Automatic brake switch of airplane

Abstract

The utility model provides an automatic brake switch of an airplane, which can finely adjust speed reduction rates of different gears. Comprising a switch panel; a knob; the gear circuit comprises a plurality of gear switches which are opened and closed according to the position of the knob, the plurality of gear switches are respectively connected to a brake control unit through different circuit channels, the gear speed reduction rate fine-tuning turntable is arranged below the knob and is provided with a turntable indicating strip, and the turntable indicating strip is arranged on the gear speed reduction rate fine-tuning turntable. The rotating disc indicating strip can rotate relative to the switch panel to the position where the rotating disc indicating strip is aligned with the scales. The turntable circuit comprises a slide rheostat, the resistance value of the slide rheostat is changed according to the position of the gear speed reduction rate fine adjustment turntable, and the slide rheostat is connected with a brake control unit in series; the brake control unit carries out fine adjustment on the speed reduction rates corresponding to the multiple gears according to the voltages corresponding to the different circuit channels in the gear circuit and the voltages corresponding to the slide rheostats in the rotating disc circuit.

Description

TECHNICAL FIELD

[0001] The utility model relates to an automatic brake switch of an airplane. BACKGROUND

[0002] In the past, the deceleration gears of the automatic brake switch of a civil airplane are fixed, for example, the automatic brake switch of a certain Boeing airplane adopts a knob type, and has 7 gears, which are OFF gear, RTO gear, DISARM gear, 1, 2, 3, 4, and MAX gear, or for example, the automatic brake switch of a certain Airbus airplane adopts a press-in type, and has 3 deceleration gears, which are LO gear, MED gear, and MAX gear.

[0003] The deceleration rate of the above-mentioned automatic brake switch is fixed after the gear is adjusted, for example, if the automatic brake switch is adjusted to MAX gear, the deceleration rate of the airplane is kept at MAX gear.

[0004] However, in actual situation, the deceleration rate of the airplane on the runway may fluctuate due to different states of the climate and runway, and therefore, the deceleration rate of the airplane at a specific gear needs to be fine-tuned according to the specific situation. SUMMARY

[0005] The utility model is completed in view of the above-mentioned technical problem, and aims to provide an automatic brake switch of an airplane, which can fine-tune the deceleration rate of different gears.

[0006] In order to achieve the above-mentioned purpose, the first aspect of the utility model provides an automatic brake switch of an airplane, which comprises: a switch panel, the switch panel is formed with a plurality of marks for indicating a plurality of gears and a plurality of scales for indicating the accuracy of fine-tuning; a knob, the knob has a knob indication strip, and can be rotated to the position where the knob indication strip aligns with a plurality of marks relative to the switch panel; and a gear circuit, the gear circuit comprises a plurality of gear switches which are opened and closed according to the position of the knob, and the plurality of gear switches are connected to a brake control unit via different circuit channels, wherein, further comprising: a gear deceleration rate fine-tuning dial, the gear deceleration rate fine-tuning dial is arranged below the knob, has a dial indication strip, and can be rotated to the position where the dial indication strip aligns with a plurality of scales relative to the switch panel; and a dial circuit, the dial circuit comprises a sliding rheostat which changes the resistance value according to the position of the gear deceleration rate fine-tuning dial, the sliding rheostat is connected in series with the brake control unit, and the brake control unit fine-tunes the deceleration rate corresponding to a plurality of gears according to the voltage corresponding to the different circuit channels in the gear circuit and the voltage corresponding to the sliding rheostat in the dial circuit.

[0007] According to the above structure, the reduction rate can be further fine-tuned by the gear reduction rate fine-tuning dial after the reduction rate is determined by the knob.

[0008] The airplane automatic brake switch of the second aspect of the present application is based on the airplane automatic brake switch of the first aspect of the present application, and supposing that the voltage inputted by the different circuit channels of the gear circuit to the brake control unit is set as V1, the corresponding reduction rate is set as Vf1, supposing that the voltage inputted by the circuit where the sliding resistor of the dial circuit is located to the brake control unit is set as V2, the corresponding reduction rate percentage is set as K (-10%≤K≤+10%), and the output of the brake control unit is set as the final reduction rate Vf', then the final reduction rate Vf' satisfies Vf'=Vf1(1+K).

[0009] According to the above structure, the reduction rate can be reliably fine-tuned by the control unit.

[0010] The airplane automatic brake switch of the third aspect of the present application is based on the airplane automatic brake switch of the second aspect of the present application, and the knob indicator bar and the dial indicator bar contain fluorescent materials.

[0011] According to the above structure, since the knob indicator bar and the dial indicator bar contain fluorescent materials, the gear of the knob can be recognized even under night navigation conditions. BRIEF DESCRIPTION OF DRAWINGS

[0012] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly introduced. Obviously, the drawings in the following description are only some embodiments of the present application, and other drawings can also be obtained by those skilled in the art without creative labor on the basis of these drawings.

[0013] Figure 1 is a schematic diagram showing the external structure of the airplane automatic brake switch of the present application.

[0014] Figure 2 is a schematic diagram showing the internal structure of the airplane automatic brake switch of the present application.

[0015] Figure 3 is a schematic diagram showing the circuit structure of the knob and the gear reduction rate fine-tuning dial of the airplane automatic brake switch of the present application.

[0016] Figure 4 is a schematic diagram showing the reduction rate fine-tuning process realized by the knob and the gear reduction rate fine-tuning dial of the airplane automatic brake switch of the present application.

[0017] (Symbol explanation)

[0018] 100 automatic airplane brake switch

[0019] 1 switch panel

[0020] 11 scale

[0021] 2 knob

[0022] 21 front end

[0023] 211 knob indication bar

[0024] 22 base end

[0025] 23 knob fixing rod

[0026] 24 knob circuit

[0027] 25 knob circuit passage switch

[0028] 3 gear reduction rate fine adjustment dial

[0029] 31 dial indication bar

[0030] 32 dial fixing rod

[0031] 33 dial circuit

[0032] 331 sliding rheostat

[0033] 332 rheostat support rod

[0034] 4 brake control unit

[0035] 41 knob signal processing circuit

[0036] 42 reduction rate fine adjustment dial signal processing circuit

[0037] 43 reduction rate processing module DETAILED DESCRIPTION

[0038] Hereinafter, referring to Figures 1 to 4 The embodiments of the automatic airplane brake switch of the present application are described. Figure 1 is a schematic diagram showing the external structure of the automatic airplane brake switch of the present application.

[0039] Figure 2 is a schematic diagram showing the internal structure of the automatic airplane brake switch of the present application. Figure 3 is a schematic diagram showing the circuit structure of the knob and the gear reduction rate fine adjustment dial of the automatic airplane brake switch of the present application. Figure 4is a schematic view showing a gear reduction rate fine adjustment process realized by the knob of the airplane automatic brake switch and the gear reduction rate fine adjustment dial of the present application. The above-mentioned Figure 1 Figure 4 are all the diagrams of the components related to the present application, and the diagrams of other components are omitted.

[0040] (first embodiment)

[0041] (structure of the airplane automatic brake switch 100)

[0042] As shown in Figures 1 to 3 , in the present embodiment, the airplane automatic brake switch 100 comprises: a switch panel 1, which is formed with marks indicating RTO gear, OFF gear, LO gear, MED gear and HI gear, wherein the "RTO gear" is the gear for interrupting takeoff of the airplane on the ground, the "OFF gear" is the airplane automatic brake off / cancel gear, the "LO gear, MED gear and HI gear" are the low, medium and high gears of the landing automatic brake reduction rate of the airplane, and a plurality of scales 11 of the precision for fine adjustment of the above-mentioned five gears are formed; a knob 2, which is formed in a substantially long strip shape, comprises a front end portion 21, a base end portion 22, a knob fixing rod 23 and a knob circuit 24, the front end portion 21 is formed in a shape with a thin front end relative to the base end portion 22, and a knob indicating strip 211 containing fluorescent material is formed on the front end portion 21, the knob 2 is electrically connected to the knob circuit 24 via the knob fixing rod 23; a gear reduction rate fine adjustment dial 3, which is arranged below the knob 2 and is provided with an arrow-shaped dial indicating strip 31 containing fluorescent material, the gear reduction rate fine adjustment dial 3 is connected to a sliding rheostat 331 via a dial fixing rod 32; and a brake control unit 4, which is electrically connected with the knob circuit 24 and the dial circuit 33.

[0043] Regarding the circuit structure of the knob 2 and the gear reduction rate fine adjustment dial 3 and its working principle, as shown in Figure 3 and Figure 4As shown, the rotation of the knob 2 drives the opening and closing of the knob circuit channel switch 25 to select different circuit channels, and different circuit channels output different voltages V1, which are input to the knob signal processing circuit 41 of the brake control unit 4, which converts the voltage V1 into different deceleration rates Vf1 and inputs them to the deceleration rate module 43. On this basis, when the operator operates the gear deceleration rate fine adjustment dial 3 to rotate, it drives the slider of the sliding rheostat 331 to move, the resistance value changes, and different voltages V2 are generated, which are input to the deceleration rate fine adjustment dial signal processing circuit 42 of the brake control unit 4, which converts the voltage V2 into different deceleration rate fine adjustment percentages K, which satisfy -10%≤K≤+10%, and are input to the deceleration rate module 43. The deceleration rate module 43 calculates the final deceleration rate Vf' through the model Vf=Vf1(1+K), and outputs it to the brake actuator (not shown) to make the brake actuator brake at the final deceleration rate Vf'.

[0044] In addition, as shown in Figure 1 The knob indicator bar 211 and the dial indicator bar 31 both contain fluorescent materials, so the gear of the knob can be identified even in night navigation conditions.

[0045] (Technical effects of the embodiment)

[0046] As described above, by continuing to rotate the gear deceleration rate fine adjustment dial after the knob is rotated to a specific gear (for example, the LO gear), the deceleration rate of the specific gear is further fine adjusted. In addition, since the knob indicator bar and the dial indicator bar contain fluorescent materials, the gear of the knob can be identified even in night navigation conditions.

[0047] The above, in order to make the purpose, technical scheme and advantages of the embodiment of the utility model more clear, the technical scheme of the embodiment of the utility model is clearly and completely described with the drawings in the embodiment of the utility model, obviously, the described embodiment is a part of the embodiment of the utility model, rather than all the embodiment. Based on the embodiment of the utility model, all other embodiments obtained by the person skilled in the art without making creative labor belong to the range to be protected by the utility model.

[0048] In the above embodiment, the knob 2 has only five gears, but the utility model is not limited thereto, and can also have other numbers of gears.

[0049] In the above embodiment, the knob indicator bar and the dial indicator bar contain fluorescent materials, but the utility model is not limited thereto, and can also have fluorescent strips pasted.

Claims

1. An automatic brake switch for an aircraft, comprising: a switch panel formed with a plurality of marks for indicating a plurality of gears and a plurality of scales for indicating the accuracy of fine adjustment; a knob having a knob indicator bar and rotatable relative to the switch panel to a position in which the knob indicator bar aligns with a plurality of the marks; and a gear circuit including a plurality of gear switches opened and closed in accordance with the position of the knob, the plurality of gear switches connected to a brake control unit via different circuit paths, characterized by further comprising: a gear deceleration rate fine adjustment dial disposed below the knob, having a dial indicator bar and rotatable relative to the switch panel to a position in which the dial indicator bar aligns with a plurality of the scales; and a dial circuit including a slide rheostat changing the resistance value in accordance with the position of the gear deceleration rate fine adjustment dial, the slide rheostat connected in series to the brake control unit, the brake control unit fine adjusting the deceleration rate corresponding to a plurality of gears in accordance with the voltage corresponding to the different circuit paths in the gear circuit and the voltage corresponding to the slide rheostat in the dial circuit.

2. The automatic brake switch for an aircraft according to claim 1, wherein assuming that the voltage inputted from the different circuit paths of the gear circuit to the brake control unit is set as VI, and the corresponding deceleration rate is set as Vfl, assuming that the voltage inputted from the circuit in which the slide rheostat of the dial circuit is located to the brake control unit is set as V2, and the corresponding deceleration rate percentage is set as K (-10% ≤ K ≤ +10%), and the output of the brake control unit is set as V3, then V3 = Vfl (1 + K) is satisfied.

3. The automatic brake switch for an aircraft according to claim 2, wherein the knob indicator bar and the dial indicator bar contain fluorescent material. ​

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