de indici la toate numerele mach indicare in fisierul AERYMACH.INP pentru avionul plin cu combustibil iar apoi pentru avionul gol. Iesirea este prin fisierul ANA.REZ si Al.REZ, A2.REZ. A doua varianta, realizeaza de asemenea calculul indicilor de calitate pentru diverse numere Mach, pentru valori masice medii. Iesirea este de asemenea prin fisierul ANA.REZ si Al.REZ, A2.REZ Ultima varianta se realizeaza la o singura viteza de calcul, pentru valori masice medii, determinandu-se in acest caz si matricele de reglaj.

3. Modulul de performante

Modulul de determinarea a performantelor permite calculul principalelor performante de zbor. Modulul se gaseste in directorul PER si contine rutine similare celor din grupul de analiza: PER -programul principal care asambleaza rutinele de calcul si asigura dialogul si iesirile. Rutine utilizate sunt: BAZAI - pentru zborul inclinat si limita din dreapta a anvelopei de zbor orizontal, BAZA2 - pentru limita din stanga a zborului orizontal. ATM - calculul atmosferei standard, CIT - pentru citirea datelor de intrare, DER - care realizeaza calculul termenilor de dezvoltare a coeficientilor aerodinamici prin interpolare liniara.

Intrarile in modul sunt cele de proiectare din fisierul DCOEFA.RRZ, mecanice din fisierul MEC.DAT, PAR.DAT si specifice aplicatiei, grupate in fisierele PARI .DAT si PAR2.DAT.

Fisierele de iesire sunt: PER1.REZ - anvelopa de zbor orizontal pentru inceputul zborului; (M,Zp), PER2.REZ - anvelopa de zbor orizontal pentru sfarsitul duratei de zbor (M,Zp); PER3.REZ - diagramele de zbor inclinat (M cos(gama), M sin(gama)).

4. Modulul de simulare

Modulul de simulare a zborului permite determinarea parametrilor miscarii autonome a aparatului de zbor, prin integrarea numerica a ecuatiilor miscarii generale. Fisierele de intrare necesare sunt din modulul de proiectare: GEO.DAT- pentru marimi geometrice; MEC.DAT - pentru marimi mecanice; DCOEFA.REZ - pentru caracteristicile aerodinamice; PAR.DAT.

IV. Modulul de proiectare aerodinamica:

Date necesare pentru modulul de proiectare:

Rezultate proiect aerodinamica

Caracteristici mecanice

xcmi [m]    15.628

xcmf [m]    16.375

ami [Kg]131023.602

amf [Kg] 63047.948

ajxi [Kg*m**2] 2089947.289

ajxf [Kg*m**2] 2052550.615

ajyi [Kg*m**2] 6654552.988

ajyf [Kg*m**2] 3902768.271

ajzi [Kg*m**2] 8561333.578

ajzf [Kg*m**2] 5697289.764

ajci [Kg*m**2]12512.430

ajcf [Kg*m**2] 3573.768

Masele, centrele de masa si momentele de inertie

1. varf fuzelaj 3604.604; 0.000; 3.008; 3862.802;4104.991; 4104.991

2. fuzelaj central gol

40773.344; 4.010; 14.935; 95254.606; **********; **********

3. fuzelaj posterior

7160.468; 25.860; 27.825; 7743.520; 19832.350; 19832.350

4. combustibil

67975.655; 4.010; 14.935; 37396.674; **********; **********

5. aripa 1 oriz.

4390.508; 11.600; 12.534; 337174.368; 3034.909; 339266.510

6. aripa 2 oriz.

4390.508; 11.600; 12.534; 337174.368; 3034.909; 339266.510

7. ampenaj 1 oriz.

951.683;27.940;28.763; 6690.524; 277.371; 6929.019;

8. ampenaj 2 oriz.

951.683;27.940;28.763; 6690.524; 277.371; 6929.019;

9. ampenaj vert.

825.150;26.250;27.089; 4470.202; 4633.028; 227.055;

ami=    **********

amf=    **********

xcmi=15.62784

xcmf=16.37482

ajxi= **********

ajxf= **********

ajyi= **********

ajyf= **********

ajzi= **********

ajzf= **********

ajci= **********

ajcf= 3573.76753

el= 32.20000

NR. DE POLARE : 18

XMACH 0.4000000E-01 0.8000000E-01 0.1200000E+00 0.1700000E+00 0.2300000E+00 0.2800000E+00 0.3400000E+00 0.4000000E+00 0.4600000E+00

0.5200000E+00 0.5600000E+00 0.6000000E+00 0.6400000E+00 0.6800000E+00 0.7200000E+00 0.7600000E+00 0.8000000E+00 0.8400000E+00

Cx0a 0.2417412E+00 0.2210976E+00 0.2119127E+00 0.2059756E+00 0.2025298E+00 0.2012776E+00 0.2009217E+00 0.2013836E+00 0.2024052E+00

0.2037527E+00 0.2047245E+00 0.2058221E+00 0.2070325E+00 0.2083478E+00 0.2097646E+00 0.5044061E+00 0.9633422E+00 0.1427177E+01

Cx0p 0.2430092E+00 0.2224365E+00 0.2132887E+00 0.2073796E+00 0.2039545E+00 0.2027139E+00 0.2023684E+00 0.2028390E+00 0.2038694E+00

0.2052272E+00 0.2062077E+00 0.2073158E+00 0.2085396E+00 0.2098719E+00 0.2113101E+00 0.5059793E+00 0.9646708E+00 0.1428438E+01

Cx2a 0.2444744E+01 0.2474930E+01 0.2523264E+01 0.2611583E+01 0.2762173E+01 0.2929067E+01 0.3270877E+01 0.3638848E+01 0.4107006E+01

0.4697700E+01 0.5173916E+01 0.5737919E+01 0.6013413E+01 0.6741023E+01 0.7627758E+01 0.7819698E+01 0.8831734E+01 0.1018121E+02

Cx2b 0.5029087E+01 0.5042507E+01 0.5059624E+01 0.5088570E+01 0.5135868E+01 0.5186767E+01 0.5347458E+01 0.5479206E+01 0.5641959E+01

0.5841845E+01 0.5999888E+01 0.6181726E+01 0.5994567E+01 0.6156321E+01 0.6341928E+01 0.6525699E+01 0.6263712E+01 0.6592257E+01

Cx2de 0.5315095E+01 0.5319627E+01 0.5329183E+01 0.5349266E+01 0.5386236E+01 0.5428605E+01 0.5494710E+01 0.5579347E+01 0.5685282E+01

0.5793198E+01 0.5849531E+01 0.5919270E+01 0.6004524E+01 0.6108001E+01 0.6233221E+01 0.6069664E+01 0.6185231E+01 0.6352325E+01

Cx2da 0.1246456E+02 0.1248839E+02 0.1252918E+02 0.1260452E+02 0.1273258E+02 0.1287318E+02 0.1308707E+02 0.1335701E+02 0.1369288E+02

0.1410852E+02 0.1443931E+02 0.1482201E+02 0.1526692E+02 0.1578780E+02 0.1640342E+02 0.1671643E+02 0.1746980E+02 0.1843852E+02

Cx2dr 0.3954369E+01 0.3963092E+01 0.3973405E+01 0.3990350E+01 0.4017628E+01 0.4046712E+01 0.4089918E+01 0.4143053E+01 0.4207247E+01

0.4283940E+01 0.4342910E+01 0.4408932E+01 0.4482826E+01 0.4565583E+01 0.4658414E+01 0.4762812E+01 0.4580073E+01 0.4758517E+01

Cxa -0.1160534E+01-0.1162595E+01-0.1166173E+01-0.1172851E+01-0.1184281E+01-0.1196881E+01-0.1216093E+01-0.1240374E+01-0.1270604E+01

-0.1307364E+01-0.1335794E+01-0.1368813E+01-0.1407316E+01-0.1452496E+01-0.1505976E+01-0.1526814E+01-0.1591207E+01-0.1674524E+01

Cz0 -0.5709266E+00-0.5717364E+00-0.5731708E+00-0.5758620E+00-0.5804724E+00-0.5855472E+00-0.5932630E+00-0.6029704E+00-0.6149841E+00

-0.6294362E+00-0.6404687E+00-0.6532044E+00-0.6679490E+00-0.6851041E+00-0.7052082E+00-0.7137919E+00-0.7383505E+00-0.7698239E+00

Cza 0.8280107E+02 0.8290802E+02 0.8310037E+02 0.8346446E+02 0.8409176E+02 0.8478443E+02 0.8594508E+02 0.8732021E+02 0.8902412E+02

0.9105129E+02 0.9256881E+02 0.9432845E+02 0.9587730E+02 0.9816276E+02 0.1008457E+03 0.1018226E+03 0.1050561E+03 0.1092217E+03

Cyb 0.1229394E+02 0.1231091E+02 0.1233314E+02 0.1237108E+02 0.1243331E+02 0.1250026E+02 0.1270593E+02 0.1287616E+02 0.1308571E+02

0.1334202E+02 0.1354391E+02 0.1377546E+02 0.1354557E+02 0.1375148E+02 0.1398671E+02 0.1417710E+02 0.1414166E+02 0.1456420E+02

Czde -0.5081775E+01-0.5084256E+01-0.5090555E+01-0.5104663E+01-0.5131432E+01-0.5162529E+01-0.5211366E+01-0.5274041E+01-0.5352430E+01

-0.5427438E+01-0.5459483E+01-0.5500987E+01-0.5553304E+01-0.5618150E+01-0.5697729E+01-0.5574540E+01-0.5642672E+01-0.5746571E+01

Cydr -0.2612215E+01-0.2616472E+01-0.2621234E+01-0.2628885E+01-0.2641071E+01-0.2653984E+01-0.2673072E+01-0.2696416E+01-0.2724441E+01

-0.2757679E+01-0.2783061E+01-0.2811301E+01-0.2842690E+01-0.2877578E+01-0.2916384E+01-0.2959621E+01-0.2888933E+01-0.2968606E+01

Cyda 0.1294340E+01 0.1296347E+01 0.1299833E+01 0.1306291E+01 0.1317259E+01 0.1329274E+01 0.1347484E+01 0.1370351E+01 0.1398620E+01

0.1433326E+01 0.1460732E+01 0.1492206E+01 0.1528491E+01 0.1570563E+01 0.1619737E+01 0.1646422E+01 0.1707546E+01 0.1785278E+01

Cza1 0.4536721E+00 0.4548186E+00 0.4566929E+00 0.4601889E+00 0.4662117E+00 0.4728881E+00 0.4830279E+00 0.4958837E+00 0.5118556E+00

0.5304832E+00 0.5438550E+00 0.5594105E+00 0.5775400E+00 0.5987548E+00 0.6237381E+00 0.6070170E+00 0.6398596E+00 0.6831191E+00

Cyb1 0.1686556E-01 0.1691781E-01 0.1698766E-01 0.1710797E-01 0.1730648E-01 0.1752131E-01 0.1784195E-01 0.1824211E-01 0.1873175E-01

0.1932559E-01 0.1978900E-01 0.2031527E-01 0.2091424E-01 0.2159853E-01 0.2238464E-01 0.2246661E-01 0.2261681E-01 0.2412385E-01

Cyp -0.1504975E+01-0.1506729E+01-0.1510165E+01-0.1516697E+01-0.1527886E+01-0.1540166E+01-0.1558768E+01-0.1582079E+01-0.1610804E+01

-0.1645922E+01-0.1673539E+01-0.1705131E+01-0.1741390E+01-0.1783222E+01-0.1831842E+01-0.1861420E+01-0.1905252E+01-0.1984640E+01

Cm0 0.3095302E+00 0.3098527E+00 0.3105434E+00 0.3119013E+00 0.3142756E+00 0.3169129E+00 0.3210438E+00 0.3262539E+00 0.3327814E+00

0.3406136E+00 0.3465043E+00 0.3533864E+00 0.3614341E+00 0.3708687E+00 0.3819770E+00 0.3843488E+00 0.3972654E+00 0.4127977E+00

Cma -0.4666564E+02-0.4672013E+02-0.4682093E+02-0.4701498E+02-0.4735290E+02-0.4772826E+02-0.4833515E+02-0.4908049E+02-0.5001382E+02

-0.5110987E+02-0.5190403E+02-0.5283725E+02-0.5389149E+02-0.5517261E+02-0.5668472E+02-0.5711775E+02-0.5890566E+02-0.6119885E+02

Cnb 0.8208071E+01 0.8221028E+01 0.8237078E+01 0.8263948E+01 0.8307605E+01 0.8354363E+01 0.8444732E+01 0.8536466E+01 0.8648947E+01

0.8785697E+01 0.8892576E+01 0.9013992E+01 0.9109953E+01 0.9258417E+01 0.9427324E+01 0.9581782E+01 0.9497531E+01 0.9806001E+01

Cmde 0.4762669E+01 0.4764994E+01 0.4770898E+01 0.4784120E+01 0.4809208E+01 0.4838353E+01 0.4884647E+01 0.4944027E+01 0.5018631E+01

0.5090771E+01 0.5122518E+01 0.5163605E+01 0.5215363E+01 0.5279447E+01 0.5357937E+01 0.5246094E+01 0.5314434E+01 0.5416384E+01

Cndr -0.2330743E+01-0.2334542E+01-0.2338790E+01-0.2345617E+01-0.2356490E+01-0.2368011E+01-0.2385361E+01-0.2406576E+01-0.2432264E+01

-0.2463027E+01-0.2486716E+01-0.2513247E+01-0.2542915E+01-0.2576054E+01-0.2613041E+01-0.2654296E+01-0.2593460E+01-0.2667489E+01

Cnda 0.6268648E+00 0.6278367E+00 0.6295251E+00 0.6326526E+00 0.6379648E+00 0.6437836E+00 0.6528461E+00 0.6642204E+00 0.6784481E+00

0.6961412E+00 0.7102626E+00 0.7266104E+00 0.7455876E+00 0.7677071E+00 0.7936355E+00 0.8088302E+00 0.8411503E+00 0.8817252E+00

Cma1 -0.4251842E+00-0.4262587E+00-0.4280153E+00-0.4312918E+00-0.4369364E+00-0.4431935E+00-0.4527452E+00-0.4648546E+00-0.4799342E+00

-0.4975771E+00-0.5102876E+00-0.5251012E+00-0.5423944E+00-0.5626576E+00-0.5865405E+00-0.5712522E+00-0.6026385E+00-0.6438685E+00

Cnb1 0.1504826E-01 0.1509488E-01 0.1515720E-01 0.1526455E-01 0.1544167E-01 0.1563335E-01 0.1592156E-01 0.1628125E-01 0.1672290E-01

0.1726069E-01 0.1768184E-01 0.1816145E-01 0.1870873E-01 0.1933536E-01 0.2005634E-01 0.2014887E-01 0.2030362E-01 0.2167688E-01

Cnp -0.8780963E+00-0.8790177E+00-0.8808694E+00-0.8844059E+00-0.8904708E+00-0.8971249E+00-0.9074521E+00-0.9203648E+00-0.9364175E+00

-0.9562277E+00-0.9719228E+00-0.9899700E+00-0.1010764E+01-0.1034800E+01-0.1062716E+01-0.1081897E+01-0.1101765E+01-0.1147680E+01

Clp 0.2894122E+01 0.2897894E+01 0.2905162E+01 0.2918961E+01 0.2942633E+01 0.2968664E+01 0.3008190E+01 0.3057859E+01 0.3119268E+01

0.3194234E+01 0.3252903E+01 0.3320325E+01 0.3398080E+01 0.3488243E+01 0.3593601E+01 0.3646147E+01 0.3774872E+01 0.3941503E+01

Clda -0.3029240E+01-0.3033937E+01-0.3042096E+01-0.3057209E+01-0.3082880E+01-0.3110998E+01-0.3153618E+01-0.3207134E+01-0.3273295E+01

-0.3354519E+01-0.3418660E+01-0.3492321E+01-0.3577240E+01-0.3675704E+01-0.3790792E+01-0.3853245E+01-0.3996296E+01-0.4178220E+01

Cldr 0.3033410E+00 0.3038354E+00 0.3043883E+00 0.3052769E+00 0.3066919E+00 0.3081914E+00 0.3104080E+00 0.3131187E+00 0.3163731E+00

0.3202329E+00 0.3231804E+00 0.3264597E+00 0.3301048E+00 0.3341560E+00 0.3386623E+00 0.3436832E+00 0.3354746E+00 0.3447266E+00

Clb -0.1536021E+01-0.1537727E+01-0.1541109E+01-0.1547551E+01-0.1558592E+01-0.1570708E+01-0.1589052E+01-0.1612020E+01-0.1640293E+01

-0.1674812E+01-0.1701922E+01-0.1732895E+01-0.1768394E+01-0.1809286E+01-0.1856725E+01-0.1886485E+01-0.1924019E+01-0.2002307E+01

CZAf 0.1665677E+01 0.1665677E+01 0.1665677E+01 0.1665677E+01 0.1665677E+01 0.1665677E+01 0.1771195E+01 0.1817403E+01 0.1875934E+01

0.1950062E+01 0.2010491E+01 0.2082096E+01 0.1671029E+01 0.1671029E+01 0.1671029E+01 0.1671029E+01 0.1671029E+01 0.1671644E+01

CZAa 0.4591599E+01 0.4597955E+01 0.4609952E+01 0.4632590E+01 0.4671305E+01 0.4713818E+01 0.4778330E+01 0.4859384E+01 0.4959620E+01

0.5082697E+01 0.5179898E+01 0.5291530E+01 0.5420226E+01 0.5569452E+01 0.5743872E+01 0.5838546E+01 0.6055350E+01 0.6331064E+01

CZAo 0.4076594E+01 0.4080735E+01 0.4089257E+01 0.4105598E+01 0.4133633E+01 0.4164357E+01 0.4210753E+01 0.4268603E+01 0.4339421E+01

0.4425254E+01 0.4492152E+01 0.4568004E+01 0.4654144E+01 0.4752259E+01 0.4864518E+01 0.4816286E+01 0.4972816E+01 0.5167470E+01

CZAv 0.2988442E+01 0.2989920E+01 0.2993728E+01 0.3001299E+01 0.3014401E+01 0.3028734E+01 0.3050226E+01 0.3076718E+01 0.3108656E+01

0.3146623E+01 0.3175649E+01 0.3207962E+01 0.3243892E+01 0.3283837E+01 0.3328275E+01 0.3377792E+01 0.3297299E+01 0.3388436E+01

XFfb 0.7278459E-01 0.7277322E-01 0.7276185E-01 0.7274763E-01 0.7273058E-01 0.7271636E-01 0.7918810E-01 0.7931039E-01 0.7946236E-01

0.7964822E-01 0.7979374E-01 0.7995913E-01 0.7878103E-01 0.7876966E-01 0.7875828E-01 0.7874691E-01 0.7873553E-01 0.7872621E-01

XFab 0.4843123E+00 0.4843123E+00 0.4843123E+00 0.4843123E+00 0.4843123E+00 0.4843123E+00 0.4844925E+00 0.4847082E+00 0.4850839E+00

0.4856825E+00 0.4862374E+00 0.4869370E+00 0.4877934E+00 0.4888103E+00 0.4899779E+00 0.4912653E+00 0.4926078E+00 0.4938866E+00

XFob 0.9372059E+00 0.9372059E+00 0.9372059E+00 0.9372059E+00 0.9372059E+00 0.9372059E+00 0.9373064E+00 0.9374266E+00 0.9376360E+00

0.9379696E+00 0.9382789E+00 0.9386688E+00 0.9391460E+00 0.9397128E+00 0.9403636E+00 0.9410811E+00 0.9418293E+00 0.9425420E+00

XFvb 0.8922478E+00 0.8922478E+00 0.8922478E+00 0.8922478E+00 0.8922478E+00 0.8922478E+00 0.8923668E+00 0.8925092E+00 0.8927570E+00

0.8931521E+00 0.8935183E+00 0.8939800E+00 0.8945451E+00 0.8952162E+00 0.8959868E+00 0.8968364E+00 0.8977224E+00 0.8985663E+00

Eo 0.7284924E-01 0.7295602E-01 0.7312419E-01 0.7342773E-01 0.7393704E-01 0.7449060E-01 0.7532344E-01 0.7635980E-01 0.7762716E-01

0.7916234E-01 0.8035853E-01 0.8171463E-01 0.8325453E-01 0.8500842E-01 0.8701510E-01 0.8615079E-01 0.8894896E-01 0.9242884E-01

Ev 0.7656763E-02 0.7667986E-02 0.7685662E-02 0.7717566E-02 0.7771096E-02 0.7829277E-02 0.7916813E-02 0.8025739E-02 0.8158943E-02

0.8320297E-02 0.8446021E-02 0.8588554E-02 0.8750404E-02 0.8934745E-02 0.9145655E-02 0.9054813E-02 0.9348913E-02 0.9714663E-02

ANfa 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01

0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01

ANFo 0.9737133E+00 0.9726015E+00 0.9714897E+00 0.9701000E+00 0.9684323E+00 0.9670425E+00 0.9653844E+00 0.9637294E+00 0.9620852E+00

0.9566520E+00 0.9479801E+00 0.9393401E+00 0.9307403E+00 0.9221885E+00 0.9136910E+00 0.9029134E+00 0.8852072E+00 0.8675756E+00

ANFv 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01

0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01 0.1000000E+01

Cx/M 0.0000000E+00-0.3728555E+00-0.1803421E+00-0.9087322E-01-0.3976530E-01-0.1635689E-01 0.8836142E-03 0.1236247E-01 0.1974243E-01

0.2356090E-01 0.2586706E-01 0.2884942E-01 0.3157220E-01 0.3415102E-01 0.3700729E+01 0.9419720E+01 0.1153464E+02 0.0000000E+00

Cza/M 0.0000000E+00 0.3741249E+01 0.5907899E+01 0.8724208E+01 0.1230867E+02 0.1634920E+02 0.2113148E+02 0.2565868E+02 0.3109234E+02

0.3627730E+02 0.4096453E+02 0.4135607E+02 0.4792884E+02 0.6210444E+02 0.4574857E+02 0.5263078E+02 0.9248844E+02 0.0000000E+00

Czd/M 0.0000000E+00-0.1097520E+00-0.2128942E+00-0.3566991E+00-0.5420391E+00-0.7092198E+00-0.9292666E+00-0.1175533E+01-0.1278303E+01

-0.9807344E+00-0.9193720E+00-0.1172757E+01-0.1464530E+01-0.1805319E+01 0.5451276E+00 0.6882127E+00-0.2150389E+01 0.0000000E+00

Cma/M 0.0000000E+00-0.1941109E+01-0.3124949E+01-0.4676907E+01-0.6654845E+01-0.8692437E+01-0.1126858E+02-0.1398897E+02-0.1691146E+02

-0.1921938E+02-0.2159233E+02-0.2484330E+02-0.2919202E+02-0.3491533E+02-0.2431420E+02-0.2776180E+02-0.5101377E+02 0.0000000E+00

Cmd/M 0.0000000E+00 0.1028602E+00 0.1995257E+00 0.3343005E+00 0.5080022E+00 0.6686519E+00 0.8806139E+00 0.1116535E+01 0.1222874E+01

0.9571318E+00 0.9104200E+00 0.1160569E+01 0.1448026E+01 0.1782172E+01-0.4169196E+00-0.5437872E+00 0.2128634E+01 0.0000000E+00

FO 0.5635875E+00 0.5635176E+00 0.5634263E+00 0.5632934E+00 0.5631099E+00 0.5629366E+00 0.5623957E+00 0.5620748E+00 0.5618008E+00

0.5613305E+00 0.5607075E+00 0.5601412E+00 0.5620881E+00 0.5620524E+00 0.5620938E+00 0.5609533E+00 0.5607066E+00 0.5603176E+00

FV 0.6676517E+00 0.6677839E+00 0.6678819E+00 0.6680052E+00 0.6681735E+00 0.6683350E+00 0.6646292E+00 0.6629667E+00 0.6609458E+00

0.6584985E+00 0.6565738E+00 0.6543512E+00 0.6725411E+00 0.6732672E+00 0.6740204E+00 0.6758631E+00 0.6715996E+00 0.6732948E+00

Cmsae 0.1530297E-01 0.1532669E-01 0.1536791E-01 0.1544426E-01 0.1557394E-01 0.1571599E-01 0.1593129E-01 0.1620164E-01 0.1653587E-01

0.1694619E-01 0.1727022E-01 0.1764234E-01 0.1807133E-01 0.1856874E-01 0.1915014E-01 0.1946563E-01 0.2018829E-01 0.2110733E-01

Cmsde 0.1345941E-01 0.1348028E-01 0.1351653E-01 0.1358368E-01 0.1369774E-01 0.1382267E-01 0.1401204E-01 0.1424982E-01 0.1454378E-01

0.1490467E-01 0.1518966E-01 0.1551695E-01 0.1589426E-01 0.1633176E-01 0.1684311E-01 0.1712060E-01 0.1775620E-01 0.1856451E-01

Cmsap-0.1757095E-01-0.1757953E-01-0.1760131E-01-0.1765009E-01-0.1774265E-01-0.1785017E-01-0.1801903E-01-0.1823574E-01-0.1850678E-01

-0.1876613E-01-0.1887693E-01-0.1902044E-01-0.1920133E-01-0.1942554E-01-0.1970070E-01-0.1927476E-01-0.1951033E-01-0.1986958E-01

Cmsdp-0.1380917E-01-0.1381591E-01-0.1383303E-01-0.1387137E-01-0.1394411E-01-0.1402861E-01-0.1416132E-01-0.1433163E-01-0.1454465E-01

-0.1474847E-01-0.1483555E-01-0.1494834E-01-0.1509050E-01-0.1526671E-01-0.1548296E-01-0.1514821E-01-0.1533335E-01-0.1561568E-01

Cmsad-0.1454402E-02-0.1456773E-02-0.1459424E-02-0.1463684E-02-0.1470468E-02-0.1477658E-02-0.1488286E-02-0.1501283E-02-0.1516886E-02

-0.1535393E-02-0.1549524E-02-0.1565247E-02-0.1582724E-02-0.1602148E-02-0.1623754E-02-0.1647828E-02-0.1608471E-02-0.1652830E-02

Cmsdd-0.1081528E-02-0.1083291E-02-0.1085262E-02-0.1088430E-02-0.1093475E-02-0.1098822E-02-0.1106725E-02-0.1116390E-02-0.1127993E-02

-0.1141754E-02-0.1152263E-02-0.1163955E-02-0.1176951E-02-0.1191396E-02-0.1207462E-02-0.1225364E-02-0.1196097E-02-0.1229084E-02

Diagramele rezultate:

Termenii coeficientului fortei axiale Cx:

Derivata coeficientului fortei normale in raport cu unghiul de incidenta C_zα si derivate coeficientului fortei transversale in raport cu unghiul de deriva C_yβ.

Derivata coeficientului momentului de tangaj cu unghiul de incidenta si derivata coeficientului momentului de giratie cu unghiul de deriva.

Termeni de comanda:

Model de calcul pentru fuselaj izolat

1. Elementele geometrice ale fuzelajului

Codificarea tipurilor de varfuri:

1- con

2-     sfera

3-     con + sfera

4-     ogiva

5-     ogiva + sfera

; ; ; ; .

2. - Derivata coeficientului fortei normale

Relatia de calcul pentru derivata coeficientului fortei portante este:

unde termenul datorat varfului in compresibil se alege din diagrame

fig. 4.3-a; fig. 4.3-b;

Daca varful are o rotunjire sferica se utilizeaza relatia:

Pentru calculul termenului posterior se utilizeaza relatia:

unde:

In cazul motorului in functiune se calculeaza un diametru posterior echivalent:

3.- Coeficientul fortei axiale la incidenta nula

Expresia generala a coeficientului fortei axiale la incidenta nula este:

La randul termenul datorat rezistentei posterioare are doua forme:

Termenul de profil in subsonic, respectiv de frecare in supersonic au urmatoarele expresii:

Coeficientul de frecare al placii plane depinde de punctul de tranzitie si de Reynolds:

Punctul de tranzitie se defineste astfel:

,

unde :

;

Pentru punctul de tranzitie se poate aplica relatia:

Relatiile de calcul pentru coeficientul de frecare al placii plane in laminar si turbulent sunt:

Factorii de corectie au urmatoarele expresii:

In subsonic corectia de alungire este:

, (4.45)

iar corectia de compresibilitate:

Pentru corectia de compresibilitate se pot utiliza si diagramele.

In supersonic se utilizeaza diagramele:

Termenul posterior are urmatoarele expresii:

unde:

Termenul de unda este dat de:

,

unde termenii expresiei se iau din diagrame :

4. - Coeficientul fortei axiale induse

Pentru acest termen se aplica relatia:

,

unde:

Grafice rezultate la modulul de aerodinamica:

V. Modulul de analiza:

Rezultate la modulul analiza

Tipul analizei:

1. Analiza la un singur numar Mach si analiza raspunsului

Viteza de calcul 200.0

Dpmax=20.00

Mach = 0.60

Alfa = 3.068

Delta = 6.849

2. Analiza la toate numerele Mach cu reprezentare indici

VI. Modulul de performanta:

Prin determinarea vitezelor minime respectiv maxime la diferite inaltimi, se poate trasa anvelopa de zbor orizontal corespunzatoare starii initiale si finale de incarcare a avionului.

Zbor orizontal la viteza maxima:

Pentru stabilirea vitezei de zbor orizontal la o inaltime data se pleaca de la urmatoarele date:

-procedeu iterative peste toate relatiile deoarece coeficientii aerodinamici sunt dependenti de Mach,

Solutia obtinuta trebuie sa verifice conditiile:

Zbor orizontal la viteza minima:

Pentru determinarea vitezei minime se impugn conditiile:

-procedeu iterative peste toate relatiile deoarece coeficientii aerodinamici sunt dependenti de Mach.

Solutia obtinuta trebuie sa verifice conditiile:

Grafice obtinute la modulul de performanta:

VII Modulul de simulare:

Modulul de simulare a zborului permite determinarea parametrilor miscarii autonome a aparatului de zbor. Se analizeaza parametrii de zbor corespunzatori unei evolutii

Rezultate obtinute la modulul de simulare:

Durata simularii: 60 s

Viteza initiala: 200

Plafon : 1000 m

Tipul evolutiei:

1. Zbor orizontal:

2. Sandela

3. Picaj

4. Tonou

II. Modelul de la proiectare aerodinamica si schita cotata:

VIII. Bibliografie:

-Internet: www.boeing.com

-"Dinamica Zborului-Note de curs" - Conf. dr. ing. Teodor-Viorel CHELARU

-"Dinamica Zborului-Proiectarea avionului fara pilot" - Conf. dr. ing. Teodor-Viorel CHELARU, Editura Printech, Bucuresti 2003

CUPRINS

I. PREZENTARE GENERALA

II. MODELUL DE LA PROIECTARE AERODINAMICA SI SCHITA COTATA

III. PREZENTAREA PACHETULUI DE CALCUL

IV. MODULUL DE PROIECTARE AERODINAMICA

V. MODULUL DE ANALIZA

VI. MODULUL DE PERFORMANTA

VII. MODULUL DE SIMULARE

VIII. BIBLIOGRAFIE