National Aerospace Laboratory of Science Technology Agency

National Space Development Agency of Japan (nasda)

Tokyo Aircraft Instrument Co., Ltd.

National Aerospace Laboratory of Science & Technology

Kawasaki Industries, Ltd.

National Aerospace Laboratory of Science &technology Agency&national

Naoaki Kuwano

Teruomi Nakaya

Seizo Suzuki

Osamu Okamoto

Shuichi Sasa

Hidehiko Nakayasu

Masakazu Sagisaka

Goji Iba

Asao Hanzawa

Toru Iwata

Yoshio Hayashi

Takashi Saitow

Masao Ebihara

Hiroshi Oda

Masao Uegusa

Mitsuo Usami

Seigou Nakamura

Kenji Ogimoto

Ryuji Sakata

Yasuaki Taniguchi

Yoshinori Sakai

Hiroyoshi Tanaka

A flight velocity vector measuring system in a wide velocity region in which an attack angle pressure coefficient C&agr; of air current, a sideslip angle pressure coefficient C&bgr; and an air current angle pressure coefficient C&ggr; are obtained from five pressure information detected by a square truncated pyramid-shape probe. The aforementioned pressure coefficients, pressure calibration coefficients with respect to a Mach number M, an attack angle &agr; and a sideslip angle &bgr; every velocity region obtained by dividing the wide velocity region into a plurality of regions stored in advance in the calculation processor, and a Mach number M, an attack angle &agr; and a sideslip angle &bgr; of unknown quantity constitute a calculation processing expression comprising a polynomial approximation to call the pressure calibration coefficients in the velocity region, and flight velocity vectors (M, &agr;, &bgr;) are calculated by the polynomial approximation.

Flight velocity vector measuring system in wide velocity region using truncated pyramid-shape probe

A transportable three-dimensional calibration wind tunnel system is comprised of a small wind tunnel portion for creating a three-dimensional calibration air having a suitable wind velocity, and a two-axis rotational deformation device portion for causing said wind tunnel portion to effect a conical motion with a nozzle blow port being an apex to suitably change a flow angle. The two-axis rotational deformation device is comprised of a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and a .alpha.-angle rotational deformation device having a .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point. In a method for the verification of a flight control system of an aircraft using the transportable three-dimensional calibration wind tunnel system, the nozzle blow port of the three-dimensional calibration wind tunnel system is positioned at the extreme end of an air data sensor probe provided on the aircraft, and the three-dimensional calibration wind tunnel system and an on-board control computer of the aircraft are connected to an out-board control computer so that a suitable three-dimensional airflow is generated by the three-dimensional calibration wind tunnel system to verify the operation and function of the control surface in the stopped state on the ground.

Transportable three-dimensional calibration wind tunnel system,

An air active control aircraft having an air three-dimensional true airspeed detection system composed of an air data sensor probe in the form of a truncated pyramid-shape Pitot probe and an air flight velocity operation processor for calculating an air flight velocity vector from three-dimensional air pressure information detected by the air data sensor probe, airframe motion detection sensors for detecting an airframe motion, and an on-board control computer for generating a flight control law. The on-board control computer inputs an air flight velocity vector signal obtained from the air flight velocity vector device into a control-surface control system in parallel with airframe motion detection sensor signals, and presumes a flight motion induced by a change in air to generate the flight control law for quickly carrying out air flight stability control.

Air active control aircraft using three dimensional true airspeed

A transportable three-dimensional calibration wind tunnel system consisting of a small wind tunnel portion for creating a three-dimensional airflow having a suitable wind velocity, and a two-axis rotational deformation device portion for causing the wind tunnel portion to effect a conical motion with a nozzle blow port being in close proximity to an apex to suitably change a flow angle. The two-axis rotational deformation device includes a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and an .alpha.-angle rotational deformation device having an .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point. When verifying a flight control system of an aircraft using the transportable three-dimensional calibration wind tunnel system, the nozzle blow port of the three-dimensional calibration wind tunnel system is positioned at the extreme end of an air data sensor probe provided on the aircraft, and the three-dimensional calibration wind tunnel system and an on-board control computer of the aircraft are connected to an out-board control computer so that a suitable three-dimensional airflow is generated by the three-dimensional calibration wind tunnel system to verify the operation and function of the control surface in the stopped state on the ground.

Verification method of a flight control system using a transportable

A transportable three-dimensional calibration wind tunnel system consists of a small wind tunnel portion for creating a three-dimensional airflow having a suitable wind velocity, and a two-axis rotational deformation device portion for causing the wind tunnel portion to effect a conical motion with a nozzle blow port being in close proximity to an apex to suitably change a flow angle. The two-axis rotational deformation device includes a .beta.-angle rotational deformation device having a .beta.-angle deformation base supported to be rotated horizontally, and an .alpha.-angle rotational deformation device having an .alpha.-angle deformation base supported to be rotated vertically. A rotational axis of the .alpha.-angle deformation base, a rotational axis of the .beta.-angle deformation base and a center axis of the small wind tunnel portion are arranged so that they intersect at a point. When verifying a flight control system of an aircraft using the transportable three-dimensional calibration wind tunnel system, the nozzle blow port of the three-dimensional calibration wind tunnel system is positioned at the extreme end of an air data sensor probe provided on the aircraft, and the three-dimensional calibration wind tunnel system and an on-board control computer of the aircraft are connected to an out-board control computer so that a suitable three-dimensional airflow is generated by the three-dimensional calibration wind tunnel system to verify the operation and function of the control surface in the stopped state on the ground.

A flight velocity detection system using a truncated pyramid-shape multi-e Pitot probe in which an extreme end portion has a truncated pyramid-shape, a cylindrical hole is provided at the apex thereof, a total pressure tube of a smaller diameter than that of the cylindrical hole is secured at a position by a predetermined length determined by a relationship with the diameter of the cylindrical hole from the extreme end of the cylindrical hole, and groups of pressure holes comprised of a plurality of pressure holes are arranged in each of the truncated pyramid surfaces of the truncated pyramid shape. Items of pressure information detected by the probe are input into a velocity vector processor to convert them into electric signals, and signals are processed using pressure coefficients of the holes of the probe with respect to the velocity vector stored in advance in the velocity vector processor to calculate flight velocity vector (V, .alpha., .beta.) with respect to the probe axis from the pressure information and air density.

Truncated pyramid-shape multi-hole pitot probe and flight velocity

A plurality of eccentric rotors are rotatably fitted between a fixed base and an output shaft on which an object to be vibrationproofed is mounted, the output shaft being supported movably in 3 to 6 Degree-of-Freedom, magnet spring mechanisms are provided on fitted wall surfaces between the fixed base and the eccentric rotor, a composite vibrationproof adjusting spring is provided between the fixed base and the output shaft, the magnet spring mechanism responding to a fine displacement of the output shaft, and in a case where the output shaft is greatly displaced, the output shaft is braked so as to be restored to a predetermined position by the composite vibrationproof adjusting spring mechanism. The magnet spring mechanism produces a large braking force since a rotational angle is large and a rotational-angle speed is high due to eccentricity of eccentric rotors.

Multidimensional damping apparatus

A docking and active damping device for space structures is provided, in a docking portion of one space structure to be docked, with a positioning device in which an output rotor can be moved and rotated within a two-dimensional plane by a composite rotation of one or more eccentric rotors capable of being independently driven and controlled by a direct drive motor and the output rotor, and a docking member having a docking ring and a latch mechanism are supported on the output rotor of the positioning device. A probe having a capture device capable of being protruded and driven in an axial direction by a linear motion is provided inwardly of the docking member, and the probe provides a 4-freedom movement according to a position of the passive side to capture and dock a drogue. The docking ring is supported through a strain sensor, a vibration of the passive side structure is detected, and the docking member is moved in a direction of suppressing the vibration to promptly suppress the vibration caused by disturbances from the inside and outside of the space structures.

Docking and active damping device for space structures

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Chofu, Japan

Naoaki Kuwano