Atlas V |
Lockheed
Martin * United Space Alliance * International Launch Services
|
Orbital launches |
Period |
Last launch |
Atlas 401 |
41 |
2002 -2022 |
|
Atlas 411 |
6 |
2006 - 2020 |
|
Atlas 421 |
9 |
2007 - 2022 |
|
Atlas N22 |
2 |
2019 - 2022 |
|
Atlas 431 |
3 |
2005 - 2016 |
|
Atlas 501 |
8 |
2010 - 2023 |
|
Atlas 511 |
1 |
2022 |
|
Atlas 521 |
2 |
2003 -2004 |
|
Atlas 531 |
5 |
2010 - 2022 |
|
Atlas 541 |
9 |
2011 - 2022 |
|
Atlas 551 |
13 |
2006 - 2023 |
|
Atlas HLV (canceled) |
- |
- |
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 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 511 |
11.00 | 9.07 | 5.25 | - |
Atlas 521 |
13.50 | 11.16 | 6.48 | 2.54 |
Atlas 531 |
15.53 | 12.88 | 7.45 | 3.08 |
Atlas 541 |
17.42 | 14.49 | 8.29 | 3.53 |
Atlas 551 |
18.85 | 15.77 | 8.90 | 3.86 |
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.