Honda Giken Kogyo Kabushiki Kaisha

Honda Motor Co., Ltd.

Honda Patents & Technologies North America, LLC

Sumitomo Precision Products Co., Ltd.

Hiroshi Yamanouchi

Wataru Yada

Minoru Uchida

Katsutoshi Tada

Hidetaka Nagano

Masaki Kobayashi

Toshiaki Fujii

Tetsuji Sato

Pascal Brisson

Masaru Oono

A flight control system loading test apparatus includes a surface-mounted sector, a cam profile sector, a dummy weight, and a cable. The surface-mounted sector attaches to an aircraft flight control system body such that the surface-mounted sector pivots along with the body about a pivot axis. The cam profile sector is configured to rotate about a rotational axis among a plurality of loading positions. The cam profile sector includes a profile surface having a plurality of curves. Each curve follows a different radius emanating from a respective axis substantially parallel to the rotational axis of the cam profile sector. The cable contacts the cam profile sector along the profile surface. An applied hinge moment using the dummy weight varies as the cam profile sector rotates about the rotational axis.

Flight control system loading test apparatus and method

An aircraft control surface operating device is provided for operating a control surface on an aircraft body portion to move between a retracted position and an extended position. The aircraft control surface operating device includes a control surface mounting assembly which movably secures the control surface to the aircraft body portion, a drive arm rotatable about a drive axis relative to the aircraft body portion, an actuator for rotating the drive, and a drive link connecting the drive arm to the control surface mounting assembly. The drive link has a control end connected to the control surface mounting assembly and a driven end connected to the drive arm via a drive bearing joint. The drive link connects the drive arm and the control surface mounting assembly such that rotation of the drive arm is causes extending or retracting movement of the control surface.

Aircraft control surface operating device

A door opening and closing mechanism for opening and closing the door from the inside of a fuselage. A door pivotally supported at an opening portion of the fuselage includes first and second position restricting links each having one end pivotally supported on the fuselage with a door driving link having one end pivotally supported on the door. The other end of the second position restricting link is pivotally supported on a middle portion of the door driving link. The door opening/closing operation lever is provided at one end with a grip with the other end pivotally supported on the other end of the door driving link. The middle portion of the door opening/closing operation lever is pivotally supported on the other end of the first position restricting link. By pulling the grip toward the inside of the fuselage and thereafter pushing downward, the door can be closed.

Door opening and closing apparatus for aircraft

A slide door device for an aircraft includes an upper guide roller at a tip end of an upper arm provided at an upper part of a slide door and a lower guide roller at a tip end of a lower arm provided at a lower part of the slide door that are rollably engaged with an upper guide rail and a lower guide rail that are fixed along an upper edge and a lower edge of a door opening frame formed in a fuselage of an aircraft, respectively. An intermediate guide roller, provided at a tip end of an intermediate arm provided in a door opening, is rollably engaged with an intermediate guide rail that is fixed to an inner surface of the slide door, while smoothly guiding the slide door with the upper guide rail, the lower guide rail, and the intermediate guide rail.

Slide door device for aircraft

A groove is provided to the rear of an inner wall of a cylinder. A locking ram capable of freely sliding in a radial direction and a cam rod having a profile changing with a transition from the rear to the front from a small diameter part to a large diameter part that are provided relative to a piston. The inner end of the locking ram makes contact with the profile, and the cam rod is urged to the rear by the spring, so that the cam rod can be pushed to the front by a push rod. The piston can therefore be locked with a simple structure, and it is possible to provide a linear actuator where locking can be released with a straightforward operation even when a pressurized oil source fails.

Linear actuator

When a single door for opening and closing an opening in a body is opened outward with its lower part as a fulcrum, a plurality of plate-shaped steps of a foldable boarding ramp provided on an inner face of the door are swung in association with one another from a stored position along the inner face of the door to a deployed position to be used for ingress and egress of the passengers. Since the boarding ramp is folded into the stored position, it does not impair the space of a passenger compartment. Further, since the steps are folded into a position so as not to interfere with a window provided in an upper part of the door, they do not give an oppressed feeling to the passengers in the passenger compartment. The step is deployed to cover the window provided in the upper part of the door during use.

Boarding ramp device for aircraft

A foldable boarding ramp is operatively connected to a door opening provided in a body and is selectively extendable to the ground. The foldable boarding ramp is stored in a folded state inside a fairing covering a connecting portion between the body and a main wing. Thus, a reduction in the space of a passenger compartment and a cargo compartment due to the storage of the folded boarding ramp is prevented. In addition, an increase in air resistance can be suppressed without providing a dedicated fairing for covering the boarding ramp. Further, an interlocking member connects together a door for opening and closing the door opening and the boarding ramp when the door is opened. The boarding ramp may be automatically deployed to improve convenience.

In a flap operating system, left and right actuators for operating left and right flaps are synchronized with each other by left and right pulleys and first and second synchronizing cables wound in an X-shape around the left and right pulleys. If one of the hydraulic actuators fall into a free failure or fails due to sticking, a difference is generated between the rotational angles of the left and right pulleys. When the difference exceeds a threshold value, the operations of the left and right actuators are stopped, whereby an excessive load is previously prevented from being applied to a main wing structure or the flap operating system.

Flap operating system

A first cylinder drives a flap to a predetermined down position. Strain gages detect strains at each part of the flap while a load that corresponds to the down position is applied to the flap by a second cylinder that has been moved by an XY table so as to track the down position. Accordingly, actual aerodynamic forces are precisely reproduced by applying a load having a size and a direction that correspond to the down position of the flap. Thus, a stationary load test, a dynamic load test, and a durability test of the flap can be carried out automatically with a small effort and in a short time.

Flap test system

A flap mounted on a tapered main wing of an aircraft, is supported by at least two link units. The link units are formed into analogous shapes with an analogous size ratio equal to the ratio between corresponding chord lengths of the main wing. As a result, the amounts of protrusion of the flap are varied in the span direction in accordance with the analogous size ratio, and the flap performs a three-dimensional motion such that it is moved in the span direction while being retracted and lowered. Thus, the flap can be moved to protrude to an optimal position and through an optimal angle according to the chord lengths of the main wing. When the flap is a slotted flap, an appropriate slot width can be ensured at each of the portions in the span direction, whereby the aerodynamic characteristic of the flap mounted on the tapered main wing can be uniform in the span direction.

Flap operating device

A flaperon operating device having a center pulley and a slider supported on a center shaft. When the center pulley and the slider are rotated about the center shaft, left and right driving pulleys are rotated in the same direction, whereby left and right flaperons are operated in opposite directions to provide aileron functions. When the slider is slid rearwards on the center shaft by an actuator, the left and right driving pulleys are rotated in opposite directions, whereby both the left and right flaperons are lowered to provide flap functions. If the left and right flaperons are lifted or lowered by a very small angle in the same phase by the actuator, boundary layers on main wings can be controlled to reduce the drag.

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Wako, Japan

Hiroshi Yamanouchi