A helicopter attitude assistance warning device and method

Abstract

The present invention belongs to the field of helicopter design, and particularly relates to a helicopter attitude auxiliary warning device and method based on a mercury switch. At present, on helicopters, the main sources of attitude signal acquisition are mechanical gyroscope groups, fiber optic gyroscope groups, laser gyroscope groups, etc., and there is no warning device for attitude overrun. In the present invention, a horizontal mounting plate is provided on the base, and a first mercury switch and a second mercury switch are mounted on the top of the mounting plate in a cross-shaped layout. The number of the first mercury switches is four, which are axially symmetrically distributed at the outer cross positions and have an outward inclination angle of 20-30°; the number of the second mercury switches is four, which are axially symmetrically distributed at the inner cross positions and have an outward inclination angle of 40-50°; the longitudinal first mercury switches and the second mercury switches are in the same direction as the heading; the first mercury switches and the second mercury switches are connected to a signal lamp and a buzzer through wires. It has a small volume, low cost, is easy to install, and the influence on the aircraft structure and electrical performance can be ignored.

Description

Technical Field

[0001] The present invention belongs to the field of helicopter design, and particularly relates to a helicopter attitude auxiliary warning device and method based on a mercury switch. Background Art

[0002] When a helicopter performs different flight maneuvers during flight, its attitude will change differently with external disturbances and the pilot's operations. When the helicopter attitude deviates too much from the reference, the flight safety factor of the helicopter decreases, and safety accidents are likely to occur. Therefore, the helicopter flight attitude should be kept within a certain range as much as possible, and when it exceeds the range, there should be a warning device to prompt the pilot that the helicopter is currently in a dangerous attitude and to raise vigilance.

[0003] Currently, on helicopters, the main sources of attitude signal acquisition are mechanical gyro groups, fiber optic gyro groups, and laser gyro groups, etc. These gyro groups are involved in helicopter autopilot and navigation and are displayed on the screen through an integrated display system. Generally, pilots do not pay attention to the helicopter attitude information on the display in real time. The pilot's maintenance of the aircraft attitude is based on the pilot's own feeling, and most existing helicopters do not have an attitude overrun warning device. Summary of the Invention

[0004] The object of the present invention: To propose a helicopter attitude auxiliary warning device and method based on a mercury switch, which sends a signal to the signal lamp and buzzer on the central instrument panel of the aircraft when the helicopter attitude deviates too much, the signal lamp lights up and the buzzer sounds to ensure flight safety.

[0005] The technical solution of the present invention: A helicopter attitude auxiliary warning device, which has a horizontal mounting plate on the base. The first mercury switch and the second mercury switch are mounted on the top of the mounting plate in a cross-shaped layout. The number of the first mercury switches is four, which are axially symmetrically distributed at the outer cross positions, with an outward inclination angle of 20 - 30°; the number of the second mercury switches is four, which are axially symmetrically distributed at the inner cross positions, with an outward inclination angle of 40 - 50°; the longitudinal first mercury switches and the second mercury switches are in the same direction as the course; the first mercury switches 9 and the second mercury switches are connected to the signal lamp and the buzzer through wires.

[0006] Further, the base includes an upper base and a lower base, and there is a connecting column between the upper base and the lower base. The lower base is mounted on the airframe, and the mounting plate is provided on the upper base.

[0007] Further, the top end of the connecting column has a connecting plate, and is connected to the upper base through the connecting plate.

[0008] Further, the lower end of the connecting column has a ball joint structure, and is mounted in the lower base through the ball joint structure and the angle is locked by a fixing knob.

[0009] Furthermore, an electrical connector is provided on the upper base, and the wires are connected through the electrical connector.

[0010] Furthermore, the tilting angle warning is achieved through the first mercury switch and the second mercury switch longitudinally on the base, and the roll angle warning is achieved through the first mercury switch and the second mercury switch transversely.

[0011] Furthermore, the outward tilting angle of the first mercury switch is 20°.

[0012] Furthermore, the outward tilting angle of the second mercury switch is 45°.

[0013] Furthermore, when the first mercury switch is connected, the signal lamp is yellow; when the second mercury switch is connected, the signal lamp is red.

[0014] The present invention also provides a method for assisting in warning the attitude of a helicopter. Using the above warning device, the warning device is installed at an appropriate position on the airframe to ensure that the first mercury switch and the second mercury switch longitudinally are consistent with the heading. When the tilting angle or the roll angle reaches the outward tilting angle of the first mercury switch, the yellow signal lamp lights up; when the tilting angle or the roll angle reaches the outward tilting angle of the second mercury switch, the red signal lamp lights up.

[0015] Advantages of the present invention: small volume, low cost, easy to install, and the influence on the aircraft structure and electrical performance can be ignored. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] When read in conjunction with the accompanying drawings, the illustrative examples and the preferred modes of use, other objects and descriptions thereof will be best understood by reference to the following detailed description of the examples of the present invention, wherein:

[0017] Figure 1 is the front view of the overall structure of the auxiliary warning device;

[0018] Figure 2 is the top view of the overall structure of the auxiliary warning device.

[0019] Wherein, 1 - lower base, 2 - fixing knob, 3 - ball joint structure, 4 - connecting column, 5 - connecting plate, 6 - electrical connector, 7 - upper base, 8 - mounting plate, 9 - first mercury switch, 10 - second mercury switch DETAILED DESCRIPTION OF THE EMBODIMENTS

[0020] The disclosed examples will be described more fully with reference to the accompanying drawings, in which some (but not all) of the disclosed examples are shown. In fact, many different examples can be described and these examples should not be construed as limited to the examples set forth herein. Rather, these examples are described so that the present disclosure will be thorough and complete and will fully convey the scope of the present disclosure to those skilled in the art.

[0021] Examples, such as Figure 1 shown, four first mercury switches 9 and four second mercury switches 10 are evenly placed at four positions on the device base at angles of 20° and 45° respectively, as Figure 2 shown, the first mercury switches 9 are on the outer cross and the second mercury switches 10 are on the inner cross. The ball joint structure 3 is adopted so that the device can be adjusted horizontally after installation and is fixed by means of bolt connection on the machine.

[0022] The installation method is as follows: Fix the lower base 1 of the device on the machine by bolts, ensure the position of the bolt installation holes by comparing on the machine, and ensure that the heading of the device is consistent with the heading of the airframe, and the heading deviation does not exceed 1°. Adjust the helicopter to a horizontal state, then adjust the ball joint structure 3 on the lower base 1, and use a positioning instrument to ensure that the lower base 1 is in a horizontal state, and the horizontal deviation does not exceed 1°. After adjustment, rotate the fixing knob 2 to fix the ball joint structure 3. There is an integral connecting column 4 at the upper end of the ball joint structure 3, and a connecting plate 5 at the top of the connecting column 4. An upper base 7 is installed on the upper side of the connecting plate 5. The upper side of the upper base 7 is an installation plate 8, and the first mercury switches 9 and the second mercury switches 10 are installed on the installation plate 8. The signal lamp and the buzzer are installed on the instrument panel and are connected to the electrical connector 6 of the upper base 7 of the device through wires.

[0023] During flight, when the deflection angle of a certain channel or multiple channels of the helicopter attitude exceeds 20° or 45°, the mercury switch corresponding to the channel is turned on, and the voltage signal is transmitted to the signal lamp and the buzzer. The signal lamp lights up and the buzzer sounds.

[0024] In a certain example, the signal lamp is yellow when it exceeds 20° and red when it exceeds 45°.

[0025] The different examples of the systems, devices and methods disclosed herein include various components, features and functions. It should be understood that the various examples of the systems, devices and methods disclosed herein may include any components, features and functions of any one of the other examples of the systems, devices and methods disclosed herein in any combination or any sub-combination, and all such possibilities are intended to fall within the scope of the present invention.

[0026] Descriptions of different advantageous arrangements have been presented for purposes of illustration and description, but the description is not intended to be exclusive or limited to examples of the disclosed forms. Many modifications and variations will be apparent to those of ordinary skill in the art. Additionally, different advantageous examples may describe different advantages compared to other advantageous examples. The selected example or examples are chosen and described in order to best illustrate the principles of the examples, the practical application, and to enable those of ordinary skill in the art to understand the disclosure of various examples that have been made various modifications suitable for the particular uses contemplated.

Claims

1. A helicopter attitude auxiliary warning device, characterized in that: The device has a horizontal mounting plate (8) on the base, and the base includes an upper base (7) and a lower base (1). An electrical connector (6) is provided on the upper base (7), and wires are connected through the electrical connector (6). There is a connecting column (4) between the upper base (7) and the lower base (1). The lower end of the connecting column (4) has a ball joint structure (3), which is installed in the lower base (1) through the ball joint structure (3), and the angle is locked by a fixing knob (2). The lower base (1) is installed on the body, and the mounting plate (8) is provided on the upper base (7); a first mercury switch (9) and a second mercury switch (10) are installed on the top of the mounting plate (8) in a cross-shaped layout. The number of the first mercury switches (9) is four, which are symmetrically distributed at the outer cross positions, and the outward inclination angle is 20 - 30°; the number of the second mercury switches (10) is four, which are symmetrically distributed at the inner cross positions, and the outward inclination angle is 40 - 50°; the longitudinal first mercury switch (9) and the second mercury switch (10) are in the same direction as the heading; the first mercury switch (9) and the second mercury switch (10) are connected to the signal lamp and the buzzer through wires. The tilting angle warning is realized through the longitudinal first mercury switch (9) and the second mercury switch (10), and the roll angle warning is realized through the transverse first mercury switch (9) and the second mercury switch (10).

2. The helicopter attitude auxiliary warning device according to claim 1, wherein: The top end of the connecting column (4) has a connecting plate (5), and is connected to the upper base (7) through the connecting plate (5).

3. The helicopter attitude assistance warning device according to claim 1, characterized in that: The outward inclination angle of the first mercury switch (9) is 20°.

4. The helicopter attitude auxiliary warning device according to claim 1, characterized in that: The outward inclination angle of the second mercury switch (10) is 45°.

5. The helicopter attitude assistance warning device according to claim 1, characterized in that: When the first mercury switch (9) is connected, the signal lamp is yellow; when the second mercury switch (10) is connected, the signal lamp is red.

6. A helicopter attitude assistance warning method, using the warning device as described in any one of claims 1-5, characterized in that: Install the warning device at an appropriate position on the body to ensure that the longitudinal first mercury switch (9) and the second mercury switch (10) are in the same direction as the heading. When the inclination angle or the roll angle reaches the outward inclination angle of the first mercury switch (9), the yellow signal lamp lights up; when the inclination angle or the roll angle reaches the outward inclination angle of the second mercury switch (10), the red signal lamp lights up.

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