A control structure for monitoring low-altitude aircraft

Abstract

The utility model discloses a control structure for monitoring a low-altitude aircraft, and relates to the technical field of aircraft. The utility model comprises an aircraft body, wherein the bottom of the aircraft body is fixedly connected with a support frame, the top of the aircraft body is fixedly and electrically connected with a control module, and a temperature monitoring trigger device and a heat dissipation control device are arranged on the control module. The temperature monitoring trigger device comprises a connecting groove. The utility model can generate high heat in the control module after the aircraft body flies for a long time through the temperature monitoring trigger device, and the heat conductive block will introduce the heat into the heat expansion airbag, and the heat expansion airbag will expand after absorbing the heat. When the heat expansion airbag expands, it will drive a connecting rod and a push plate to move, and the push plate will squeeze the switch of the power supply after moving to a fixed position, so as to turn on the heat dissipation control device, thereby effectively monitoring the temperature of the control module and having strong practicality.

Description

Technical Field

[0001] The utility model belongs to the technical field of aircraft, and particularly relates to a control structure for monitoring low-altitude aircraft. Background Art

[0002] A drone is an aerial vehicle that is not completely dependent on human control and can perform certain tasks. A drone is a type of low-altitude aircraft, and its flight mode is: autonomous control of flight attitude, and completing the required flight tasks under manual flight, ground radio control or autonomous memory.

[0003] In the prior art, low-altitude aircraft cannot be well monitored and controlled during flight, and may generate high temperatures after a long period of flight, causing damage. Therefore, the present application proposes a control structure for monitoring low-altitude aircraft to solve the above problem. Utility Model Content

[0004] The utility model aims to provide a control structure for monitoring low-altitude aircraft, which solves the existing problems through a temperature monitoring trigger device and a heat dissipation control device.

[0005] In order to solve the above technical problems, the utility model is achieved through the following technical solutions:

[0006] The utility model is a control structure for monitoring low-altitude aircraft, comprising an aircraft body, the bottom of which is fixedly connected to a support frame, the top of which is fixedly and electrically connected to a control module, and the control module is provided with a temperature monitoring trigger device and a heat dissipation control device;

[0007] The temperature monitoring trigger device includes a connecting groove, a heat-conducting block is fixedly connected to the inside of the connecting groove, a heat-expandable airbag is fixedly connected to the top of the heat-expandable airbag, a connecting rod is fixedly connected to the top of the heat-expandable airbag, a push plate is fixedly connected to the top of the connecting rod, a power supply is arranged above the push plate, and a limiting block is fixedly connected to a side of the power supply close to the push plate.

[0008] Furthermore, a connection groove is provided on the top of the control module, and a heat-conducting block is fixedly connected to the top of the control module, so that the control module can effectively control the aircraft body to fly.

[0009] Furthermore, the heat-expandable airbag, the connecting rod and the push plate are all arranged on the inner side of the limiting block, and the heat-expandable airbag will expand after absorbing heat.

[0010] Furthermore, the side of the limit block away from the power supply is fixedly connected to the top of the control module, and the interior of the limit block is set to be in a hollow state. The limit block can effectively limit the heat-expanded airbag.

[0011] Furthermore, the heat dissipation control device includes a connecting wire, a side of the connecting wire is fixed and electrically connected to a motor, a side of the motor rotates and is electrically connected to an electric rotating rod, a side of the electric rotating rod away from the motor is fixedly connected to a cooling fan, a side of the motor away from the electric rotating rod is fixedly connected to a protective shell, a heat dissipation groove is provided on the protective shell, and the heat dissipation control device can effectively dissipate heat and cool the control module, thereby improving the control performance of the control module.

[0012] Furthermore, the side of the connecting wire away from the motor is fixed and electrically connected to the power supply, and the side of the power supply away from the limit block is fixedly connected to the inner wall of the protective shell. The connecting wire can effectively introduce the current in the power supply into the interior of the motor.

[0013] Furthermore, the heat dissipation fans are arranged on both sides of the control module, and the heat dissipation slots are arranged on both sides of the control module without the heat dissipation fans, and the heat dissipation fans can effectively dissipate the heat of the control module.

[0014] The utility model has the following beneficial effects:

[0015] 1. The utility model uses a temperature monitoring trigger device. After the aircraft body flies for a long time, the control module will generate high heat. The heat-conducting block will introduce the heat to the heat expansion airbag. The heat expansion airbag will expand after absorbing the heat. When the heat expansion airbag expands, it will drive the connecting rod and the push plate to move. After moving to a fixed position, the push plate will squeeze the power switch to turn on the heat dissipation control device, which can effectively monitor the temperature of the control module and has strong practicality.

[0016] 2. The utility model uses the heat dissipation control device, which can transmit the current inside the power supply to the motor through the connecting line after the power is turned on. The motor will drive the electric rotating rod and the heat dissipation fan to rotate. The heat dissipation fan can effectively dissipate heat and cool the control module, and can effectively protect the control module to prevent damage to the aircraft body, thereby further enhancing the practicality of the entire device.

[0017] Of course, any product implementing the present invention does not necessarily need to achieve all of the advantages described above at the same time. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] In order to more clearly illustrate the technical solutions of the embodiments of the utility model, the drawings required for describing the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the utility model. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0019] Figure 1It is a schematic diagram of the three-dimensional appearance structure of the utility model;

[0020] Figure 2 It is a three-dimensional side structural schematic diagram of the utility model;

[0021] Figure 3 It is a schematic diagram of the three-dimensional cross-sectional structure of the utility model;

[0022] Figure 4 It is an enlarged structural diagram of the temperature monitoring trigger device of the utility model;

[0023] Figure 5 It is an enlarged structural schematic diagram of the heat dissipation control device of the utility model.

[0024] In the accompanying drawings, the components represented by the reference numerals are listed as follows:

[0025] 1. Aircraft body; 2. Support frame; 3. Control module; 4. Temperature monitoring trigger device; 41. Connection slot; 42. Heat conducting block; 43. Heat expansion airbag; 44. Connection rod; 45. Push plate; 46. Power supply; 47. Limit block; 5. Heat dissipation control device; 51. Connection line; 52. Motor; 53. Electric rotating rod; 54. Cooling fan; 55. Protective shell; 56. Heat dissipation slot. DETAILED DESCRIPTION

[0026] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments of the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model.

[0027] See also Figure 1-5 As shown, the utility model is a control structure for monitoring low-altitude aircraft, comprising an aircraft body 1, a support frame 2 is fixedly connected to the bottom of the aircraft body 1, a control module 3 is fixed and electrically connected to the top of the aircraft body 1, and a temperature monitoring trigger device 4 and a heat dissipation control device 5 are arranged on the control module 3;

[0028] The temperature monitoring trigger device 4 includes a connecting groove 41, a heat conductive block 42 is fixedly connected to the inside of the connecting groove 41, a heat expansion airbag 43 is fixedly connected to the top of the heat expansion airbag 43, a connecting rod 44 is fixedly connected to the top of the heat expansion airbag 43, a push plate 45 is fixedly connected to the top of the connecting rod 44, a power supply 46 is arranged above the push plate 45, and a limiting block 47 is fixedly connected to the side of the power supply 46 close to the push plate 45.

[0029] A connection slot 41 is provided on the top of the control module 3 , and a heat-conducting block 42 is fixedly connected to the top of the control module 3 . The control module 3 can effectively control the aircraft body 1 to fly.

[0030] The heat-expandable airbag 43 , the connecting rod 44 and the push plate 45 are all arranged on the inner side of the limiting block 47 , and the heat-expandable airbag 43 will expand after absorbing heat.

[0031] The side of the limit block 47 away from the power supply 46 is fixedly connected to the top of the control module 3 , and the interior of the limit block 47 is set to be in a hollow state. The limit block 47 can effectively limit the heat-expandable airbag 43 .

[0032] The heat dissipation control device 5 includes a connecting line 51, a side of the connecting line 51 is fixed and electrically connected to a motor 52, a side of the motor 52 is rotatable and electrically connected to an electric rotating rod 53, a side of the electric rotating rod 53 away from the motor 52 is fixedly connected to a cooling fan 54, a side of the motor 52 away from the electric rotating rod 53 is fixedly connected to a protective shell 55, a heat dissipation groove 56 is provided on the protective shell 55, and the heat dissipation control device 5 can effectively dissipate heat and cool the control module 3, thereby improving the control performance of the control module 3.

[0033] The side of the connecting wire 51 away from the motor 52 is fixed and electrically connected to the power supply 46, and the side of the power supply 46 away from the limit block 47 is fixedly connected to the inner wall of the protective shell 55. The connecting wire 51 can effectively introduce the current in the power supply 46 into the interior of the motor 52.

[0034] The cooling fans 54 are arranged on both sides of the control module 3 , and the cooling slots 56 are arranged on both sides of the control module 3 where there are no cooling fans 54 . The cooling fans 54 can effectively dissipate heat for the control module 3 .

[0035] The utility model can generate high heat in the control module 3 after the aircraft body 1 flies for a long time through the temperature monitoring trigger device 4, and the heat conducting block 42 will introduce the heat into the heat expansion airbag 43. The heat expansion airbag 43 will expand after absorbing the heat. When the heat expansion airbag 43 expands, it will drive the connecting rod 44 and the push plate 45 to move. After the push plate 45 moves to a fixed position, it will squeeze the switch of the power supply 46, turn on the heat dissipation control device 5, and effectively monitor the temperature of the control module 3, which is highly practical. The utility model can transmit the current inside the power supply 46 to the inside of the motor 52 through the connecting line 51 after the power supply 46 is turned on through the heat dissipation control device 5, and the motor 52 will drive the electric rotating rod 53 and the heat dissipation fan 54 to rotate. The heat dissipation fan 54 can effectively dissipate heat and cool the control module 3, and can effectively protect the control module 3 to prevent damage to the aircraft body 1, further enhancing the practicality of the entire device.

[0036] A specific application of this embodiment is: after the aircraft body 1 flies for a long time, the control module 3 will generate a higher temperature, the heat-conducting block 42 will introduce the heat at the control module 3 into the interior of the heat-expanding airbag 43, and the heat-expanding airbag 43 will expand after absorbing the heat. While the heat-expanding airbag 43 expands, it will drive the connecting rod 44 and the push plate 45 to move, and the push plate 45 will squeeze the switch of the power supply 46, and the power supply 46 will turn on, turning on the heat dissipation control device 5, which can effectively monitor the heat at the control module 3. After the temperature at the control module 3 is in a normal state, the heat-conducting block 42 will not continue to conduct heat, and the gas inside the heat-expanding airbag 43 will return to its original state without the drive of high temperature. , the heat-expanded airbag 43 will also return to its original state, the connecting rod 44 and the push plate 45 will also return to their original positions, the switch of the power supply 46 will not continue to be squeezed, and the power supply 46 will be turned off, which is convenient for the next use, and the practicality is strong. After the power supply 46 is turned on, the connecting line 51 will transmit the current at the power supply 46 to the inside of the motor 52, and the motor 52 will drive the electric rotating rod 53 and the cooling fan 54 to rotate. The cooling fan 54 can effectively dissipate heat for the control module 3, and enhance the control performance of the control module 3. After the temperature at the control module 3 returns to normal, the power supply 46 will be turned off, the motor 52 will also be turned off, and the cooling fan 54 will stop rotating, which is convenient for the next use, further enhancing the practicality of the entire device.

[0037] In the description of this specification, the description with reference to the terms "one embodiment", "example", "specific example", etc. means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the utility model. In this specification, the schematic representation of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0038] The preferred embodiments of the utility model disclosed above are only used to help explain the utility model. The preferred embodiments do not describe all the details in detail, nor do they limit the utility model to the specific implementation methods described. Obviously, many modifications and changes can be made according to the content of this specification. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the utility model, so that technicians in the relevant technical field can well understand and use the utility model. The utility model is limited only by the claims and their full scope and equivalents.

Claims

1. A control structure for monitoring a low-altitude aircraft, comprising an aircraft body (1), characterized in that: The bottom of the aircraft body (1) is fixedly connected to a support frame (2), the top of the aircraft body (1) is fixedly and electrically connected to a control module (3), and the control module (3) is provided with a temperature monitoring trigger device (4) and a heat dissipation control device (5); The temperature monitoring trigger device (4) comprises a connecting groove (41), the interior of the connecting groove (41) is fixedly connected to a heat conductive block (42), the top of the heat conductive block (42) is fixedly connected to a heat expansion airbag (43), the top of the heat expansion airbag (43) is fixedly connected to a connecting rod (44), the top of the connecting rod (44) is fixedly connected to a push plate (45), a power source (46) is arranged above the push plate (45), and a limiting block (47) is fixedly connected to a side of the power source (46) close to the push plate (45).

2. A control structure for monitoring low-altitude aircraft according to claim 1, characterized in that: A connection groove (41) is provided on the top of the control module (3), and a heat conduction block (42) is fixedly connected to the top of the control module (3).

3. A control structure for monitoring low-altitude aircraft according to claim 2, characterized in that: The heat-expandable airbag (43), the connecting rod (44) and the push plate (45) are all arranged on the inner side of the limiting block (47).

4. A control structure for monitoring low-altitude aircraft according to claim 3, characterized in that: The side of the limit block (47) away from the power source (46) is fixedly connected to the top of the control module (3), and the interior of the limit block (47) is arranged to be in a hollow state.

5. A control structure for monitoring low-altitude aircraft according to claim 4, characterized in that: The heat dissipation control device (5) comprises a connecting line (51), the side of the connecting line (51) is fixed and electrically connected to a motor (52), the side of the motor (52) is rotatable and electrically connected to an electric rotating rod (53), a side of the electric rotating rod (53) away from the motor (52) is fixedly connected to a heat dissipation fan (54), and a side of the motor (52) away from the electric rotating rod (53) is fixedly connected to a protective shell (55), and a heat dissipation groove (56) is provided on the protective shell (55).

6. A control structure for monitoring low-altitude aircraft according to claim 5, characterized in that: The side of the connecting wire (51) away from the motor (52) is fixedly connected to the power source (46) and electrically connected thereto, and the side of the power source (46) away from the limit block (47) is fixedly connected to the inner wall of the protective shell (55).

7. A control structure for monitoring low-altitude aircraft according to claim 6, characterized in that: The heat dissipation fans (54) are arranged on both sides of the control module (3), and the heat dissipation slots (56) are arranged on both sides of the control module (3) where there are no heat dissipation fans (54).

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