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US 12,497,163 B1Granted
Rotary toggle mechanism for landing gear system
AssigneeAmerican Honda Motor Co., Inc.
InventorAaron John Vincent
Life of this patent
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Abstract
Systems for activating and deactivating an emergency landing gear system in an aircraft include a rotary toggle mechanism that actuates a switch. When the switch is actuated, the emergency landing gear system is activated and the operation of one or more other aircraft systems may be modified accordingly. The rotary toggle mechanism may be placed in three different states: a ready state, an active state, and a reset state. In the ready state, the switch is not actuated and the emergency landing gear system is not activated. In the active state the switch is actuated and the emergency landing gear system is activated. While the mechanism is in the active state the mechanism cannot be returned to the ready state without first passing through the reset state.
Claims20
A rotary toggle mechanism, comprising:
- a housing including a housing slot with a main slot portion and a slot detent;
- a cam secured to the housing such that the cam is rotatable direction relative to the housing in a first rotational direction and a second rotational direction opposite the first rotational direction, the cam including a cam detent;
- a locking pin extending through the housing slot;
- wherein the rotary toggle mechanism has a first state where the locking pin is secured between the cam and the main slot portion of the housing slot;
- wherein the rotary toggle mechanism has a second state where the locking pin is disposed in the cam detent, wherein the second state is reached by rotating the cam in the first rotational direction from the first state, and wherein the cam is prevented from rotating in the second rotational direction while the rotary toggle mechanism is in the second state;
- wherein the rotary toggle mechanism has a third state where the locking pin is disposed in the slot detent, wherein the third state is reached by rotating the cam in the first rotational direction from the second state, and wherein the cam is rotated in the second rotational direction from the third state to the first state.
3 more elements
An assembly, comprising:
- a lever comprising a first end and a second end;
- a handle attached to the first end of the lever;
- a rotary toggle mechanism associated with the second end of the lever;
- wherein the rotary toggle mechanism has three different states corresponding to three different positions of the handle;
- and wherein the rotary toggle mechanism further includes:
- a housing including a housing slot with a main slot portion and a slot detent;
- a cam secured to the housing such that the cam is rotatable direction relative to the housing in a first rotational direction and a second rotational direction opposite the first rotational direction, the cam including a cam detent;
- a locking pin extending through the housing slot;
- wherein the rotary toggle mechanism has a first state where the locking pin is secured between the cam and the main slot portion of the housing slot;
- wherein the rotary toggle mechanism has a second state where the locking pin is disposed in the cam detent, wherein the second state is reached by rotating the cam in the first rotational direction from the first state, and wherein the cam is prevented from rotating in the second rotational direction while the rotary toggle mechanism is in the second state;
- wherein the rotary toggle mechanism has a third state where the locking pin is disposed in the slot detent, wherein the third state is reached by rotating the cam in the first rotational direction from the second state, and wherein the cam is rotated in the second rotational direction from the third state to the first state.
8 more elements
A system for controlling an emergency landing gear system in an aircraft, the system comprising:
- a switch having an actuated position in which the emergency landing gear system is activated and a non-actuated position in which the emergency landing gear system is deactivated;
- a rotary toggle mechanism for changing the switch between the actuated position and the non-actuated position;
- a lever for controlling the rotary toggle mechanism;
- and
- a handle connected to the lever, wherein the handle is configured to be accessible by a pilot of the aircraft;
- and
- wherein the rotary toggle mechanism further includes:
- a housing including a housing slot with a main slot portion and a slot detent;
- a cam secured to the housing such that the cam is rotatable in a first rotational direction and a second rotational direction opposite the first rotational direction relative to the housing, the cam including a cam detent;
- a locking pin extending through the housing slot;
- wherein the rotary toggle mechanism has a first state where the locking pin is secured between the cam and the main slot portion of the housing slot;
- wherein the rotary toggle mechanism has a second state where the locking pin is disposed in the cam detent, wherein the second state is reached by rotating the cam in the first rotational direction from the first state, and wherein the cam is prevented from rotating in the second rotational direction while the rotary toggle mechanism is in the second state;
- wherein the rotary toggle mechanism has a third state where the locking pin is disposed in the slot detent, wherein the third state is reached by rotating the cam in the first rotational direction from the second state, and wherein the cam is rotatable in the second rotational direction while the rotary toggle mechanism is in the third state.
10 more elements
Dependencies are inferred from the claim text.