Starcraft Boosters, Inc. The StarBooster 200 System - A cargo aircraft for space

Aldrin, Buzz; Davis, H. P.

doi:10.2514/6.1999-2619

Cited by 3 publications

(6 citation statements)

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“…------------- 1 Senior Aerospace Engineer, Associate Fellow AIAA. 2 Senior Aerospace Engineer, Senior Member AIAA. ‡ Aerospace Engineer, Member AIAA.…”

Section: Nomenclaturementioning

confidence: 99%

“…This vehicle concept is a three-stage system with a reusable first-stage booster and expendable upper stages. The design is based on the use of low cost pressure-fed LOX/RP engines developed by Microcosm 1 and the slide-in propulsion module concept of Starcraft Boosters Inc. 2 An advantage of this concept is that the entire propulsion system can be removed and serviced off-line and kept ready for a new launch to reduce the turnaround time. This SLV system is designed to place about 330 lbs in a polar orbit at 150 nm.…”

Section: Introductionmentioning

confidence: 99%

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Aerodynamic Characteristics and Glide-Back Performance of Langley Glide-Back Booster

Pamadi

Covell

Tartabini

et al. 2004

22nd Applied Aerodynamics Conference and Exhibit

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NASA-Langley Research Center is conducting system level studies on an-house concept of a small launch vehicle to address NASA's needs for rapid deployment of small payloads to Low Earth Orbit. The vehicle concept is a three-stage system with a reusable first stage and expendable upper stages. The reusable first stage booster, which glides back to launch site after staging around Mach 3 is named the Langley Glide-Back Booster (LGBB). This paper discusses the aerodynamic characteristics of the LGBB from subsonic to supersonic speeds, development of the aerodynamic database and application of this database to evaluate the glide back performance of the LGBB. The aerodynamic database was assembled using a combination of wind tunnel test data and engineering level analysis. The glide back performance of the LGBB was evaluated using a trajectory optimization code and subject to constraints on angle of attack, dynamic pressure and normal acceleration.

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“…------------- 1 Senior Aerospace Engineer, Associate Fellow AIAA. 2 Senior Aerospace Engineer, Senior Member AIAA. ‡ Aerospace Engineer, Member AIAA.…”

Section: Nomenclaturementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Aerodynamic Characteristics and Glide-Back Performance of Langley Glide-Back Booster

Pamadi

Covell

Tartabini

et al. 2004

22nd Applied Aerodynamics Conference and Exhibit

View full text Add to dashboard Cite

show abstract

“…The first stage vehicle is a pressure-fed LOX/kerosene, reusable, wing-body booster similar to the Starcraft booster design. 2 A schematic diagram of the small launch vehicle is shown in Fig. 2 and a three-view drawing of the booster is presented in Fig.…”

Section: Vehicle Descriptionmentioning

confidence: 99%

“…The estimated mass properties at staging, that is, when the booster propellants are depleted and the upper stages are fully loaded with propellants are presented in Table 2. 344.0 16,000.0 I yy , slugs-ft 2 167,000.0 304,000.0 I zz , slugs-ft 2 167,000.0 314,000.0…”

Section: Vehicle Descriptionmentioning

confidence: 99%

“…This vehicle concept is a three-stage system with a reusable first stage and expendable upper stages. The design is based on the use of low cost pressure-fed LOX/RP engines developed by Microcosm 1 and the slide-in propulsion module concept of Starcraft Boosters Inc. 2 An advantage of this concept is that the entire propulsion system can be removed and serviced off-line and kept ready for a new launch to reduce the turn-around time. This SLV system is designed to place about 330 lbs in a polar orbit at 150 nm.…”

Section: Introductionmentioning

confidence: 99%

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Ascent, Stage Separation and Glideback Performance of a Partially Reusable Small Launch Vehicle

Pamadi

Tartabini

Starr

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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An integrated analysis is presented for ascent, stage separation and glide back performance of a small, partially reusable launch vehicle sized for a payload of about 330 lbs to a 150 nm polar orbit. The altitude margin was used a performance metric for the glideback performance. Aerodynamic databases for each of these three phases of flight were developed using a combination of engineering level code, free stream and proximity wind tunnel test data and Euler CFD results. The ascent and glideback trajectories were generated using POST and the stage separation simulation was done using the in-house software Sep-Sim as a front end to the commercially available multi-body dynamic simulation code ADAMS ®. The payload to the designated polar orbit was optimized subject to the constraints imposed by stage separation and adequate performance reserve for the glideback booster in addition to the usual ascent trajectory constraints. Nomenclature A N normal acceleration, g's α angle of attack, deg ∆α relative difference in angle of attack, deg C A , C N axial and normal force coefficient C A,b , C N,b base (free flight) axial and normal force coefficient C A,int , C N,int interference axial and normal force coefficient ∆C A,δe , ∆C N,δe axial and normal force coefficient increments due to elevon deflection ∆C A,δc , ∆C N,δc axial and normal force coefficient increments due to canard deflection C L , C D lift and drag coefficients C m pitching moment coefficient Cmd command δ c canard deflection, deg δ e elevon deflection, deg F N normal Force, lb f γ flight path angle, deg h altitude, ft k 1 stage separation interpolation constant k α , k q , k δe angle of attack, pitch rate and elevon deflection feedback gains L ref vehicle reference length, ft M Mach number q dynamic pressure, psf σ bank angle, deg V velocity, ft/s ∆x, ∆z relative axial and normal distances during separation, ft

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Separation Flight Testing of a Subsonic Glideback Booster Demonstrator

Tsukamoto

DeTurris

Foster

2003

41st Aerospace Sciences Meeting and Exhibit

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Starcraft Boosters, Inc. The StarBooster 200 System - A cargo aircraft for space

Cited by 3 publications

References 0 publications

Aerodynamic Characteristics and Glide-Back Performance of Langley Glide-Back Booster

Aerodynamic Characteristics and Glide-Back Performance of Langley Glide-Back Booster

Ascent, Stage Separation and Glideback Performance of a Partially Reusable Small Launch Vehicle

Separation Flight Testing of a Subsonic Glideback Booster Demonstrator

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