CN211060933U

CN211060933U - Airplane backup electronic instrument inertia measurement unit structure body

Info

Publication number: CN211060933U
Application number: CN201921561789.2U
Authority: CN
Inventors: 张海波; 孙延东; 王文涛; 李晶晶; 杨科元
Original assignee: Beijing Andawell Ltd
Current assignee: Beijing Andawell Ltd
Priority date: 2019-09-19
Filing date: 2019-09-19
Publication date: 2020-07-21
Anticipated expiration: 2029-09-19

Abstract

The utility model discloses an inertia measuring unit structure of an electronic instrument for airplane backup, relating to the measuring field of electronic instruments; the unit structure body is of a hexahedral structure and comprises an inertial measurement unit structure support, an atmospheric pressure sensor module, three groups of MEMS accelerometers, a gyroscope circuit, a display module, a signal processing circuit and an atmospheric pipeline channel, wherein the three groups of MEMS accelerometers, the gyroscope circuit, the display module, the signal processing circuit and the atmospheric pipeline channel are respectively arranged on six surfaces of the inertial measurement unit structure support, and the atmospheric pressure sensor module is arranged in the unit structure body. The structural body has high space utilization rate, and the mass and the volume of equipment are effectively reduced; reasonable arrangement, concentrated mass distribution and strong practicability.

Description

Airplane backup electronic instrument inertia measurement unit structure body

Technical Field

The utility model relates to an electronic instrument measures the field, especially relates to a backup electronic instrument inertial measurement unit structure of aircraft.

Background

The airplane backup electronic instrument inertial measurement unit structure is a device for measuring three-axis attitude angle (or angular velocity) and acceleration of an object. The common airplane backup electronic instrument inertia measurement unit structure body comprises a hexahedron and a T-shaped body. The hexahedron guarantees the spatial position relation of three two liang of perpendicular planes of three group MEMS accelerometers and gyroscopes of nearly apex angle, and space utilization is low, and the T type body uses two "T" shape hollow framves as the support of three two liang of perpendicular planes of base member constitution, and space utilization is higher, but two kinds of structures only have inertial measurement unit, do not integrate other functional module.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to provide a space utilization height just can integrate a plurality of functional module's inertia measurement's unit structure body to solve the aforementioned problem that exists among the prior art.

In order to realize the purpose, the utility model discloses a technical scheme as follows:

the utility model provides an aircraft backup electronic instrument inertial measurement unit structure, the unit structure is the hexahedron structure, including inertial measurement unit structure support, atmospheric pressure sensor module, three MEMS accelerometers of group and gyroscope circuit, display module, signal processing circuit, atmosphere pipeline passageway, three MEMS accelerometers of group and gyroscope circuit the display module signal processing circuit with atmosphere pipeline passageway arranges respectively on six faces of unit structure, atmospheric pressure sensor module sets up the inside at the unit structure.

Preferably, the three groups of MEMS accelerometers and gyroscope circuits are mounted on three mutually perpendicular planes sharing a vertex angle, and the display module, the signal processing circuit and the atmospheric duct channel are respectively mounted on the other three planes.

Preferably, the display module is used for displaying the image-text information and adjusting and displaying the information content of the interface.

Preferably, the signal processing circuit is configured to process the atmospheric pressure sensor module, the three sets of MEMS accelerometers and gyroscope circuit signals, and send the processed signals to a display module.

Preferably, the barometric pressure sensor module is used to estimate aircraft speed and altitude data.

Preferably, the atmosphere conduit channel is used to introduce the back-end external atmosphere into the internal atmospheric pressure sensor.

Preferably, the MEMS accelerometer and gyroscope circuits are used for strap-down resolving aircraft motion parameters, three circuit boards where the three groups of MEMS accelerometers and gyroscope circuits are located are connected through a flexible circuit board, and one circuit board is connected and communicated with a circuit board where the signal processing circuit is located through an inter-board connector.

Preferably, the unit structure body further comprises a rear shell, the rear shell is mounted at the rear end of the unit structure body and used for protecting internal devices, an external atmosphere introducing channel port and an electric signal transmission interface are arranged on the rear shell, the external atmosphere introducing channel port is connected with an atmosphere pipeline channel, and the electric signal transmission interface is connected with the signal processing circuit.

The utility model has the advantages that:

the utility model provides a novel plane backup electronic instrument inertia measurement unit structure, which integrates functional modules of an inertia measurement unit, a display module, a signal processing circuit and the like of a plane backup electronic instrument into a hexahedron, and the functional modules are centralized; the space utilization rate is high, and the mass and the volume of the equipment are effectively reduced; reasonable arrangement, concentrated mass distribution and strong practicability.

Drawings

Fig. 1 is a front view of an exploded view of a structural body of an inertial measurement unit of a novel airplane backup electronic instrument in embodiment 1;

FIG. 2 is a top view of the structural body of the inertial measurement unit of the novel backup electronic instrument for an airplane in example 1;

fig. 3 is a right side view of the novel aircraft backup electronic instrument inertial measurement unit structure in example 1;

fig. 4 is a circuit connection diagram of the structural body of the inertia measurement unit of the novel airplane backup electronic instrument in embodiment 1;

1. the system comprises a display module, 2, an atmospheric pressure sensor module, 3, an inertia measurement unit structure support, 4, an MEMS accelerometer and a gyroscope circuit board, 5, a rear shell, 6, a signal processing circuit board and 7, an atmospheric pipeline channel;

FIG. 5 is a front view of a structural support of the inertial measurement unit in embodiment 1;

FIG. 6 is a rear view of the structural support of the inertial measurement unit in embodiment 1;

FIG. 7 is a left side view of the structural support of the inertial measurement unit in embodiment 1;

FIG. 8 is a right side view of the structural frame of the inertial measurement unit in embodiment 1;

FIG. 9 is a plan view of the structural support of the inertial measurement unit in embodiment 1;

fig. 10 is a bottom view of the structural support of the inertial measurement unit in embodiment 1.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the invention, are given by way of illustration only.

Example 1

The embodiment provides a novel aircraft backup electronic instrument inertia measurement unit structure, the unit structure is the hexahedron structure, including inertia measurement unit structure support, atmospheric pressure sensor module, three MEMS accelerometers of group and gyroscope circuit, display module, signal processing circuit, atmosphere pipeline passageway, three MEMS accelerometers of group and gyroscope circuit the display module signal processing circuit with atmosphere pipeline passageway arranges respectively on six faces of inertia measurement unit structure support, atmospheric pressure sensor module sets up the inside at the unit structure. Its front view is shown in fig. 1, its top view is shown in fig. 2, and its right side view is shown in fig. 3.

In the embodiment, a display module (1) is arranged in the X forward direction of a structural support (3) of the inertial measurement unit in the figure, and the display module (1) is used for displaying image-text information and adjusting the information content of a display interface. And a signal processing circuit board (6) is arranged on the Y negative direction of the structural support (3) of the inertia measurement unit, and the signal processing circuit is used for processing circuit signals and sending the processed signals to the display module (1).

In the figure, an atmospheric pressure sensor module (2) is arranged in an inertial measurement unit structural support (3), and the atmospheric pressure sensor module (2) is used for measuring and calculating the speed and altitude data of the airplane. In the figure, an atmosphere pipeline channel (7) is arranged in the Z positive direction of an inertia measurement unit structure support (3), and the atmosphere pipeline channel (7) is used for introducing the external atmosphere at the rear end into an internal atmosphere pressure sensor.

In the figure, an MEMS accelerometer and a gyroscope circuit board (4) are arranged in the X direction, the Y direction and the Z direction of an inertial measurement unit structure support (3), and the MEMS accelerometer and the gyroscope circuit board (4) are used for strap-down resolving airplane motion parameters. The three groups of MEMS accelerometers and the gyroscope sensitive shafts are vertical to each other in pairs, three circuit boards are connected through a flexible circuit board, and one circuit board is connected and communicated with the signal processing circuit board through an inter-board connector.

The rear part of the inertia measurement unit structure support (3) is connected with a rear shell (5), the rear shell (5) is used for protecting internal devices, the rear end of the rear shell is provided with an external atmosphere introducing channel port and an electric signal transmission interface, the external atmosphere introducing channel port is connected with an atmosphere pipeline channel, and the electric signal transmission interface is connected with a signal processing circuit.

The inertia measurement unit structure support (3) in this embodiment integrates the above functional modules and components into a single hexahedron, so that the arrangement requirements of the functional modules are reduced, the mass is concentrated on the front fixed end of the backup electronic instrument where the inertia measurement unit structure body is located, and the whole arrangement is reasonable.

Through adopting the utility model discloses an above-mentioned technical scheme has obtained following profitable effect:

The foregoing is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, a plurality of improvements and decorations can be made without departing from the principle of the present invention, and these improvements and decorations should also be viewed as the protection scope of the present invention.

Claims

1. The utility model provides an aircraft backup electronic instrument inertia measurement unit structure, its characterized in that, the unit structure is the hexahedron structure, including inertia measurement unit structure support, atmospheric pressure sensor module, three MEMS accelerometers of group and gyroscope circuit, display module, signal processing circuit, atmosphere pipeline passageway, three MEMS accelerometers of group and gyroscope circuit the display module signal processing circuit with atmosphere pipeline passageway arranges respectively on six faces of inertia measurement unit structure support, atmospheric pressure sensor module sets up the inside at the unit structure.

2. The aircraft backup electronic instrument inertial measurement unit structure of claim 1, wherein the three sets of MEMS accelerometers and gyroscope circuits are mounted on three mutually perpendicular planes sharing a common apex angle, and the display module, the signal processing circuit and the atmospheric duct channel are mounted on the other three planes respectively.

3. The aircraft backup electronic instrument inertial measurement unit structure of claim 1, wherein the display module is configured to display image-text information and adjust display interface information content.

4. The aircraft backup electronic instrument inertial measurement unit structure of claim 1, wherein the signal processing circuitry is configured to process the barometric pressure sensor module, the three sets of MEMS accelerometer and gyroscope circuitry signals and send the processed signals to a display module.

5. The aircraft backup electronic instrument inertial measurement unit structure of claim 1, wherein the barometric pressure sensor module is configured to measure aircraft speed and altitude data.

6. The aircraft backup electronic instrument inertial measurement unit structure of claim 1, wherein the atmospheric duct channel is configured to introduce back-end outside atmosphere into the internal atmospheric pressure sensor.

7. The aircraft backup electronic instrument inertial measurement unit structure of claim 1, wherein the MEMS accelerometer and gyroscope circuits are used for strap-down resolving aircraft motion parameters, three circuit boards where the three groups of MEMS accelerometer and gyroscope circuits are located are connected by a flexible circuit board, and one of the circuit boards is connected with a circuit board where the signal processing circuit is located through an inter-board connector for communication.

8. The aircraft backup electronic instrument inertial measurement unit structure body according to claim 1, wherein the unit structure body further comprises a rear housing, the rear housing is installed at the rear end of the unit structure body, the rear housing is used for protecting internal devices, an external atmosphere introducing channel port and an electrical signal transmission interface are arranged on the rear housing, the external atmosphere introducing channel port is connected with an atmosphere pipeline channel, and the electrical signal transmission interface is connected with the signal processing circuit.