JPS62253558A - Brake controller - Google Patents

Abstract

PURPOSE:To simplify the brake system by installing a pressure control valve for controlling the hydraulic pressure supplied into a brake cylinder according to the output of a brake control box, thus obtaining the optimum relation between the pedal stepping force and brake application. CONSTITUTION:When a pilot 4 applies a brake power F onto a brake pedal 5 which does not shift, a power sensor 6 detects the magnitude of the force, and the brake power is sent as electric signal into a brake control box 7 through an electric wire 23a. When no power is input into said box 7, a brake signal P1 in a specific function relation with the brake power F is generated in a logic 8, and sent into a pressure control valve 17 through an electric wire 23b. In the valve 17, the hydraulic pressure is converted to PB=PB1 proportional to the signal P1, and a brake cylinder 20 is pressurized by a necessary quantity, and a brake torque TB is obtained, and deceleration or stop state is maintained.

Description

[Detailed description of the invention] [Industrial application field] The present invention relates to a brake control device for aircraft, vehicles, etc.

[Conventional technology]

Conventionally, aircraft brake systems apply braking to wheels attached to the main landing gear 2 of an aircraft 1, as shown in the side view of FIG. 2(A) and the system diagram of FIG. 2(B), for example. When attempting to do so, the oil in the master brake cylinder 24 is pressurized by the pressing force and displacement of the pilot 4 applied to the brake pedal 5, and the pressure is increased directly to the hydraulic piping 19 of the hydraulic power source 18 or by the brake control valve 25. By applying hydraulic pressure to the brake cylinder 20 and restraining the rotation of a rotor (not shown) directly connected to the wheel 3, the braking force of the wheel B is obtained.

In this case, as a countermeasure in the event of a skid, the rotation speed of the wheel 3 is detected by the wheel rotation sensor 21, the anti-skid controller is sent a command to the brake pressure control valve 27 by e, 26, and the brake cylinder is activated. 20
The braking force is controlled by removing hydraulic pressure from the brake.

In addition, the carbon material used for wheel brakes may have a static friction coefficient or a dynamic friction coefficient, so in order to obtain sufficient braking force when stopping, the two-stage switching brake control device must be operated automatically or manually to control the brake cylinder 20. Switching hydraulic pressure. After the pilot 4 feels the landing impact of the main landing gear 2, he brakes the aircraft by applying force on the brake pedal 5.

However, such a brake control device has the following drawbacks.

(1) With brakes that are subject to displacement along with the force applied to the brake pedal, the cockbit size increases.

(2) In a mechanical brake that transmits brake pedal depression force and displacement to the master cylinder, the depression force, pedal displacement, and brake pressure, that is, braking force, have a constant linear relationship, and it is extremely difficult to obtain an arbitrary nonlinear relationship. It is.

(6) Since the anti-skid controller box is installed independently of the brakes, there are many components, making the brake system complicated.

(4) A two-stage switching brake control device requires a switching pulp, a control switch, etc.

Also, since there is basically a one-to-one relationship between pedal depression force and brake cylinder pressure, K
requires a great deal of force. Alternatively, if the pedal force when stationary is set to an appropriate level, the pedal force when not stationary becomes too small.

(5) Brake braking is mechanically and hydraulically controlled by the pilot's pedal force, and manual input or automatic braking cannot be performed, so the braking distance becomes longer due to a delay in brake braking. Furthermore, there is a human-like time delay before the brakes are applied after landing, which increases the landing run distance.

[Problem that the invention seeks to solve]

The present invention was proposed in view of these circumstances, and
It eliminates the need for brake pedal displacement, allows for a compact cockpit, provides the optimum relationship between pedal force and braking for the pilot's feeling, and allows braking to be performed using a manual switch other than the pedal force, as well as at the same time as landing. It is an object of the present invention to provide a brake control device that can automatically operate the brakes to minimize the sliding distance, and can also compensate for pre-kinesia caused by a decrease in the coefficient of static friction of carbon brakes.

[Failure to solve the problem]

To this end, the present invention provides a brake pedal that does not displace even when a pedal force is applied, a force sensor that emits a signal according to the magnitude of the force applied to the brake pedal, a manual controller that emits an appropriate deceleration signal, and a brake pedal that does not displace even when a pedal force is applied. A wheel rotation sensor that detects a rotational speed signal, a wheel rotation sensor, and a manual controller for the force sensor 1.

A brake control valve receives signals from the wheel rotation sensor and integrator and issues a brake signal based on a relational formula according to each signal, and a pressure control valve controls hydraulic pressure to the brake cylinder according to the output of the brake control box. It is characterized by having the following.

[For production]

The above configuration eliminates the need for brake pedal displacement, makes the cock bit compact, provides the optimum relationship between pedal force and braking for the pilot's feeling, and allows braking to be performed using a manual switch, etc. other than the pedal force. It is possible to obtain a brake control device that can minimize the sliding distance by automatically applying the brakes at the same time as the landing, and can also compensate for pre-kine footing caused by a decrease in the coefficient of static friction of carbon brakes.

"Chapter fill 11 An embodiment in which the present invention is applied to a brake control device for an aircraft will be described with reference to the drawings. FIG. 1(A) is a side view of the aircraft, and FIG. 1 CB) is a system diagram of the brake control device.

In the above figure, the same symbols as in Fig. 2 indicate the same members as in the same figure, and when the pilot 4 applies a brake force F to the brake pedal 5 that does not displace, the force sensor 6 detects the magnitude of the force. , the braking force is transmitted as an electric signal to the wire 23.
It is sent to the brake control box 7 through a. In the brake control box 7, first, in the logic P18 when there is no other input, a brake signal P having a specific functional relationship with the brake force F is generated, and the brake signal P' is sent to the pressure control valve 17 via the electric wire 23b. sent to.

The pressure control valve 17 is connected to the hydraulic power source 18 and the piping 19.
The hydraulic pressure sent via the input signal P=P1 is converted into PB=PB1 which is proportional to the input signal P=P1, and the brake cylinder 20 is pressurized by the required amount to obtain the brake braking torque TT3.

This brake braking torque TB is applied to wheel 3. A braking force FB is applied to the aircraft 1 through the main landing gear 2 against the forward force FX, thereby decelerating the aircraft or keeping it in a stopped state.

Left and right legs G A S (Ground Air 5afe
ty ), x, itchi 15 't If the auto switch 13 is set to auto with the IC in the closed state (ground), an electric circuit is formed via the electric wire 23c, and in this state, the knob of the manual controller 12 any,
For example, if the deceleration is adjusted to 0.2G, the electric signal C is added to the logic P29 via the adder 14.
A brake signal P2 having a specific relationship is generated, and a brake pressure PB=PB2 is generated in the same manner as described above to apply a braking force to the aircraft 1.

That is, the pilot 4 can manually apply a brake force without applying a pedal force F, and the magnitude of the brake force can be set to an arbitrary deceleration.

Furthermore, if the auto switch 13 is set to auto and the manual controller 12 is set to a predetermined setting, the brakes can be applied automatically at the same time as the aircraft 1 lands and the GAS switches 15 and 16 are closed.

Furthermore, the wheel rotation sensor 21 detects the rotational speed S of the wheel A, and an integrator 22 obtains an approximate signal of the aircraft speed V, which is applied to the logic P310. Logic P3 generates high brake pressure signal P5 at low speed, P=P1+P3, PB=P
It becomes B1+PB3. This makes it possible to compensate for insufficient braking force due to a decrease in the static friction coefficient of the carbon brake.

The rotation speed S detected by the wheel rotation sensor 21 is based on logic P4.
111C is added. The logic P4 is equivalent to a normal anti-skid function that generates the P4 signal based on the wheel skid signal ΔS, but is housed in the control box 7 and the brake system is simplified.

〔Effect of the invention〕

In short, according to the present invention, a brake pedal that does not displace even when a pedal force is applied, a force sensor that emits a signal according to the magnitude of the force applied to the brake pedal, a manual controller that emits an appropriate deceleration signal, and a wheel a wheel rotation sensor that detects the rotational speed signal of the wheel rotation sensor; an integrator that outputs the integral value of the speed signal of the wheel rotation sensor; a brake control box that emits a brake signal based on a corresponding relational expression;
Equipped with a pressure control valve that controls hydraulic pressure to the brake cylinder according to the output of the brake control box, it eliminates the need for brake pedal displacement and has a compact cock bit, making it the perfect pedal for pilot feeling. It is possible to obtain the relationship between pedal force and braking, and it is also possible to perform braking using a manual switch other than the pedal force, and the brakes are automatically activated upon landing to minimize the sliding distance.Furthermore, the static friction coefficient of the carbon brake The present invention is industrially extremely useful because it provides a brake control device that can compensate for the prekinesia caused by the drop.

[Brief explanation of drawings]

FIG. 1 shows an embodiment in which the present invention is applied to an aircraft brake control device, and FIG. 1A is a side view of the aircraft, and FIG.
B) is a system diagram of the brake control device. FIG. 2 shows a conventional brake control device, where (A) is a side view of an aircraft, and FIG. 2 (CB) is a system diagram of the brake control device. 1... Aircraft, 2... Main landing gear, 3... Wheels, 4...
・Pilot, 5... Brake pedal, 6... Force sensor +, 7... Brake control box, 8...
...Logic P, 9...Logic P2.10...Logic P 11...Logic P4,123 %...Manual controller, 13...Auto switch, 14...Adder, 15,16 ...GAS switch, 17...Pressure control valve, 18...Hydraulic pressure source, 19...Pressure oil piping, 20...Brake cylinder, 21...Wheel rotation sensor, 22...Integrator ,
23...Electric wire.

Claims (1)

[Scope of Claims] A brake pedal that does not displace even when a pedal force is applied, a force sensor that emits a signal according to the magnitude of the force applied to the brake pedal, a manual controller that emits an appropriate deceleration signal, and a wheel controller that emits an appropriate deceleration signal. A wheel rotation sensor that detects a rotation speed signal, an integrator that outputs an integral value of the speed signal of the wheel rotation sensor, and a sensor that receives signals from the force sensor, manual controller, wheel rotation sensor, and integrator and responds to each signal. A brake control device comprising: a brake control box that issues a brake signal based on a relational formula; and a pressure control valve that controls hydraulic pressure to a brake cylinder according to the output of the brake control box.