JPH0316896A - Steering leg for aircraft having actuators interconnected in series - Google Patents

Abstract

PURPOSE:To reduce probability of the occurrence of a serious trouble, sticking or runaway of an actuator, sticking of a wheel in a state that it is left at some steering angle, and to improve reliability by a method wherein each drive stroke employs two actuators mounted additively in series. CONSTITUTION:During normal operation, outputs from two actuators of the one being a first actuator 3 and the other being a second actuator 6 are added in the same direction to rotate wheels. In the case of emergency in which the one actuator of the first and second actuators 3 and 6 being brought into a stuck state or a runaway state, an output from the other actuator being sound is added in a reverse direction to correct the direction of the wheels.

Description

DETAILED DESCRIPTION OF THE INVENTION [Field of Industrial Application] The present invention relates to a steering leg of an aircraft in which steering actuators are connected in series.

[Prior art] In the conventional steering gear of an aircraft, as shown in FIG.
By equipping one steering actuator 01 for one steering leg or by equipping two steering actuators in parallel for one steering leg and adding power (output), the gear 02 can be rotated. The torque arm 03 was rotated (rotated) to rotate the wheels 04 around the axis Y for steering.

(Problems to be Solved by the Invention) The above-mentioned conventional steering legs of aircraft had the following problems to be solved. Namely, in the conventional steering legs, if one actuator goes out of control or becomes stuck, the wheels There is a high probability that an accident will occur where the aircraft becomes uncontrollable or becomes fixed at a certain steering angle, causing the aircraft to travel in a direction not intended by the operator and ultimately deviate from the runway. expensive.

Especially when using an electric actuator,
There is a high possibility that electrical runaway and actuator sticking will occur.

[Means to solve the problem]

The present invention, as a means of solving the above problem, provides a steering leg for an aircraft that steers the aircraft on the ground and guides the aircraft in a predetermined direction using the drive stroke of an actuator. The object of the present invention is to provide a steering leg for an aircraft, characterized in that it is equipped with an actuator, and in which actuators are connected in series.

[For production]

Since the present invention is structured as described above, it has the following effects. In other words, by installing two actuators in series so that their drive strokes can be added, the steering stroke becomes the sum of the strokes of the two actuators, so even if one actuator is stuck and does not operate, the steering stroke will be the sum of the strokes of the two actuators. One actuator allows steering of the wheels.

That is, if one actuator becomes out of control or becomes stuck, the other actuator can correct the steering angle and safely decelerate and stop the aircraft on the runway.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 and 2.

FIG. 1 is a diagram of this embodiment, in which (a) is a plan view, (b) is a side view, and FIG. 2 is a plan view showing the operating principle of this embodiment. In both figures, the first actuator 3 attached to the fixed plate 2 integrated with the cylinder 1 of the steering leg connects the floating plate 5 and the second actuator 6 attached to the floating plate 5 via the first gear 4. The leg piston 10 is rotated around its axis (the state shown in FIG. 2(a)).

The second actuator 6 rotates the torque collar 8 via the second gear 7. The rotation of the torque collar 8 is transmitted to the leg piston 10 via the torque arm 9 to steer wheels (not shown) below the leg piston 10.

In normal operation, the outputs (strokes) of the two actuators, the first actuator 3 and the second actuator 6, are added in the same direction to rotate the wheel (see Figure 2).
b) condition). In an emergency case where one of the first actuator 3 and second actuator 6 is stuck or runs out of control, the output (stroke) of the other healthy actuator is added in the opposite direction to correct the wheel direction. (The state shown in FIG. 2(c)). In addition, the method of using the first actuator 3 and the second actuator 6 in the normal state is to treat the two actuators on the same level and take charge of half the stroke each, or to establish a master-slave relationship between the two actuators and use one only in an emergency. There are ways to do this.

As described above, according to this embodiment, in normal conditions, the stroke of the second actuator 6 is added to the stroke of the first actuator 3 to steer the wheels, so high efficiency steering is achieved, and the first If either the actuator 3 or the second actuator 6 becomes stuck or some other unexpected trouble occurs, the actuator on the healthy side will perform the steering function independently, so there is a significant advantage that normal steering will not be impaired. There is.

〔Effect of the invention〕

Since the present invention is structured as described above, it has the following effects. In other words, the actuators connected in series mutually form a so-called override system, which reduces the probability of serious failures such as the actuators sticking or running out of control, resulting in the wheels being fixed at a certain steering angle, and improving reliability. Improve.

Note that the reliability can be expected to be twice as high as that of the conventional steering leg with one actuator.

[Brief explanation of the drawing]

FIG. 1 is a diagram of one embodiment of the present invention, (a) is a plan view thereof, (b) is a side view, and FIG. 2 is a plan view explaining the operation of the above embodiment, (a) is an operation (b) shows the state after normal operation (steering), (c) shows the state after emergency operation (steering), and FIG. 3 shows the conventional example (steering with one actuator). (a) is a side view; (a) is a side view;
b) is a plan cross-sectional view taken along line bb in (a). 1...Cylinder. 2... Fixed plate 3... First actuator, 4... First gear, 5... Idle plate, 6... Second actuator, 7... Second gear, 8... Torque Color 9...Torque arm, 10...
・Leg piston.

Claims (1)

[Claims] The steering leg of an aircraft steers the aircraft in a predetermined direction by steering the aircraft in a predetermined direction by the drive stroke of the actuator, and is characterized by comprising two actuators installed in series so that the respective drive strokes can be added. An aircraft steering leg with actuators connected in series.