Aerospace Plane

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Kenneth D. Mease - One of the best experts on this subject based on the ideXlab platform.

  • Near-Optimal Control of Altitude and Path Angle During Aerospace Plane Ascent
    Journal of Guidance Control and Dynamics, 1997
    Co-Authors: Jean-paul Kremer, Kenneth D. Mease
    Abstract:

    Altitude and e ight-path-angle control during the posttransonic airbreathing segment of Aerospace Plane ascent is addressed, with objectives to minimize fuel usage and respect the vehicle e ight envelope. Based on a time-scale separation between energy/mass and altitude/path-angle dynamics, the altitude/path-angle control problem is viewedina singularperturbation framework asan initialboundary-layerproblem. Afeedbacklawapproximating theminimum-fuelinitialboundary-layercontrolisobtainedbysolvinganeighboring-optimalproblem.Tofacilitate this derivation, the state constraint that is active on the slow solution is modeled in the boundary layer using an appropriatepenaltyfunction.Theneighboring-optimalfeedbacklawperformswellaslongastemporaryconstraint violations are acceptable in the boundary layer. An alternate linear feedback law is derived with gains calculated to reduce constraint violations, but this law leads to increased fuel usage. Numerical results are presented for a lifting-body cone guration of an Aerospace Plane and a Mach 8 e ight condition. The results show that fuel usage and control activity are reduced when the peak dynamic pressure is allowed to increase. Differences in fuel usage are small for the vehicle model employed.

  • Aerospace Plane ascent guidance considering aeropropulsive interactions
    Guidance Navigation and Control Conference, 1995
    Co-Authors: Jean-paul Kremer, Kenneth D. Mease
    Abstract:

    The ascent guidance is considered for an Aerospace Plane vehicle with aeropropulsive interactions. The attention is on the control of the fast translational dynamics, altitude and flight-path angle. The objective is to continue the developments towards a fuel-efficient control of the fast dynamics during the ascent. The twopoint boundary value problem for the minimum-fuel ascent trajectory is decomposed into a slow part, and left and right boundary layer corrections. Hard or soft models are used for the maximum dynamic pressure constraint. Optimal left boundary layer solutions are calculated numerically at Mach 8, for the hard constraint and for different soft constraint shapes. The analysis of the solutions shows the existence of a tradeoff between peak dynamic pressure, fuel consumption, and control activity. Feedback solutions are obtained for the neighboring-optimal left boundary layer problem, and offer satisfactory performance for mild constraint modeling. For sharp constraint modeling, a different, sub-optimal linear feedback is proposed.

  • Geometric synthesis of Aerospace Plane ascent guidance logic
    Automatica, 1994
    Co-Authors: Kenneth D. Mease, Mark A. Van Buren
    Abstract:

    Abstract A single-stage vehicle using airbreathing propulsion holds promise for a more economical delivery of payloads to orbit. The utility of the vehicle is contingent on having a guidance capability for flying a near minimum-fuel ascent trajectory. In this paper, feedback guidance logic is developed for the hypersonic ascent phase. The two-time-scale behavior present in the vehicle translation dynamics allows the corresponding state space to be decomposed approximately into an invariant slow manifold and an invariant foliation of fast manifolds. Robust near-optimal guidance is synthesized as a composite of the minimum-fuel control on the slow manifold—as determined by the dynamic pressure and heat rate constraints—and a fast control for robust tracking of the slow manifold in the presence of atmospheric disturbances and modeling errors. The tracking problem is solved as a family of regulation problems on the fast foliation, using feedback linearization and a bandwidth-limited variable structure controller. Simulations indicate the effectiveness of the guidance logic.

  • ASCENT GUIDANCE FOR AN Aerospace Plane
    Automatic Control in Aerospace 1992, 1993
    Co-Authors: Kenneth D. Mease
    Abstract:

    A single-stage vehicle using airbreathing propulsion holds promise for a more economical delivery of payloads to orbit. The utility of the vehicle is contingent on having a guidance capability for flying a near minimum-fuel ascent trajectory. The challenges in ascent guidance are identified via an analysis of the guidance problem relative to that for the U.S. Space Shuttle. Feedback guidance logic for the hypersonic phase of a near-minimum-fuel ascent trajectory is described. The two-time- scale nature of the vehicle translational dynamics allows the translational state space to be decomposed approximately into an invariant slow manifold and an invariant foliation of fast manifolds. Robust near-optimal guidance is synthesized as a composite of the minimum-fuel control on the slow manifold—as determined by the dynamic pressure and heat rate constraints—and a fast control for robust tracking of the slow manifold in the presence of atmospheric disturbances and modeling errors. The tracking control is designed using feedback linearization and the bandwidth-limited variable structure control method. Simulations indicate the effectiveness of the guidance logic.

  • Aerospace Plane guidance using time-scale decomposition and feedback linearization
    Journal of Guidance Control and Dynamics, 1992
    Co-Authors: Mark A. Van Buren, Kenneth D. Mease
    Abstract:

    Single-stage vehicles using air-breathing propulsion hold promise for more economical delivery of payloads to orbit. Feedback guidance logic is developed for steering and accelerating such a vehicle along the superand hypersonic segments of a near-minimum-fuel ascent trajectory. Accurate solutions of the minimum-fuel ascent problem show the effects of dynamic pressure, acceleration, and heating constraints and establish a basis for the development and assessment of guidance logic. The two-time-scale behavior in the optimal solution allows the state space to be decomposed into a control-dependent slow manifold and a family of fast manifolds. Near-optimal guidance is obtained by constructing a composite control law from the control for flying the minimum-fuel reduced-order trajectory on the slow manifold and a control for tracking the optimal reduced-order trajectory. The tracking problem is solved as a family of regulation problems corresponding to the family of fast manifolds, using the feedback linearization methodology from nonlinear geometric control theory. A complete characterization is given of all state transformation-static feedback pairs that lead to exact linearization of the fast dynamics. Simulation shows that the composite control law produces a near-minimum-fuel ascent.

A. R. Urbach - One of the best experts on this subject based on the ideXlab platform.

  • Slush Hydrogen Quantity Gaging and Mixing for the National Aerospace Plane
    Advances in Cryogenic Engineering, 1992
    Co-Authors: R. S. Rudland, I. M. Kroenke, A. R. Urbach
    Abstract:

    The National Aerospace Plane (NASP) design team has selected slush hydrogen as the fuel needed to power the high-speed ramjet/scramjet engines. Use of slush hydrogen rather than normal hydrogen provides significant improvements in density and cooling capacity for the aircraft. The loading of slush hydrogen in the NASP tank must be determined accurately to allow the vehicle size and weight to be kept to a minimum. A unique sensor developed at Ball to measure the slush density will be used in each region of the hydrogen tank to accurately determine the total mass of fuel loaded in the vehicle.

Mark A. Van Buren - One of the best experts on this subject based on the ideXlab platform.

  • Geometric synthesis of Aerospace Plane ascent guidance logic
    Automatica, 1994
    Co-Authors: Kenneth D. Mease, Mark A. Van Buren
    Abstract:

    Abstract A single-stage vehicle using airbreathing propulsion holds promise for a more economical delivery of payloads to orbit. The utility of the vehicle is contingent on having a guidance capability for flying a near minimum-fuel ascent trajectory. In this paper, feedback guidance logic is developed for the hypersonic ascent phase. The two-time-scale behavior present in the vehicle translation dynamics allows the corresponding state space to be decomposed approximately into an invariant slow manifold and an invariant foliation of fast manifolds. Robust near-optimal guidance is synthesized as a composite of the minimum-fuel control on the slow manifold—as determined by the dynamic pressure and heat rate constraints—and a fast control for robust tracking of the slow manifold in the presence of atmospheric disturbances and modeling errors. The tracking problem is solved as a family of regulation problems on the fast foliation, using feedback linearization and a bandwidth-limited variable structure controller. Simulations indicate the effectiveness of the guidance logic.

  • Aerospace Plane guidance using time-scale decomposition and feedback linearization
    Journal of Guidance Control and Dynamics, 1992
    Co-Authors: Mark A. Van Buren, Kenneth D. Mease
    Abstract:

    Single-stage vehicles using air-breathing propulsion hold promise for more economical delivery of payloads to orbit. Feedback guidance logic is developed for steering and accelerating such a vehicle along the superand hypersonic segments of a near-minimum-fuel ascent trajectory. Accurate solutions of the minimum-fuel ascent problem show the effects of dynamic pressure, acceleration, and heating constraints and establish a basis for the development and assessment of guidance logic. The two-time-scale behavior in the optimal solution allows the state space to be decomposed into a control-dependent slow manifold and a family of fast manifolds. Near-optimal guidance is obtained by constructing a composite control law from the control for flying the minimum-fuel reduced-order trajectory on the slow manifold and a control for tracking the optimal reduced-order trajectory. The tracking problem is solved as a family of regulation problems corresponding to the family of fast manifolds, using the feedback linearization methodology from nonlinear geometric control theory. A complete characterization is given of all state transformation-static feedback pairs that lead to exact linearization of the fast dynamics. Simulation shows that the composite control law produces a near-minimum-fuel ascent.

  • A geometric approach to regulator and tracker design for an Aerospace Plane
    3rd International Aerospace Planes Conference, 1991
    Co-Authors: Mark A. Van Buren, Kenneth D. Mease
    Abstract:

    The paper presents a nonlinear design approach drawing from singular perturbations, feedback linearization, and variable structure control, that leads to regulators with automatic gain scheduling which exhibit similar dynamic behavior over the entire flight envelope of the Aerospace Plane. Additionally, design approach provides for a systematic way to counter disturbance effects as well as modeling uncertainties. The unifying feature of the three nonlinear feedback control methodologies is that they all have a geometric interpretation. First, the translational dynamics are decomposed into reduced-order slow and fast dynamics by way of a formal singular perturbation analysis. After feedback linearization the fast dynamics are robustly stabilized via a variable structure control approach. The slow dynamics are stabilized using conventional proportional-integral compensation based on the nominal slow dynamics. A number of sample command and disturbance responses at opposite ends of the flight envelope are presented for a nonlinear Aerospace Plane model.

  • Aerospace Plane guidance using time scale decomposition a geometric approach
    Navigation and Control Conference, 1991
    Co-Authors: Mark A. Van Buren, Kenneth D. Mease
    Abstract:

    A method is proposed for developing the necessary guidance logic to steer single-stage vehicles into orbit. The minimum-fuel ascent problem is first considered to analyze the effects of dynamic pressure, acceleration, and heating constraints on guidance systems to thereby develop the guidance logic. The optimal solution consists of behavior with two time scales, and the control law is used to develop near-optimal guidance. The solution uses the slow manifold to delineate the control for minimum-fuel reduced-order trajectory and a separate control for tracking the optimal reduced-order trajectory. A family of fast manifolds is then employed to resolve the tracking problem via the feedback linearization methodology from nonlinear geometric control theory. The two-time-scale decomposition is found to produce a near-optimal ascent by tracking the applicable state-constraint boundary, as well as to simplify the control-design task.

Yongyuan Qin - One of the best experts on this subject based on the ideXlab platform.

  • Information Fusion Based on Complementary Filter for SINS/CNS/GPS Integrated Navigation System of Aerospace Plane
    Sensors (Basel Switzerland), 2020
    Co-Authors: Yanming Zhao, Gongmin Yan, Yongyuan Qin
    Abstract:

    In order to solve the problems of heavy computational load and poor real time of the information fusion method based on the federated Kalman filter (FKF), a novel information fusion method based on the complementary filter is proposed for strapdown inertial navigation (SINS)/celestial navigation system (CNS)/global positioning system (GPS) integrated navigation system of an Aerospace Plane. The complementary filters are designed to achieve the estimations of attitude, velocity, and position in the SINS/CNS/GPS integrated navigation system, respectively. The simulation results show that the proposed information fusion method can effectively realize SINS/CNS/GPS information fusion. Compared with FKF, the method based on complementary filter (CF) has the advantages of simplicity, small calculation, good real-time performance, good stability, no need for initial alignment, fast convergence, etc. Furthermore, the computational efficiency of CF is increased by 94.81%. Finally, the superiority of the proposed CF-based method is verified by both the semi-physical simulation and real-time system experiment.

  • information fusion based on complementary filter for sins cns gps integrated navigation system of Aerospace Plane
    Sensors, 2020
    Co-Authors: Yanming Zhao, Gongmin Yan, Yongyuan Qin
    Abstract:

    In order to solve the problems of heavy computational load and poor real time of the information fusion method based on the federated Kalman filter (FKF), a novel information fusion method based on the complementary filter is proposed for strapdown inertial navigation (SINS)/celestial navigation system (CNS)/global positioning system (GPS) integrated navigation system of an Aerospace Plane. The complementary filters are designed to achieve the estimations of attitude, velocity, and position in the SINS/CNS/GPS integrated navigation system, respectively. The simulation results show that the proposed information fusion method can effectively realize SINS/CNS/GPS information fusion. Compared with FKF, the method based on complementary filter (CF) has the advantages of simplicity, small calculation, good real-time performance, good stability, no need for initial alignment, fast convergence, etc. Furthermore, the computational efficiency of CF is increased by 94.81%. Finally, the superiority of the proposed CF-based method is verified by both the semi-physical simulation and real-time system experiment.

Nobuyuki Tomita - One of the best experts on this subject based on the ideXlab platform.

  • Control Aspects of Aerospace Plane Docking and Undocking with Moving EkranoPlane
    IFAC Proceedings Volumes, 2004
    Co-Authors: Alexander Nebylov, Yoshiaki Ohkami, Nobuyuki Tomita
    Abstract:

    Abstract The concept of Aerospace Plane (ASP) horizontal launch and landing with the assist of large-scale ekranoPlane is analyzed1. Undocking of these two winged vehicles after ASP acceleration up to the necessary initial velocity for independent flight and their docking at the final stage of ASP descent for water landing are the critical points of the concept feasibility. The requirements to appropriate systems of navigation and motion control of both wing craft are presented. The structure of the integrated system of relative motion control is suggested. Principles of docking and undocking, requirements to the main onboard systems of both vehicles are considered.

  • Adaptive Controller in the Aerospace Plane to EkranoPlane Landing System
    IFAC Proceedings Volumes, 2001
    Co-Authors: V.n. Kalinichenko, Alexander Nebylov, Nobuyuki Tomita
    Abstract:

    Abstract The control system for stabilizing the lateral motion at landing the Aerospace Plane (ASP) onto moving ekranoPlane is developed. As the disturbances character applied to ASP are being changed at different weather conditions, the system analysis and synthesis are made in a wide class of disturbances. This class may be represented by some numerical characteristics - the upper bounds of derivatives dispersions. The way for estimation of such bounds by means of current observations is proposed. The algorithm for adapting the controller in accordance with the current bounds of dispersions of the input signal. It allows to increase the accuracy and reliability of docking the ASP and ekranoPlane.

  • performance and technological feasibility of rocket powered hthl ssto with take off assist Aerospace Plane ekranoPlane
    Acta Astronautica, 1999
    Co-Authors: Nobuyuki Tomita, Alexander Nebylov, Victor V Sokolov, Yoshiaki Ohkami
    Abstract:

    Abstract It might be said that it is common understanding that rocket-powered single stage to orbit (SSTO) Aerospace Planes will become feasible with near-term technology as described in 1 , 2 . Among two methods of launching Aerospace Planes into orbit, vertical take-off (VT) and horizontal take-off (HT), it seems that VT takes the lead from HT 1 , 2 . The decision for the X-33 program by NASA, also, seems to favor VT. In retrospect, almost all of the launch vehicles in the past have been VT, mainly because VT solved the problem of exit from atmosphere to space. However, broadening the range of requirements for space transportation systems from military to commercial and unmanned to manned seems to favor the need for HT. In this paper, the authors are going to prove that Aerospace Plane/ekranoPlane system, which is a reusable launch vehicle system based on the HT concept, with ekranoPlane as a take-off and possibly, landing assist, could be competitive with the VT concept from both technological and economical view points. EkranoPlane is a wing-in-ground-effect craft (WIG), which moves at a speed of approximately 0.5 M, carrying heavy loads above the sea surface. Combination of high initial velocity and high performance tri-propellant engine for Aerospace Plane makes it possible to configure an Aerospace Plane which is competitive with VT. Other specific features of HT in comparison with VT are discussed.

  • Performance and technological feasibility of rocket powered HTHL-SSTO with take-off assist (Aerospace Plane/ekranoPlane)
    Acta Astronautica, 1999
    Co-Authors: Nobuyuki Tomita, Alexander Nebylov, Victor V Sokolov, Yoshiaki Ohkami
    Abstract:

    Abstract It might be said that it is common understanding that rocket-powered single stage to orbit (SSTO) Aerospace Planes will become feasible with near-term technology as described in 1 , 2 . Among two methods of launching Aerospace Planes into orbit, vertical take-off (VT) and horizontal take-off (HT), it seems that VT takes the lead from HT 1 , 2 . The decision for the X-33 program by NASA, also, seems to favor VT. In retrospect, almost all of the launch vehicles in the past have been VT, mainly because VT solved the problem of exit from atmosphere to space. However, broadening the range of requirements for space transportation systems from military to commercial and unmanned to manned seems to favor the need for HT. In this paper, the authors are going to prove that Aerospace Plane/ekranoPlane system, which is a reusable launch vehicle system based on the HT concept, with ekranoPlane as a take-off and possibly, landing assist, could be competitive with the VT concept from both technological and economical view points. EkranoPlane is a wing-in-ground-effect craft (WIG), which moves at a speed of approximately 0.5 M, carrying heavy loads above the sea surface. Combination of high initial velocity and high performance tri-propellant engine for Aerospace Plane makes it possible to configure an Aerospace Plane which is competitive with VT. Other specific features of HT in comparison with VT are discussed.

  • Control Strategies and Means of SpacePlane Landing with EkranoPlane Assist
    IFAC Proceedings Volumes, 1999
    Co-Authors: Alexander Nebylov, Yoshiaki Ohkami, Nobuyuki Tomita
    Abstract:

    Abstract The concept of Aerospace Plane landing with ekranoPlane assist is proposed. It is shown, that their docking on a final stage of Aerospace Plane alighting is favorable to expansion of functional capacity of the transport system. The requirements to corresponding systems of navigation and motion control of both wing craft are presented, the structure of the integrated system of relative motion control is offered