Aircraft airborne satellite navigation and inertial navigation system combined positioning device

Abstract

The invention relates to the technical field of aviation navigation and positioning, in particular to an aircraft airborne satellite navigation and inertial navigation system combined positioning device. Comprising a box cover, a substrate, a bottom plate, a 4G wireless module, a first partition plate, a second partition plate, a third partition plate, a first heat dissipation cavity, a second heat dissipation cavity, two air inlets, an air guide box, a mounting box, a heat dissipation fan, a plurality of through holes, a satellite positioning navigation module, a main antenna interface, an auxiliary antenna interface, a 4G antenna interface, a WiFi antenna interface, a data line interface and an inertial measurement module. Effective heat dissipation is achieved through ingenious structural design, the box cover is provided with an air inlet, an air guide box, a heat dissipation fan and an air outlet, a complete air channel is formed, external air can enter the device in order, a satellite positioning navigation module, various interfaces and an inertia measurement module are reasonably distributed, air can flow through a heating element, and heat dissipation is achieved. And internal air can circulate well, heat generated by elements can be dissipated in time, and temperature rise is avoided.

Description

Technical Field

[0001] The present invention relates to the technical field of aviation navigation and positioning, and particularly to an aircraft airborne satellite navigation and inertial navigation system combined positioning device. Background Art

[0002] In aviation navigation, satellite navigation technology uses satellite signals such as the Global Positioning System (GPS) and the Beidou Satellite Navigation System (BDS) to provide the absolute position information of an aircraft, while inertial navigation technology measures the acceleration and angular velocity of the aircraft through an Inertial Measurement Unit (IMU), and integrates and calculates to obtain the relative position, speed and attitude information of the aircraft. Based on the positioning device, the advantages of satellite navigation and inertial navigation are combined, and finally the positioning accuracy and reliability are improved through a data fusion algorithm.

[0003] The prior art patent CN119594964A discloses an aircraft airborne satellite navigation and inertial navigation system combined positioning device, including 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. The three-axis embedded resonant cavity assembly is arranged inside the embedded body; first inner cavities are opened on three sides of the embedded body, and the embedded resonant cavity assembly is installed in the first inner cavity by screws. The flatness of the installation surface of the first inner cavity is 0.005, the installation surfaces are perpendicular to each other in pairs, and the perpendicularity does not exceed 0.01. The embedded resonant cavity assembly is installed in the first inner cavity by screws. This prior art can be embedded and installed inside the embedded body through the provided three-axis embedded resonant cavity assembly, and the structure of the embedded body serves as the support structure of the embedded resonant cavity assembly, thus meeting the needs of medium-sized platforms for high-precision and long-endurance inertial navigation equipment.

[0004] However, in the aforementioned prior art, since the embedded installation easily causes poor air circulation inside the device, especially when operating at high power or working for a long time, the heat generated by the components may not be dissipated in time, resulting in a temperature rise. Summary of the Invention

[0005] The purpose of the present invention is to provide an aircraft airborne satellite navigation and inertial navigation system combined positioning device, which solves the technical problem that in the prior art, due to the embedded installation, it is easy to cause poor air circulation inside the device, especially when operating at high power or working for a long time, the heat generated by the components may not be dissipated in time, resulting in a temperature rise.

[0006] To achieve the above object, the present invention provides a combined positioning device for an aircraft airborne satellite navigation and inertial navigation system, including a box cover, a base plate and a bottom plate. A 4G wireless module is provided above the box cover. A first partition, a second partition and a third partition are provided on the inner top of the box cover, and a first heat dissipation cavity is formed between the first partition and the second partition, and a second heat dissipation cavity is formed between the third partition and the box cover. One end of the box cover has two air inlets, and a wind guide box is arranged between the two air inlets. An installation box is arranged on the wind guide box, and a heat dissipation fan is arranged in the installation box. The other end of the box cover has a plurality of through holes. A satellite positioning and navigation module is arranged on the base plate by screws. The base plate is also provided with a main antenna interface, a sub-antenna interface, a 4G antenna interface, a WiFi antenna interface and a data line interface. An inertial measurement module is arranged on the bottom plate through a positioning component. The box cover is fixedly connected to the bottom plate by screws and is located above the bottom plate. The base plate is fixedly connected to the bottom plate by screws and is located on the bottom plate, and the satellite positioning and navigation module is located in the first heat dissipation cavity. The main antenna interface, the sub-antenna interface, the 4G antenna interface, the WiFi antenna interface, the data line interface and the inertial measurement module are all located in the second heat dissipation cavity.

[0007] Wherein, a wind guide block is arranged in the wind guide box. Both sides of the wind guide block have a first wind guide surface and a second wind guide surface, and the first wind guide surface faces one of the air inlets, and the second wind guide surface faces the other air inlet.

[0008] Wherein, one side of the box cover has two air outlets, and one end of the first heat dissipation cavity and the second heat dissipation cavity communicates with the corresponding air inlet, and the other end of the first heat dissipation cavity and the second heat dissipation cavity communicates with the corresponding air outlet.

[0009] Wherein, the combined positioning device for the aircraft airborne satellite navigation and inertial navigation system further includes an air inlet filter cover and an air outlet filter cover. The air inlet filter cover is fixedly connected to the installation box and is located on the installation box and also at the air inlet end of the heat dissipation fan. The air outlet filter cover is fixedly connected to the box cover and is located on one side of the box cover and also at the two air outlets.

[0010] Wherein, a plurality of first heat dissipation fins are arranged on the outer side of the box cover, and a plurality of second heat dissipation fins are arranged on the top of the box cover.

[0011] Wherein, a plurality of positioning blocks are arranged on the upper end surface of the base plate, and the plurality of positioning blocks are respectively located at the four bottom corners of the satellite positioning and navigation module.

[0012] Above the bottom plate, a plurality of supporting blocks are provided. The main antenna interface, the sub-antenna interface, the 4G antenna interface, the WiFi antenna interface, and the data line interface are all abutted against the corresponding supporting blocks, and the plurality of supporting blocks are also respectively located in the corresponding through holes.

[0013] A combined positioning device for an aircraft airborne satellite navigation and inertial navigation system according to the present invention includes a box cover, a substrate, and a bottom plate. A 4G wireless module is provided above the box cover. A first partition, a second partition, and a third partition are provided on the inner top of the box cover, and a first heat dissipation cavity is formed between the first partition and the second partition, and a second heat dissipation cavity is formed between the third partition and the box cover. One end of the box cover has two air inlets, a wind guide box is provided between the two air inlets, a mounting box is provided on the wind guide box, a cooling fan is provided in the mounting box, and the other end of the box cover has a plurality of through holes. A satellite positioning and navigation module is provided on the substrate by screws, and a main antenna interface, a sub-antenna interface, a 4G antenna interface, a WiFi antenna interface, and a data line interface are also provided on the substrate. An inertial measurement module is provided on the bottom plate by a positioning component. Through a clever structural design, effective heat dissipation is achieved. The box cover is provided with the air inlets, the wind guide box, the cooling fan, and the air outlet to form a complete air duct, so that external air can enter the device interior orderly; the first heat dissipation cavity and the second heat dissipation cavity are provided to reasonably distribute the satellite positioning and navigation module, various interfaces, and the inertial measurement module, etc., so that air can flow through the heating elements and the internal air can circulate well, and the heat generated by the components can be dissipated in time to avoid temperature rise. In this way, the technical problem that due to embedded installation, it is easy to cause poor air circulation inside the device, especially when operating at high power or working for a long time, the heat generated by the components may not be dissipated in time, resulting in temperature rise is effectively solved. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art.

[0015] Figure 1 is the three-dimensional perspective view of the first embodiment of the present invention.

[0016] Figure 2 is the front view of the first embodiment of the present invention.

[0017] Figure 3 is of the present invention Figure 2 cross-sectional view taken along line A-A.

[0018] Figure 4 is the internal structure schematic diagram of the first embodiment of the present invention.

[0019] Figure 5 It is a three-dimensional view of the second embodiment of the present invention.

[0020] Figure 6 It is the front view of the second embodiment of the present invention.

[0021] Figure 7 It is of the present invention Figure 6 The sectional view taken along line B-B.

[0022] Figure 8 It is the side view of the third embodiment of the present invention.

[0023] Figure 9 It is of the present invention Figure 8 The sectional view taken along line C-C.

[0024] Figure 10 It is of the present invention Figure 8 The sectional view taken along line D-D.

[0025] Figure 11 It is the structural schematic diagram of the positioning component in the third embodiment of the present invention.

[0026] 101 - Lid, 102 - Substrate, 103 - Bottom plate, 104 - 4G wireless module, 105 - First partition, 106 - Second partition, 107 - Third partition, 108 - First heat dissipation cavity, 109 - Second heat dissipation cavity, 110 - Air inlet, 111 - Air guide box, 112 - Installation box, 113 - Heat dissipation fan, 114 - Through hole, 115 - Satellite positioning and navigation module, 116 - Main antenna interface, 117 - Sub-antenna interface, 118 - 4G antenna interface, 119 - WiFi antenna interface, 120 - Data line interface, 121 - Positioning component, 122 - Inertial measurement module, 123 - Air guide block, 124 - First air guide surface, 125 - Second air guide surface, 126 - Air outlet, 201 - Air inlet filter cover, 202 - Air outlet filter cover, 203 - First heat dissipation fin, 204 - Second heat dissipation fin, 205 - Positioning block, 206 - Lifting block, 301 - Supporting block, 302 - C-shaped positioning seat, 303 - Engaging block, 304 - Fixing bolt, 305 - Threaded seat, 306 - C-shaped groove. Detailed implementation manners

[0027] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings. The embodiments described below by referring to the drawings are exemplary and are intended to explain the present invention, and should not be construed as a limitation to the present invention.

[0028] First embodiment:

[0029] Please refer to Figures 1 to 4 , wherein Figure 1Is a three-dimensional perspective view of the first embodiment of the present invention, Figure 2 Is the front view of the first embodiment of the present invention, Figure 3 Is of the present invention Figure 2 Cross-sectional view taken along line A-A in Figure 4 Is a schematic diagram of the internal structure of the first embodiment of the present invention.

[0030] The present invention provides an aircraft airborne satellite navigation and inertial navigation system combined positioning device, which includes a box cover 101, a substrate 102 and a bottom plate 103. A 4G wireless module 104 is arranged above the box cover 101. A first partition 105, a second partition 106 and a third partition 107 are arranged on the inner top of the box cover 101. A first heat dissipation cavity 108 is formed between the first partition 105 and the second partition 106. A second heat dissipation cavity 109 is formed between the third partition 107 and the box cover 101. Two air inlets 110 are arranged at one end of the box cover 101. A wind guide box 111 is arranged between the two air inlets 110. An installation box 112 is arranged on the wind guide box 111. A heat dissipation fan 113 is arranged in the installation box 112. A plurality of through holes 114 are arranged at the other end of the box cover 101. A satellite positioning and navigation module 115 is arranged on the substrate 102 by screws. A main antenna interface 116, a secondary antenna interface 117, a 4G antenna interface 118, a WiFi antenna interface 119 and a data line interface 120 are also arranged on the substrate 102. An inertial measurement module 122 is arranged on the bottom plate 103 by a positioning component 121. The box cover 101 is fixedly connected to the bottom plate 103 by screws and is located above the bottom plate 103. The substrate 102 is fixedly connected to the bottom plate 103 by screws and is located on the bottom plate 103. The satellite positioning and navigation module 115 is located in the first heat dissipation cavity 108. The main antenna interface 116, the secondary antenna interface 117, the 4G antenna interface 118, the WiFi antenna interface 119, the data line interface 120 and the inertial measurement module 122 are all located in the second heat dissipation cavity 109. A stable infrastructure is constructed through the combination of the box cover 101, the substrate 102 and the bottom plate 103. The satellite positioning and navigation module 115 is arranged in the first heat dissipation cavity 108. The main antenna interface 116, the secondary antenna interface 117, the 4G antenna interface, the WiFi antenna interface, the data line interface 120 and the inertial measurement module 122 are arranged in the second heat dissipation cavity 109. This partition layout provides a basis for subsequent heat dissipation design. Two air inlets 110 are arranged at one end of the box cover 101. The heat dissipation fan 113 is installed through the wind guide box 111 and the installation box 112 in the middle. A plurality of through holes 114 are arranged at the other end. A path for air circulation is initially formed, which helps the air exchange between the inside and outside of the device, creates conditions for the implementation of subsequent heat dissipation measures, can effectively cope with the heat generated during the operation of the device, and ensures that each component works in a suitable temperature environment.

[0031] Among them, a wind guiding block 123 is arranged in the air guiding box 111. Both sides of the wind guiding block 123 have a first wind guiding surface 124 and a second wind guiding surface 125. The first wind guiding surface 124 faces one of the air inlets 110, and the second wind guiding surface 125 faces the other air inlet 110. Through this design, the air entering from the two air inlets 110 can be guided to flow more orderly towards the cooling fan 113, avoiding the phenomenon of air disorder or vortex in the air guiding box 111, improving the efficiency of air flow, thereby enhancing the suction effect of the cooling fan 113 on the internal air of the device, further improving the heat dissipation effect, and ensuring that when the device operates at high power or works for a long time, the internal air can circulate more smoothly and timely take away the heat generated by the components.

[0032] Secondly, one side of the box cover 101 has two air outlets 126. One end of the first heat dissipation cavity 108 and the second heat dissipation cavity 109 communicates with the corresponding air inlet 110, and the other end of the first heat dissipation cavity 108 and the second heat dissipation cavity 109 communicates with the corresponding air outlet 126. Through such a wind channel design, air can enter from the air inlet 110, pass through the heat dissipation cavity, take away the heat generated by the components, and then be discharged from the air outlet 126, realizing the circulation of the internal air of the device. This orderly air circulation can more effectively reduce the internal temperature of the device, ensure that components such as the satellite positioning and navigation module 115, various interfaces, and the inertial measurement module 122 work within a normal temperature range, and improve the stability and reliability of the device.

[0033] When using the combined positioning device of an aircraft airborne satellite navigation and inertial navigation system according to this embodiment, the cooling fan 113 is started inside the installation box 112, and air is inhaled from the outside through the two air inlets 110. The air guiding block 123 in the air guiding box 111 plays a guiding role, and the first air guiding surface 124 and the second air guiding surface 125 on both sides thereof face the two air inlets 110 respectively. Under the action of the cooling fan 113, the air first enters the first heat dissipation cavity 108. Since the satellite positioning and navigation module 115 is located in this cavity, the air will take away the heat generated by the module. Then, the air flows into the second heat dissipation cavity 109, where the main antenna interface 116, the sub-antenna interface 117, the 4G antenna interface, the WiFi antenna interface, the data line interface 120 and the inertial measurement module 122 are located. The air will also absorb the heat generated by these components. Finally, the heated air is discharged outside the device through the two air outlets 126 on one side of the box cover 101. In this way, a complete heat dissipation air duct is formed, ensuring that when the device operates at high power or works for a long time, the heat generated by the internal components can be dissipated in time, maintaining the device to work stably in a suitable temperature environment. In this way, the technical problem that due to the embedded installation, it is easy to cause poor air circulation inside the device, especially when operating at high power or working for a long time, the heat generated by the components may not be dissipated in time, resulting in a temperature rise is effectively solved.

[0034] Second Embodiment:

[0035] Based on the first embodiment, please refer to Figures 5 to 7 , wherein Figure 5 is the three-dimensional view of the second embodiment of the present invention, Figure 6 is the front view of the second embodiment of the present invention, Figure 7 is of the present invention Figure 6 The cross-sectional view taken along the line B-B in

[0036] The present invention provides an aircraft airborne satellite navigation and inertial navigation system combined positioning device, which further includes an air inlet filter cover 201 and an air outlet filter cover 202. The air inlet filter cover 201 is fixedly connected to the installation box 112, is located on the installation box 112, and is also located at the air inlet end of the cooling fan 113. The air outlet filter cover 202 is fixedly connected to the box cover 101, is located on one side of the box cover 101, and is also located at the two air outlet openings 126. The air inlet filter cover 201 can prevent dust, debris, etc. from entering the device interior, avoiding these impurities from adhering to the surface of components or blocking the heat dissipation channels, which may affect the performance of components and the heat dissipation effect. The air outlet filter cover 202 can prevent the dust inside the device from spreading into the surrounding environment when discharged with the air, and can also, to a certain extent, avoid new impurities being brought in when the external air backflows. This filtering design not only ensures the cleanliness inside the device, but also helps to maintain a good heat dissipation environment, extending the service life of the device.

[0037] Wherein, a plurality of first heat dissipation fins 203 are provided on the outer side of the box cover 101, and a plurality of second heat dissipation fins 204 are provided on the top of the box cover 101. When the heat inside the device is transferred to the box cover 101, the heat dissipation fins can dissipate the heat to the surrounding air more quickly. This way of increasing the heat dissipation area to improve the heat dissipation efficiency helps to further reduce the overall temperature of the device. Especially when the device operates at high power and generates a large amount of heat, the heat dissipation fins can play an important role in ensuring that the device temperature is stably within a reasonable range and guaranteeing the normal operation of each component.

[0038] Secondly, a plurality of positioning blocks 205 are provided on the upper end surface of the substrate 102, and the plurality of positioning blocks 205 are respectively located at the four bottom corners of the satellite positioning and navigation module 115. The positioning blocks 205 can accurately position and fix the satellite positioning and navigation module 115, preventing the module from shifting or loosening due to factors such as vibration and impact during the operation of the device. This helps to ensure the connection stability between the satellite positioning and navigation module 115 and other components and the accuracy of signal transmission, improving the positioning accuracy and reliability of the device, and ensuring the normal operation of the aircraft airborne satellite navigation and inertial navigation system combined positioning device.

[0039] Meanwhile, a plurality of lifting blocks 206 are arranged above the bottom plate 103. The main antenna interface 116, the secondary antenna interface 117, the 4G antenna interface 118, the WiFi antenna interface 119, and the data line interface 120 are all abutted against the corresponding lifting blocks 206, and the plurality of lifting blocks 206 are also respectively located in the corresponding through holes 114. Through the design of the lifting blocks 206, these interfaces can be stably installed on the bottom plate 103, avoiding signal interference or damage that may be caused by the direct contact between the interfaces and the bottom plate 103. Meanwhile, the design of the through holes 114 is beneficial to the connection and wiring between the interfaces and external devices, improving the operability and maintainability of the device, ensuring the normal operation of each interface, and further ensuring that the entire aircraft airborne satellite navigation and inertial navigation system combined positioning device can operate stably and reliably.

[0040] Third Embodiment:

[0041] Based on the second embodiment, please refer to Figures 8 to 11 , where Figure 8 is a side view of the third embodiment of the present invention, Figure 9 is of the present invention Figure 8 is a cross-sectional view taken along line C-C in Figure 10 is of the present invention Figure 8 is a cross-sectional view taken along line D-D in Figure 11 is a schematic structural diagram of the positioning component in the third embodiment of the present invention.

[0042] The present invention provides an aircraft airborne satellite navigation and inertial navigation system combined positioning device. The positioning component 121 includes an abutting block 301, a plurality of fixing members, and a C-shaped positioning seat 302. A clamping block 303 is arranged below the inertial measurement module 122. The abutting block 301 is arranged on one side of the C-shaped positioning seat 302 through the fixing members and also abuts against the clamping block 303. The inertial measurement module 122 is arranged on the C-shaped positioning seat 302 through the clamping block 303, and the clamping block 303 is slidably arranged in the C-shaped positioning seat 302. The C-shaped positioning seat 302 is fixedly connected to the bottom plate 103 and is located on the bottom plate 103. Through the synergistic action of the abutting block 301, the plurality of fixing members, and the C-shaped positioning seat, the stable installation and precise positioning of the inertial measurement module 122 are achieved. The abutting block 301 abuts against the clamping block 303 to keep the inertial measurement module 122 stable on the C-shaped positioning seat. This design not only ensures the position accuracy of the inertial measurement module 122 during operation but also effectively reduces the displacement of the module caused by factors such as vibration and impact, thereby improving the positioning accuracy and reliability of the entire aircraft airborne satellite navigation and inertial navigation system combined positioning device and ensuring that the aircraft can obtain accurate position and attitude information during flight.

[0043] Among them, the fixing member includes a fixing bolt 304 and a threaded seat 305. The fixing bolt 304 is threadedly connected to the threaded seat 305 and is located within the threaded seat 305. Moreover, it also penetrates through the abutting block 301. The threaded seat 305 is fixedly connected to the bottom plate 103 and is located on the bottom plate 103. Through this design, the installation and disassembly of the abutting block 301 are very convenient, facilitating the maintenance and replacement of the inertial measurement module 122.

[0044] Secondly, the inner side of the C-shaped positioning seat 302 has a C-shaped groove 306, and the engaging block 303 is located within the C-shaped groove 306, and the abutting block 301 is located at the opening of the C-shaped groove 306.

[0045] The above-disclosed are only one or more preferred embodiments of the present application, and the scope of rights of the present application cannot be limited thereby. Those of ordinary skill in the art can understand the entire or partial processes of implementing the above embodiments, and the equivalent changes made according to the claims of the present application still fall within the scope covered by the present application.

Claims

1. An aircraft airborne satellite navigation and inertial navigation system combined positioning device, characterized in that it includes a box cover, a substrate and a bottom plate. A 4G wireless module is arranged above the box cover. A first partition, a second partition and a third partition are arranged on the inner top of the box cover. And there is a first heat dissipation cavity between the first partition and the second partition, and a second heat dissipation cavity between the third partition and the box cover. One end of the box cover has two air inlets, and a wind guide box is arranged between the two air inlets. An installation box is arranged on the wind guide box, and a cooling fan is arranged in the installation box. The other end of the box cover has a plurality of through holes. The satellite positioning and navigation module is arranged on the substrate by screws. The substrate is also provided with a main antenna interface, a sub-antenna interface, a 4G antenna interface, a WiFi antenna interface and a data line interface. The inertial measurement module is arranged on the bottom plate through a positioning component. The box cover is fixedly connected to the bottom plate by screws and is located above the bottom plate. The substrate is fixedly connected to the bottom plate by screws and is located on the bottom plate. And the satellite positioning and navigation module is located in the first heat dissipation cavity. The main antenna interface, the sub-antenna interface, the 4G antenna interface, the WiFi antenna interface, the data line interface and the inertial measurement module are all located in the second heat dissipation cavity.

2. The aircraft airborne satellite navigation and inertial navigation system combined positioning device according to claim 1, characterized in that a wind guide block is arranged in the wind guide box. Both sides of the wind guide block have a first wind guide surface and a second wind guide surface. And the first wind guide surface faces one of the air inlets, and the second wind guide surface faces the other air inlet.

3. The aircraft airborne satellite navigation and inertial navigation system combined positioning device according to claim 2, characterized in that one side of the box cover has two air outlets. And one end of the first heat dissipation cavity and the second heat dissipation cavity communicates with the corresponding air inlet, and the other end of the first heat dissipation cavity and the second heat dissipation cavity communicates with the corresponding air outlet.

4. The aircraft airborne satellite navigation and inertial navigation system combined positioning device according to claim 3, characterized in that the aircraft airborne satellite navigation and inertial navigation system combined positioning device further includes an air inlet filter cover and an air outlet filter cover. The air inlet filter cover is fixedly connected to the installation box and is located on the installation box and also at the air inlet end of the cooling fan. The air outlet filter cover is fixedly connected to the box cover and is located on one side of the box cover and also at the two air outlets.

5. The aircraft airborne satellite navigation and inertial navigation system combined positioning device according to claim 4, characterized in that a plurality of first heat dissipation fins are arranged on the outer side of the box cover, and a plurality of second heat dissipation fins are arranged on the top of the box cover.

6. The aircraft airborne satellite navigation and inertial navigation system combined positioning device according to claim 5, characterized in that a plurality of positioning blocks are arranged on the upper end surface of the substrate, and the plurality of positioning blocks are also respectively located at the four bottom corners of the satellite positioning and navigation module.

7. The combined positioning device of the aircraft airborne satellite navigation and inertial navigation system according to claim 6, wherein a plurality of supporting blocks are arranged above the bottom plate, the main antenna interface, the secondary antenna interface, the 4G antenna interface, the WiFi antenna interface and the data line interface are all abutted against the corresponding supporting blocks, and the plurality of supporting blocks are respectively located in the corresponding through holes.

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