Aircraft airborne satellite navigation and inertial navigation system combined positioning device

Abstract

The invention discloses an aircraft airborne satellite navigation and inertial navigation system combined positioning device, which comprises a three-axis embedded resonant cavity assembly, a three-axis quartz accelerometer, an embedded body, a magnetic shielding structure, a cover plate and a shock absorber, and is characterized in that the three-axis embedded resonant cavity assembly is arranged in the embedded body; first inner cavities are formed in the three sides of the embedded body, embedded resonant cavity assemblies are installed in the first inner cavities through screws, the planeness of installation faces of the first inner cavities is 0.005, every two installation faces are perpendicular, the perpendicularity does not exceed 0.01, and the embedded resonant cavity assemblies are installed in the first inner cavities through screws. The three-axis embedded resonant cavity assembly can be installed in the embedded body in an embedded mode, and the embedded body structure is a supporting structure of the embedded resonant cavity assembly, so that the requirement of a medium-sized platform for high-precision and long-endurance inertial navigation equipment is met.

Description

Technical Field

[0001] The invention relates to the technical field of inertial navigation equipment, and in particular to a combined positioning device of an aircraft-borne satellite navigation and inertial navigation system. Background Art

[0002] High-precision laser inertial navigation is an advanced autonomous dead reckoning navigation technology that combines the advantages of laser technology and inertial navigation systems. It can achieve high-precision real-time calculation of speed, position, attitude and other parameters without relying on external information.

[0003] The common high-precision laser inertial navigation body component is composed of a three-axis high-precision laser gyroscope, a three-axis quartz accelerometer, a body, a magnetic shield, and connectors. The body is the supporting structure of the laser gyroscope. The weight of the high-precision laser inertial navigation body component is about 25kg, and the corresponding inertial navigation equipment weighs more than 100kg.

[0004] However, in order to ensure that the laser gyro can stably provide high-precision data output, the common high-precision laser inertial navigation body components have a high rigidity requirement for the body, which leads to a large body size and heavy weight, and is only suitable for large platforms, which greatly limits the application of high-precision inertial navigation equipment. Therefore, it is urgent to design a combined positioning device of aircraft-borne satellite navigation and inertial navigation system to solve the above problems. Summary of the invention

[0005] The purpose of the present invention is to provide a combined positioning device of an aircraft-borne satellite navigation and inertial navigation system to solve the above-mentioned deficiencies in the prior art.

[0006] In order to achieve the above object, the present invention provides the following technical solutions:

[0007] It comprises a three-axis embedded resonant cavity component, a three-axis quartz accelerometer, an embedded body, a magnetic shielding structure, a cover plate and a vibration damper, wherein the three-axis embedded resonant cavity component is arranged in the embedded body;

[0008] The embedded body is provided with a first inner cavity on three sides, the embedded resonant cavity component is screwed and installed in the first inner cavity, the flatness of the first inner cavity mounting surface is 0.005, the mounting surfaces are perpendicular to each other, and the verticality does not exceed 0.01, the embedded resonant cavity component is screwed and installed in the first inner cavity, the three-axis embedded resonant cavity component is divided into three axial directions of X, Y, and Z, each axial direction is perpendicular to each other, and the verticality is determined by the verticality between the three first inner cavity mounting surfaces of the embedded body, and the structural layout of the high-precision inertial navigation body component is optimized, and the weight of the high-precision inertial navigation body component is reduced from 25kg to 12kg, which is 50% lighter than the traditional solution.

[0009] The three-axis embedded resonant cavity component can be embedded in the embedded body and make the embedded body structure the supporting structure of the embedded resonant cavity component, thereby meeting the needs of medium-sized platforms for high-precision and long-flight inertial navigation equipment.

[0010] The embedded resonant cavity component is used as a core sensor of a high-precision inertial navigation body component and provides angular velocity information for the high-precision inertial navigation body component. The accuracy of the high-precision resonant cavity component is within 0.001° / h.

[0011] A second inner cavity is provided on one side of the embedded body, and the three-axis quartz accelerometers are screw-mounted in the second inner cavity, and the three-axis quartz accelerometers are perpendicular to each other.

[0012] The quartz accelerometer is used as a core sensor of a high-precision inertial navigation body component, and provides acceleration information for the high-precision inertial navigation body component.

[0013] The four sides of the embedded body are all provided with card slots, and the cover plate is carded in the card slots.

[0014] The cover plate is used to make the embedded body form a closed hexahedron and adjust the center of gravity of the embedded body.

[0015] Both sides of the embedded body are provided with mounting grooves, and the vibration damper screws are installed in the mounting grooves.

[0016] The vibration absorber adopts 2 groups of plane 4-point layout to form a spatial 8-point layout, and the deviation between the center of the vibration absorber and the center of gravity of the embedded body does not exceed 1mm.

[0017] The magnetic shielding structure includes a first magnetic shielding plate, a second magnetic shielding plate, a third magnetic shielding plate, a fourth magnetic shielding plate and a fifth magnetic shielding plate. The first magnetic shielding plate is glued to the inner surface of the cover plate, the second magnetic shielding plates are glued to the first inner cavity, the third magnetic shielding plates are arranged on both sides of the embedded body, the fourth magnetic shielding plate is arranged on one side of the embedded body, and the fifth magnetic shielding plate is arranged on the front side of the embedded body. The magnetic shielding structure is used to completely wrap the embedded body.

[0018] A wire outlet slot is provided between the fifth magnetic shielding plate and the embedded body, and an external connector is provided on the front side of the embedded body. The external connector is used to collect gyroscope and accelerometer information and provide power supply requirements for the entire device.

[0019] In the above technical solution, the present invention provides an aircraft airborne satellite navigation and inertial navigation system combined positioning device, the beneficial effects are:

[0020] 1. The three-axis embedded resonant cavity assembly can be embedded in the embedded body and make the embedded body structure the supporting structure of the embedded resonant cavity assembly, thus meeting the needs of medium-sized platforms for high-precision and long-flight inertial navigation equipment.

[0021] 2. The quartz accelerometer can provide acceleration information for the high-precision inertial navigation body component and cooperate with the embedded resonant cavity component, thereby improving the positioning effect of the combined positioning device of the aircraft's airborne satellite navigation and inertial navigation system.

[0022] 3. The magnetic shielding structure can provide double-layer magnetic shielding protection for the embedded body, thereby reducing the influence of geomagnetism on the accuracy of the laser gyroscope. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings.

[0024] Figure 1 A schematic structural diagram of a high-precision inertial navigation body component provided in an embodiment of a combined positioning device of an aircraft-borne satellite navigation and inertial navigation system of the present invention.

[0025] Figure 2 The present invention is a schematic diagram of an external connector structure provided in an embodiment of a combined positioning device for an aircraft-borne satellite navigation and inertial navigation system.

[0026] Figure 3 The present invention is a schematic diagram of the structure of a quartz accelerometer provided in an embodiment of a combined positioning device for an aircraft-borne satellite guidance and inertial navigation system.

[0027] Figure 4 A schematic diagram of a magnetic shielding structure provided for an embodiment of a combined positioning device for an aircraft-borne satellite guidance and inertial navigation system of the present invention.

[0028] Figure 5 A schematic diagram of the structure of an embedded resonant cavity component provided in an embodiment of a combined positioning device for an aircraft-borne satellite guidance and inertial navigation system of the present invention.

[0029] Description of reference numerals:

[0030] 1. Embedded resonant cavity assembly; 2. Quartz accelerometer; 3. Embedded body; 4. Magnetic shielding structure; 5. Cover plate; 6. Shock absorber; 7. First inner cavity; 8. Second inner cavity; 9. Card slot; 10. Mounting slot; 11. First magnetic shielding plate; 12. Second magnetic shielding plate; 13. Third magnetic shielding plate; 14. Fourth magnetic shielding plate; 15. Fifth magnetic shielding plate; 16. Wire outlet slot; 17. External connector. DETAILED DESCRIPTION

[0031] In order to enable those skilled in the art to better understand the technical solution of the present invention, the present invention will be further described in detail below with reference to the accompanying drawings.

[0032] like Figure 1-5 As shown, an embodiment of the present invention provides a combined positioning device of an aircraft-borne satellite navigation and inertial navigation system.

[0033] It includes a three-axis embedded resonant cavity component 1, a three-axis quartz accelerometer 2, an embedded body 3, a magnetic shielding structure 4, a cover plate 5 and a vibration absorber 6, wherein the three-axis embedded resonant cavity component 1 is arranged in the embedded body 3;

[0034] The embedded body 3 is provided with a first inner cavity 7 on three sides, the embedded resonant cavity component 1 is screwed and installed in the first inner cavity 7, the flatness of the mounting surface of the first inner cavity 7 is 0.005, the mounting surfaces are perpendicular to each other, and the verticality does not exceed 0.01, the embedded resonant cavity component 1 is screwed and installed in the first inner cavity 7, the three-axis embedded resonant cavity component 1 is divided into three axial directions of X, Y, and Z, and each axial direction is perpendicular to each other, and the verticality is determined by the verticality between the 33 first inner cavity 7 mounting surfaces of the embedded body. The structural layout of the high-precision inertial navigation body component is optimized, and the weight of the high-precision inertial navigation body component is reduced from 25kg to 12kg, which is 50% lighter than the traditional solution.

[0035] The three-axis embedded resonant cavity assembly 1 can be embeddedly installed inside the embedded body 3 and make the embedded body 3 structure the supporting structure of the embedded resonant cavity assembly 1, thereby meeting the needs of medium-sized platforms for high-precision and long-flight inertial navigation equipment.

[0036] Reference Figure 5 The embedded resonant cavity component 1 of this embodiment is used as the core sensor of the high-precision inertial navigation body component and provides angular velocity information for the high-precision inertial navigation body component. The accuracy of the high-precision resonant cavity component is within 0.001° / h.

[0037] The embedded resonant cavity component 1 can provide angular velocity information for the high-precision inertial navigation body component, thereby increasing the positioning effect of the combined positioning device of the aircraft-borne satellite navigation and inertial navigation system.

[0038] Reference Figure 3 In this embodiment, a second inner cavity 8 is provided on one side of the embedded body 3, and the three-axis quartz accelerometers 2 are screwed into the second inner cavity 8, and the three-axis quartz accelerometers 2 are perpendicular to each other.

[0039] The quartz accelerometer 2 is used as the core sensor of the high-precision inertial navigation body component, providing acceleration information for the high-precision inertial navigation body component.

[0040] The quartz accelerometer 2 can provide acceleration information for the high-precision inertial navigation body component and cooperate with the embedded resonant cavity component 1, thereby improving the positioning effect of the aircraft airborne satellite navigation and inertial navigation system combined positioning device.

[0041] Reference Figure 2 In this embodiment, the four sides of the embedded body 3 are all provided with card slots 9, and the cover plate 5 is carded in the card slots 9.

[0042] The cover plate 5 is used to make the embedded body 3 form a closed hexahedron and adjust the center of gravity of the embedded body 3 at the same time.

[0043] The cover plate 5 can close the first cavity 7 and the second cavity 8 while adjusting the center of gravity of the embedded body 3, thereby increasing the stability of the high-precision inertial navigation body assembly during use.

[0044] Both sides of the embedded body 3 are provided with mounting grooves 10 , and the vibration absorber 6 is screwed into the mounting grooves 10 .

[0045] The vibration absorber 6 adopts 2 groups of 4-point layouts to form a spatial 8-point layout. The deviation between the center of the vibration absorber 6 and the center of gravity of the embedded body 3 does not exceed 1 mm.

[0046] The shock absorber 6 can ensure the three-axis equal stiffness of the vibration reduction system.

[0047] Reference Figure 4 The magnetic shielding structure 4 of this embodiment includes a first magnetic shielding plate 11, a second magnetic shielding plate 12, a third magnetic shielding plate 13, a fourth magnetic shielding plate 14 and a fifth magnetic shielding plate 15. The first magnetic shielding plate 11 is glued to the inner surface of the cover plate 5, the second magnetic shielding plates 12 are glued in the first inner cavity 7, the third magnetic shielding plates 13 are arranged on both sides of the embedded body 3, the fourth magnetic shielding plate 14 is arranged on one side of the embedded body 3, and the fifth magnetic shielding plate 15 is arranged on the front side of the embedded body 3. The magnetic shielding structure 4 is used to completely wrap the embedded body 3.

[0048] The magnetic shielding structure 4 can provide double-layer magnetic shielding protection for the embedded body 3, thereby reducing the influence of the earth's magnetism on the accuracy of the laser gyroscope.

[0049] A wire outlet slot 16 is provided between the fifth magnetic shielding plate 15 and the embedded body 3 , and an external connector 17 is provided on the front side of the embedded body 3 . The external connector 17 is used to collect information of the gyroscope and accelerometer, and provide power supply requirements for the entire device.

[0050] Working principle:

[0051] S1; connect the high-precision inertial navigation body component to other devices through the external connector 17 and power the entire device:

[0052] S2: starting the three-axis embedded resonant cavity component 1 to provide angular velocity information for the high-precision inertial navigation body component, and starting the three-axis quartz accelerometer 2 to provide acceleration information for the high-precision inertial navigation body component;

[0053] S3: The collected angular velocity information and acceleration information are transmitted to other devices through the external connector 17 .

[0054] The above description is only by way of illustration of certain exemplary embodiments of the present invention. It is undoubted that those skilled in the art can modify the described embodiments in various ways without departing from the spirit and scope of the present invention. Therefore, the above drawings and descriptions are illustrative in nature and should not be construed as limiting the scope of protection of the claims of the present invention.

Claims

1. An aircraft-mounted satellite navigation and inertial navigation system combined positioning device, characterized in that: It comprises a three-axis embedded resonant cavity component (1), a three-axis quartz accelerometer (2), an embedded body (3), a magnetic shielding structure (4), a cover plate (5) and a vibration damper (6), wherein the three-axis embedded resonant cavity component (1) is arranged in the embedded body (3); The embedded body (3) is provided with a first inner cavity (7) on three sides, the embedded resonant cavity component (1) is screwed and installed in the first inner cavity (7), the flatness of the installation surface of the first inner cavity (7) is 0.005, the installation surfaces are perpendicular to each other, and the verticality does not exceed 0.01, the embedded resonant cavity component (1) is screwed and installed in the first inner cavity (7), the three-axis embedded resonant cavity component (1) is divided into three axial directions of X, Y, and Z, each of which is perpendicular to each other, and the verticality is determined by the verticality between the three installation surfaces of the first inner cavity (7) of the embedded body (3).

2. The combined positioning device of an aircraft-borne satellite navigation and inertial navigation system according to claim 1, characterized in that: The embedded resonant cavity component (1) is used as a core sensor of a high-precision inertial navigation body component and provides angular velocity information for the high-precision inertial navigation body component. The accuracy of the high-precision resonant cavity component is within 0.001° / h.

3. The combined positioning device of an aircraft-borne satellite navigation and inertial navigation system according to claim 1, characterized in that: A second inner cavity (8) is provided on one side of the embedded body (3), and the three-axis quartz accelerometers (2) are screw-mounted in the second inner cavity (8), and the three-axis quartz accelerometers (2) are mutually perpendicular in pairs.

4. The combined positioning device of an aircraft-borne satellite navigation and inertial navigation system according to claim 3, characterized in that: The quartz accelerometer (2) is used as a core sensor of a high-precision inertial navigation body component, and provides acceleration information for the high-precision inertial navigation body component.

5. The combined positioning device of an aircraft-borne satellite navigation and inertial navigation system according to claim 1, characterized in that: The four sides of the embedded body (3) are all provided with card slots (9), and the cover plate (5) is card-engaged in the card slots (9).

6. The combined positioning device of an aircraft-borne satellite navigation and inertial navigation system according to claim 5, characterized in that: The cover plate (5) is used to enable the embedded body (3) to form a closed hexahedron and to adjust the center of gravity of the embedded body (3).

7. The aircraft-borne satellite navigation and inertial navigation system combined positioning device according to claim 5, characterized in that: Both sides of the embedded body (3) are provided with mounting grooves (10), and the vibration damper (6) is screw-mounted in the mounting grooves (10).

8. The combined positioning device of an aircraft-borne satellite navigation and inertial navigation system according to claim 7, characterized in that: The vibration absorber (6) adopts two groups of four-point layouts in a plane to form an eight-point layout in space, and the deviation between the center of the vibration absorber (6) and the center of gravity of the embedded body (3) does not exceed 1 mm.

9. The aircraft-borne satellite navigation and inertial navigation system combined positioning device according to claim 7, characterized in that: The magnetic shielding structure (4) comprises a first magnetic shielding plate (11), a second magnetic shielding plate (12), a third magnetic shielding plate (13), a fourth magnetic shielding plate (14) and a fifth magnetic shielding plate (15); the first magnetic shielding plate (11) is glued to the inner surface of the cover plate (5); the second magnetic shielding plates (12) are glued into the first inner cavity (7); the third magnetic shielding plates (13) are arranged on both sides of the embedded body (3); the fourth magnetic shielding plate (14) is arranged on one side of the embedded body (3); the fifth magnetic shielding plate (15) is arranged on the front side of the embedded body (3); and the magnetic shielding structure (4) is used to completely wrap the embedded body (3).

10. The aircraft-borne satellite navigation and inertial navigation system combined positioning device according to claim 9, characterized in that: A wire outlet slot (16) is provided between the fifth magnetic shielding plate (15) and the embedded body (3), and an external connector (17) is provided on the front side of the embedded body (3). The external connector (17) is used to collect gyroscope and accelerometer information and provide power supply requirements for the entire device.

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