20834581 Aerospace Design Project JS TTT

8/11/2019 20834581 Aerospace Design Project JS TTT

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J V, S N

, T L H, T J, T D


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1.0 I ...................................................................................................................................... 3

2.0 I C ........................................................................................................................ 3

3.0 D O .......................................................................................................................... 6

3.1 C A ........................................................................................................................ 6

3.2 D T S ..................................................................................................................... 7

4.0 S .................................................................................................................................... 9

4.1 S S ............................................................................................................ 9

4.2 P ............................................................................................................................... 10

5.0 C ....................................................................................................................................... 10

6.0 R ...................................................................................................................................... 10

A A W E .......................................................................................................... 11

I W E A .................................................................................................... 11

R W ................................................................................................................. 14

E W F ..................................................................................................................... 17

A B T S ........................................................................................................................ 19

A C C A.......................................................................................................... 20

A D S .................................................................................................................. 26

G S ............................................................................................................... 26

A E L W C G.......................................................................... 29

W L E L ............................................................................................................. 29

A F C P S .................................................................. 32

A G L G ................................................................................................................... 34


3/45

1.0 T M U D M A E JS A

D . T

, JSTTT.

T :

1

PP 80 80

PB 20

C 2 2 , 80 15

R 800 (1481.6)

R F 100 (185.2) 45

C A 35000 (10668)

C S M N = 0.8

C 1)

D .2) M 2 0.024 (

)

3) M 300/

T 4500 , , 400C

L 120 (61.73 1) , , 400C

P 2

P 5000 (1524 ) 35000 (10668 )

C JAR P 25

I .

T

. A

.

T ,

.

T

.


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E. T

.

2

W A SW, 2 85

W S , 27

A R AR 8.8

W S , 25

M A C , 3

O E F 0.8

P D CD,0 0.02

M L C CL, 2.4

I W W0, 40000

I . T

, , . I

, . T

.

O , . I

. G , ,

. S F 1.


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2 ( )

T .

I F 2. A 3

.

B , . A

, . T

, ,

. B , ,

.

I , T . T

,

.


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3.0

3.1 T

. T

0.3997

S , .

1

. A

( A C

. T

F 3. T ,

3377 P.

3

, ,

(P)

C A),

,

,


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T, , S

80m 107990.46N. T

A A W E,

15135.29 .

3.2

L, . T ,

,

, . C . T , , ,

, .

3

BR,

4 5 6

(P) 3377.39 3377.39 3377.39

/ 0.3866 0.3997 0.4108W , S ( 80.00 80.00 80.00MTOM, 27541.16 27541.16 27541.16T, T (N) 104451.12 107990.46 110989.44/ 0.54909312 0.549551632 0.5499080567

E W, () 15122.66 15135.29 15145.11A R, A 8.8 8.8 8.8

2.4 2.4 2.4 4 A R, A 8.0 8.8 10.0 (P) 3377.39 3377.39 3377.39

/ 0.4061 0.3997 0.3922

W , S ( 80.26 80.00 79.66MTOM, 27630.62 27541.16 27424.28T, T (N) 110076.00 107990.46 105514.42/ 0.5431771813 0.549551632 0.55836214735E W, () 15008.32 15135.29 15312.68

BR, 5 5 5


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5

2.0 2.4 2.6

(P) 2814.49 3377.39 3658.84/ 0.4506 0.3997 0.3814W , S ( 100.00 80.00 73.20MTOM, 28675.82 27541.16 27300.63

T, T (N) 126758.19 107990.46 102146.24

/ 0.552104479 0.549551632 0.5482852752

E W,

() 15832.05 15135.29 14968.53

BR, 5 5 5A R, A 8.8 8.8 8.8B ,

2.6, 5, 8.8.

6

V V 3658.84/ 0.3814W , S () 73.20MTOM, () 27300.63T, T (N) 102146.24

/ 0.5482852752E W, () 14968.53


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4.0

4.1

7

C C 2S C 80

S P () 0.75

S () 0.48

L () 38.71

W S () 25.4

T H () 3.695

W 25

0

A R 8.8

F () 3

F () 3

C W () 2.468

C H () 2.137

E W () 14968.53

M () 27300.63

T M () 1371.6 (4500 )C S M N = 0.8

R () 1481.6 (800 )

E(2) G E CF348C1

M T (2) (N) 122.7

F T D () 1.17348

E L () 3.2512

T A D S.


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4.2

8

P R V V A I D

C , 300 / 1072.19 /

T 17.35

T 1.37 5.85

A 61.73 / 60.596 /

T 4500 2930.2

M M = 0.838

T 8 P V

. A ,

. T

, , , , . T A F

C P S.

5.0

T , JS TTT, ,

.

6.0

R DP, 2006, , 4, R V, L

S L, L

A JD, 2005, , MG H, B

S RD, 2000, , A, S A


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I , ( 0

2), 1481.6 (800 2 3) ( 3 4). I

, .

I ( 4 5), 100

( 5 6), 45 ( 6 7) (

7 8).

4:

3: 1

0 1

2 3

4

5 6

7

8


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T , :

0.970 0.985 0.995F 2 3 , :

4:

W: R G V T S F C

= 1481.6 = 14.1 /NT A R 8.8.

6 1.5 19


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148611039.8114.1106

236.316.454 0.95

S 5 6 ,

...

.. 0.993

5:

45 60 2700 11.3

19

.. 0.984865.0995.0984.0993.0985.0984.0995.095.0985.097.0

0

8==

W

W

143.0)1(06.10

8

0

==

W

W

W

Wf

6:


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T M :

838010.1430.97.I:

S 0W = 40000

9

1 40000 24405

2 24405 25555

3 25555 25442

4 25442 25453

5 25453 25452

E 6

I E M T W 25450

A ,

3377.392 0.3997.F , MTOW . B ;

7

8 1


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T,

0.91210664.515 3377.3920.2888S

10

1 W 0.02 11 1W A O E , 0.8. T,

1 8 . 8 0 . 8 0.0452

A , 10.020.2888 0.0452 0.2888

12.15

N, ,

.2

3 5 6


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12

For cruising range, wW e xp 13

For loitering endurance, WW e xp

Rrangeggravitational acceleration,9.81ms

c thrust speciic fuel consumptionSince we have a bypass ratio of 5 which is quite high,c for highbypass turbofan is14.1x10k g N s for cruising and 11.3x10k g N s for loitering.O ,

. T,

0.970 0.985 0.93137 0.995 0.985 0.99115 0.97567 0.9950.83918 14

1.0611.0610.839180.17047

S

15


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8380

10.170470.97.

T 25450 (

).

10 ,

.

1 25450 27768.82

2 27768.82 27517.70

3 27517.70 27543.59

4 27543.59 27540.91

5 27540.91 27541.19

6 27541.19 27541.16

T, 27541.16.

N,

.

16 F ;

= 0.32 =0.66 C1=0.13 C2=0.30 C3=0.06 C4=0.05 C5=0.05

=1

H, . T S.I. ,

. . N. T


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18

where a is the speed of sound

0.320.66 14.448

. 147.88

. 27541.169.81.8.8.0.3997.3377.392.0.838.0.549551632

A ,

0.54955163227541.1615135.29

T, , 15135.29 .


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I T . I

, . T

T 5%.

F , 0.95, E 19

.

19 0.95W E 19 ,

. B

MA.

, 6 0.45 . U . G

.

W , E

20 0.0855.

20

0.0855 T 0.71.2

0.61.0 . S

, .

F .

F :

T 10%


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O 120 . F

, 0 . 8 7. ,2

1.127 , 2.4 120 61.73 0.87 1.3 1.1272.461.73

20 . 871 . 3 3506.04 I , 0.903. T 3377.39P.

G

, = 1, V/ = 0

( ),

,

, .

W

V 2 WS k

C

I .


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1 . 2 2 5 k g m

1 0.451 10.75G M0.60.11 G MM Mach number Va

2 WS kC where a is the speed of sound at take off sea levela speed of sound at sea level 340m s bypass ratio 5 taken from present aircrafts data which are similar to our designGbetween 0.9 and 1.2 so we chose 1.1

Firstly, we calculate the Mach number, M; 20.971.225 1.22.4340 2.91110WS

Therefore,

1 0.451 5

1 0 . 7 5 51.1 2.91110

0.60.11 51.12.91110

W

S

13. 4385 10 9.321310 As a result,


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W: TOP: T O P

W T W L,= M

857.4284.30.0185 W: TOFL: T O F LF A R, T 4500 .

4500857.428.430.0185

0.0185 28.433642.60 42 28.43 28.43 40.01853642.620.0185

118.922 5694.01 F :

F A R, ff 40 C

W:

:

/

: 1.225/


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= W L

T 40 C: 101325287313.16 1.127 /S :

1.1271.225 0.92S TOP :

5694.01 10.92 1,A , 2.4 10.92 12.4 15694.01 7.95410 T : 7.95410 /

U : , K ,


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,

0.02 0.8 1 2 0.970.985 1.952 0.932 0.5 . . 0.50.3103. 5. 0.206 0.3103 35000

0.3801 35000

1 1 8 . 8 0 . 8 0.0452 12 0.50.3801296.50.8 10690.12

0.93210690.12

0 8 . 7 1 0

5 0

A , :

,

1

,

1

0.9550.206 0.028.710 WS 0.0452 8.7 10 WS 1296.5 1.5240.8 1050 43


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0.5 .

.

0.50.3103.

5.

0.206

0.3103 35000

0.3801 35000 1.524

0.8296.5/237.2/ 1 1 8 . 8 0 . 8 0.0452 12 0.50.3801237.2 10690.12

0.93210690.12

0

8 . 7 1 05 0


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11

A (2) S 73.2

A R AR 8.8S () B 25.4

T 0.3

R C () 4.43T C () 1.33M G C () 2.88M A C ()

2.89

A T C R 0.105T () 0.302S A () 25 A S NACA 2410

12

T L, 38.7103

S S L, 22.000

O D, 3.00

I D, 2.850

L / D, 12.90343

13


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14

S, HT 10.441

T C, T 0.870

R C, 0 1.934

M C, 1.402H T V C CHT 0.950

A R ARHT 6.000

T R HT 0.450

T A, LHT 11.060

T A, 2 SHT 18.171

S, HT 30.000

I, 2.000

E S C/C 0.25

T / SHT/S 0.248

15

H, VT 3.695

T C, T 3.457

R C, 0 4.322

M C, 3.890

V C CVT 0.086

A R ARVT 0.950

T R VT 0.800

R C C/C 0.320


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N T 16 1 . S

, 2.

16 (3481)

M CF348C1

U I O A CRJ700701/701ER

D T (N) 61340.98D S F C (/N.) 0.03773

B R 5.0

N O S 2

F D () 1.17348

L () 3.2512

W/D O E () 1.3208

D W () 1065.9420695

3.2512

1.17348

1.3208


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I ,

. T F 106 S ,

.

7:

T 14969 . T :

17

W E G W M () W(N)

W G 0.21 3143.49 30837.6369

T G 0.045 673.605 6608.06505B G 0.2 2993.8 29369.178

L G 0.085 938.124 9202.99644

N G 0.035 523.915 5139.60615

P G 0.04 598.76 5873.8356


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T

.

21

, W,W .T , , , , , , ,

.

T ,

.

T

XLE:

18

X 15X 34.6117

X 27.8035

C1 0.4

C2 0.35

W: XLE: D : : W

: M E W

C1 : LE

C2 : CG


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S E 21,

2049118 .

T

.

T :

22

XXXXCGCGCGCG 18.18.18.18.91919191mmmm

S .

23

T XLE:


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A

. T . 2.6 8.8 3658.841 0.458078 0.841897 73.2

27636.23 14968.53 122681.952 5, 0.020.04521.127

, 1

R, , S ,

237.2280.4580780.2061950.95545 0.020.3273 0.04520.3273 5.445 ,1072.19

,, ,

W,

1 0.451 10 75G M0.60.11 G M


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R,

s i n ,, , S , s i n 0.458078 0.8277

0.97 1.2 0.02

2.60.0452 2.6

1.2

17.35 s i n 2 ,, ,

s i n 0.4580782 0.82770.97 1.2 0.022.6 0.0452 2.61.25.89

,

2

R, 2,S ,

3658.841 20.871.31.127 2.6 60.596


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A

( ). T

.

8

A ,

, . T

. F

,


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T, : ( )

N : .

M : .

= . . = 2065.5 6196.50

W: = 27540

0.39 0.48 0.39 2065.50.48 15.21517 5.99 5.3 . 5.3 2065.5. 58.68253 23.10

0 . 3 9 . 0.396196.50. 25.78 10.15

5 . 3 . 5.326196.50. 82.95 32.66F , T 20 N G S T 21 M G S. 20

: (D W) 307.7

M 16500 P 270

R 12.7

W D 16

N 18


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T .

N : 2 3

29.810.752.8 0.47

0.750.0508

0.186601 0.211601332 M :

2

329.810.752.8 0.470.75 0.0864 0.164317

0.1893171 W:S = .= V ( = 3/) (9.81 /^2) = S ( =0.75)

= G ( = 2.8)= T (0.47)= T : 29.42 12.7 0.0254 0.0508


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A :

=

()

= (0.60842 + +1.48)

(27)

= 1.0641 + 0.509525 ()W:S () = .= H L CG (M ).= T + CG (C

.

T = R + + .

= (16.50.0254) +0.1893171 + = 0.60842 + ()= 1.48 A ( )

.F ( 3) .

L

C T = 27

L

H L CG

(M ) = L

:V CG

A :P X. L

9


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F , 711,

11. C , CG

, X .

T := () W:

H CG = 18.91 . = H N ( ) X N M .= 26 (18.91)= 7.09 ()

= T X.

= T .

= R = 0.4191 + ()

T:

= ()

0.4191 + = (11) 7.09 )= 1.378156 (11)()C :

0.4191 + = 1.378156 (11)(1.0641 + 0.509525 )= 1.378156 0.202684 0.09904

1.09904

= 0.7563

= 0.688034

T M : = 0.688034 + 0.4191 + 0.18932= 1.296


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= 0.09

= 0.91

= 0.91/0.09 = . .. 14.1467 W:

= N C.G

= R N

= 9% N G.= R M = 91% N GA) T, N 4.7633 14.1467

C.G .

B) T L M 1.4147 C.G .

C)

A, M 1.296 . T

. S M

.

( ).

T N (

).

H, M

55 C.G

( 4 5).

X T

Y: T T C.G

.


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:

12

F , :

X =

=

.

= 1.81153

W:

X = N M

.

= ( 55)

Y = T C.G ( ).

= 0.688034 + 0.4191 + 1.48

= 2.587134

T:

=

(

)

= (.. )= 7.357W:

X .

L, X.

C.G

M G

N G

L:

A :


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= H N M .=

= 1.4147 + 14.1467= 15.5614 F M (F 13). A N

.

13

.

L,

5

.


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0.47512.7 2.1419 0.5092 0.3274 0.47512.7 0.03129

W:

= . = T 0.5092 M .

H 0.3274

.

A :

(M

).

= + + + = 0.688034 + 0.4191 + 0.03129 +0.3274

= 1.4658

T 7 .


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A 7.6 5,

.

W:= T .= = (0.475 0.32740.03129) + 1.4658= 1.5821

= H .= B (0.5092 + 0.3274)= 12.7 (0.5092 + 0.3274)

= 11.8634

22 :

N T , D W (307.7 () , 0.7620.1956 ()N W 16 (0.406 )N 1.296

N T

M T , D W 4014 (), 1.0160.3556 ()

M W : 16 (0.406 )

M 1.668 M : T

L N L 14.1467 C.G .

L M L 1.4147 C.G .

L N L A

L M L 2.0092 C.G .


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20834581 Aerospace Design Project JS TTT

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Transcript of 20834581 Aerospace Design Project JS TTT