High Speed Flight Demonstration Research Articles

Study on the Computation Method for the Generalized Force and Mass of Flexible Aerial Rudder in Space Vehicle

Aerial rudders are significant actuators in the spacecraft control systems and are responsible for the stability and control of different motions such as pitching, yawing and rolling around mass center. With the development of new generation of space vehicles, high speed flight demonstration, light and thin aerial rudders with large span-chord ratio have been widely used. In the design of control strategies in pitching, yawing and rolling channels and control feedback loop parameters, the influence caused by aerial rudder elastic deformation should be considered particularly. In this paper, elastic motion equations of the spacecraft flexible rudder are studied firstly. Then, according to the modal vibration features, aerodynamic force derivative distribution characteristics and generalized force expressions, the rudder station division and computation method of generalized rudder aerodynamic force derivatives are proposed in the pitching, yawing and rolling channels based on the computational fluid dynamics simulation. By comparison the results of the proposed method with these of the traditional computation methods, the accuracy and validity of the proposed method are verified which can provide considerable references and basis in the control design of flexible rudder in the spacecraft.

GUIDANCE AND ATTITUDE CONTROL LAW FOR THE FINAL PART OF A REENTRY VEHICLE TRAJECTORY - ALTERNATE LAWS FOR THE EXPERIMENTAL VEHICLE HSFD II

The experimentation part of HSFD-II (High Speed Flight Demonstrator phase II) was conducted under a CNES (French Space Agency) - JAXA (Japaneese Space Agency) cooperation. JAXA provided the instrumented mock-up and CNES provided stratospheric ascending balloons (for mock-up release at up to 30 km in altitude) at the Kiruna-Esrange (Sweden) test falicity. In the terms of the cooperation was included the development of an alternate set of guidance and attitude control laws provided by ONERA.The control law was obtained using a robust polytopic method. The original guidance law of the US Shuttle was used as a baseline, but with significant adaptations, in particular for deep slope angle values (down to -50° in guidance phase versus about -5° for the Shuttle).The article first recalls the Flight Mechanics equations involved along with notations. The principle of the attitude control law is indicated and the guidance law is detailed. Finally the results of worst case simulations are presented.

High Speed Flight Demonstration, HSFD

High Speed Flight Demonstration, HSFD

3406 高速飛行実証フェーズIIの数学モデルと飛行実験結果(S87-2 飛翔体のモデリングとシステム同定(2),S87 飛翔体のモデリングとシステム同定)

The High-Speed Flight Demonstration (HSFD) project is the latest in a series of flight experiments in a research program into reusable space transportation systems being conducted by JAXA. HSFD Phase II was a drop test from a stratospheric balloon to clarify the transonic aerodynamic characteristics of the HOPE-X configuration and to obtain data to validate wind tunnel tests and computational fluid dynamics (CFD) predictions. Since a phased flight experiment can not applied because of its launch method, it was necessary to establish a mathematical model as precise as possible and to conduct accurate flight simulation analysis beforehand. This paper describes the mathematical model of the experiment and the comparison between the results of flight simulation and the flight experiment.

Current Status of Japanese Aerospace Programs - Focusing on the High Speed Flight Demonstration

The paper presents an overview of the current status of Japanese aerospace programs, including launch vehicles, satellites, university space programs, and aeronautical research and development. Following the overview, the paper describes the High Speed Flight Demonstration program, a flight experiment program using sub-scale vehicles to investigate the re-entry terminal flight phase of re-usable space vehicles. The program was conducted in two phases: a Phase I experiment at Christmas Island in 2002, and a Phase 11 experiment at Esrange, Sweden in 2003. Phase 11 is a joint program between NAL/NASDA and CNES.

Hope-X high speed flight demonstration program phase II – a CNES/NAL/NASDA cooperation

In the frame of its cooperation with the National Space Development Agency of Japan (NASDA), the CNES French Space Agency takes part in the High Speed Flight Demonstration (HSFD) Phase II. The HSFD program is planned as part of the National Aerospace Laboratory (NAL) and NASDA joint research for the H-II Orbiting Plane Experiment (HOPE-X), an unmanned re-entry vehicle project. The program consists of two phases, and the purpose of HSFD Phase II is to estimate the HOPE-X transonic aerodynamic characteristics: a sub-scaled vehicle will be lifted to high altitude by a stratospheric balloon, from where it will be released and will accelerate into free fall to transonic region. The CNES Balloon Division is responsible for the balloon system, the launch operation, and the recovery of the vehicle after touch down. Six flights are planned between May and August 2003.

Hope-X high speed flight demonstration program phase II ? a CNES/NAL/NASDA cooperation

In the frame of its cooperation with the National Space Development Agency of Japan (NASDA), the CNES French Space Agency takes part in the High Speed Flight Demonstration (HSFD) Phase II. The HSFD program is planned as part of the National Aerospace Laboratory (NAL) and NASDA joint research for the H-II Orbiting Plane Experiment (HOPE-X), an unmanned re-entry vehicle project. The program consists of two phases, and the purpose of HSFD Phase II is to estimate the HOPE-X transonic aerodynamic characteristics: a sub-scaled vehicle will be lifted to high altitude by a stratospheric balloon, from where it will be released and will accelerate into free fall to transonic region. The CNES Balloon Division is responsible for the balloon system, the launch operation, and the recovery of the vehicle after touch down. Six flights are planned between May and August 2003.

Development of GPS Aided Inertial Navigation System for High Speed Flight Demonstrator

Development of GPS Aided Inertial Navigation System for High Speed Flight Demonstrator