A quick matching installation device and method suitable for aerial remote sensing equipment

Abstract

A kind of quick matching installation device and installation method suitable for aerial remote sensing equipment, belong to aerial remote sensing and mechanical technical field.Transition plate is fixedly installed on the floor of aircraft by rotating flange plate and cooperating with the slot hole of transition plate flange plate slot, and the rotating flange plate can rotate freely after being put into the slot hole of transition plate flange plate slot, according to different aircraft models and different floor fixed dimensions, the angle of rotating flange plate is adjusted to select different multi-point self-adaptive fixed screw hole positions to adapt to the aircraft floor screws or tracks with unadjustable positions.

Description

Technical Field

[0001] This invention relates to a rapid matching and installation device and method for airborne remote sensing equipment, belonging to the fields of airborne remote sensing and mechanical technology. Background Technology

[0002] Airborne remote sensing is a technology that acquires information about the Earth's surface or subsurface by mounting remote sensing equipment on aircraft. In recent years, airborne remote sensing has developed rapidly. Unlike in the past, when there were fewer types of airborne remote sensing equipment, resulting in relatively simple installation methods and fixed installation dimensions, the development of airborne remote sensing technology has led to the emergence of numerous airborne remote sensing devices for different fields and needs, such as oblique aerial photography, airborne lidar, airborne depth sounding radar, airborne hyperspectral imaging, and airborne SAR. Furthermore, the range of compatible aircraft has also expanded, including Cessna 208B, Great Bear, King Air series, and Pilatus series aircraft. This has resulted in significant uncertainty and unique characteristics in the installation methods of airborne remote sensing equipment.

[0003] Taking the airborne laser testing system mounted on the Cessna 208B fixed-wing flight platform as an example, the most common solution is to customize a special aircraft floor and equipment transition plate according to the equipment size parameters, or temporarily drill fixing screw holes on the existing transition plate. This traditional transition plate and installation method has certain safety hazards, and even the risk of equipment damage. It is not only inefficient, but may also lead to economic losses. Summary of the Invention

[0004] To overcome the shortcomings of existing technologies, this invention provides a rapid matching and installation device and method for aerial remote sensing equipment.

[0005] A rapid matching and installation method for aviation remote sensing equipment is disclosed. By pressing a rotating flange into the groove of a transition plate flange, the transition plate is fixedly installed on the aircraft floor. After the rotating flange is inserted into the groove of the transition plate flange, it can rotate freely. Depending on the different aircraft models and different floor fixing sizes, different multi-point adaptive fixing screw hole positions can be selected by adjusting the angle of the rotating flange to adapt to aircraft floor screws or tracks that cannot be adjusted.

[0006] Two or more through holes are made on the rotating flange. The diameter of the through holes is 2 mm to 20 mm. The position of the through holes is as follows: a radial line is formed from the center of the circular end face of the rotating flange in the circumferential direction. Concentric circles are set at the center of the circular end face. The intersection of the concentric circles and the radial line is the center of the through hole. The number of through holes is less than the number of concentric circles. The diameter difference between two adjacent concentric circles is the diameter of the through hole. The through holes are used as multi-point adaptive fixing screw holes. The hole positions of the through holes are offset from the center of the circular end face in the radial direction. An aviation remote sensing window is opened in the transition plate. The aviation remote sensing equipment is installed on the transition plate.

[0007] A rapid matching and installation device for aviation remote sensing equipment is provided. The transition plate has transition plate flange slots, and a rotating flange is connected to the transition plate flange slots. The transition plate is connected to the aircraft floor. Two or more through holes are opened on the rotating flange. The transition plate flange slots are distributed at the four corners of the transition plate. There is a round connecting plate at the bottom of the transition plate flange slots. The rotating flange falls into the transition plate flange slots, and the round connecting plate contacts the end face of the rotating flange when it falls in.

[0008] This invention is used to fix aerial remote sensing equipment on aircraft floor rails or bolts, and can realize real-time adjustment of the relative position of the equipment and the aircraft to quickly complete the installation and fixation of the equipment and the aircraft. It can not only reduce the amount of field work and improve work efficiency, but also ensure the rigidity of the transition plate and guarantee the safety of the equipment and flight.

[0009] This invention effectively solves the problem of temporary drilling; this invention can adjust and fix the relative installation position in real time; this invention ensures that the installation holes are evenly distributed and guarantees the load-bearing capacity of the transition plate; this invention has a rotation adjustment design; this invention's fixing pins ensure stable fixation; this invention has a method for adjusting the position of the transition plate of aviation remote sensing equipment; this invention's size and specifications are convenient for field transport; this invention's aviation aluminum material makes the device lightweight.

[0010] This invention is mainly used when installing aerial remote sensing equipment on fixed-wing aircraft, where the spacing of the fixed tracks varies due to different models or batches of aircraft, making it difficult to adapt the aerial remote sensing equipment to the aircraft floor. It can also solve the problem of avoiding repetitive drilling when the relative position of the mobile device and the aircraft's remote sensing window needs to be adjusted.

[0011] This invention can effectively improve the installation efficiency of aerial remote sensing equipment and can be adapted to aircraft with various parameters, achieving multiple uses with one device. It can significantly reduce time and economic costs, while taking into account the safety of aerial photography operations, the convenience of personnel installation and transportation, and the operability of equipment debugging.

[0012] This invention significantly improves the installation speed of various aerial remote sensing devices on different aircraft, while also increasing operational efficiency. When installing aerial remote sensing devices on different flight platforms, existing fixing screw holes can be completely eliminated. Even with a wide variety of sizes, it is impossible to fully adapt to all existing models of aerial remote sensing devices and aircraft. When working at the airport, it effectively avoids the inconvenience of temporarily drilling holes based on on-site measurement data.

[0013] The rapid matching and installation method proposed in this invention can effectively solve the problem that existing fixed hole positions cannot meet the dimensional deviation caused by various random combinations. Therefore, when the hole positions change, there is no need to drill on site. After adjusting the corresponding rotating hole position mechanism, it can directly match the aircraft floor track and track screws, avoiding the complicated process of measurement, comparison, drilling and reinstallation, and greatly improving work efficiency.

[0014] This invention effectively solves the potential safety hazards in the installation of aerial remote sensing equipment. Given the current issues with temporary drilling due to fixed hole positions, temporarily opening holes on existing transition plates may result in uneven hole distribution or excessively close spacing, leading to insufficient strength of the screw holes connecting to the aircraft floor. Alternatively, too many temporary holes may cause the overall strength of the equipment transition plate to fail to meet flight safety requirements.

[0015] The rapid matching device proposed in this invention is used for installation and fixation with aircraft tracks or floors. The device is rotatable, and the density and distribution of the openings in the device itself meet the rigidity requirements. The multi-size adaptable mounting holes can be adjusted at any time. It can be adjusted in four directions according to the size of the equipment, the position and size of the aircraft window openings, and the position of the aircraft floor tracks or floor fixing bolts to quickly match the equipment with the aircraft installation position, thereby greatly reducing the amount of fieldwork, significantly improving work efficiency, and ensuring equipment and flight safety. Attached Figure Description

[0016] When considered in conjunction with the accompanying drawings, the invention will be more fully and better understood, and its many accompanying advantages will become readily apparent, by referring to the following detailed description. However, the accompanying drawings, which are provided to further illustrate the invention and form part of this invention, are used to explain the invention and do not constitute an undue limitation thereof, as shown in the figures:

[0017] Figure 1 This is a schematic diagram of the transition plate structure of the present invention.

[0018] Figure 2 This is a schematic diagram of one structure of the rotating flange of the present invention.

[0019] Figure 3 This is a schematic diagram of the second structure of the rotating flange of the present invention.

[0020] Figure 4 This is a schematic diagram of the third structure of the rotating flange of the present invention.

[0021] Figure 5 This is a schematic diagram of the fourth structure of the rotating flange of the present invention.

[0022] Figure 6 This is a schematic diagram of the fifth structure of the rotating flange of the present invention.

[0023] Figure 7 This is a schematic diagram of the sixth structure of the rotating flange of the present invention.

[0024] Figure 8 This is a schematic diagram of the seventh structure of the rotating flange of the present invention.

[0025] Figure 9 This is a schematic diagram of the eighth structure of the rotating flange of the present invention. Detailed Implementation

[0026] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0027] Obviously, many modifications and variations made by those skilled in the art based on the spirit of this invention fall within the scope of protection of this invention.

[0028] Those skilled in the art will understand that, unless specifically stated otherwise, the singular forms “a,” “an,” “the,” and “the” used herein may also include the plural forms. It should be further understood that the term “comprising” as used in this specification means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. It should be understood that when an element or component is referred to as “connected” to another element or component, it may be directly connected to the other element or component, or there may be intermediate elements or components. The term “and / or” as used herein includes any and all combinations of one or more of the associated listed items.

[0029] Those skilled in the art will understand that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art.

[0030] To facilitate understanding of the embodiments, further explanations and descriptions will be provided below, and the various embodiments do not constitute a limitation of the present invention.

[0031] Example 1: As Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 and Figure 9As shown, a rapid matching and installation device suitable for aviation remote sensing equipment is provided. The transition plate 1 has a transition plate flange slot 2. The rotating flange 5 is connected to the transition plate flange slot 2. The transition plate 1 is connected to the aircraft floor. Two or more through holes 6 are opened on the rotating flange. The transition plate flange slot 2 is distributed at the four corners of the transition plate 1. The diameter of the through holes 6 is 2 mm to 20 mm.

[0032] The bottom of the transition plate flange slot 2 has a circular connecting plate. The rotating flange 5 falls into the transition plate flange slot 2, and the circular connecting plate contacts the end face where the rotating flange 5 falls.

[0033] The rotating flange 5 can rotate within the transition plate flange slot 2. After the rotating flange 5 is connected to the transition plate flange slot 2, the rotating flange 5 and the transition plate flange slot 2 have the same end face. Alternatively, the end face of the rotating flange 5 may be higher than the end face of the transition plate 1.

[0034] The transition plate 1 has an airborne remote sensing window 3 and an airborne remote sensing device 4.

[0035] Example 2: As Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , Figure 6 , Figure 7 , Figure 8 and Figure 9 As shown, a rapid matching and installation method for aviation remote sensing equipment is described. The transition plate is fixed to the aircraft floor by pressing a rotating flange into the groove of the transition plate flange. After the rotating flange is inserted into the groove of the transition plate flange, it forms a seamless plane. The rotating flange does not protrude from the plane of the transition plate and can rotate freely. Depending on the aircraft model and the floor fixing size, different multi-point adaptive fixing bolt hole positions can be selected by adjusting the angle of the rotating flange to adapt to aircraft floor bolts or rails whose positions cannot be adjusted. Two or more through holes 6 are drilled on the rotating flange 5, with a diameter of 2 mm to 20 mm. mm, the position of through hole 6: a radial line is formed from the center of the circular end face of the rotating flange 5 in the circumferential direction. Concentric circles are set at the center of the circular end face. The intersection of the concentric circles and the radial line is the center of the through hole 6. The number of through holes 6 is less than the number of concentric circles. The diameter difference between two adjacent concentric circles is the diameter value of the through hole 6. The through hole 6 serves as a multi-point adaptive fixing screw hole. The hole positions of the through holes 6 are offset from the center of the circular end face in the radial direction. An aviation remote sensing window 3 is opened in the transition plate 1. The aviation remote sensing equipment 4 is installed on the transition plate 1.

[0036] Example 3: A method for rapid matching and installation of airborne remote sensing equipment, such as... Figure 2 , Figure 3 , Figure 4, Figure 5 , Figure 6 and Figure 7 As shown, radial lines are divided into 16 equal parts on the rotating flange 5 at an angle of 22.5°. Through holes with a diameter of 5 to 20 mm, preferably 10 mm, are opened on each of the equal parts to serve as through holes 6 for multi-point adaptive fixing screw holes.

[0037] like Figure 2 As shown, the included angle between the radial lines of adjacent through holes 6 is 45°.

[0038] like Figure 3 As shown, the included angle between the radial lines of adjacent through holes 6 is 67.5°.

[0039] like Figure 4 As shown, the included angle between the radial lines of adjacent through holes 6 is 90°.

[0040] like Figure 5 As shown, the included angle between the radial lines of adjacent through holes 6 is 112.5°.

[0041] like Figure 6 As shown, the included angle between the radial lines of adjacent through holes 6 is 135°.

[0042] like Figure 7 As shown, the included angle between the radial lines of adjacent through holes 6 is 157.5°.

[0043] Adjacent is defined as concentric circles being adjacent.

[0044] like Figure 8 As shown, the radial lines on the rotating flange 5 are divided into 8 equal parts. The center positions of the through holes 6 are distributed at the intersection points of the concentric circles and the radial lines. The center positions of the through holes 6 on the rotating flange 5 are arbitrary.

[0045] like Figure 9 As shown, the rotating flange 5 is divided into 8 equal parts at an angle of 45°. The center of the through hole 6 is distributed at the intersection of the concentric circle and the radial line. The center of the through hole 6 is arbitrary on the rotating flange 5.

[0046] Alternatively, the radial lines on the rotating flange 5 are not equally divided, and the center of the through hole 6 is distributed at the intersection of the concentric circles and the radial lines. The center of the through hole 6 is arbitrary on the rotating flange 5.

[0047] Depending on the aircraft model and the floor fixing size, this aviation remote sensing equipment can quickly match the installation device by adjusting the angle of the rotating flange to select different multi-point adaptive fixing screw hole positions to adapt to aircraft floor screws or tracks that cannot be adjusted.

[0048] When it is necessary to adjust the relative position of the equipment on the aircraft window, the angle of the rotating flange can be adjusted separately. The left and right and up and down are infinitely adjustable, and the angle can be adjusted accordingly. It is mainly used when the aviation remote sensing equipment is installed on a fixed-wing aircraft. Due to the different models or batches of aircraft, the fixed track spacing is different, and the aviation remote sensing equipment cannot be adapted when it is fixed to the aircraft floor. It can also solve the problem of avoiding repetitive drilling work when the relative position of the mobile device and the aircraft remote sensing window needs to be adjusted.

[0049] As described above, embodiments of the present invention have been explained in detail. However, many modifications are possible without departing substantially from the inventive points and effects of the present invention, which will be apparent to those skilled in the art. Therefore, all such modifications are also included within the scope of protection of the present invention.

Claims

1. A method for rapid matching and installation of airborne remote sensing equipment, characterized in that, The transition plate is fixed to the aircraft floor by pressing the rotating flange into the groove of the transition plate flange. After the rotating flange is inserted into the groove of the transition plate flange, it can rotate freely. Depending on the aircraft model and the different floor fixing dimensions, different multi-point adaptive fixing bolt hole positions can be selected by adjusting the angle of the rotating flange to adapt to aircraft floor bolts or rails that cannot be adjusted. Through holes serve as multi-point adaptive fixing screw holes. Location of the through hole: Radial lines are formed from the center of the circular end face of the rotating flange in a circumferential direction. Concentric circles are set at the center of the circular end face, and the intersection of the concentric circles and the radial lines is the center of the through hole. Each of the multiple through holes is located on a circle of different radii centered at the center of the circular end face of the rotating flange.

2. The method for rapid matching and installation of airborne remote sensing equipment according to claim 1, characterized in that, Two or more through holes are made on the rotating flange, with a diameter of 2 mm to 20 mm.

3. The method for rapid matching and installation of aerial remote sensing equipment according to claim 2, characterized in that, The number of through holes is less than the number of concentric circles.

4. The method for rapid matching and installation of airborne remote sensing equipment according to claim 3, characterized in that, The difference in diameter between two adjacent concentric circles is the numerical value of the diameter of the through hole.

5. A method for rapid matching and installation of airborne remote sensing equipment according to claim 2, characterized in that, The holes between the through holes are offset from the center of the circular end face in a radial direction.

6. A method for rapid matching and installation of airborne remote sensing equipment according to claim 2, characterized in that, An aerial remote sensing window is provided in the transition plate, and the aerial remote sensing equipment is installed on the transition plate.

7. A rapid matching and installation device for airborne remote sensing equipment, characterized in that, The transition plate has flange slots for the swivel flange, which mate with the transition plate flange slots for connection. The transition plate connects to the aircraft floor. The swivel flange has two or more through holes. The flange slots are located at the four corners of the transition plate. A rounded connecting plate is located at the bottom of each flange slot. When the swivel flange falls into the flange slot, the rounded connecting plate contacts the end face of the swivel flange. After the swivel flange is inserted into the flange slot, it can rotate freely. Location of the through hole: Radial lines are formed from the center of the circular end face of the rotating flange in a circumferential direction. Concentric circles are set at the center of the circular end face, and the intersection of the concentric circles and the radial lines is the center of the through hole. Multiple through holes are respectively set on circles of different radii with the center of the circular end face of the rotating flange as the center.

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