Universal data link shielding device for aircraft testing

Abstract

The utility model relates to an aircraft test general type data chain shielding device in the technical field of aircraft test technology, contain connecting rod, fixed rod, folding rod, positioning sliding sleeve and shielding casing, the head end of connecting rod is equipped with fastening band ring, the pole body of connecting rod is close to the tail end and is equipped with test window, the top of fixed rod is connected with the tail end of connecting rod, the top of folding rod is hinged with the bottom of fixed rod through hinge shaft, positioning sliding sleeve is sleeved in fixed rod outward, and can move down so that folding rod and fixed rod keep coaxial, shielding casing is equipped with inner chamber, the outer top surface of shielding casing is connected with the bottom of folding rod correspondingly, the bottom of shielding casing is equipped with communication interface, the front side wall of shielding casing is equipped with data chain test mouth in the middle part correspondingly fastening band ring, the front side wall outer wall surface lower part of shielding casing is equipped with the bearing part for bearing aircraft tail end, the upper surface both sides of bearing part are equipped with side stop part, this general type data chain shielding device is strong in universality, and test clamping is stable, and use and storage are convenient.

Description

Technical Field

[0001] This invention relates to the field of aircraft testing technology, and in particular to a universal data link shielding device for aircraft testing. Background Technology

[0002] Most existing data link shields for aircraft testing are fixed-model dedicated test components, which cannot achieve universal testing for multiple aircraft models. This directly results in a wide variety of data link shield models, poor versatility, and inconvenience in use. In addition, most existing shield models are also large in size, making them inconvenient to operate and occupying a lot of space when stored. Summary of the Invention

[0003] To overcome the shortcomings of the prior art, the present invention discloses a universal data link shielding device for aircraft testing, which is highly versatile, stable in test clamping, and convenient to use and store.

[0004] To achieve the above-mentioned objectives, the present invention adopts the following technical solution:

[0005] A universal data link shielding device for aircraft testing includes a connecting rod, a fixed rod, a folding rod, a positioning sleeve, and a shielding housing. The connecting rod has an adjustable fastening ring at its head end, a test window near the tail end of the connecting rod, a top end of the fixed rod perpendicularly connected to the tail end of the connecting rod, and a top end of the folding rod hinged to the bottom end of the fixed rod via a hinge axis perpendicular to both the connecting and fixed rods. The positioning sleeve is fitted over the fixed rod and can be moved down to the hinge axis to keep the folding and fixed rods coaxial. The shielding housing has an inner cavity for mounting a data link antenna, a top surface of the shielding housing corresponding to the bottom end of the folding rod, a communication interface on the bottom surface of the shielding housing, a data link test port in the middle of the front sidewall corresponding to the fastening ring, a support portion for supporting the tail end of the aircraft on the lower part of the outer surface of the front sidewall of the shielding housing, and side baffles on both sides of the upper surface of the support portion.

[0006] Furthermore, the fastening band is formed by a circular elastic fastening band, one end of which is installed on one side of the connecting rod head, and the other end of which is detachably snapped onto the other side of the connecting rod head.

[0007] Furthermore, the fastening band is made of semi-transparent silicone rubber.

[0008] Furthermore, the connecting rod is made of a lightweight metal material, and the lower surface of the connecting rod is designed as a concave arc surface, with protective pads provided on both the concave arc surface and the wall of the test window.

[0009] Furthermore, the upper surface of the tail end of the connecting rod is provided with a mounting groove, the groove opening of the mounting groove is detachably covered with a groove cover, the bottom of the mounting groove is provided with an insertion hole, the top end of the fixing rod is provided with a plug portion adapted to the insertion hole, and the top surface of the plug portion is provided with a connecting screw hole in the center.

[0010] Furthermore, the bottom end of the fixed rod is provided with a hinge seat, the hinge seat includes two side plates for rotatably mounting the two ends of the hinge shaft respectively, the top surface of the folding rod is provided with a hinge lug plate corresponding to the two side plates, the surface of the hinge lug plate is provided with a hinge hole corresponding to the hinge shaft, and the side of the hinge seat away from the fastening band is provided with a limiting stop.

[0011] Furthermore, the upper and lower parts of the fixing rod are both provided with external threads, the upper inner wall of the positioning sleeve is provided with an internal thread that matches the external threads, and the top of the folding rod is provided with a frustum structure that corresponds to the lower end of the positioning sleeve for positioning.

[0012] Furthermore, the folding rod has a square body, and the bottom end of the folding rod is detachably connected to the shielding housing.

[0013] Furthermore, the front sidewall of the shielding shell is recessed to form a cavity, the outer edges of the two sides of the cavity opening are the first reference surface, the front end face of the side baffle is the second reference surface, the opposite sides of the two side baffles are set as the third reference surface, and the upper surface of the bearing part is set as the fourth reference surface. The first reference surface, the second reference surface, the third reference surface and the fourth reference surface are all provided with wave-absorbing material.

[0014] Furthermore, the inner wall of the rear side wall of the shielding housing is provided with an antenna mounting slot.

[0015] By employing the technical solution described above, the present invention has the following beneficial effects:

[0016] The universal data link shielding device for aircraft testing disclosed in this invention features multi-model compatibility, compact size, lightweight, and convenient use and storage. In terms of applicability, it breaks the limitation of one-to-one testing of dedicated test components, realizing a universal testing function applicable to multiple aircraft models with a single test device. Regarding the fixing method, it utilizes the outer surface of the fairing of the aircraft under test as a positioning reference. During use, simply align the shielding shell with the fairing, then press the connecting rod against the surface of the device and tighten the fastening strap to achieve reliable clamping and fixation, which is both stable and convenient. Furthermore, the shielding shell can be folded for storage and transportation, occupying minimal space and facilitating transport. In addition, it possesses shielding functionality, significantly reducing radiation to the surrounding environment and test personnel, lowering the intensity value to a safe range, and greatly reducing the number and volume of structural components while meeting testing requirements, making the overall device simple and lightweight to use. Attached Figure Description

[0017] Figure 1 This is a three-dimensional schematic diagram of an embodiment of the present invention;

[0018] Figure 2 yes Figure 1 Another perspective 3D illustration;

[0019] Figure 3 This is a schematic diagram of the connecting rod.

[0020] Figure 4 This is a cross-sectional view of the fixed rod.

[0021] Figure 5 This is a cross-sectional view of the folding rod.

[0022] Figure 6 This is a schematic diagram of the structure of the shielding shell;

[0023] Figure 7 This is a schematic diagram of the internal structure of the shielding housing;

[0024] Figure 8 This is a schematic diagram of the folded state of the present invention;

[0025] Figure 9 This is a schematic diagram of the usage state of the present invention.

[0026] In the diagram: 1. Fastening band; 2. Connecting rod; 201. Concave arc surface; 202. Mounting slot; 203. Insertion hole; 3. Test window; 4. Positioning sleeve; 5. Fixing rod; 501. Plug part; 502. Connecting screw hole; 503. External thread; 504. Side plate part; 505. Limiting stop; 6. Shielding shell; 601. First reference surface; 7. Folding rod; 701. Hinge plate; 702. Frustum structure; 8. Side stop part; 801. Second reference surface; 802. Third reference surface; 9. Support part; 901. Fourth reference surface; 10. Slot cover; 11. Hinge shaft; 12. Data link test port; 13. Communication interface; 14. Antenna mounting slot frame. Detailed Implementation

[0027] The technical solution of the present invention will now be described with reference to the accompanying drawings of the embodiments of the present invention. In the description, it should be understood that the terms "upper," "lower," "front," "rear," "left," and "right," etc., indicating directions or positional relationships, are only used to correspond to the accompanying drawings of the present invention for the purpose of facilitating the description of the present invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation.

[0028] Combined with appendix Figure 1-7The aforementioned universal data link shielding device for aircraft testing includes a connecting rod 2, a fixing rod 5, a folding rod 7, a positioning sliding sleeve 4, and a shielding shell 6, which is generally a cuboid structure.

[0029] The head end of the connecting rod 2 is equipped with an adjustable fastening band 1, which is used to adjust the hoop force when clamping the aircraft. Specifically, it can be adjusted directly by adjusting the circumference length, or it can be made into an elastic element to adjust the tightness. For example, as needed, the fastening band 1 is formed by a loop of elastic fastening band. One end of the fastening band is installed on one side of the head end of the connecting rod 2, and the other end of the fastening band is detachably snapped onto the other side of the head end of the connecting rod 2 for quick assembly and disassembly. Specifically, the fastening band can be integrally cast by a special mold, with two connecting holes at both ends. By passing a shaft through the connecting holes, one end is hinged to one side of the head end of the connecting rod 2, and the other end is hinged to a hanging ring. A hook is fixed on one side of the head end of the connecting rod 2 for easy hooking and connection of the hanging ring. The entire structure is reliable and durable. In addition, the fastening band 1 is made of semi-transparent silicone rubber, which can effectively avoid contamination of the appearance color of the tested aircraft.

[0030] The connecting rod 2 has a test window 3 near its tail end for testing the tail components of the aircraft under test. Depending on the requirements, the connecting rod 2 is made of a lightweight metal material, such as magnesium-aluminum alloy, which ensures the rigidity of the entire component while effectively reducing its overall weight. The upper surface of the connecting rod 2 is a raised arc surface for easy handling, while the lower surface is a concave arc surface 201 to match the outer circular surface of the aircraft under test. Both the concave arc surface 201 and the walls of the test window 3 are equipped with protective pads, which can also be made of semi-transparent silicone rubber. The rubber material serves as a buffer and protector, preventing contamination of the tested aircraft's exterior color. The top of the fixing rod 5 is vertically connected to the tail of the connecting rod 2. As needed, the upper surface of the tail of the connecting rod 2 is provided with an installation groove 202. The groove opening of the installation groove 202 is detachably covered with a groove cover 10. The bottom of the installation groove 202 is provided with an insertion hole 203. The top of the fixing rod 5 is provided with a plug part 501 that is adapted to the insertion hole 203. The top surface of the plug part 501 is provided with a connecting screw hole 502, which not only ensures a stable connection but also facilitates disassembly and maintenance.

[0031] The top end of the folding rod 7 and the bottom end of the fixed rod 5 are hinged to each other via a hinge pin 11 that is perpendicular to both the connecting rod 2 and the fixed rod 5. In addition, the bottom end of the fixed rod 5 is provided with a hinge seat, which includes two side plate portions 504 for rotatably mounting the two ends of the hinge pin 11 respectively. The top surface of the folding rod 7 is provided with a hinge ear plate 701 that is inserted between the two side plate portions 504. The surface of the hinge ear plate 701 is provided with a hinge hole corresponding to the hinge pin 11, ensuring a tight connection and flexible rotation. A limiting stop 505 is provided on the side of the hinge seat away from the fastening band 1. The limiting stop 505 is used for folding limit to prevent the folding rod 7 from rotating and folding towards the end away from the fastening band 1, which would cause the folding rod 7 to unfold at an excessive angle.

[0032] The positioning sleeve 4 is fitted outside the fixed rod 5 and can be moved down to the hinge pin 11 so that the folding rod 7 and the fixed rod 5 are kept coaxial. As needed, the upper and lower parts of the fixed rod 5 are provided with external threads 503. The upper inner wall of the positioning sleeve 4 is provided with an internal thread that matches the external thread 503. The top of the folding rod 7 is provided with a frustum structure 702 that is fitted and positioned at the lower end of the positioning sleeve 4. All threads are fine threads. The upper external thread 503 is used to fix the positioning sleeve 4 in the folded state to prevent the positioning sleeve 4 from slipping and shaking. The lower external thread 503 is used to tighten the positioning sleeve 4 in the unfolded state so that the frustum structure 702 and the inner conical surface of the positioning sleeve 4 are fitted and tightened. This can eliminate the small gap at the hinge pin 11 connection, ensure the coaxiality of the folding rod 7 and the fixed rod 5, and also improve the rigidity of the entire folding mechanism.

[0033] The shielding housing 6 has an inner cavity for mounting the data link antenna. In addition, the inner wall of the rear side of the shielding housing 6 has an antenna mounting slot 14, in which the data link antenna can be installed for easy cable routing. The outer top surface of the shielding housing 6 is connected to the bottom end of the folding rod 7. If necessary, the folding rod 7 can be made into a square rod, and the bottom end of the folding rod 7 can be detachably connected to the shielding housing 6. Specifically, a square groove can be opened on the bottom end face of the folding rod 7, and a fixed protrusion can be fixed on the outer top wall of the shielding housing 6. The protrusion and the square groove are inserted and then fixed by a pin to ensure the reliability of the connection.

[0034] The bottom surface of the shielding housing 6 is provided with a communication interface 13, which is connected to the test system through a dedicated connector. The shielding housing 6 has a data link test port 12 in the middle of the front side wall corresponding to the fastening band 1. The height and distance are determined according to the test requirements and it can be used for various types of aircraft under test. The lower part of the outer wall of the front side of the shielding housing 6 is provided with a support part 9 for supporting the tail end of the aircraft. The upper surface of the support part 9 is provided with side baffles 8 on both sides. If necessary, the center of the front side wall of the shielding housing 6 is recessed to form a cavity. The outer edges of the two sides of the cavity opening are the first reference surface 601. The front end face of the side shield 8 is the second reference surface 801, the opposite sides of the two side shields 8 are set as the third reference surface 802, and the upper surface of the bearing part 9 is set as the fourth reference surface 901. The positioning reference surfaces are designed according to the appearance characteristics of various types of aircraft under test to ensure that they can fit and be positioned tightly when applied to different aircraft under test. The first reference surface 601, the second reference surface 801, the third reference surface 802 and the fourth reference surface 901 are all provided with wave-absorbing materials, which can absorb and reduce test radiation and protect the appearance of the aircraft under test.

[0035] The universal data link shielding device for aircraft testing described in this invention has two states: a folded state and an unfolded state. The folded state is the state during transportation and placement, while the unfolded state is the state during use. In the folded state, the positioning sleeve 4 needs to be pulled upward and rotated to the upper external thread of the fixing rod 5 to fix the positioning sleeve 4. Then, the folding rod 7 is pushed forward and rotated 90° around the hinge axis 11. In the unfolded state, the folding rod 7 needs to be rotated 90° backward around the hinge axis 11. Then, the positioning sleeve 4 is rotated off from the upper external thread of the fixing rod 5 and pressed downward and rotated to fix it to the lower external thread of the fixing rod 5 to achieve reliable fixation and start use.

[0036] When using it, the shielding shell 6 must first be converted to the unfolded state. Then, the positioning reference surface should be aligned with the feature surface of the aircraft under test, the fastening strap 1 should be tightened, and the hanging ring should be hung on the hook. The method of use is simple and convenient, and the repeatability of positioning is high. After multiple uses, the positioning and shielding effects are good, which meets the general testing requirements of various types of aircraft under test.

[0037] The parts of this invention not described in detail are prior art. It will be apparent to those skilled in the art that this invention is not limited to the details of the above exemplary embodiments, and that the invention can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. Therefore, the above embodiments should be regarded as exemplary and non-limiting in all respects. The scope of this invention is defined by the appended claims rather than the foregoing description. Therefore, it is intended to include all changes that fall within the meaning and scope of the equivalents of the claims within this invention, and no reference numerals in the claims should be regarded as limiting the content of the claims.

Claims

1. A universal data link shielding device for aircraft testing, characterized in that: It includes a connecting rod (2), a fixing rod (5), a folding rod (7), a positioning sleeve (4), and a shielding shell (6); the lower surface of the connecting rod (2) is a concave arc surface (201) adapted to the outer circular surface of the aircraft under test; the head end of the connecting rod (2) is equipped with an adjustable fastening ring (1); the rod body of the connecting rod (2) near the tail end is provided with a test window (3); the top end of the fixing rod (5) is perpendicularly connected to the tail end of the connecting rod (2); the top end of the folding rod (7) and the bottom end of the fixing rod (5) are connected by a hinge (1) perpendicular to both the connecting rod (2) and the fixing rod (5). 1) Corresponding to the hinge, the positioning sleeve (4) is sleeved outside the fixed rod (5) and can be moved down to the hinge axis (11) so that the folding rod (7) and the fixed rod (5) are kept in the same direction. The upper and lower parts of the fixed rod (5) are provided with external threads (503). The upper inner wall of the positioning sleeve (4) is provided with an internal thread that matches the external thread (503). The top of the folding rod (7) is provided with a frustum structure (702) that corresponds to the lower end of the positioning sleeve (4) for positioning. The upper external thread (503) is used to fix the positioning sleeve (4) when the device is in the folded state for transportation and placement. The lower external thread (503) is used to fix the positioning sleeve (4). The thread (503) is used to tighten the positioning sleeve (4) when the device is in the unfolded state, so that the frustum structure (702) and the inner conical surface of the positioning sleeve (4) are fitted together and tightened; the shielding shell (6) is provided with an inner cavity for installing the data link antenna, the outer top surface of the shielding shell (6) is connected to the bottom end of the folding rod (7), the bottom surface of the shielding shell (6) is provided with a communication interface (13), the middle of the front side wall of the shielding shell (6) corresponding to the fastening band (1) is provided with a data link test port (12), and the lower part of the outer wall of the front side wall of the shielding shell (6) is provided with a support for the tail end of the aircraft. The supporting part (9) has side baffles (8) on both sides of its upper surface; the front side wall of the shielding shell (6) is recessed to form a groove cavity, the outer edges of the groove opening on both sides of the groove cavity are the first reference surface (601), the front end surface of the side baffle (8) is the second reference surface (801), the opposite sides of the two side baffles (8) are set as the third reference surface (802), and the upper surface of the supporting part (9) is set as the fourth reference surface (901). The positioning reference surface is designed according to the appearance characteristics of various types of aircraft under test to ensure that it can fit and position tightly when applied to different aircraft under test.

2. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The fastening band (1) is formed by a circular elastic fastening band, one end of which is installed on one side of the head end of the connecting rod (2), and the other end of which is detachably snapped onto the other side of the head end of the connecting rod (2).

3. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The fastening band (1) is a semi-transparent silicone rubber band.

4. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The connecting rod (2) is made of light metal material, and the concave arc surface (201) and the wall of the test window (3) are provided with protective pads.

5. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The upper surface of the tail end of the connecting rod (2) is provided with a mounting groove (202). The groove opening of the mounting groove (202) is detachably covered with a groove cover (10). The bottom of the mounting groove (202) is provided with a plug hole (203). The top end of the fixing rod (5) is provided with a plug part (501) adapted to the plug hole (203). The top surface of the plug part (501) is provided with a connecting screw hole (502).

6. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The bottom end of the fixed rod (5) is provided with a hinge seat, which includes two side plate parts (504) for rotating and installing the two ends of the hinge shaft (11) respectively. The top surface of the folding rod (7) is provided with a hinge ear plate (701) that is inserted between the two side plate parts (504). The surface of the hinge ear plate (701) is provided with a hinge hole through which the hinge shaft (11) passes. The side of the hinge seat away from the fastening band (1) is provided with a limiting stop (505).

7. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The folding rod (7) has a square rod body, and the bottom end of the folding rod (7) is detachably connected to the shielding shell (6).

8. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The first reference surface (601), the second reference surface (801), the third reference surface (802) and the fourth reference surface (901) are all provided with wave-absorbing material.

9. The universal data link shielding device for aircraft testing according to claim 1, characterized in that: The inner wall of the rear side of the shielding housing (6) is provided with an antenna mounting slot (14).

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