CN219056596U

CN219056596U - Rotor ice preventing and removing blade detection tool

Info

Publication number: CN219056596U
Application number: CN202223552635.1U
Authority: CN
Inventors: 汪佳; 陈松; 周为
Original assignee: Wuhan Aviation Instrument Co Ltd
Current assignee: Wuhan Aviation Instrument Co Ltd
Priority date: 2022-12-28
Filing date: 2022-12-28
Publication date: 2023-05-23
Anticipated expiration: 2032-12-28

Abstract

The utility model discloses a rotor anti-icing and anti-deicing blade detection tool. The device comprises main blade detection equipment and in-cabin detection equipment, wherein the main blade detection equipment is installed on an aircraft and is connected with a helicopter rotor main blade and a main blade collecting ring, the installation position of the main blade distributor on the aircraft is the same, and the in-cabin detection equipment is placed in an aircraft cabin and is connected with the main blade collecting ring on the aircraft. The utility model meets the requirements of automatic fault detection and positioning detection of the aircraft on the ground under the dynamic state of the heating component in the main blade.

Description

Rotor ice preventing and removing blade detection tool

Technical Field

The utility model relates to the technical field of detection devices, in particular to a rotor anti-icing blade detection tool.

Background

In a helicopter rotor wing ice control system, a detection method of a blade heating assembly is ground static detection, namely, the blade is detached, and a detector measures whether the resistance value of the heating assembly accords with a rule through an electric connector port of the blade by using a three-purpose meter, so that whether the blade heating assembly is good is judged. However, in the actual use situation, the ground static detection of the blade heating assembly is qualified, and the heating assembly is broken or leaked in dynamic states such as a driving car or the air.

In order to meet the detection of the main blade under the dynamic state, the actual performance of the heating assembly under the working state of the main blade is further detected, and the rotor anti-icing blade detection tool is designed and developed.

Disclosure of Invention

The purpose of the utility model is that: the utility model provides a rotor prevents deicing paddle and detects frock. The utility model meets the requirements of automatic fault detection and positioning detection of the aircraft on the ground under the dynamic state of the heating component in the main blade.

The technical scheme of the utility model is as follows: the main blade detection equipment is arranged on an aircraft and is connected with a helicopter rotor main blade and a main blade collecting ring, the installation position of the main blade collecting ring is the same as that of a main blade distributor on the aircraft, and the in-cabin detection equipment is arranged in an aircraft cabin and is connected with the main blade collecting ring on the aircraft;

the main blade detection equipment consists of a shell and an internal detection module, wherein the shell is of a disc-shaped structure, the side surface of the disc-shaped structure is uniformly distributed with an electric interface I connected with blades, and the bottom of the disc-shaped structure is provided with an electric interface II connected with a main blade collecting ring of an airplane; the internal detection module comprises a main blade switching circuit and a main blade detection circuit, and the blade switching circuit is used for switching and detecting the main blade of the aircraft; the main blade detection circuit is used for detecting the fault condition of the heating component in the main blade;

the in-cabin detection equipment comprises a case, wherein a display module is arranged at the top of the case, a main control module and a power module are arranged in the case, the main control module is connected with the display module, and an electrical interface III arranged at the back of the case is connected with a main propeller collecting ring on the aircraft; the main control module is used for sending a control instruction to the main blade detection equipment so as to enable the main blade detection equipment to switch detection logic of the main blade to be detected and the heating component inside the main blade according to a preset program, and fault judgment and positioning are carried out according to the acquired data, and comprises a programmable logic controller and an A/D conversion module, wherein the programmable logic controller is connected with the A/D conversion module through a special port of the programmable logic controller.

In the rotor anti-deicing blade detection tool, the main blade switching circuit comprises a decoder, an inverter, a resistor, a triode and a connector P1, wherein a signal input by the connector P1 is connected with an input pin of the decoder U1, an output pin of the decoder U1 is connected with an input pin of the inverter U2 in a one-to-one correspondence manner, a 1Y pin of an output end of the inverter U2 is connected with the resistor R1, the other end of the resistor R1 is connected to a base electrode of the triode Q1, a collector electrode of the triode Q1 is connected with a coil negative end of the relay K1, a coil positive end of the relay K1 is connected with a 5V power supply, and an emitter electrode of the triode Q1 is grounded; and other output pins of the inverter U2 are respectively connected with a resistor, a triode and a relay coil.

In the rotor anti-deicing blade detection tool, the main blade detection circuit comprises a connector P2, a double-contact relay and a resistor, wherein a pin 2 of the connector P2 is connected with negative terminals of a relay coil K1, the relay coil K2 and a relay coil K3, and positive ends of the relay coil K1, the relay coil K2 and the relay coil K3 are connected with a 5V power supply; the neutral contact 1 of the relay K1 is connected with the resistor R1 and is connected with the pin 1 of the connector P2, the other end of the resistor R1 is grounded, the normally closed contact 1 of the relay K1 is connected with the pin 14 of the connector P1, and the normally open contact 1 of the relay K1 is connected with the pin 15 of the connector P1; the neutral contact 1 and the neutral contact 2 of the relay K2 are respectively connected with the pin 10 and the pin 13 of the connector P1, the normally closed contact 1 and the normally closed contact 2 of the relay K2 are respectively connected with the pin 8 and the pin 11 of the connector P1, and the normally open contact 1 and the normally open contact 2 of the relay K2 are respectively connected with the pin 9 and the pin 12 of the connector P1; the neutral contact 1 and the neutral contact 2 of the relay K3 are respectively connected with the pin 4 and the pin 7 of the connector P1, the normally closed contact 1 and the normally closed contact 2 of the relay K3 are respectively connected with the pin 2 and the pin 5 of the connector P1, and the normally open contact 1 and the normally open contact 2 of the relay K3 are respectively connected with the pin 3 and the pin 6 of the connector P1; pin 1 of connector P1 is connected to 5V power supply; the circuit corresponds to one blade to be detected, and the detection circuit structures and the connection structures corresponding to the rest main blades are the same as those described above.

In the rotor anti-icing blade detection tool, the blade switching module and the main blade detection module are arranged on a circuit board.

In the rotor wing deicing blade detection tool, the internal detection module structure layout adopts a symmetrical layout, and the component layout is uniformly distributed with reference to the center point.

In the rotor anti-icing and anti-deicing blade detection tool, the display module provides an operation interface and a result display interface for a user, can check detection data and communicates with the main control module through the RS 422.

The utility model has the advantages that: the rotor wing deicing prevention blade detection tool can realize automatic detection and switching of all main blade heating assemblies through a switching control circuit formed by the decoder and the relay, and can realize automatic fault detection and positioning of all main blade heating assemblies in a working state when a helicopter is driven on the ground by adopting an interface with the same installation structure as a main blade distributor on an airplane.

Drawings

FIG. 1 is a schematic diagram showing the cross-linking of equipment during operation of the rotor anti-icing blade detection tool of the present utility model;

FIG. 2 is a schematic external view showing an assembly main blade detection apparatus of the present utility model;

FIG. 3 is a view showing the external appearance of the in-module inspection apparatus of the present utility model;

FIG. 4 is a schematic view showing the internal structure of the in-module inspection apparatus of the present utility model;

FIG. 5 is a schematic view showing the structure of a rear panel of the in-module inspection apparatus of the present utility model;

FIG. 6 is a schematic diagram of a main blade switching circuit illustrating the present utility model;

FIG. 7 is a schematic diagram of a main blade detection circuit illustrating the present utility model;

FIG. 8 is a control line connection schematic diagram illustrating the present utility model;

FIG. 9 is an equivalent schematic diagram showing the heating assembly sampling principle of the present utility model;

FIG. 10 is a schematic diagram showing a test flow of the present utility model;

FIG. 11 is a diagram of a human-machine interface master interface showing the present utility model.

Detailed Description

The utility model is further illustrated by the following figures and examples, which are not intended to be limiting.

Example 1. The rotor wing ice preventing and removing blade detection tool comprises main blade detection equipment and cabin detection equipment, wherein the main blade detection equipment is arranged on an aircraft, is connected with a helicopter rotor wing main blade and a main blade collecting ring, is the same as the installation position of a main blade distributor on the aircraft, and is arranged in a cabin of the aircraft and is connected with the main blade collecting ring on the aircraft;

the main blade detection equipment consists of a shell and an internal detection module, wherein the shell 1 is of a disc-shaped structure, the side surface of the disc-shaped structure is uniformly distributed with an electric interface I2 connected with blades, and the bottom of the disc-shaped structure is provided with an electric interface II 3 connected with a main blade collecting ring of an airplane; the internal detection module comprises a main blade switching circuit and a main blade detection circuit, and the blade switching circuit is used for switching and detecting the main blade of the aircraft; and the main blade detection circuit is used for detecting the fault condition of the heating component in the main blade.

The in-cabin detection equipment comprises a case 4, a display module 5 is arranged at the top of the case 4, a main control module 6 and a power module 7 are arranged in the case 4, the main control module 6 is connected with the display module 5, and an electrical interface III 8 arranged at the back of the case 4 is connected with a main propeller collecting ring on the aircraft; the main control module 6 is configured to send a control instruction to the main blade detection device to switch detection logic of the main blade to be detected and the heating component inside the main blade according to a preset program, and perform fault judgment and positioning according to the collected data, where the main control module 6 includes a programmable logic controller 61 and an a/D conversion module 62, and the programmable logic controller 61 is connected to the a/D conversion module 62 through a dedicated port thereof.

The main blade switching circuit comprises a decoder, an inverter, a resistor, a triode and a connector P1, wherein a signal input by the connector P1 is connected with an input pin of the decoder U1, an output pin of the decoder U1 is connected with an input pin of the inverter U2 in a one-to-one correspondence manner, a 1Y pin at the output end of the inverter U2 is connected with the resistor R1, the other end of the resistor R1 is connected to a base electrode of the triode Q1, a collector electrode of the triode Q1 is connected with a coil negative end of the relay K1, a coil positive end of the relay K1 is connected with a 5V power supply, and an emitter electrode of the triode Q1 is grounded; other output pins of the inverter U2 are respectively connected with a resistor, a triode and a relay coil;

the main blade detection circuit comprises a connector P2, a double-contact relay and a resistor, wherein a pin 2 of the connector P2 is connected with negative terminals of a relay coil K1, the relay coil K2 and a relay coil K3, and positive terminals of the relay coil K1, the relay coil K2 and the relay coil K3 are connected with a 5V power supply; the neutral contact 1 of the relay K1 is connected with the resistor R1 and is connected with the pin 1 of the connector P2, the other end of the resistor R1 is grounded, the normally closed contact 1 of the relay K1 is connected with the pin 14 of the connector P1, and the normally open contact 1 of the relay K1 is connected with the pin 15 of the connector P1; the neutral contact 1 and the neutral contact 2 of the relay K2 are respectively connected with the pin 10 and the pin 13 of the connector P1, the normally closed contact 1 and the normally closed contact 2 of the relay K2 are respectively connected with the pin 8 and the pin 11 of the connector P1, and the normally open contact 1 and the normally open contact 2 of the relay K2 are respectively connected with the pin 9 and the pin 12 of the connector P1; the neutral contact 1 and the neutral contact 2 of the relay K3 are respectively connected with the pin 4 and the pin 7 of the connector P1, the normally closed contact 1 and the normally closed contact 2 of the relay K3 are respectively connected with the pin 2 and the pin 5 of the connector P1, and the normally open contact 1 and the normally open contact 2 of the relay K3 are respectively connected with the pin 3 and the pin 6 of the connector P1; pin 1 of connector P1 is connected to 5V power supply; the circuit corresponds to one blade to be detected, and the detection circuit structures and the connection structures corresponding to the rest main blades are the same as those described above.

The blade switching module and the main blade detection module are arranged on a circuit board.

The internal detection module structure layout adopts a symmetrical layout, and the component layout is uniformly distributed with reference to the center point.

The display module provides an operation interface and a result display interface for a user, can check detection data and communicates with the main control module through the RS 422.

The original helicopter main blade distributor is replaced by the assembly main blade detection equipment in situ, the structural consistency of the helicopter is guaranteed, the electromagnetic relay module in the main blade detection equipment is controlled by the assembly cabin detection equipment to realize the switching of different heating areas of the blade heating assembly, and meanwhile, the internal detection module consisting of a 38 decoder and an electromagnetic relay is used for realizing the switching of blade detection. And loading sampling voltage signals at two ends of a heating element of the blade to be detected on the aircraft, and judging the fault of the blade heating assembly and the positioning of the fault blade through the value of the sampling voltage signals. The automatic fault detection and positioning of the blade heating assembly in the dynamic state can be realized under the condition that the helicopter is driven on the ground.

The rotor deicing blade detection tool comprises two components of main blade detection equipment and in-cabin detection equipment, wherein the main blade detection equipment and the in-cabin detection equipment are connected through a main blade collecting ring on an aircraft, the connection relationship is that the main blade detection equipment is connected with the main blade collecting ring on the aircraft through an electric interface II 3 and a screw, and meanwhile, the main blade detection equipment is connected with the main blade through an electric interface I2, the in-cabin detection equipment is connected with the electric interface of the main blade collecting ring on the aircraft through the electric interface II 3 and a special test cable, and the cross-linking of the equipment is shown in an opinion figure 1-figure.

The operator removes the main blade distributor on the aircraft, installs the main blade detection device in the same manner, and connects the in-cabin test device and the main blade slip ring on the aircraft using the cable. After preparation, clicking one-key detection on a test interface of a display module 5 at the top of the cabin detection equipment, transmitting detection instructions from the display module 5 to a main control module 6, sequentially sending control signals to main blade detection equipment by the main control module 6, controlling a main blade switching circuit to be connected with a corresponding relay module, and starting detection from a number a blade. Simultaneously, the main control module 6 sends out a blade detection control signal, a relay module of the main blade detection circuit is driven to load 5V direct current sampling voltages onto blade heating assemblies of different ports respectively, the collected sampling voltages are returned to the A/D conversion module 62 of the main control module 6 in the in-cabin detection equipment, fault state interpretation of the blade heating assemblies is achieved, and interpretation results are displayed on the display module 5. and after the detection of the blade A is finished, the main control module 6 sends out a control instruction to switch to the blade B for detection until all the blades are detected.

The interpretation of the fault state is: the sampling voltage is 5V direct current voltage, and when the heating component is normal, the return sampling voltage is about 5V; if the heating component has a short circuit fault, the return sampling voltage should be about 0V; if the heating component is in leakage fault, the sampling voltage is more than 0V and less than 5V.

Claims

1. The utility model provides a rotor control ice paddle detects frock which characterized in that: the device comprises main blade detection equipment and cabin inner detection equipment, wherein the main blade detection equipment is arranged on an aircraft and is connected with a helicopter rotor main blade and a main blade collecting ring, the installation position of the main blade detecting equipment is the same as that of a main blade distributor on the aircraft, and the cabin inner detection equipment is arranged in a cabin of the aircraft and is connected with the main blade collecting ring on the aircraft;

the main blade detection equipment consists of a shell and an internal detection module, wherein the shell (1) is of a disc-shaped structure, electric interfaces I (2) connected with blades are uniformly distributed on the side surface of the disc-shaped structure, and an electric interface II (3) connected with a main blade collecting ring of an airplane is arranged at the bottom of the disc-shaped structure; the internal detection module comprises a main blade switching circuit and a main blade detection circuit, and the blade switching circuit is used for switching and detecting the main blade of the aircraft; the main blade detection circuit is used for detecting the fault condition of the heating component in the main blade;

the cabin interior detection equipment comprises a chassis (4), a display module (5) is arranged at the top of the chassis (4), a main control module (6) and a power module (7) are arranged in the chassis (4), the main control module (6) is connected with the display module (5), and an electrical interface III (8) arranged at the back of the chassis (4) is connected with a main propeller collecting ring on an airplane; the main control module (6) is used for sending a control instruction to the main blade detection equipment to enable the main blade detection equipment to switch detection logic of the main blade to be detected and the heating component inside the main blade according to a preset program, fault judgment and positioning are carried out according to collected data, the main control module (6) comprises a programmable logic controller (61) and an A/D conversion module (62), and the programmable logic controller (61) is connected with the A/D conversion module (62) through a special port thereof.

2. The rotor anti-icing and anti-deicing blade detection tool of claim 1, wherein: the main blade switching circuit comprises a decoder, an inverter, a resistor, a triode and a connector P1, wherein a signal input by the connector P1 is connected with an input pin of the decoder U1, an output pin of the decoder U1 is connected with an input pin of the inverter U2 in a one-to-one correspondence manner, a 1Y pin at the output end of the inverter U2 is connected with the resistor R1, the other end of the resistor R1 is connected to a base electrode of the triode Q1, a collector electrode of the triode Q1 is connected with a coil negative end of the relay K1, a coil positive end of the relay K1 is connected with a 5V power supply, and an emitter electrode of the triode Q1 is grounded; and other output pins of the inverter U2 are respectively connected with a resistor, a triode and a relay coil.

3. The rotor wing ice control blade detection tool according to claim 2, wherein: the main blade detection circuit comprises a connector P2, a double-contact relay and a resistor, wherein a pin 2 of the connector P2 is connected with negative terminals of a relay coil K1, the relay coil K2 and a relay coil K3, and positive terminals of the relay coil K1, the relay coil K2 and the relay coil K3 are connected with a 5V power supply; the neutral contact 1 of the relay K1 is connected with the resistor R1 and is connected with the pin 1 of the connector P2, the other end of the resistor R1 is grounded, the normally closed contact 1 of the relay K1 is connected with the pin 14 of the connector P1, and the normally open contact 1 of the relay K1 is connected with the pin 15 of the connector P1; the neutral contact 1 and the neutral contact 2 of the relay K2 are respectively connected with the pin 10 and the pin 13 of the connector P1, the normally closed contact 1 and the normally closed contact 2 of the relay K2 are respectively connected with the pin 8 and the pin 11 of the connector P1, and the normally open contact 1 and the normally open contact 2 of the relay K2 are respectively connected with the pin 9 and the pin 12 of the connector P1; the neutral contact 1 and the neutral contact 2 of the relay K3 are respectively connected with the pin 4 and the pin 7 of the connector P1, the normally closed contact 1 and the normally closed contact 2 of the relay K3 are respectively connected with the pin 2 and the pin 5 of the connector P1, and the normally open contact 1 and the normally open contact 2 of the relay K3 are respectively connected with the pin 3 and the pin 6 of the connector P1; pin 1 of connector P1 is connected to 5V power supply; the circuit corresponds to one blade to be detected, and the detection circuit structures and the connection structures corresponding to the rest main blades are the same as those described above.

4. The rotor anti-icing and anti-deicing blade detection tool of claim 1, wherein: the paddle switching circuit and the main paddle detection circuit are arranged on a circuit board.

5. The rotor anti-icing and anti-deicing blade detection tool of claim 4, wherein: the internal detection module structure layout adopts a symmetrical layout, and the component layout is uniformly distributed with reference to the center point.

6. The rotor anti-icing and anti-deicing blade detection tool of claim 1, wherein: the display module provides an operation interface and a result display interface for a user, can check detection data and communicates with the main control module through the RS 422.