Aerial launch position sensor of unmanned aerial vehicle

Abstract

The utility model discloses a UAV (unmanned aerial vehicle) aero-launch position sensor, which comprises a pipe body with a closed head end and an open tail end; an external thread is arranged on the outer cylindrical surface of the pipe body; the pipe body is sleeved with the mounting bracket in a threaded manner; the pipe body is sleeved with the positioning nut; the heat transfer assembly is arranged at the bottom of the pipe body; the Hall element is arranged on the upper surface of the heat transfer assembly and clings to the heat transfer assembly; the winding group is arranged on the upper surface of the Hall element and is in contact with the inner wall of the tube body; the magnetic shielding assembly is arranged on the upper surface of the winding assembly; the controller assembly is arranged above the screen magnetic assembly and is in point connection with the winding group and the Hall element; the head end of the external wire is connected with the controller assembly, and the tail end of the external wire penetrates out of the pipe body; and the plugging head sleeves the outer surface of the external wire to plug the tail end of the tube body. The device can be applied to a severe aviation environment, and is high in precision and good in use stability.

Description

Technical Field

[0001] The utility model relates to the field of aviation engine sensor accessories, in particular to an aviation engine position sensor for a drone. Background Art

[0002] Position sensors are conventional sensors that detect the rotational position of an object. They are widely used. Conventional structures include magnetic induction, photoelectric, Hall and other structures. At present, the Hall structure is simple, stable and reliable, and is used in drone engines. Since drone engines have high requirements for position detection accuracy, and the use environment is more demanding than other environments, and its product stability requirements are higher, conventional Hall position sensors cannot meet the use requirements, that is, the detection accuracy is insufficient and the stability is poor. Utility Model Content

[0003] In view of the above-mentioned defects of the prior art, the purpose of the utility model is to provide a UAV aeroengine position sensor that can be used in harsh aviation environments and has high accuracy and good stability in use.

[0004] The purpose of the utility model is achieved through such technical solution:

[0005] A UAV aeroengine position sensor, comprising:

[0006] The tube body has a closed head end and an open tail end; an external thread is provided on the cylindrical surface of the tube body;

[0007] Mounting bracket, with the threaded sleeve on the outside of the tube body;

[0008] A positioning nut, which is sleeved on the pipe body;

[0009] A heat transfer component is arranged at the bottom of the tube body;

[0010] The Hall element is arranged on the upper surface of the heat transfer component and is in close contact with the heat transfer component;

[0011] The winding group is arranged on the upper surface of the Hall element and contacts the inner wall of the tube body;

[0012] A magnetic shield assembly is arranged on the upper surface of the winding assembly;

[0013] The controller component is arranged above the magnetic shield component and is respectively connected to the winding group and the Hall element;

[0014] The external wire has its head end connected to the controller assembly and its tail end passing through the tube body;

[0015] The plugging head is sheathed on the outer surface of the externally connected wire to seal the tail end of the tube body.

[0016] Furthermore, the mounting bracket comprises:

[0017] The ring tube has an inner thread on its inner wall and is covered on the tube body;

[0018] Two wing plates are axially symmetrically arranged on the surface of the ring tube around the axis of the ring tube, the plate surface of the wing plate is parallel to the axis of the ring tube; the long axis of the wing plate is perpendicular to the axis of the ring tube; the angle between the two wing plates is 90° to 150°; and the wing plate is provided with a strip groove along its axial direction.

[0019] Furthermore, the outer contour of the Hall element is circular, and the outer cylindrical surface of the Hall element is in contact with the inner wall of the tube body;

[0020] The heat transfer component comprises:

[0021] The outer cylindrical surface of the limiting ring is in close contact with the inner wall of the tube body;

[0022] Liquid metal is contained in the space enclosed by the inner ring of the limiting ring and the bottom of the tube body; the Hall element seals the upper end surface of the limiting ring, and the lower surface of the Hall element contacts the liquid metal.

[0023] Furthermore, it also includes: a lower limit assembly, the lower limit assembly includes:

[0024] A lower annular magnetic steel is arranged on the upper surface of the Hall element, and the outer cylindrical surface of the lower annular magnetic steel is seamlessly sealed with the inner wall of the tube body;

[0025] Lower conical spring; the smaller end of the lower conical spring abuts against the upper surface of the lower annular magnetic steel; the inner wall of the tube body is provided with a lower annular groove facing the larger diameter end of the lower conical spring, the larger end of the lower conical spring is accommodated in the lower annular groove, and the lower annular magnetic steel is pressed toward the Hall element.

[0026] Furthermore, a sealing gasket layer is provided on the lower surface of the lower annular magnetic steel, and the sealing gasket layer and the upper surface of the Hall element are pressed against each other.

[0027] Furthermore, the winding set comprises:

[0028] The winding frame has a through hole in the middle; the outer side surface of the lower end of the winding frame is provided with an annular notch groove; the lower conical spring is sleeved in the annular notch groove; the outer sides of the upper and lower ends of the winding frame are in contact with the inner wall of the tube body;

[0029] Wind the wire and wrap it around the winding frame.

[0030] Furthermore, an upper limit assembly is provided between the magnetic shield assembly and the winding frame, and the upper limit assembly includes:

[0031] The upper annular magnetic steel is arranged on the upper surface of the winding frame; the outer cylindrical surface of the upper annular magnetic steel is seamlessly sealed with the inner wall of the tube body;

[0032] An upper conical spring, wherein the smaller end of the upper conical spring abuts against the upper surface of the upper annular magnetic steel; an inner wall of the tube body is provided with an upper annular groove facing the larger diameter end of the upper conical spring, and the larger end of the upper conical spring is accommodated in the upper annular groove, squeezing the upper annular magnetic steel toward the winding frame.

[0033] Furthermore, the magnetic shield assembly comprises:

[0034] A base, which is sleeved in the upper conical spring and is located on the upper surface of the winding frame;

[0035] The glass fiber reinforced plastic sheet is arranged on the base, and the end surface thereof is in seamless contact with the inner wall of the tube body; and the controller component is arranged on the glass fiber reinforced plastic sheet.

[0036] Furthermore, electronic potting glue is poured between the upper surface of the fiberglass sheet and the sealing head.

[0037] Furthermore, the plugging head comprises:

[0038] T-shaped plug, the outer diameter of the inner plug tube is smaller than the inner diameter of the tube body, and the outer diameter of the blocking tube is larger than the inner diameter of the tube body; the external wire passes through the inner plug tube and the blocking tube;

[0039] A plurality of ribs are evenly distributed in a circle around the outer cylindrical surface of the inner plug tube of the T-shaped plug; the outer contour diameter formed by the plurality of ribs is the same as the inner diameter of the tube body;

[0040] The plug is made of rubber and has an outer sleeve with an external guide to close the plugging tube.

[0041] Due to the adoption of the above technical solution, the utility model has the following advantages:

[0042] 1. Use heat transfer components to transfer the heat generated by the Hall element when it is working to the tube body in time, reduce the working environment temperature of the Hall element, ensure that it works in the optimal working environment temperature, and at the same time extend the service life of the Hall element and reduce errors.

[0043] 2. The winding group is used as a magnetic field generator. The magnetic field strength generated by the winding group can be adjusted according to actual needs to improve the sampling accuracy of the Hall element.

[0044] 3. The controller components and the winding group are magnetically shielded to a certain extent through the magnetic shield component to reduce the interference of the magnetic field generated by the winding group on the controller components and improve the working stability of the controller.

[0045] Other advantages, objectives and features of the present invention will be described in the following description to some extent, and will be apparent to those skilled in the art based on the following examination and study, or may be taught from the practice of the present invention to some extent. BRIEF DESCRIPTION OF THE DRAWINGS

[0046] The accompanying drawings of the present utility model are as follows:

[0047] Figure 1 Schematic diagram of the three-dimensional structure of the UAV engine position sensor in this embodiment.

[0048] Figure 2 Schematic diagram of the front view structure of the UAV engine position sensor in this embodiment.

[0049] Figure 3 for Figure 2 Schematic diagram of the structure at the AA section.

[0050] Figure 4 Schematic diagram of the top view of the structure of the UAV engine position sensor in this embodiment.

[0051] Figure 5 for Figure 4 Schematic diagram of the structure of the middle BB section.

[0052] Figure 6 for Figure 5 Enlarged structural diagram at point C in the middle.

[0053] Figure 7 for Figure 5 Enlarged structural diagram at D in the middle.

[0054] Figure 8 Schematic diagram of the circuit connection of the UAV engine position sensor in this embodiment.

[0055] In the figure: 1. tube body; 11. lower annular groove; 12. upper annular groove; 21. annular tube; 22. wing plate; 221. strip groove; 3. positioning nut; 41. limit ring; 42. liquid metal; 43. lower annular magnetic steel; 44. lower conical spring; 45. sealing gasket; 5. Hall element; 61. winding frame; 611. annular notch groove; 62. winding; 63. upper annular magnetic steel; 64. upper conical spring; 71. base; 72. fiberglass sheet; 8. controller assembly; 9. external wire; 101. inner plug tube; 102. plugging tube; 103. support rib; 104. plug. DETAILED DESCRIPTION

[0056] The utility model is further described below in conjunction with the accompanying drawings and embodiments.

[0057] Example:

[0058] like Figures 1 to 8 As shown, a UAV aeroengine position sensor includes:

[0059] The tube body 1 has a closed head end and an open tail end; an external thread is provided on the outer cylindrical surface of the tube body 1;

[0060] The mounting bracket has a threaded sleeve on the outside of the tube body 1;

[0061] A positioning nut 3 is sleeved on the tube body 1;

[0062] A heat transfer component is arranged at the bottom of the tube body 1;

[0063] The Hall element 5 is arranged on the upper surface of the heat transfer component and is in close contact with the heat transfer component;

[0064] The winding group is arranged on the upper surface of the Hall element 5 and contacts the inner wall of the tube body 1;

[0065] A magnetic shield assembly is arranged on the upper surface of the winding assembly;

[0066] The controller component 8 is arranged above the magnetic shield component and is connected to the winding group and the Hall element at 5 points respectively;

[0067] An external wire 9, the head end of which is connected to the controller assembly 8, and the tail end of which passes through the tube body 1;

[0068] The plugging head is sheathed on the outer surface of the externally connected wire 9 to plug the tail end of the tube body 1.

[0069] The heat generated by the Hall element 5 when it is working is transferred to the tube body 1 in a timely manner by using a heat transfer component, so as to reduce the working environment temperature of the Hall element 5, ensure that it works in the optimal working environment temperature, and at the same time extend the service life of the Hall element 5 and reduce the error. The winding group is used as a magnetic field generator, and the magnetic field strength generated by the winding group can be adjusted according to actual needs to improve the sampling accuracy of the Hall element 5. The controller component 8 and the winding group are magnetically shielded to a certain extent through the magnetic shielding component, so as to reduce the interference of the magnetic field generated by the winding group on the controller component 8 and improve the working stability of the controller.

[0070] In this embodiment, the mounting bracket includes:

[0071] The ring tube 21 has an inner thread on its inner wall and is externally mounted on the tube body 1;

[0072] Two wing plates 22 are axially symmetrically arranged on the surface of the ring tube 21 around the axis of the ring tube 21, and the plate surface of the wing plate 22 is parallel to the axis of the ring tube 21; the long axis of the wing plate 22 is perpendicular to the axis of the ring tube 21; the angle between the two wing plates 22 is 90° to 150°; the wing plate 22 is provided with a strip groove 221 along its axial direction.

[0073] By tightening the ring tube 21 and the positioning nut 3, the position of the ring tube 21 on the tube body 1 can be fixed, thereby achieving the purpose of installing the tube body 1. At the same time, the distance between the end of the tube body 1 and the ring tube 21 can be adjusted, that is, the gap between the end of the tube body 1 and the component to be tested can be adjusted.

[0074] In this embodiment, the outer contour of the Hall element 5 is circular, and the outer cylindrical surface of the Hall element 5 is in contact with the inner wall of the tube body 1;

[0075] The heat transfer component comprises:

[0076] The outer cylindrical surface of the limiting ring 41 is in close contact with the inner wall of the tube body 1;

[0077] The liquid metal 42 is accommodated in the space enclosed by the inner ring of the limiting ring 41 and the bottom of the tube body 1 ; the Hall element 5 seals the upper end surface of the limiting ring 41 , and the lower surface of the Hall element 5 contacts the liquid metal 42 .

[0078] The liquid metal 42 is made of gallium-based low melting point metal, which has excellent thermal conductivity and good magnetic conductivity, and does not affect the operation of the winding group.

[0079] In this embodiment, it also includes: a lower limit assembly, the lower limit assembly includes:

[0080] The lower annular magnetic steel 43 is arranged on the upper surface of the Hall element 5, and the outer cylindrical surface of the lower annular magnetic steel 43 is seamlessly sealed with the inner wall of the tube body 1;

[0081] Lower conical spring 44; the smaller end of the lower conical spring 44 is against the upper surface of the lower annular magnetic steel 43; the inner wall of the tube body 1 is provided with a lower annular groove 11 facing the larger diameter end of the lower conical spring 44, and the larger end of the lower conical spring 44 is accommodated in the lower annular groove 11, pressing the lower annular magnetic steel 43 toward the Hall element 5.

[0082] The Hall element 5 is effectively fixed by the lower annular magnetic steel 43 and the lower conical spring 44, while preventing the liquid metal from overflowing.

[0083] In this embodiment, a sealing gasket layer 45 is provided on the lower surface of the lower annular magnetic steel 43 , and the sealing gasket layer 45 and the upper surface of the Hall element 5 are pressed against each other.

[0084] The sealing pad layer 45 is made of a flexible material that does not react with the liquid metal 42 and can play a sealing role.

[0085] In this embodiment, the winding set includes:

[0086] The winding frame 61 has a through hole in the middle; the outer side surface of the lower end of the winding frame 61 is provided with an annular notch groove 611; the lower conical spring 44 is sleeved in the annular notch groove 611; the outer sides of the upper and lower ends of the winding frame 61 are in contact with the inner wall of the tube body 1;

[0087] The winding wire 62 is wound on the winding frame 61 .

[0088] The contact between the winding frame 61 and the inner wall of the tube body 1 can not only limit the position of the winding frame 61, but also transfer the heat generated by the winding 62 to the tube body 1 through the winding frame 61, and finally dissipate the heat.

[0089] In this embodiment, an upper limit assembly is further provided between the magnetic shield assembly and the winding frame 61, and the upper limit assembly includes:

[0090] The upper annular magnetic steel 63 is arranged on the upper surface of the winding frame 61; the outer cylindrical surface of the upper annular magnetic steel 63 is seamlessly sealed with the inner wall of the tube body 1;

[0091] An upper conical spring 64, the smaller end of which is against the upper surface of the upper annular magnetic steel 63; an upper annular groove 12 is provided on the inner wall of the tube body 1, which is opposite to the larger diameter end of the upper conical spring 64; the larger end of the upper conical spring 64 is accommodated in the upper annular groove 12, pressing the upper annular magnetic steel 63 toward the winding frame 61.

[0092] The upper annular magnetic steel 63 and the upper conical spring 64 have the same function as the lower annular magnetic steel 43 and the conical spring.

[0093] In this example, the magnetic shield assembly includes:

[0094] The base 71 is sleeved in the upper conical spring 64 and is located on the upper surface of the winding frame 61;

[0095] The glass fiber reinforced plastic sheet 72 is disposed on the base 71 , and its end surface is in seamless contact with the inner wall of the tube body 1 ; the controller component 8 is disposed on the glass fiber reinforced plastic sheet 72 .

[0096] The non-magnetic properties of fiberglass can reduce the magnetic field generated by the winding 62 from entering the controller assembly 8 .

[0097] In this embodiment, electronic potting glue is poured between the upper surface of the fiberglass sheet 72 and the sealing head.

[0098] In this embodiment, the plugging head includes:

[0099] T-shaped plug, the outer diameter of the inner plug tube 101 is smaller than the inner diameter of the tube body 1, and the outer diameter of the blocking tube 102 is larger than the inner diameter of the tube body 1; the external wire 9 passes through the inner plug tube 101 and the blocking tube 102;

[0100] A plurality of supporting ribs 103 are evenly distributed in a circle around the outer cylindrical surface of the inner plug tube 101 of the T-shaped plug; the outer contour diameter formed by the plurality of supporting ribs 103 is the same as the inner diameter of the tube body 1;

[0101] The plug 104 is made of rubber and has an outer cover connected to a guide to seal the plugging tube 102 .

[0102] After the electronic potting glue is poured into the tube body 1 , when a T-shaped plug is inserted, the excess air inside can flow out along the gaps between the supporting ribs 103 , so that the electronic potting glue is poured densely and the bonding strength with the inner wall of the tube body 1 is increased.

[0103] The drone engine position sensor of this embodiment is used in the following way: the Hall element 5, the winding 62, the controller component 8, and the external guide are electrically connected using a conventional existing controller component 8 and a circuit scheme of a Hall sensor.

[0104] The specific structure is as follows Figure 5 Assemble in sequence as shown, and finally adjust the positions of the ring tube 21 and the positioning nut 3 according to the installation position of the assembled sensor and squeeze the ring tube 21 and the positioning nut 3 tightly against each other. Install the sensor outside the aircraft engine or in a cavity with gas flow for use.

[0105] Finally, according to actual needs, the magnetic field strength of the winding 62 is adjusted by adjusting the current and voltage, and the heat generation of the Hall element 5 is controlled by adjusting the current of the Hall element 5, so that the temperature of the Hall element 5 during operation is moderate and within the optimal operating range.

[0106] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the utility model rather than to limit it. Although the utility model has been described in detail with reference to the preferred embodiments, ordinary technicians in the field should understand that the technical solution of the utility model can be modified or replaced by equivalents without departing from the purpose and scope of the technical solution, which should be included in the scope of the claims of the utility model.

Claims

1. A drone engine position sensor, characterized in that: include: The tube body has a closed head end and an open tail end; an external thread is provided on the cylindrical surface of the tube body; The mounting bracket has a threaded sleeve on the outside of the tube body; A positioning nut, which is sleeved on the pipe body; A heat transfer component is arranged at the bottom of the tube body; The Hall element is arranged on the upper surface of the heat transfer component and is in close contact with the heat transfer component; The winding group is arranged on the upper surface of the Hall element and contacts the inner wall of the tube body; A magnetic shield assembly is arranged on the upper surface of the winding assembly; The controller component is arranged above the magnetic shield component and is respectively connected to the winding group and the Hall element; The external wire has its head end connected to the controller assembly and its tail end passing through the tube body; The plugging head is sheathed on the outer surface of the externally connected wire to seal the tail end of the tube body.

2. The UAV launch position sensor according to claim 1, characterized in that: The mounting bracket comprises: The ring tube has an inner thread on its inner wall and is fitted over the tube body; Two wing plates are axially symmetrically arranged on the surface of the ring tube around the axis of the ring tube, the plate surface of the wing plate is parallel to the axis of the ring tube; the long axis of the wing plate is perpendicular to the axis of the ring tube; the angle between the two wing plates is 90° to 150°; and the wing plate is provided with a strip groove along its axial direction.

3. The UAV aircraft launch position sensor according to claim 1, characterized in that: The outer contour of the Hall element is circular, and the outer cylindrical surface of the Hall element is in contact with the inner wall of the tube body; The heat transfer component comprises: The outer cylindrical surface of the limiting ring is in close contact with the inner wall of the tube body; Liquid metal is contained in the space enclosed by the inner ring of the limiting ring and the bottom of the tube body; the Hall element seals the upper end surface of the limiting ring, and the lower surface of the Hall element contacts the liquid metal.

4. The UAV aircraft launch position sensor according to claim 1, characterized in that: Also includes: A lower limit assembly, the lower limit assembly comprising: A lower annular magnetic steel is arranged on the upper surface of the Hall element, and the outer cylindrical surface of the lower annular magnetic steel is seamlessly sealed with the inner wall of the tube body; Lower conical spring; the smaller end of the lower conical spring abuts against the upper surface of the lower annular magnetic steel; the inner wall of the tube body is provided with a lower annular groove facing the larger diameter end of the lower conical spring, the larger end of the lower conical spring is accommodated in the lower annular groove, and the lower annular magnetic steel is pressed toward the Hall element.

5. The UAV launch position sensor according to claim 4, characterized in that: A sealing pad layer is provided on the lower surface of the lower annular magnetic conductive steel, and the sealing pad layer and the upper surface of the Hall element are pressed against each other.

6. The UAV launch position sensor according to claim 4, characterized in that: The winding set comprises: The winding frame has a through hole in the middle; the outer side surface of the lower end of the winding frame is provided with an annular notch groove; the lower conical spring is sleeved in the annular notch groove; the outer sides of the upper and lower ends of the winding frame are in contact with the inner wall of the tube body; Wind the wire and wrap it around the winding frame.

7. The UAV launch position sensor according to claim 6, characterized in that: An upper limit assembly is also provided between the magnetic shield assembly and the winding frame, and the upper limit assembly includes: The upper annular magnetic steel is arranged on the upper surface of the winding frame; the outer cylindrical surface of the upper annular magnetic steel is seamlessly sealed with the inner wall of the tube body; An upper conical spring, wherein the smaller end of the upper conical spring abuts against the upper surface of the upper annular magnetic steel; an inner wall of the tube body is provided with an upper annular groove facing the larger diameter end of the upper conical spring, and the larger end of the upper conical spring is accommodated in the upper annular groove, squeezing the upper annular magnetic steel toward the winding frame.

8. The UAV aircraft launch position sensor according to claim 7, characterized in that: The magnetic shield assembly comprises: A base, which is sleeved in the upper conical spring and is located on the upper surface of the winding frame; The glass fiber reinforced plastic sheet is arranged on the base, and the end surface thereof is in seamless contact with the inner wall of the tube body; and the controller component is arranged on the glass fiber reinforced plastic sheet.

9. The UAV aircraft launch position sensor according to claim 8, characterized in that: Electronic potting glue is poured between the upper surface of the glass fiber reinforced plastic sheet and the sealing head.

10. The UAV engine position sensor according to claim 9, characterized in that: The plugging head comprises: T-shaped plug, the outer diameter of the inner plug tube is smaller than the inner diameter of the tube body, and the outer diameter of the blocking tube is larger than the inner diameter of the tube body; the external wire passes through the inner plug tube and the blocking tube; A plurality of ribs are evenly distributed in a circle around the outer cylindrical surface of the inner plug tube of the T-shaped plug; the outer contour diameter formed by the plurality of ribs is the same as the inner diameter of the tube body; The plug is made of rubber and has an outer sleeve with an external guide to close the plugging tube.

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