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Spacecraft Summary Weight Statement

Configuration: Apollo Spacecraft

Mass Property Section

Date: May 1, 1968

     

Code

System

(U.S. Custom: lbs & ft)

Item Or Module

Craft

A

B

C

D

E

F

M

1

Aerodynamic Surface

323

         

323

2

Body Surface

1,102

2,103

2,452

3,170

   

8,827

3

Induced Envir. Prot.

998

3,874

532

100

   

5,504

4

Lnch Recov & dkg

 

956

       

965

5

Main Propulsion

1,631

 

2,751

     

4,382

6

Orient Control

596

307

454

     

1,357

7

Prime Power Source

 

315

1,285

     

1,600

8

Power Conv. & Dist.

73

1.090

450

79

   

1,692

9

Guidance & Navigation

 

595

       

595

10

Instrumentation

 

42

74

     

116

11

Communication

 

301

147

1

   

449

12

Environmental Control

 

553

220

     

773

13

Reserved Equipment

             

14

Personnel Provisions

 

422

       

422

15

Crew Sta. & Control

 

396

       

396

16

Range Safety & Abort

             

Subtotal Dry weight

4,723

10,963

8,365

3,350

   

27,401

17

Personnel

 

1,075

       

1,075

18

Cargo

     

*32,508

   

32,508

19

Ordnance

45

33

52

441

   

571

20

Ballast

958

         

958

21

Residual Prop. & Serv. Item

 

140

1,027

     

1,167

Subtotal Inert Weight

5,726

12,211

9,444

36,299

   

63,680

22

Residual Prop. & Serv. Item

             

23

In flight losses

9

274

2,050

     

2,333

24

Thrust Decay Propellant

             

25

Full Thrust Propellant

3,178

 

39,741

     

42,919

26

Thrust Prop Buildup

             

27

Pre-ignition Losses

             
                 
                 

Total Gross Weight

8,913

12,485

51,235

36,299

   

108,932

Design Envelope (ft3)

212

556

1,970

6,540

   

9,202

Pressure Volume (ft3)

 

366

 

250

   

616

Design Envelope Surface Area (ft2)

300

377

613

1,515

   

3,054

Pressurized Surface Area(ft2)

             
               

Design g Max

 

20

         

Design Power Max (KW)

             

Design No. Man/Days

           

3/10

From the "Fundamental Techniques of Weight Estimating and Forcasting for Advanced Manned Spacecraft and Space Stations" by Willie Heineman, Jr.; NASA TN D-6349

* See the lander for these details, 32,508 pounds.

A = Launch Escape System

B = Command Module

C = Service Module

D = Adapter and Lunar Module

M = Manned Launch Total

Moon data, Earth data, Apollo data, Lander Data, Rocket data.

1. Launch - Day 1

2. 17,500 mph, 11min, 119 above earth.

3. 25,000 mph -

221463 perigee, 252,710 miles apogee, 238,856 miles average

Assume the path is correct, assume the moon orbit is circular.

4. 220,000 the moon gravity takes effect.

5. 70 mile high orbit around the moon.

6. 5,500 mph out of lunar orbit.

7. Earth orbit

8. Landing.

   

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