Jupiter (rocket family)

Jupiter^[1]

The Jupiter common core stage would have used Shuttle components
Function	Crewed launch vehicle
Country of origin	United States
Size
Height	70.9–92.3 m (233–303 ft)
Diameter	8.41 m (27.6 ft)
Mass	2,061,689–2,177,650 kg (4,545,246–4,800,896 lb)
Stages	1.5 or 2
Capacity
Payload to LEO (185 km x 51.6°)
Mass	60,282 kg (132,899 lb) (Jupiter-130)
Payload to LEO (241 km x 29°)
Mass	91,670 kg (202,100 lb) (Jupiter-246)
Associated rockets
Family
Comparable	National Launch System
Launch history
Status	Proposed
Launch sites	LC-39B, Kennedy Space Center
Notable payloads	Orion Crew Exploration Vehicle Altair Lunar Surface Access Module
Boosters – Shuttle RSRM
No. boosters	2
Engines	1 solid
Thrust	12,868–13,977 kN (2,893,000–3,142,000 lbf) (sea level - vacuum)
Total thrust	25,737–27,955 kN (5,786,000–6,285,000 lbf) (sea level - vacuum)
Specific impulse	237.0 - 269.1 sec (sea level - vacuum)
Burn time	123.8 sec
Propellant	APCP/PBAN
First stage (Jupiter-130) – Common core stage
Diameter	8.41 m (27.6 ft)
Engines	3 SSME-Block-II
Thrust	5,235–6,550 kN (1,177,000–1,472,000 lbf) (sea level - vacuum; three engines combined)
Specific impulse	361.4 - 452.2 sec (sea level - vacuum)
Burn time	524.5 sec
Propellant	LOX/LH2
First stage (Jupiter-246) – Common core stage
Diameter	8.41 m (27.6 ft)
Engines	4 SSME-Block-II
Thrust	6,981–8,734 kN (1,569,000–1,963,000 lbf) (sea level - vacuum)
Specific impulse	361.4 (SL) 452.2 sec (sea level - vacuum)
Burn time	384.1 sec
Propellant	LOX/LH2
Second stage (Jupiter-246) – Jupiter Upper Stage
Diameter	8.41 m (27.6 ft)
Engines	6 RL10B-2
Thrust	661 kN (149,000 lbf) (vacuum)
Specific impulse	459 sec (vacuum)
Burn time	609.9 sec
Propellant	LOX/LH2

The Jupiter family of super heavy-lift launch vehicles was part of the proposed DIRECT Shuttle-Derived Launch Vehicle architecture. It was intended to be the alternative to the Ares I and Ares V rockets which were under development for the US Project Constellation.^{[citation needed]}

Major benefits were projected from re-using as much hardware and facilities from the Space Shuttle program as possible, including cost savings, experience with existing hardware, and preserving the workforce.^{[citation needed]}

DIRECT proposal[]

Some envisioned Jupiter configurations, including crew and cargo variants

Jupiter was designed to be a high-commonality family of rockets, adapted closely from existing Shuttle systems. Each Jupiter launch vehicle would use a "common core stage" consisting of a tank structure based closely on the existing Space Shuttle External Tank with a pair of standard four-segment Solid Rocket Boosters (SRBs) mounted at the sides as on the Space Shuttle. Up to four Space Shuttle Main Engines (SSMEs) from the Space Shuttle Orbiter would be attached to the bottom of the tank and would be expended along with the tank. For heavier payloads a proposed Jupiter Upper Stage (JUS) would be added atop the tank structure. For extra-planetary expeditions, the JUS would serve in a role similar to the Earth Departure Stage planned for Ares V. DIRECT purposefully specified existing components for the launch vehicles, but contended that improvements such as the more powerful five-segment SRB or the J-2X upper stage engine could have been incorporated.^{[citation needed]}

Crews would be carried atop the launch vehicle in NASA's planned Orion Crew Exploration Vehicle. Cargo, whether carried under Orion or alone on a cargo-only launch, would be enclosed by a payload fairing.^{[citation needed]}

Variants[]

Many configurations of Jupiter were projected, with the May 2009 DIRECT version 3.0 proposal recommending two: the Jupiter-130 and Jupiter-246, with claimed lift capacities exceeding 60 and 90 tonnes (t), respectively, to low Earth orbit.^[1].

Jupiter-130[]

Expanded diagram of the DIRECT v3.0 Jupiter-130 configuration

DIRECT proposed that the Jupiter-130 be the first configuration developed, with the goal of becoming operational within four years of the start of the development program. The Jupiter-130 would have consisted of the Jupiter common core stage with one SSME removed, no upper stage, and a payload fairing on top. "130" stands for one cryogenic core stage, three main engines, and zero upper-stage engines. Initial launches would rotate crews and bring cargo to the International Space Station, a function carried out by Soyuz rockets at the time.^{[citation needed]}

DIRECT calculations indicated that the Jupiter-130 would have been able to deliver between over 60 t and over 70 t of cargo or cargo and crew to a variety of circular and elliptical inclined low Earth orbits.^[1] When the mass of the proposed Orion spacecraft and crew is subtracted (18 - 22 t depending on the mission^[2]), the remainder compared favorably with the approximately 25 t cargo capacity of the Space Shuttle, and the lack of capacity of Ares I besides the Orion spacecraft.

Jupiter-246[]

The Jupiter-246 would have used four Space Shuttle Main Engines (SSMEs) in the common core stage with an upper stage, informally called the Jupiter Upper Stage (JUS). The Jupiter-246 would use six RL10B-2 engines on the upper stage. "246" stands for two cryogenic stages, four main engines, and six upper stage engines. The primary role for the Jupiter-246 would be to launch heavier cargo as well as crew and cargo for lunar missions.^{[citation needed]}

Jupiter Upper Stage[]

Because the Jupiter-246 would have used four SSMEs on propellant tanks originally sized for three engines, the core stage propellant would be depleted before achieving low Earth orbit, and a large capacity upper stage would deliver payload into orbit. Launched with a partial upper stage propellant load of 75 t, a Jupiter-246 could deliver over 84 t of crew and cargo to a circular 241 km (130 nmi), 29° inclined orbit.^[3] Launched with no crew or payload, the same 75 t of propellant could deliver an additional 100 t of propellant to the same orbit.^[4] The total JUS capacity was to be approximately 175 t. For lunar missions where the JUS is to serve as the Earth departure stage, a full load of 175 t of propellant would be launched and 75 t would be consumed in achieving low Earth orbit, leaving 100 t available for the Earth departure burn.

In line with the DIRECT v3.0 theme of using as much existing hardware as possible, DIRECT proposes the veteran RL10 engine family to power the JUS. However, DIRECT anticipated similar performance for its upper stage from the J-2X engine, previously under development for the Ares I and Ares V upper stages.^{[citation needed]}

Design considerations[]

Existing engine use[]

One of the primary goals of the DIRECT proposal is to develop a new heavy lift rocket in a shorter time frame. When the DIRECT project began in 2006, the Shuttle was expected to be operational for another four years or so. DIRECT was planned to use the four-segment Solid Rocket Booster (SRB) unchanged from the Shuttle and to make use of work already underway for the Constellation Project on the RS-68 main engine and J-2X upper stage engine.^{[citation needed]}

By 2009, however, there were concerns that the ablatively-cooled RS-68 engine could not survive the intense heat from the nearby SRBs. With this worry and with Shuttle retirement imminent, the DIRECT v3.0 proposal called for using the more expensive regeneratively-cooled, reusable Space Shuttle Main Engine (SSME) in a disposable role. Three or four SSMEs attached to the bottom of the core tank structure would be discarded in Earth's atmosphere along with the tank. For missions beyond lower Earth orbit, the Jupiter Upper Stage would use six Pratt and Whitney RL10B-2s.^{[citation needed]}

Before it could be launched, NASA's proposed Ares I rocket would have required both a new, modified five-segment version of the Space Shuttle SRB and the J-2X upper stage engine, a modification of the J-2 engine used on the Saturn V. The proposed Jupiter family could have launched with currently available engines, with the ability to upgrade to a more powerful SRB and J-2X upper stage engine should they become available.^{[citation needed]}

Crew safety[]

DIRECT envisioned continued development and operation of NASA's Orion crewed spacecraft, including its Launch Abort System (LAS). In the event of an emergency, the LAS would pull the crew capsule to safety as it would on NASA's Ares I. The DIRECT Team asserted, however, that the Jupiter-130's greater lift capacity - 64 tonnes, versus 25 tonnes for Ares I - would enable the Orion to be designed with more crew safety capability than was planned.^{[citation needed]}

For crewed flights to the International Space Station (ISS), DIRECT said the added lift capacity of the Jupiter would allow significant cargo to be carried in a separate module mounted below the Orion spacecraft. Once orbit was reached, the Orion would dock with this module and ferry it to the ISS. By comparison, Ares I would be capable of bringing only the Orion spacecraft to the ISS. DIRECT asserted that flying Orion and a separate payload module on a Jupiter would satisfy the safety concerns raised about flying crew separately from cargo following the 2003 Space Shuttle Columbia disaster, since the Orion capsule would still be able to separate from the launch vehicle and any cargo in the event of a launch abort.^{[citation needed]}

Jupiter vs. Ares I[]

The DIRECT Team cited a number of particular features that were claimed to make a Jupiter-130 safer than the Ares I:

The Jupiter design would re-use the proven method of Space Shuttle of attaching the SRBs to the tankage though an internal structural member. DIRECT says this would avoid the inducing of potentially severe vibration in the vehicle, resulting from a "thrust oscillation" effect endemic in large solid rockets. This effect became a concern for the Ares I.^[5]

As with the Space Shuttle, the liquid main engines of a Jupiter-130 would be ignited on the ground and undergo a rapid checkout before SRB ignition and launch. Start-sequence problems could be detected before committing to the launch, and the only vehicle staging event would be the burnout and separation of the SRBs. By comparison, the Ares I launch consists of the immediate ignition of its single SRB first stage, then requires a staging event and ignition at altitude of its cryogenic second stage. While staging is common launch vehicle practice, it introduces safety, risk and reliability concerns, particularly on crewed flights. (The larger Jupiter-246, with its upper stage, would typically include this risk.)^{[citation needed]}

The DIRECT Team asserted that the Jupiter-130 and -246, with their multiple main engines, would be capable of reaching orbit even in the event of an engine shutdown.^{[citation needed]}

In the Jupiter concept, the crewed Orion spacecraft would be supported by a large aerodynamic fairing. This arrangement would place the Orion at least 10 m (33 ft) further away from propellant-filled stages than it would be on an Ares I. DIRECT asserted this would provide a valuable additional "buffer space" between an exploding vehicle and the crew.^{[citation needed]}

The envisioned lift capacity of the Jupiter-130 could allow protective hardware to be mounted inside the payload fairing, below the Orion spacecraft. DIRECT postulated mounting a lightweight shield made from boron carbide and Kevlar between the spacecraft and the stages below to help protect the crew from shrapnel and other debris from a vehicle explosion.^{[citation needed]}

See also[]

• DIRECT
• Jupiter-C, 1950's-era launch system
• Saturn (rocket family)
• Shuttle-Derived Heavy Lift Launch Vehicle
• Space Launch System
• Studied Space Shuttle Variations and Derivatives

References[]

External links[]

• DIRECT Launcher proposal website