A radar assembly for take-off and landing guidance

Abstract

The utility model discloses a radar assembly for take-off and landing guidance, and relates to the technical field of radar assemblies. The utility model includes two bracket frames, and connecting plates are fixedly installed on the side walls of the two bracket frames, and spring hinges are hingedly installed on the side walls of the connecting plates, and a spring telescopic plate is fixedly installed on one side of the spring hinge, and a radar support mechanism is fixedly installed on one side of the spring telescopic plate, and a measuring radar is arranged on the radar support mechanism, and a connecting mechanism is fixedly installed on the side walls of the bracket frames, and a traction mechanism is arranged on the connecting mechanism, and a connecting hinge is arranged on one side of the traction mechanism. The utility model can expand the compressed airbag in the storage box, and the expanded compressed airbag can be used to protect the measuring radar, thereby further reducing the probability of damage to the measuring radar, improving the safety of the use of the measuring radar, and facilitating the application of the measuring radar on unmanned aerial vehicles.

Description

Technical Field

[0001] The utility model relates to the technical field of radar components, in particular to a radar component for take-off and landing guidance. Background Art

[0002] Currently, some unmanned aircraft are equipped with airborne lidar, which is usually used for laser detection and ranging. The lidar on drones is usually more expensive. When carried on a drone, if the drone fails or is damaged, the unmanned components of the lidar will be at greater risk of damage.

[0003] At present, due to the lack of corresponding components to protect the radar in ordinary drones, laser radars are not carried on ordinary drones, which limits the scope and application of radars and also adversely affects the safety of airborne radars. For this reason, a radar component for take-off and landing guidance is proposed. Utility Model Content

[0004] The purpose of the utility model is to solve the problem that ordinary unmanned aerial vehicles lack corresponding components to protect the radar, so that ordinary unmanned aerial vehicles will not be equipped with laser radars, thereby limiting the use range and application of the radar and also causing adverse effects on the safety of the use of the airborne radar. The utility model provides a radar component for take-off and landing guidance.

[0005] In order to achieve the above-mentioned purpose, the utility model specifically adopts the following technical solutions:

[0006] A radar assembly for take-off and landing guidance comprises two support frames, connecting plates are fixedly installed on the side walls of the two support frames, spring hinges are hingedly installed on the side walls of the connecting plates, and a spring telescopic plate is fixedly installed on one side of the spring hinge, a radar support mechanism is fixedly installed on one side of the spring telescopic plate, and a measuring radar is arranged on the radar support mechanism, a connecting mechanism is fixedly installed on the side walls of the support frames, and a traction mechanism is arranged on the connecting mechanism, a connecting hinge is arranged on one side of the traction mechanism, and the connecting hinge is fixedly installed on the radar support mechanism, and two side protection mechanisms are arranged on the radar support mechanism.

[0007] Preferably, the radar support mechanism includes a connecting plate, one side of which is fixedly mounted on the measuring radar, and a rotating slot is symmetrically provided on the side wall of the connecting plate, a clamping shaft is rotatably mounted in both of the rotating slots, and a support plate is fixedly mounted on one side of the clamping shaft, and one side of the support plate is fixedly mounted on the spring telescopic plate.

[0008] Preferably, the connection mechanism comprises a support rod, one end of which is fixedly mounted on the bracket frame, and the other end of which is fixedly mounted with an elastic traction rope.

[0009] Preferably, the traction mechanism comprises an electric hydraulic rod, one end of which is fixedly mounted on the elastic traction rope, and the other end of which is fixedly mounted on the connecting hinge.

[0010] Preferably, the side protection mechanism includes a storage box, one side of the storage box is fixedly mounted on a support plate, and an isolation plate is fixedly mounted inside the storage box, a connecting pipe is provided on the isolation plate, and an electric control valve is fixedly mounted on the side wall of the connecting pipe, the storage box is filled with compressed gas on one side of the isolation plate, and a compressed air bag is fixedly mounted inside the storage box.

[0011] Preferably, the two storage boxes are fixedly mounted on two support plates respectively, and the two storage boxes are distributed in a staggered manner.

[0012] The beneficial effects of the utility model are as follows:

[0013] 1. In the utility model, when the measuring radar is used normally, the support plate is kept in a horizontal state with the help of a spring hinge, so that the measuring radar can be used normally. When the UAV fails to fly, the electric hydraulic rod on the support rod can be started to drive the support plate to lift upward, so that the spring telescopic plate is extended to arch the connecting plate and the measuring radar, so that the measuring radar is lifted above the bottom end of the bracket frame, which can avoid damage to the measuring radar. At the same time, the electric control valve on the isolation plate is started to release the compressed gas, so that the compressed air bag in the storage box can be expanded. The expanded compressed air bag can protect the measuring radar, thereby further reducing the probability of damage to the measuring radar, improving the safety of the use of the measuring radar, and facilitating the application of the measuring radar on the UAV. BRIEF DESCRIPTION OF THE DRAWINGS

[0014] Figure 1 This is a front view schematic diagram of the overall three-dimensional connection structure of the utility model;

[0015] Figure 2 It is a schematic diagram of the three-dimensional connection structure between the connecting plate and the radar supporting mechanism in the utility model;

[0016] Figure 3 It is a schematic diagram of the three-dimensional connection structure of the side protection mechanism in the utility model;

[0017] Figure 4 yes Figure 3 Schematic diagram of the enlarged structure at point A in the middle.

[0018] Figure numerals: 1. Unmanned aircraft; 2. Bracket frame; 3. Connecting plate; 4. Spring telescopic plate; 5. Spring hinge; 6. Support plate; 7. Measuring radar; 8. Storage box; 9. Compression airbag; 10. Support rod; 11. Elastic traction rope; 12. Electric hydraulic rod; 13. Connecting hinge; 14. Isolation plate; 15. Connecting plate; 16. Rotating slot; 17. Card-connected rotating shaft; 18. Connecting pipe; 19. Electric control valve. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the embodiments of the utility model clearer, the technical scheme in the embodiments of the utility model will be clearly and completely described below in conjunction with the drawings in the embodiments of the utility model. Obviously, the described embodiments are part of the embodiments of the utility model, not all of the embodiments. Generally, the components of the embodiments of the utility model described and shown in the drawings here can be arranged and designed in various different configurations.

[0020] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the present invention to be protected, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0021] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings. In addition, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0022] In the description of the embodiments of the present invention, it should be noted that the terms "inside", "outside", "upper", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, or are the orientations or positional relationships in which the utility model product is usually placed when in use. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0023] like Figure 1-4As shown, a radar assembly for take-off and landing guidance includes two bracket frames 2, one side of the bracket frames 2 is fixedly installed on the lower side of the unmanned aircraft 1, a connecting plate 3 is fixedly installed on the side walls of the two bracket frames 2, a spring hinge 5 is hingedly installed on the side wall of the connecting plate 3, and a spring telescopic plate 4 is fixedly installed on one side of the spring hinge 5, and a radar support mechanism is fixedly installed on one side of the spring telescopic plate 4, the radar support mechanism includes a connecting plate 15, and a rotating card slot 16 is symmetrically opened on the side wall of the connecting plate 15, a card-connecting rotating shaft 17 is rotatably installed in each of the two rotating card slots 16, and a support plate 6 is fixedly installed on one side of the card-connecting rotating shaft 17, a measuring radar 7 is fixedly installed on the support plate 6, one side of the connecting plate 15 is fixedly installed on the measuring radar 7, and one side of the support plate 6 is fixedly installed on the spring telescopic plate 4, when the measuring radar 7 is used normally, the support plate 6 is kept in a horizontal state by means of the spring hinge 5, so that the measuring radar 7 can be used normally.

[0024] A connecting mechanism is fixedly installed on the side wall of the bracket frame 2, and the connecting mechanism includes a support rod 10, one end of the support rod 10 is fixedly installed on the bracket frame 2, and the other end of the support rod 10 is fixedly installed with an elastic traction rope 11, and a traction mechanism is arranged on the elastic traction rope 11, and the traction mechanism includes an electric hydraulic rod 12, one end of the electric hydraulic rod 12 is fixedly installed on the elastic traction rope 11, and the other end of the electric hydraulic rod 12 is fixedly installed on the connecting hinge 13, and a connecting hinge 13 is arranged on one side of the traction mechanism, and the connecting hinge 13 is fixedly installed on the support plate 6. When a failure occurs in the flight of the drone, the electric hydraulic rod 12 on the support rod 10 is started to drive the support plate 6 to lift upward, so that the spring telescopic plate 4 is extended to arch the connecting plate 15 and the measuring radar 7, so as to lift the measuring radar 7 above the bottom end of the bracket frame 2, so as to avoid damage to the measuring radar 7.

[0025] Two side protection mechanisms are arranged on the radar support mechanism, and the side protection mechanisms include a storage box 8, one side of the storage box 8 is fixedly mounted on the support plate 6, and two storage boxes 8 are respectively fixedly mounted on the two support plates 6, and the two storage boxes 8 are arranged in a staggered distribution. An isolation plate 14 is fixedly mounted in the storage box 8, a connecting pipe 18 is arranged on the isolation plate 14, and an electric control valve 19 is fixedly mounted on the side wall of the connecting pipe 18. One side of the isolation plate 14 in the storage box 8 is filled with compressed gas, and a compressed air bag 9 is fixedly mounted in the storage box 8. The electric control valve 19 on the isolation plate 14 is activated to release the compressed gas, so that the compressed air bag 9 in the storage box 8 can be expanded. The expanded compressed air bag 9 can protect the measuring radar 7, thereby further reducing the probability of damage to the measuring radar 7, improving the safety of the use of the measuring radar 7, and facilitating the application of the measuring radar 7 on the drone.

[0026] In summary: when the measuring radar 7 is in normal use, the support plate 6 is kept in a horizontal state with the help of the spring hinge 5, so that the measuring radar 7 can be used normally. When the UAV fails to fly, the electric hydraulic rod 12 on the support rod 10 is started to drive the support plate 6 to move upward, and the spring telescopic plate 4 is extended to arch the connecting plate 15 and the measuring radar 7, so as to lift the measuring radar 7 above the bottom end of the bracket frame 2, and at the same time, the electric control valve 19 on the isolation plate 14 is started to release the compressed gas, so that the compressed airbag 9 in the storage box 8 can be expanded, and the expanded compressed airbag 9 can be used to protect the measuring radar 7.

[0027] The above description enables those skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A radar assembly for take-off and landing guidance, characterized in that: The invention comprises two support frames (2), the side walls of the two support frames (2) are fixedly mounted with connecting plates (3), the side walls of the connecting plates (3) are hingedly mounted with spring hinges (5), and one side of the spring hinges (5) is fixedly mounted with a spring expansion plate (4), one side of the spring expansion plate (4) is fixedly mounted with a radar support mechanism, and a measuring radar (7) is arranged on the radar support mechanism, a connecting mechanism is fixedly mounted on the side walls of the support frames (2), and a traction mechanism is arranged on the connecting mechanism, one side of the traction mechanism is provided with a connecting hinge (13), and the connecting hinge (13) is fixedly mounted on the radar support mechanism, and two side protection mechanisms are arranged on the radar support mechanism.

2. A take-off and landing guidance radar assembly according to claim 1, characterized in that: The radar support mechanism comprises a connecting plate (15), one side of which is fixedly mounted on the measuring radar (7), and a rotating slot (16) is symmetrically provided on the side wall of the connecting plate (15), a clamping shaft (17) is rotatably mounted in each of the two rotating slots (16), and a supporting plate (6) is fixedly mounted on one side of the clamping shaft (17), and one side of the supporting plate (6) is fixedly mounted on the spring telescopic plate (4).

3. The radar assembly for take-off and landing guidance according to claim 1, characterized in that: The connection mechanism comprises a support rod (10), one end of the support rod (10) is fixedly mounted on the support frame (2), and the other end of the support rod (10) is fixedly mounted with an elastic traction rope (11).

4. A take-off and landing guidance radar assembly according to claim 3, characterized in that: The traction mechanism comprises an electric hydraulic rod (12), one end of which is fixedly mounted on an elastic traction rope (11), and the other end of which is fixedly mounted on a connecting hinge (13).

5. The radar assembly for take-off and landing guidance according to claim 1, characterized in that: The side protection mechanism comprises a storage box (8), one side of the storage box (8) is fixedly mounted on a support plate (6), an isolation plate (14) is fixedly mounted inside the storage box (8), a connecting pipe (18) is provided on the isolation plate (14), and an electric control valve (19) is fixedly mounted on the side wall of the connecting pipe (18), the storage box (8) is filled with compressed gas on one side of the isolation plate (14), and a compressed air bag (9) is fixedly mounted inside the storage box (8).

6. The radar assembly for take-off and landing guidance according to claim 5, characterized in that: The two storage boxes (8) are respectively fixedly mounted on the two support plates (6), and the two storage boxes (8) are arranged in a staggered distribution.

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