ようこそ. S P A C E TOURISM II Lecture Series given by Dr.-Ing. Robert Alexander Goehlich 2003 by Robert A. Goehlich スペースツーリズム II レクチャーへ

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1 Fall Semester 2004 Part 9 No. 1 TM S P A C E TOURISM II Lecture Series given by Dr.-Ing. Robert Alexander Goehlich 2003 by Robert A. Goehlich ようこそ スペースツーリズム II レクチャーへ - Part 9: Suborbital Rocket Plane - General Contact Dr.-Ing. Robert Alexander GOEHLICH Mobile: +81-(0) Fax: +81-(0) mail@robert-goehlich.de Internet: Ms. Akiko FUJIMOTO (Teaching Assistant) Mobile: +81-(0) af @yahoo.co.jp Mr. Kenji HASEGAWA (Webmaster) Mobile: n.a. malayzaru@hotmail.com No. 2 Keio University Department of System Design Engineering Ohkami Laboratory (Space System Engineering) Office / Hiyoshi Kohoku-ku Yokohama JAPAN

2 Content No. 3 General Guest Speaker: Prof. Yoshiaki Ohkami, Keio University Note: The following slides were provided courtesy of Prof. Y. Ohkami and Mr. M. Ogawa Requests from Audience for Lectures Concept Design of Suborbital Rocket Plane for Space Tourism Keio University Ohkami Laboratory Yoshiaki Ohkami Masayoshi Ogawa

3 Space Ship Ship One One A New Trend in in Manned Space Flight The first manned space flight by a private company was successful to win X-prize X in October, 2004 NASA started to investigate the Orbital Space Plane to replace Space Shuttle Orbital Space Plane A New Trend in in Manned Space Flight

4 Definition Orbital vs. vs. Suborbital Orbit 7900 m/s Suborbital m/s 250 km 450 km EARTH - 50 km km - Aerosphere - Mesosphere - Outer Space Mission To Design the SoRP satisfying the following constraint Suborbital Rocket Plane Max Altitude Over 120 km Passengers Safety Price Comfort Over 3 pax and 1 crew 1 Fault/ Flight Under 0.25 M$/pax Under 3 G (Acceleration) To Achieve the Mission Requirements Price Safety Comfort Design Philosophy Simplicity Reusability Reliable Components

5 Design Sequence Selection Phase From so many Concepts, 4 concept will be picked in this Phase Follow Items will be taken account. Engine Type Take-off and Landing Type Stage Number Investigation Phase So Many Concepts Four Concepts About 4 Concepts, Vehicle Concept Verification will be done By Shape and Trajectory Simultaneous Optimization Method. And then Best Concept will be decided. Concept Design Phase One Concept About the Best Concept, More detailed Design will be done By Conventional Design Method using CAD Selection Phase

6 Concepts SoRP Concept will be generated by selecting elements of follows. Stage Number 1 Stage, 2 Stage, 3 Stage, 4 Stage Take-off Type Vertical or Horizontal SoRP Concept Landing Type Vertical or Horizontal Propulsion System Rocket, ABE * Reusability Fully or Partially * ABE: Air Breathing Engine Stage : The System that contributes Acceleration or Ascent to achieve Space Rocket (RKT) Rocket Propulsion System for Ascent and Acceleration Solid Rocket Booster (SRB) Rocket Propulsion System for only Lift-off Cut off from the Orbiter just after Lift-off Flyback Booster (FBB) Returnable Rocket Propulsion System Not using Aerodynamic Force in Ascent Airplane (PLN) Airplane System for Ascent and Acceleration Using Aerodynamic Force in Ascent Balloon (BLN) Balloon System just for Ascent or Descent Sled (SLD) Ground Take-off Support System ( e.g: MagRev,, Train, Ship, Ekranoplan ) Gauchito Space Shuttle Space Cub Space Ship One Wild Fire Magnet Revitalization Canadian Arrow Thunderbird Shuttle Flyback Booster AS&T Suborbital Spaceplane NEGEV-5 Hyperion SSTO Delta Clliper SLI Buran-T Eclipse Astroliner Orizont Keio SoRP

7 System Configuration System Stage 1 Stage 2 Stage 3 Stage 4 Take-off Landing Reusability Stage PLN SLD RKT FBB SRB BLN PLN RKT FBB PLN RKT FBB PLN RKT FBB Concept H H F S 53 (17) 50 (12) 6 H H F M Too Complex 2 H H P M 2 H V F M 1 Not Safe 1 V H F S 14 (2) V H F M (1) 14 (1) V H P M Too Complex V V F S 51 (15) V V F M 1 Not Safe 2 (2) V V P M 4 (2) H: Horizontal V: Vertical F: Fully Reusable P: Partially Reusable S: Single Stage M: Multi Stage Aspect Concept A Vertical Take-off / Horizontal Landing Usage of Conventional Runway for Landing Single System Flight Profile Vertical Ascent Phase Ascending until Lift increases over Own Weight At 90 deg Path Angle with 0 deg Attack Angle From 0 m/s Initial Velocity Powered Flight Phase Coasting Phase Ascending by Rocket Power From the States of the End of Vertical Ascent Phase Optimized by DGV Method Ascending without Rocket Power From the Altitude of km every 5 km With 0 deg Attack Angle

8 Aspect Concept B Horizontal Take-off / Horizontal Landing Usage of Conventional Runway for Take-off & Landing Single System Flight Profile Running Phase Running on the Conventional Runway With own Running Gear Until the Lift increases over own Weight Powered Flight Phase Coasting Phase Ascending by Rocket Power From the States of the End of Running Phase Optimized by DGV Method Ascending without Rocket Power From the Altitude of km every 5 km With 0 deg Attack Angle Aspect Concept C Horizontal Take-off from the Extant Ship Hishoh Horizontal Landing on the Conventional Runway Two Stage System Flight Profile Cruising Phase Cruising on the Sea with the Ship for Acceleration Until 55.8 m/s (105 knot) that s s double of Cruise Speed Unoptimized in the Optimization Sequence Powered Flight Phase Coasting Phase Ascending by Rocket Power at the Velocity of 55.8 m/s and the Attack Angle of 20 deg Optimized by DGV Method Ascending without Rocket Power From the Altitude of km every 5 km With 0 deg Attack Angle

9 Techno Super Liner --HISYOH -- Velocity knot knot (27.91 m/s) m/s) Sale Sale Route Cruise Time Payload 23,000 yen yen 100,000 pax/year Tokyo Bay Bay Ogasawa Islands hour hour (One (One Way) Way) 1,000 kg kg Size (L Size (L W H) (L W H) H) m m m Reference: kun/tsl2.html Aspect Concept D Horizontal Take-off from Ekranoplan Horizontal Landing on the Conventional Runway Two Stage System Flight Profile Cruising Phase Cruising on the Sea with Ekranoplan for Acceleration Until 170 m/s that s s half of Sonic Velocity Unoptimized in the Optimization Sequence Powered Flight Phase Coasting Phase Ascending by Rocket Power at the Velocity of 170 m/s and the Attack Angle of 20 deg Optimized by DGV Method Ascending without Rocket Power From the Altitude of km every 5 km With 0 deg Attack Angle

10 Concept A Concept B VTHL SSTO HTHL SSTO Investigation Phase Concept C Concept D HTHL Take-off Assist 1 HTHL Take-off Assist 2 Take-off Powered Flight Coasting On Orbit Concept A Concept B By RP-1/LOX Rocket Engine From km Dynamic Pressure < 40 kpa Unpowered Attack Angle < 25 deg With 0 deg Attack Angle Acceleration < 3 G Attitude Angle < 90 deg Over 120 km Concept C Concept D

11 Design Method Optimized Variables Vehicle Configuration Trajectory Profile Aerodynamic Analysis (DATCOM, CBM) Weight Analysis (HASA) Trajectory Analysis (DGV Method) SQP Routine CBM: : Component Buildup Method HASA: : Hypersonic Aerospace Sizing Analysis DGV: : Discretized Guidance Variable Method SQP: : Sequential Quadratic Programming Method Cost Assessment (SUBORB-TRANSCOST) Objective Function Ticket Price Minimum Vehicle Parameter Orbiter Rocket Engine - Fuel: Kerosine - Oxidizer: LOX - Thrust (T/W) Wing - Aspect Rate (AR) - Taper Rate (TR) - Delta Planform - x/c : 0.5 Body - t/c : 0.03 Diameter (Db) Cabin - 1 Crew - N Pax Wing Span (b) Stabilizer Tank - Propellant (Wp/W)

12 Result Take-off Mass Concept A Concept B Concept C Concept D Take-off Mass [M g] Mg Passenger Result Ticket Price (SUBORB-TRANSCOST (SUBORB-TRANSCOST Model) Model) 3.4 M$ 4.5 M$ Concept A Concept B Concept C Concept D Ticket Price [M $] M$ 0.75 M$ 0.5 M$ M$ Number of Passenger

13 Result Economical Feasibility Number of Pax per Launch 49 Pax Pax / Year 19 Pax Infeasible 1000 Feasible 9 Pax 7 Pax 5 Pax Concept A Concept B Concept C Concept D Bekey Model Bekey Model Limit of Interest Ticket Price [M $] 1.00 ORBITER Concept C 9 Pax Optimum Concept --Shape Cabin Diameter: 1.97 m Take-off Mass: 17.0 Mg Payload Mass: 1.0 Mg Structure Mass: 6.9 Mg Propellant Mass: 9.1 Mg Avionics Area Length: 12.9 m LOX Tank Wing Area: 56.2 m 2 Aspect Rate: 1.97 Taper Rate: 0.30 Thrust: 25.7 Mgf Cockpit Area Cabin Area ECLSS Area Tank Area Wing Span: 10.5 m Engine Area

14 Optimum Concept --Mass Take-off Mass: 17.0 Mg Payload Mass: 1.0 Mg Structure Mass: 6.9 Mg Propellant Mass: 9.1 Mg Structure: 41.0 % Avionics 2.4% Electronics 1.5% Hydraurics 0.5% Engine 2.1% Tank 0.2% Thrust Strct 0.4% TPS 2.7% Landing Gear 1.4% Vertical Tail 2.2% Wing 5.1% Fuselage 2.8% Equipment 19.6% Payload: 5.8 % Payload 5.8% LOX 38.9% RP1 14.3% Propellant: 53.2 % Detailed Information Gross kg Payload 1000 kg Propellant 9114 kg RP kg LOX 6664 kg Structure 6930 kg Fuselage 487 kg Wing 878 kg Vertical Tail 372 kg Landing Gear 244 kg TPS 469 kg Thrust Strct 64 kg Tank 34 kg Engine 366 kg Hydraurics 89 kg Electronics 262 kg Avionics 405 kg Equipment 3361 kg Optimum Concept --Trajectory Altitude [km] Distance [km]

15 Trajectory Selected Concept - Trajectory 90 Powered Flight Phase 80 Coasting Phase Path Angle Path Angle Ref Attack Angle Angle [deg] Path Angle & Attack Angle Time [sec] Acceleration Accerelation [G] Powered Flight Phase Max Acceleration: 2.2 G Acceleration (Lateral) Acclreration (Longitudinal) Coasting Phase Time [sec] Indirect Operating Cost: 11.7 % Abolition 0.5% Improvement 1.2% Financing 0.9% Development Amortization 5.2% Maintenance 11.8% Transportation 2.5% Administration 11.8% Fix Direct Operating Cost: 7.8 % Optimum Concept --Cost Profit: 10.0 % Profit 1.0% Pre-Launch 12.6% Vehicle Amortization 27.5% Variable Direct Operating Cost: 79.5 % Launch Operating 23.4% Launch Site 1.3% Vehicle Insurance 0.8% Detailed Information Development M$ Winged Vehicle M$ Rocket Engine M$ Production M$ Winged Vehicle M$ Rocket Engine M$ Operation M$/Launch Variable Direct Operating Cos M$/Launch Pre-Launch M$/Launch Launch Operating M$/Launch Propellant M$/Launch Launch Site M$/Launch Vehicle Insurance M$/Launch Vehicle Amortization M$/Launch Transportation M$/Launch Maintenance M$/Launch Fix Direct Operating Cost M$/Launch Development Amortization M$/Launch Financing M$/Launch Improvement M$/Launch Abolition M$/Launch Indirect Operating Cost M$/Launch Administration M$/Launch Profit M$/Launch Propellant 0.2%

16 Concept Design Preliminary Design Detail Design System HTHL Suborbital Space Transportation System SoRP: Suborbital Rocket Plane LOX Tank LNG Tank Avionics RCS (Fore) Cabin (6 Passengers) ECLSS Area Sea Rudder Main Gear TLAV: Take-off Landing Assist Vehicle Operation Engine RCS (Aft) Elevon Orbiter Proof of Concept Experiment Winged Vehicle Flight Tests in Overseas Areas ALFLEX in Australia in July 1996 SST in Australia in July 2002 HST in Christmas Ils. in Nov HST in Sweden in 2003

17 Test Range like Mojave Desert Exists in Japan? No, even Hokkaido or Okinawa is not sparse enough. Taiki Town Shimoji Island Solution Use of open sea! Proof-Of Of-Concept Approach Keio University Ohkami Laboratory Keio University Ohkami l

18 SoRP Concept 14.9 m Majpor Specifications 1.8 m 3~5 m 20.0 m 2.5 m 3.0 m 2.5 m 10.0 m High Speed Boat Length: 20.0 m Wing Span: 10.0 m Height: 3~5 m Power: HP Max Speed: 200~250 km/h SoRP Take-off Mass: Mg Propellant Mass: 7.70 Mg Length: 14.9 m Wing Span: 8.27 m Body Diameter: 1.8 m Wing Area: 39.8 m 2 Thrust (vac): 2 97 kn Isp (vac): 345 sec

19 Operations and Tour Plan 3000 m OKINAWA Shimoji Shima Island Longitude: 24, 49, 36 Latitude : 125, 08, 41 Itoman Harbor Longitude: 26, 7, 55 Latitude : 127, 39, 54 Return 120 km Cruising Phase Powered Flight Phase Coasting Phase Descent Phase 290 km Naha Airport Operations Scenario 1 st 2 nd 3 rd st Day/ Flight to Naha Airport in Okinawa nd Day/ Preparation for flight with health check-up rd Day/ Boarding to mother ship to leave the harbor Boarding to SoRP to move to the Site Confirmation of Take-Off readiness Start of engines and full acceleration Take-off and climbing to Space Reach Space with altitude of 120 km Return to the Earth and landing Briefing and receipt of space tour certification Astronaut Wing awarded th day/ Return flight from Naha Airport 4 th A few Days for maintenance, repair, refueling etc.

20 No. 39 Dr.-Ing. Robert Alexander GOEHLICH Keio University Department of System Design Engineering Space System Engineering (Ohkami Laboratory) Hiyoshi, Kohoku-ku Yokohama , JAPAN Mobile: +81-(0) Fax.: +81-(0) Internet: