JARVIS HEAVY LAUNCH VEHICLE

By Forum Orbiter Italia Version 2.62 – October 2012

USER MANUAL

Disclaimer and credits

This add-on is provided “as is”, without any kind of warranty; it is compatible with Orbiter 2006-P1 (build 060929) and with Orbiter 2010-P1 (build 100830). Many thanks to Dr. Martin Schweiger, for the Orbiter Space Simulator.

For the others developers: You are free to use parts of our work, eg sound and texture, but you must credit us as the original source of your work.

FOI Credits - Andrew: add-on conception; rocket textures, meshes and configuration; documentation editing. - Fausto: new launch pad textures, meshes and configuration. - Pete Conrad: engine meshes and textures; Shuttle SRB meshes and textures; “dummy” payload meshes and textures. - FedeX: beta testing. - Dany: “Forum Orbiter Italia” logo. - Ripley: D3D9/D3D11 documentation.

Forum Orbiter Italia: http://orbiteritalia.forumotion.com/

Introduction

In the mid-eighties, the "Jarvis" project was the last serious attempt to revive the glorious Saturn V rocket, and at the same time, one of the first ideas of an alternative use for the Space Shuttle hardware, many years before the current "Ares", "Direct" and “SLS” projects. The Jarvis rocket combines the powerful Apollo-era F-1 and J-2 engines with Space Shuttle electronics and 8.4 m stages (the same size of the Shuttle External Tank). Later versions, with Space Shuttle Main Engines (SSME) and/or Solid Rocket Boosters (SRB), were proposed, but never realized. Forum Orbiter Italia has developed a complete and versatile family of heavy launchers around these original ideas and projects.

The versions included in this package are:

Jarvis S (“Single engine” version): the smallest and cheapest version of the rocket. The first stage is a scaled-down version of the standard JS-1 stage utilized in all the other versions of the Jarvis, with a diameter of 6.49 meters and only one F-1 engine instead of two. The second stage is the new HES-3 with three cryogenic “Vinci” engines. This version has a payload capacity of 20,700 Kg to LEO.

Jarvis L ("Light" version): the second smallest version of the rocket, with a standard JS-1 stage and 8.38 meter fairings. This version has a capacity of 27,900 Kg to LEO.

Jarvis C ("Commercial" version): basically, a Jarvis L optimized for GTO commercial launches, with a small cryogenic third stage and a dual-payload carrying system. This version has a capacity of 34,100 Kg to LEO and 13,400 Kg to GTO.

Jarvis B ("Basic" version): the original (improved) two-stage configuration of the Jarvis rocket, with a J-2S powered second stage and a payload capacity of 44,400 Kg to LEO.

Jarvis E ("Enhanced" version): a Jarvis B with a third stage powered by four RL-10 engines, for a payload capacity of 55,400 Kg to LEO.

Jarvis H ("Heavy" version): the most powerful version of the rocket (in terms of liftoff thrust). It is a Jarvis E with longer fairing and two Shuttle Solid Rocket Boosters, for a large payload capacity of 80,700 Kg to LEO.

Jarvis M ("Moon" version): the largest version of the rocket, specifically designed for manned circumlunar flights, with the following features: a new, more efficient cryogenic core stage powered by five RS-25E engines; HES-5 third stage with five cryogenic “Vinci” engines; two Jarvis S first stages as liquid boosters. The payload capacity is in the same class of the Saturn V rocket: 128,800 Kg to LEO and 48,700 Kg to TLI.

The updated Jarvis family of launch vehicles. Colors represents the common parts.

Installation and requirements

Unzip the content of the new add-on in your Orbiter directory. As always, it's better to delete the previous Jarvis package prior to install the new version. The following add-ons are required:

Vinka’s Multistage2 Vinka’s Spacecraft3 (with Orbiter 2006-P1 patch, included in the package). Orbiter 2010-P1 requires the “stage.dll” patch (included in the package). http://users.swing.be/vinka/

For the Capo Passero scenarios, is also required the ASVI base - Capo Passero, v1.0 or higher, by Orbiter Forum Italia. http://www.orbithangar.com/searchid.php?ID=5172 For the "Verrazzano Moon Mission" scenario, is required the Antares Manned Spacecraft, v2.1 or higher, by Orbiter Forum Italia. http://www.orbithangar.com/searchid.php?ID=4682

Payload management

The 6.5, 8.4 and 10 meter fairings atop the Jarvis launch vehicle can easily accommodate a large variety of payloads. The "Heavy" and “Moon” versions (Jarvis-H and Jarvis-M) has enough payload capacity to match the performances of the Soviet N-1 and the Saturn V rocket, and can hypothetically put into orbit a new Skylab-class space station in a single launch. Launching of very large spacecraft/payloads to the moon or distant planets is also possible.

Configuration of the payloads must be managed by the Jarvis_x.ini file located in the Config/Jarvis directory. Open the .ini file and locate the following text:

[PAYLOAD_1] off=(0.,0.00,60) speed=(0.0,0.0,0.0) rot_speed=(0.,0.,0.0) MeshName="jarvis\cargo" Module="spacecraft\spacecraft3" name="cargo_jarvis" Diameter=2.9 Height=5.6 Mass=55400

Jarvis rockets come with a dummy cargo: a non-operational module filled with ballast. When setting your custom payload, be careful not to exceed the maximum payload capacity of the rocket and the dimensional limits of the fairings.

You can use an adapter for your payloads: some adapters are available directly in the config file. Open the .ini file and locate the following text:

;[SEPARATION_23] Height=3 Diameter=6 Emptymass=300 Meshname="jarvis\adapterLBEH" OFF=(0,0,54.595) ROT_SPEED=0

Then, just remove the semicolon on "Separation" string for utilize the adapter.

Jarvis S and Jarvis M have the possibility of choice between two size of payload fairing. Open the .ini file and locate the following text:

;[FAIRING] N=2 MeshName="jarvis\Jfairing2" Diameter=8.4 Height=25 angle=0 off=(2.0883,0.0,77.666) SPEED=(4.6,0.0,1.8) ROT_SPEED=(0.0,-12,0.0) emptymass=4040

Then, just remove the semicolon on "Fairing" string for utilize the specific fairing.

Special payloads

In this version of the addon, the logistic spacecraft / space tug “Giovanni da Verrazzano” and a special DoD payload, the KH-11 spy satellite, are included in the package: the scenarios are in the Jarvis/Verrazzano and Jarvis/DoD folders. Read the Verrazzano and KH-11 documentations for further details.

“Nosecone Art”

In the “Extras” folder are included the .bmp files of the payload fairings: the one used in the “standard” versions of the rocket (S, L, B, and E) and the one used in the “heavy” versions (H, M). Also, an empty fairing (without logo) is included. You can modify these images, then convert it in dds format (various converters are available out there) and, finally, copy the new file in the Textures/Jarvis folder for customize the rocket for your needs. Make a backup of the original files. Thanks to Phantom Cruiser, who give us the idea.

Launch procedures

Pre-launch settings

After the payload configuration, the next step is, possibly, setting the azimuth for the automatic launch. This parameter must be edited directly in the guidance_Jarvis_x.txt located in the Config/Jarvis directory. Open the .txt file and locate the line of the “roll” program: roll(init_pitch_time,init_pitch_angle,heading_target,pitch_target,pitch_mode).

For example:

7=roll(5,90,90,84,1)

The launcher is pitched in the direction indicated by “pitch_mode” (1=pitch up, -1=pitch_down) until it reaches the “init_pitch_angle”(in °), then the pitch guidance loop is closed and the pitch is controlled in order to reach the pitch target. When the “init_pitch_time” has elapsed, the roll and yaw guidance are terminated to reach the proper heading target. This is a complex manoeuvre and inputting bad parameters can lead to a catastrophic roll. For manual launch, this step can be skipped. For more details about the configuration of the guidance file, see the Vinka’s multistage documentation.

The date of the launch must be managed by editing the scenario file. Open the file and locate the correct string:

Date MJD 62415.7029763416

The string indicates the Modified Julian Day. If you want modify this parameter, you must insert a new date. A converter from MM-DD-YYYY to MJD can be useful; for example, you can utilize the “Date.exe” converter, located in the Utils folder of Orbiter, or this one: http://www.fourmilab.ch/documents/calendar/

Launch

The launch is automatic. The scenarios starts at about T-80 seconds. The launch pad animations are also automatic. At T-30 seconds, the speaker begin his comment of the launch; at T-5, the main engines are ignited.

The launcher is configured for automatic orbital insertion. For a manual ascent, press P key a second time immediately after the liftoff. The autopilot cannot be reactivated. After the MECO, you have full control of the spacecraft. In orbit, press J to release the payload.

“Quicklaunch”

In the Scenarios/Jarvis/Quicklaunch folder you have some launch scenarios without autopilots and other automatic launch procedures. You can use these scenarios for enjoy the challenge of a fully manual flight.

External graphic clients

For the D3D9 and D3D11 external graphic clients, some specific procedures can be needed. See this guide for further details: http://www.orbithangar.com/searchid.php?ID=5854

Technical description

Engines

F-1M The famed F-1 engine, developed for the Saturn V lunar rocket, still remains today the most powerful single-chamber rocket engine ever utilized in an operational spacecraft. Only the Russian, four- chamber RD-170 engine, utilized on the Saturn V counterpart, the Energia rocket, is more powerful than the F-1.

This engine burns liquid oxygen and rocket-grade kerosene. Five of them were utilized in the Saturn-V first stage.

The original Jarvis project employs two F-1 engines, without modifications; instead of them, the Orbiter version of the rocket uses a fictional, completely modernized version of this engine, designated F-1M, with light-weight metal alloys, staged combustion cycle, higher liftoff thrust and better specific impulse than the original F-1.

J-2S A vital part of the Apollo/Saturn architecture, the J-2 was utilized both in the second and third stage of the Saturn V. This powerful cryogenic engine has a high specific impulse and the capability of being ignited multiple times. The original Jarvis project uses a single J- 2 (probably the modernized, never flown version J-2S) in the second stage; the Orbiter version, designed for heavier payloads and superior flight efficiency, employs two J-2S engines for this stage. The J-2S burns liquid oxygen and liquid hydrogen, has a high efficiency and reliability and retains the capability of multiple burns.

RS-25E The Space Shuttle Main Engine was, for many years, the most powerful and one of the most efficient Lox/LH2 engines in the world, and it was the only specifically designed to be reusable. A cheaper, expendable version of the SSME was the logical choice for many projects of shuttle-derived heavy launchers, including various proposed versions of the original Jarvis. In the Orbiter version of the rocket, the expendable SSME (RS-25E) is employed in the first and second stage, only in the Jarvis-M arrangement.

RL-10B-2 One of the most successful rocket engines ever designed, the RL-10 is an another Apollo-era legacy, heavily modified throughout the years for even better performances. Six of them were utilized on the second stage of the early Saturn I rocket; one or two are fitted nowadays in all versions of the famous Centaur, the upper stage for the Atlas V launchers; one modified RL-10 is fitted in the upper stage of the modern Delta IV and Delta IV Heavy rockets. Optimized for vacuum operations, this cryogenic Lox/LH2 engine has high trust, perfect reliability, very high specific impulse and capability of multiple ignitions. The original, two stage Jarvis did not use this engine; the Orbiter version utilizes four RL-10B-2 engines.

Vinci Designed for the upper stage of the Ariane 5 ESC-B rocket, this modern and powerful cryogenic engine has an extendable nozzle. This allows the use of a large nozzle extension for maximum engine efficiency with minimum length. The HES stages in Jarvis-S and Jarvis- M rockets make use of this engine.

Jarvis rocket stages

First Stage Designed as JS-1, the Jarvis first stage is powered by two modernized F-1 Lox/Kerosene engines. This stage is the core of all versions of the Jarvis launch system, with the exception of the scaled down, single-engine stage utilized in the Jarvis-S and (as booster) in the Jarvis-M.

Specifications (twin engine version): Gross Mass: 949,414 kg Empty Mass: 59,414 kg. Length: 35.00 m. Diameter: 8.38 m. Motor: 2 x F-1M Thrust (average): 2 x 7,740.630 kN. Isp: 310 sec. Burn time: 175 sec. Propellants: Lox/Kerosene.

Specifications (single engine version): Gross Mass: 481,490 kg Empty Mass: 36,490 kg. Length: 30.00 m. Diameter: 6.49 m. Motor: 1 x F-1M Thrust (average): 1 x 7,740.630 kN. Isp: 310 sec. Burn time: 175 sec. Propellants: Lox/Kerosene.

Cryogenic first stage Designed as JS-1M, is used in the new Jarvis M “Block II” (that will replace the previous version) as replacement of the first and second stage of the rocket. This modification allows a superior efficiency and minor complexity, with the elimination of the second stage with the related staging phase.

Specifications: Gross Mass: 923,570 kg Empty Mass: 63,570 kg. Length: 54.00 m. Diameter: 8.38 m. Motor: 5 x RS-25E Thrust (vac): 5 x 2,278.000 kN. Thrust (average): 5 x 2,187.484 kN. Isp (vac): 453 sec. Burn time: 336 sec. Propellants: Lox/LH2.

Second Stage Designed as JS-2, the Jarvis second stage comes in two distinct tank capacity (130 and 205t) and engine arrangements: (two J-2S or two RS-25E).

Specifications (JS-2): Gross Mass: 146,362 kg Empty Mass: 16,362 kg. Length: 10.00 m. Diameter: 8.38 m. Motor: 2 x J-2S. Thrust (vac): 2 x 1,138.500 kN. Isp: 436 sec. Burn time: 244 sec. Propellants: Lox/LH2.

Specifications (JS-2M): Gross Mass: 224,916 kg Empty Mass: 19,916 kg Length: 10.00 m. Diameter: 8.38 m. Motor: 2 x RS-25E. Thrust (vac): 2 x 2,278.000 kN. Isp: 453 sec. Burn time: 200 sec. Propellants: Lox/LH2.

Third Stage Designed as JS-3, the Jarvis upper stage/space tug is an original creation by Forum Orbiter Italia team, powered by four RL-10B-2 cryogenic engines. It is utilized as second stage in the Light version of the rocket, and as third stage in the Enhanced and Heavy versions.

Specifications: Gross Mass: 39,097 kg Empty Mass: 5,393 kg. Length: 3.00 m. Diameter: 8.38 m. Motor: 4 x RL-10B-2. Thrust (vac): 4 x 110.000 kN. Isp: 462 sec. Burn time: 347 sec. Propellants: Lox/LH2.

GTO upper stage Designed as JS-4, this upper stage is used in the Jarvis C version and increases substantially the GTO performances of the rocket, making it competitive in the commercial market. An original creation by Forum Orbiter Italia, powered by a single RL-10B-2 cryogenic engine. Isn’t ideal for large LEO payloads, because of his long burn time and low thrust.

Specifications: Gross Mass: 15,990 kg Empty Mass: 2,140 kg. Length: 4.00 m. Diameter: 4.60 m. Motor: 1 x RL-10B-2. Thrust (vac): 1 x 110.000 kN. Isp: 462 sec. Burn time: 571 sec. Propellants: Lox/LH2.

Solid Rocket Boosters (SRB) The standard, four segment Shuttle SRBs, without modifications. Jarvis-H version utilizes two of them.

Specifications: Gross Mass: 589,670 kg Empty Mass: 86,183 kg. Length: 38.47 m. Diameter: 3.71 m. Motor: SRB Thrust (average): 11,520.000 kN Isp: 269 sec. Burn time: 124 sec. Propellants: Solid.

HES Stages HES stands for: “High Energy Stage”; is an upper stage specifically designed for the maximum Delta-V performance in the LEO and BEO launches. It has light-weight structure and engines with the best thrust-to-weight ratio and Isp currently available. Two sizes: HES-3 (three engines; 43t tanks) for the Jarvis S; HES-5 (five engines; 86t tanks) for the Jarvis M.

Specifications (HES-3): Gross Mass: 48,485 kg. Empty Mass: 5,270 kg. Length: 6.00 m. Diameter: 6.49 m. Motor: 3 x Vinci Thrust (vac): 3 x 180.000 kN. Isp: 467 sec. Burn time: 367 sec. Propellants: Lox/LH2.

Specifications (HES-5): Gross Mass: 94,450 kg. Empty Mass: 8,020 kg. Length: 8.00 m. Diameter: 8.38 m. Motor: 5 x Vinci Thrust (vac): 5 x 180.000 kN. Isp: 467 sec. Burn time: 440 sec. Propellants: Lox/LH2.

Interstage Located between the second and the third stage, only in the Jarvis M arrangement, this structure serves as shroud for the light but delicate structures of the HES-5 stage. It has four high-thrust solid ullage rockets.

Specifications: Gross Mass: 4,300 kg Length: 7.40 m. Diameter: 8.38 m. Motor: 4 x solid. Thrust (vac): 4 x 182.500 kN Burn time: 3.5 sec.

Table of comparison

Jarvis S Jarvis L Jarvis C Jarvis B Jarvis E Jarvis H Jarvis M Jarvis M (block II) Stage 0 (boosters) Designation - - - - - Shuttle SRB JS-1S JS-1S Gross mass - - - - - 2 x 589,670 kg 2 x 479,690 kg 2 x 479,690 kg Empty mass - - - - - 2 x 86,183 kg 2 x 34,690 kg 2 x 34,690 kg Engines - - - - - SRB 2 x F-1M 2 x F-1M rated at 100% rated at 105% Thrust - - - - - 2x11,520.000 kN 2 x 7,740.630 kN 2 x 8,127.660 kN Isp - - - - - 269 sec 310 sec 310 sec Burn time - - - - - 124 sec 140 sec * 167 sec Propellants - - - - - Solid Lox/Kerosene Lox/Kerosene Stage 1 Designation JS-1S JS-1 JS-1 JS-1 JS-1 JS-1 JS-1 JS-1M Gross mass 481,490 kg 949,414 kg 949,414 kg 949,414 kg 949,414 kg 949,414 kg 949,414 kg 923,570 kg Empty mass 36,490 kg 59,414 kg 59,414 kg 59,414 kg 59,414 kg 59,414 kg 59,414 kg 63,570 kg Engines 1 x F-1M 2 x F-1M 2 x F-1M 2 x F-1M 2 x F-1M 2 x F-1M 2 x F-1M 5 x RS-25E rated at 100% rated at 100% rated at 100% rated at 100% rated at 100% rated at 100% rated at 100% Thrust 1 x 7,740.630 kN 2 x 7,740.630 kN 2 x 7,740.630 kN 2 x 7,740.630 kN 2 x 7,740.630 kN 2 x 7,740.630 kN 2 x 7,740.630 kN 5 x 2,187.484 kN Isp 310 sec 310 sec 310 sec 310 sec 310 sec 310 sec 310 sec 453 sec Burn time 175 sec 175 sec 175 sec 175 sec 175 sec 175 sec 210 sec * 336 sec Propellants Lox/Kerosene Lox/Kerosene Lox/Kerosene Lox/Kerosene Lox/Kerosene Lox/Kerosene Lox/Kerosene Lox/LH2 Stage 2 Designation HES-3 JS-3 JS-3 JS-2 JS-2 JS-2 JS-2M HES-5 Gross mass 48,485 kg 39,097 kg 39,097 kg 146,362 kg 146,362 kg 146,362 kg 224,916 kg 94,450 kg Empty mass 5,270 kg 5,393 kg 5,393 kg 16,362 kg 16,362 kg 16,362 kg 19,916 kg 8,020 kg Engines 3 x Vinci 4 x RL-10B-2 4 x RL-10B-2 2 x J-2S 2 x J-2S 2 x J-2S 2 x RS-25 E 5 x Vinci Thrust 3 x 180.000 kN 4 x 110.000 kN 4 x 110.000 kN 2 x 1,138.500 kN 2 x 1,138.500 kN 2 x 1,138.500 kN 2 x 2,278.000 kN 5 x 180.000 kN kN Isp 467 sec 462 sec 462 sec 436 sec 436 sec 436 sec 453 sec 467 sec Burn time 367 sec 347 sec 347 sec 244 sec 244 sec 244 sec 200 sec 440 sec Propellants Lox/LH2 Lox/LH2 Lox/LH2 Lox/LH2 Lox/LH2 Lox/LH2 Lox/LH2 Lox/LH2 Stage 3 Designation - - JS-4 - JS-3 JS-3 HES-5 - Gross mass - - 15,990 kg - 39,097 kg 39,097 kg 94,450 kg - Empty mass - - 2,140 kg - 5,393 kg 5,393 kg 8,020 kg - Engines - - 1 x RL-10B-2 - 4 x RL-10B-2 4 x RL-10B-2 5 x Vinci - Thrust - - 1 x 110.000 kN - 4 x 110.000 kN 4 x 110.000 kN 5 x 180.000 kN - kN Isp - - 462 sec - 462 sec 462 sec 467 sec - Burn time - - 571 sec - 347 sec 347 sec 440 sec - Propellants - - Lox/LH2 - Lox/LH2 Lox/LH2 Lox/LH2 - Fairing Diameter 6.49 m 8.38 m 8.38 m 8.38 m 8.38 m 8.38 m 8.38 / 10. 06 m 8.38 / 10. 06 m (external) Total Mass 553,175 kg 1,023,411 kg 1,044,900 kg 1,147,176 kg 1,197,273 kg 2,402,990 kg 2,363,240 kg 2,117,580 kg 554,875 kg 2,366,900 kg 2,121,240 kg Thrust 8,280.630 kN 15,921.260 kN 16,031.260 kN 17,758.260 kN 18,198.260 kN 41,238.260 kN 36,418.520 kN 28,092.740 kN Payload capacity (from KSC) LEO 20,700 kg 27,900 kg 34,100 kg 44,400 kg 55,400 kg 80,700 kg 122,700 kg 128,800 kg GTO 7,200 kg 9,100 kg 13,400 kg 12,700 kg 22,700 kg 33,100 kg 54,800 kg 55,200 kg GEO 3,300 kg 4,200 kg 8,000 kg 3,400 kg 13,500 kg 20,000 kg 34,900 kg 34,400 kg LTO 6,000 kg 7,600 kg 11,700 kg 9,800 kg 19,900 kg 29,000 kg 48,600 kg 48,700 kg LLO 3,900 kg 5,000 kg 8,900 kg 4,900 kg 15,000 kg 22,200 kg 38,200 kg 37,800 kg

* Propellant cross-feed from boosters to core stage.

Bibliography

Encyclopedia Astronautica http://www.astronautix.com/lvs/jarvis.htm http://www.astronautix.com/astros/jarvis.htm http://www.astronautix.com/stages/centaur.htm

Space Launch Report – The road to Ares V http://www.spacelaunchreport.com/sdv.html