A review of aeroassisted orbit transfer

Walberg, Gerald D.

doi:10.2514/6.1982-1378

Cited by 50 publications

(11 citation statements)

References 9 publications

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“…Location of the booster vehicle with respect to Earth, 3) Obtain new values of h\ and h\ using the following expressions,…”

Section: Position and Velocity Of The Vehiclementioning

confidence: 99%

“…(1), using Eqs. (3)(4)(5)(6) and subject to constraint (7) gives the velocity and position of the vehicle in inertial space. The position and velocity in other reference systems can be obtained using the relations given in Appendix A.…”

Section: Simulation Of Vehicle Dynamicsmentioning

confidence: 99%

“…1 ' 3 Such a vehicle delivers its payload to a space station in low Earth orbit (LEO) or to an orbit transfer vehicle at the space station for final delivery to the geosynchronous orbit.…”

mentioning

confidence: 99%

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Adaptive guidance for an aero-assisted boost vehicle

Pamadi

Taylor

Price

1990

Journal of Guidance, Control, and Dynamics

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An adaptive guidance system incorporating a dynamic pressure constraint is developed for a single stage to low Earth orbit, with thrust gimbal angle as the control variable. The ascent profile is represented in the form of a two-segment cubic spline function whose parameters are optimized for maximum payload. The flight to low Earth orbit is divided into initial and terminal phases. In the initial phase, a fully adaptive scheme is used wherein a new ascent profile is generated for the remainder of flight whenever the simulated vehicle deviates beyond a prescribed limit. In the terminal phase, a semiadaptive scheme with a linear feedback control is used to keep the vehicle close to the nominal path. This two-phase adaptive guidance algorithm is applied to a generic aeroassisted booster.endpoint altitude for initial guidance phase hi = intermediate altitude where the two spline segments are connected des = desired altitude as given by spline ascent profile, Eq. (8) h a = current altitude of the booster vehicle hf = final altitude Ki,K 2 = feedback gains L -aerodynamic lift LQ = longitude M = Mach number m = mass of the boost vehicle ra 0 = initial mass (t = 0) m p -final mass at h = h f q -dynamic pressure = Vip Vl R = position vector T = thrust V = current inertial velocity V 0 = inertial velocity on the surface of Earth Vf, Vi = inertial velocity at h = h f and h\ 9 respectively ROI -radius vector from Earth's center to origin of Xny n z n system xyz = rectangular coordinate system Bandu N. 587 0! 0 7 6 e X = angle of attack = coefficient in the exponential atmospheric density model = flight-path angle = semivertex angle of the booster = percent error margin (A/*//*) = geographical latitude = thrust gimbal angle iin = maximum and minimum limits, respectively, of thrust gimbal angle = angular velocity of the Earth about its own axis = differentiation with respect to inertial velocity = differentiation with respect to time Subscripts b e i n max = body = Earth-related = inertial = navigational = maximum value

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“…Location of the booster vehicle with respect to Earth, 3) Obtain new values of h\ and h\ using the following expressions,…”

Section: Position and Velocity Of The Vehiclementioning

confidence: 99%

Section: Simulation Of Vehicle Dynamicsmentioning

confidence: 99%

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Adaptive guidance for an aero-assisted boost vehicle

Pamadi

Taylor

Price

1990

Journal of Guidance, Control, and Dynamics

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“…based on the ballistic coefficient influence on peak heat flux given in Eq. (1) and the correlation function (Eq. ( 2 ) ) for a 1-m-radius reference sphere.…”

Section: Materials Selectionmentioning

confidence: 99%

An AOTV aeroheating and thermal protection study

Scott

Ried

Maraia

et al. 1984

19th Thermophysics Conference

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rake angleThe aerothermodynamics and thermal protection of aerobraking orbital transfer vehicles are studied with a view toward design methodology and technology requirements. A particular class of geometries is investigated: the ellipsoidally blunted raked-off elliptic cone. Discussed are the influence of various geometrical parameters on the trajectory and the heat flux as well as heating prediction methods ranging from an engineering correlation formula to computational solutions of the Navier-Stokes equations. Finite-rate catalytic thermal protection materials and gas radiation are considered. Estimates of the specific mass of possible thermal protection systems indicate that support structure is a large contributor to the aerobrake mass as compared with the thermal protection insulation itself. Sizing curves are included which enable the designer to estimate the size aerobrake required from heating considerations for different mass vehicles having aerobrakes of several specific masses.

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“…NASA has investigated the use of a bentaxis geometry for aerocapture missions as outlined by Walberg in [1].…”

Section: Introductionmentioning

confidence: 99%

Attitude Controller Design for Variable-Bend-Tail Vehicle

Guo

Zhou

2009

2009 International Conference on Intelligent Human-Machine Systems and Cybernetics

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According to the problem of attitude control for variable-bend-tail vehicle, the mathematics models are established and the robust attitude control system is proposed based on variable structure control theory. The movement model of the bend tail section is derived from considering the coupling mutual action between tail and front of vehicle, and the nonlinear mathematics dynamic model of variable-bendtail vehicle is built by introducing the semi-body frame and the semi-velocity frame adopting the muti-rigid body dynamics model method. The acceleration control system for variablebend-tail vehicle is designed to improve the preciseness and robustness of the whole attitude control system by applying the tail deflection angular rate applying variable structure control theory. Finally an illustrative example is given to show preliminarily that the model is valid and that the attitude control scheme can meet the need of performance of system and have the capabilities of the celerity and robustness.

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A review of aeroassisted orbit transfer

Cited by 50 publications

References 9 publications

Adaptive guidance for an aero-assisted boost vehicle

Adaptive guidance for an aero-assisted boost vehicle

An AOTV aeroheating and thermal protection study

Attitude Controller Design for Variable-Bend-Tail Vehicle

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