Atlas V

 
 

Lockheed Martin * United Space Alliance * International Launch Services

 

 

 

 Orbital launches

 Period

Last launch

Atlas 401

 

37

2002 -2017

 

Atlas 402

 

-

-

Atlas 411

 

4

2006 - 2016

Atlas 421

 

6

2007 - 2016

Atlas 431

 

3

2005 - 2016

Atlas 501

 

6

2010 - 2015

Atlas 502

 

-

-

Atlas 511

 

-

-

Atlas 512

 

-

-

Atlas 521

 

2

2003 -2004

Atlas 522

 

-

-

Atlas 531

 

3

2010 - 2013

Atlas 532

 

-

-

Atlas 541

 

4

2011 - 2016

Atlas 542

 

-

-

Atlas 551

 

7

2006 - 2016

Atlas 552

 

-

-

Atlas HLV

 

-

-

 

In order to meet commercial and U.S. government launch service requirements in the next century, Lockheed Martin is developing the Atlas V series of launch vehicles. The Atlas V will use the RD-180 first stage engine and the Centaur design from Atlas III, in conjunction with a new first-stage design called the common core booster (CCB). three basic varieties of the Atlas V will be available.
The Atlas V 400 version use the same 4-m diameter class fairing as the Atlas III. The Atlas V 500 versions have a new 5-m diameter payload fairing, and can have up to 5 solid strap-on boosters for increased performance. The Atlas V HLV (Heavy-lift Launch Vehicle) uses two additional CCBs like the first stage as liquid strap-on boosters. The Atlas V 500 and HLV will have the capability to deliver payloads directly into GEO.

 

Nomenclature of Atlas V:
    first digit         Approximate payload fairing diameter in meters
    second digit    Number of strap-on boosters
    third digit        Number of engines on Centaur upper stage

 

(weight in t)   

LEO LPEO GTO GEO

Atlas 401

9.80 8.08 4.75 -

Atlas 402

       

Atlas 411

12.03 10.00 5.95 -

Atlas 421

13.60 11.14 6.90 2.85

Atlas 431

15.27 12.13 7.70 3.30

Atlas 501

8.21 6.77 3.78 -

Atlas 502

       

Atlas 511

11.00 9.07 5.25 -

Atlas 512

       

Atlas 521

13.50 11.16 6.48 2.54

Atlas 522

       

Atlas 531

15.53 12.88 7.45 3.08

Atlas 532

       

Atlas 541

17.42 14.49 8.29 3.53

Atlas 542

       

Atlas 551

18.85 15.77 8.90 3.86

Atlas 552

       

Atlas HLV

25.00 19.00 12.65 6.35


The Atlas V first-stage structure will be completely redesigned. In the CCB the stainless steel pressure-stabilized tanks are replaced by structurally stable aluminum isogrid tanks with a larger diameter of 3.8 m (12.5 ft.). The total stage length is increased, and instead of sharing a common bulkhead the tanks are independent. Two interstage assemblies are added to the top of the CCB, with different configurations depending on the payload fairing size. For the Atlas V 400, a conical 0.450 t graphite-epoxy interstage adapter provides the interface between the larger diameter first stage and the smaller diameter Centaur. A 0.375 t aluminum-lithium Centaur interstage adapter on the top of the CCB supports the upper stage. To interface with the larger fairing of the Atlas V 500 series, a short cylindrical 0.270 t booster interstage adapter is used. This is topped by a 1.30 t composite-sandwich Centaur interstage adapter.
When used inside the 5-m payload fairing of the Atlas V 500 or HLV, the upper stage Centaur can be modified to support injection directly into GEO. The short and medium length fairing (20.7/23.4 m) are available for the Atlas V 500, while the long fairing (26.4 m) is designed for the Atlas HLV.
The Atlas V 500 strap-on solid rocket motor is a new design produced by Aerojet. Atlas V 500 can fly with zero to five of strap-on boosters. All boosters are ignited at liftoff and are jettisoned in pairs after burnout.