Heat dissipation control device for near space low-speed unmanned aerial vehicle propelling system

Abstract

The invention discloses a heat dissipation control device for a near space low-speed unmanned aerial vehicle propulsion system, and relates to the technical field of unmanned aerial vehicle heat dissipation. The heat dissipation cover plate is movably arranged on the inner wall of the propelling supporting rod, the heat dissipation cover plate is connected with the self-locking structure, when the heat dissipation cover plate is pressed, the self-locking structure drives the heat dissipation cover plate to close the air outlet hole, and when the heat dissipation cover plate is pressed again, the self-locking structure drives the heat dissipation cover plate to open the air outlet hole; the light sensation control unit is arranged on the inner wall of the propelling supporting rod, the light sensation control unit is matched with the heat dissipation cover plate, and the light sensation control unit makes contact with the heat dissipation cover plate according to the brightness of the surrounding environment; the control device can alleviate the problem of energy shortage during the flight of the unmanned aerial vehicle at night, and realizes the on-off of the heat dissipation path of the propulsion support rod through the opening and closing of the heat dissipation cover plate, so that the environment temperature of the motor controller can be actively controlled, and the heat dissipation requirements under different conditions are met.

Description

Technical Field

[0001] The present invention belongs to the technical field of heat dissipation of unmanned aerial vehicles, and more specifically, relates to a heat dissipation control device for a propulsion system of a low-speed unmanned aerial vehicle in near space. Background Art

[0002] Near-space UAVs have high flight altitudes and long flight times. They have the characteristics of both conventional aircraft and low-orbit satellites. They are mainly used for reconnaissance, surveillance and communication relay. They are a new direction for the development of aerospace technology and have extremely high strategic value and economic benefits. As the best power propulsion device for solar-powered UAVs, the near-space propeller electric propulsion system consumes more than 70% of the total system energy. Its energy flow efficiency has a very important impact on the solar-powered UAVs to maintain energy balance and achieve day and night cycle flight. At present, with the rapid development of the industrial and aerospace fields, the number of near-space long-flight aircraft is increasing. During night flights, energy storage batteries are used to power the aircraft. In order to ensure the normal operation of aircraft equipment in harsh environments, auxiliary heating is essential. In addition to ensuring the propulsion power required for UAV flight, heating power accounts for a large proportion. The power of UAVs at night is limited. In order to save energy and alleviate the pressure of electricity consumption, other means are needed to maintain the temperature of the equipment. Summary of the invention

[0003] The purpose of the present invention is to address the deficiencies in the prior art and to provide a heat dissipation control device for a near-space low-speed UAV propulsion system. The control device can alleviate the problem of energy shortage during nighttime flight of the UAV. The heat dissipation path of the propulsion strut is opened and closed by opening and closing the heat dissipation cover, thereby actively controlling the ambient temperature of the motor controller to meet the heat dissipation requirements under different conditions.

[0004] In order to achieve the above object, the present invention provides a heat dissipation control device for a propulsion system of a low-speed UAV in near space, comprising:

[0005] The air inlet and the air outlet are correspondingly arranged at the two ends of the propulsion support rod;

[0006] A heat dissipation cover plate, movably arranged on the inner wall of the propulsion support rod, the heat dissipation cover plate is connected to a self-locking structure, when the heat dissipation cover plate is pressed, the self-locking structure drives the heat dissipation cover plate to close the air outlet, and when the heat dissipation cover plate is pressed again, the self-locking structure drives the heat dissipation cover plate to open the air outlet;

[0007] A light sensing control unit is arranged on the inner wall of the propulsion support rod, the light sensing control unit cooperates with the heat dissipation cover plate, and the light sensing control unit touches the heat dissipation cover plate according to the brightness of the surrounding environment.

[0008] Optionally, the light sensing control unit includes a light sensing element and a push-pull electromagnet, the light sensing element is arranged on the outer wall of the propulsion support rod, the light sensing element is control-connected to the push-pull electromagnet, and the push-pull electromagnet and the heat dissipation cover are correspondingly arranged on both sides of the air outlet.

[0009] Optionally, the push-pull electromagnet includes a sliding rod and an electromagnetic coil, the electromagnetic coil is connected to the photosensitive element, the middle part of the sliding rod passes through the electromagnetic coil, a limiting portion is provided at one end of the sliding rod, a first return spring is provided between the limiting portion and the end surface of the electromagnetic coil, and the other end of the sliding rod cooperates with the heat dissipation cover.

[0010] Optionally, the self-locking structure includes a guide rod and a guide block, one end of the guide rod is hinged on a support of the self-locking structure, the other end of the guide rod is slidably disposed in a guide groove of the guide block, a second return spring is disposed between one side of the guide block and the support, and the other side of the guide block is connected to the heat dissipation cover plate.

[0011] Optionally, the guide groove is a closed polygon, a first stop position and a second stop position are provided on the polygon, and a line connecting the first stop position and the second stop position is parallel to a sliding direction of the heat dissipation cover plate.

[0012] Optionally, a plurality of heat dissipation openings are respectively provided in the air inlet and the air outlet, and an air flow path connecting the air inlet and the air outlet corresponds to a fin of the motor controller.

[0013] Optionally, the heat dissipation cover plate and the self-locking structure are arranged between the motor controller and the inner wall of the propulsion support rod.

[0014] Optionally, an air inlet cover is provided on the air inlet hole.

[0015] Optionally, the outer side of the propulsion support rod is wrapped with a foam insulation layer.

[0016] The present invention provides a heat dissipation control device for a propulsion system of a low-speed UAV in near-space, which has the following beneficial effects:

[0017] 1. The heat dissipation control device adopts the method of closing heat dissipation holes to reduce heat dissipation. The heat generated by the motor controller when it is working normally heats the surrounding environment. When flying at night, the airflow path is closed compared with the traditional auxiliary heating, which improves the energy utilization rate, saves electricity, and increases the night flight time. When the auxiliary heating function fails, the heat dissipation control device can also achieve the heating effect through the heat of the motor controller itself, ensuring the normal operation of the motor controller at low temperatures, and a redundant temperature control form;

[0018] 2. The heat dissipation control device uses the power module in the motor controller to power the heat dissipation control device, which can minimize the impact of the heat dissipation control device on the drone, reduce the modification cost, make the operation easy to implement, save cables, simplify the design, and improve the reliability of the aircraft;

[0019] 3. A self-locking structure is provided in the heat dissipation control device, and the electromagnet controls the sliding rod to press the heat dissipation cover plate and self-lock to realize the switching between the open and closed states of the heat dissipation holes. Compared with the rotating closing method, this sliding method optimizes the design, utilizes the mechanical structure, and reduces the servo system. In addition, the self-locking structure can effectively solve the problem that the electromagnet cannot be powered on for a long time, and realizes the alternating switching between opening and closing by controlling in a click triggering manner;

[0020] 4. The heat dissipation control device adopts both manual and automatic control modes. When the UAV enters the night or day flight state, the solar radiation state is identified by the light sensing element, and the heat dissipation cover is automatically closed or opened. Manual control mode can also be provided for operation.

[0021] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The above and other objects, features and advantages of the present invention will become more apparent through a more detailed description of exemplary embodiments of the present invention in conjunction with the accompanying drawings, wherein like reference numerals generally represent like components throughout the exemplary embodiments of the present invention.

[0023] Figure 1 A schematic structural diagram of a heat dissipation control device for a near-space low-speed UAV propulsion system according to an embodiment of the present invention is shown.

[0024] Figure 2 Shows Figure 1 A partial schematic diagram of .

[0025] Figure 3 A schematic diagram showing the positions of a self-locking structure and a light sensing control unit according to an embodiment of the present invention is shown.

[0026] Figure 4 A working principle diagram of a heat dissipation control device for a near-space low-speed UAV propulsion system according to an embodiment of the present invention is shown.

[0027] Description of reference numerals:

[0028] 1. Self-locking structure; 101. Second return spring; 102. Guide block; 103. Heat dissipation cover; 2. Push-pull electromagnet; 201. Sliding rod; 202. First return spring; 3. Air outlet; 4. Propelling support rod; 5. Motor controller; 6. Air inlet cover; 7. Light sensing element. DETAILED DESCRIPTION

[0029] The preferred embodiments of the present invention will be described in more detail below. Although the preferred embodiments of the present invention are described below, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided to make the present invention more thorough and complete, and to fully convey the scope of the present invention to those skilled in the art.

[0030] The present invention provides a heat dissipation control device for a propulsion system of a low-speed UAV in near space, comprising:

[0031] The air inlet and the air outlet are correspondingly arranged at the two ends of the propulsion support rod;

[0032] The heat dissipation cover is movably arranged on the inner wall of the propulsion support rod, and the heat dissipation cover is connected with the self-locking structure. When the heat dissipation cover is pressed, the self-locking structure drives the heat dissipation cover to close the air outlet hole, and when the heat dissipation cover is pressed again, the self-locking structure drives the heat dissipation cover to open the air outlet hole;

[0033] The light sensing control unit is arranged on the inner wall of the propulsion support rod, and the light sensing control unit cooperates with the heat dissipation cover plate. The light sensing control unit touches the heat dissipation cover plate according to the brightness of the surrounding environment.

[0034] Specifically, the heat dissipation control device is provided with an air inlet and an air outlet on the propulsion strut. When the two air holes are in an open state, the airflow in the propulsion strut can take away the heat emitted by the motor controller; when the heat exchange needs to be reduced in the propulsion strut, the heat dissipation cover can be pressed once, so that the heat dissipation cover will completely close the air outlet, or the heat dissipation cover can be pressed according to the radiation intensity by the light sensing control unit, so that the heat exchange mode can be turned off in the night mode.

[0035] Optionally, the light sensing control unit includes a light sensing element and a push-pull electromagnet. The light sensing element is arranged on the outer wall of the propulsion support rod. The light sensing element is control-connected to the push-pull electromagnet. The push-pull electromagnet and the heat dissipation cover are correspondingly arranged on both sides of the air outlet.

[0036] Optionally, the push-pull electromagnet includes a sliding rod and an electromagnetic coil, the electromagnetic coil is connected to the photosensitive element, the middle part of the sliding rod passes through the electromagnetic coil, a limiting portion is provided at one end of the sliding rod, a first return spring is provided between the limiting portion and the end surface of the electromagnetic coil, and the other end of the sliding rod cooperates with the heat dissipation cover.

[0037] Specifically, when the heat dissipation cover is driven to move by the light sensing control unit, the push-pull electromagnet is arranged opposite to the heat dissipation cover. When the light sensing element detects the alternation of day and night, the push-pull electromagnet will be energized once, and the sliding rod will move toward the heat dissipation cover, pressing the heat dissipation cover to switch the heat dissipation cover to the open and closed state of the air outlet. After power failure, the sliding rod will retract under the action of the first return spring.

[0038] Optionally, the self-locking structure includes a guide rod and a guide block, one end of the guide rod is hinged on a support of the self-locking structure, the other end of the guide rod is slidably set in a guide groove of the guide block, a second return spring is arranged between one side of the guide block and the support, and the other side of the guide block is connected to the heat dissipation cover plate.

[0039] Optionally, the guide groove is a closed polygon, a first stop position and a second stop position are provided on the polygon, and a line connecting the first stop position and the second stop position is parallel to a sliding direction of the heat dissipation cover plate.

[0040] Specifically, the guide rod in the self-locking structure slides with the guide groove on the guide block. When the heat dissipation cover does not close the air outlet, when the heat dissipation cover is pressed, the guide block moves once toward the support direction, and the guide rod slides from the first stop position of the guide groove to the second stop position, and then the guide rod stays at the second stop position, and the heat dissipation cover closes the air outlet; when the heat dissipation cover is pressed again, the guide block moves once again toward the support direction, and the guide rod slides from the second stop position of the guide groove to the first stop position, and then the guide rod stays at the first stop position, and the heat dissipation cover opens the air outlet again.

[0041] In one embodiment, the self-locking structure can also adopt the existing structure. As long as the heat dissipation cover can be pressed once, the opening and closing states of the heat dissipation cover and the air outlet can be switched. The push-pull electromagnet in this technical solution can be controlled manually and automatically: when in manual control mode, the switch of the heat dissipation hole can be manually controlled to meet different heat dissipation needs according to the complex environment at high altitude during the day. When the photosensitive device fails, it can still be manually controlled to open and close the cover. In the automatic control mode, the push-pull electromagnet is automatically controlled by the photosensitive element to achieve automatic switching between day and night. Both manual control and automatic control reduce the heat exchange of the propulsion support rod by controlling the action of the electromagnet. The difference is that manual control is manual control, and automatic control automatically identifies day and night through photosensitive elements. The two control methods can improve system redundancy.

[0042] Optionally, a plurality of heat dissipation openings are respectively provided in the air inlet and the air outlet, and an air flow path connecting the air inlet and the air outlet corresponds to the fins of the motor controller.

[0043] Specifically, the air inlet and the air outlet are arranged relative to the fins of the motor controller, so that when the air outlet is in an open state, the airflow can quickly take away the heat of the motor controller, thereby improving the heat dissipation efficiency.

[0044] Optionally, the heat dissipation cover plate and the self-locking structure are arranged between the motor controller and the inner wall of the propulsion support rod.

[0045] Specifically, the motor controller and the propulsion support rod are arranged in the gap between the inner wall of the propulsion support rod and the motor controller, which does not affect the original structural design of the propulsion support rod and does not interfere with the internal structure of the propulsion support rod.

[0046] Optionally, an air inlet cover is provided on the air inlet hole.

[0047] Optionally, the outer side of the propulsion support rod is wrapped with a foam insulation layer.

[0048] Specifically, an air intake hood is set outside the air intake hole, which can collect a large amount of air to enter the propulsion support rod, thereby facilitating the rapid cooling of the motor controller. An insulation layer is set outside the propulsion support rod, which can have a thermal insulation effect when the air outlet is closed, thereby significantly reducing the heat exchange in the propulsion support rod.

[0049] Example

[0050] like Figures 1 to 4 As shown, the present invention provides a heat dissipation control device for a propulsion system of a near-space low-speed UAV, comprising:

[0051] The air inlet and outlet holes 3 are correspondingly arranged at the two ends of the propulsion support rod 4;

[0052] The heat dissipation cover plate 103 is movably arranged on the inner wall of the propulsion support rod 4. The heat dissipation cover plate 103 is connected to the self-locking structure 1. When the heat dissipation cover plate 103 is pressed, the self-locking structure 1 drives the heat dissipation cover plate 103 to close the air outlet 3. When the heat dissipation cover plate 103 is pressed again, the self-locking structure 1 drives the heat dissipation cover plate 103 to open the air outlet 3.

[0053] The light sensing control unit is arranged on the inner wall of the propulsion support rod 4. The light sensing element 7 supplies power to the push-pull electromagnet 2 according to the brightness of the surrounding environment. When switching between day and night, the push-pull electromagnet 2 is energized, and the sliding rod 201 presses the heat dissipation cover 103 once, and then the sliding rod 201 retracts under the action of the first return spring 202, so that the heat dissipation cover 103 can realize the opening and closing switching of the air outlet 3.

[0054] In this embodiment, the self-locking structure 1 includes a guide block 102 provided with a guide groove. When the heat dissipation cover 103 is pressed, the guide rod moves under the guidance of the guide groove, and under the action of the second return spring 101, the guide rod stays at the first stop position or the second stop position, so that the air outlet 3 can remain in an open or closed state.

[0055] In summary, the heat dissipation control device supplies power to the push-pull electromagnet 2 through the motor controller 5. When the light sensing element 7 detects that the radiation intensity is lower than the first set value, it indicates that the drone is in a night environment, the push-pull electromagnet 2 is energized once, and the sliding rod 201 presses the heat dissipation cover 3 once. Under the action of the self-locking structure 1, the heat dissipation cover 3 blocks the air outlet 3, so that the airflow path in the propulsion support rod 4 is interrupted, and the heat exchange is greatly reduced; when the light sensing element 7 detects that the radiation intensity is higher than the second set value, it indicates that the drone is in a daytime environment, the push-pull electromagnet 2 is energized again, and the sliding rod 201 presses the heat dissipation cover 3 once. Under the action of the self-locking structure 1, the heat dissipation cover 3 opens the air outlet 3, so that the airflow path in the propulsion support rod 4 is connected, thereby realizing the heat exchange between the inside and outside of the propulsion support rod 4.

[0056] The embodiments of the present invention have been described above, and the above description is exemplary, not exhaustive, and is not limited to the disclosed embodiments. Many modifications and changes will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments.

Claims

1. A heat dissipation control device for a propulsion system of a low-speed UAV in near space, characterized in that: include: The air inlet and the air outlet are correspondingly arranged at the two ends of the propulsion support rod; A heat dissipation cover plate, movably arranged on the inner wall of the propulsion support rod, the heat dissipation cover plate is connected to a self-locking structure, when the heat dissipation cover plate is pressed, the self-locking structure drives the heat dissipation cover plate to close the air outlet, and when the heat dissipation cover plate is pressed again, the self-locking structure drives the heat dissipation cover plate to open the air outlet; A light sensing control unit is arranged on the inner wall of the propulsion support rod, the light sensing control unit cooperates with the heat dissipation cover plate, and the light sensing control unit touches the heat dissipation cover plate according to the brightness of the surrounding environment.

2. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 1 is characterized in that: The light sensing control unit includes a light sensing element and a push-pull electromagnet. The light sensing element is arranged on the outer wall of the propulsion support rod. The light sensing element is control-connected with the push-pull electromagnet. The push-pull electromagnet and the heat dissipation cover are correspondingly arranged on both sides of the air outlet.

3. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 2 is characterized in that: The push-pull electromagnet includes a sliding rod and an electromagnetic coil, the electromagnetic coil is connected to the photosensitive element, the middle part of the sliding rod passes through the electromagnetic coil, a limiting portion is provided at one end of the sliding rod, a first return spring is provided between the limiting portion and the end surface of the electromagnetic coil, and the other end of the sliding rod cooperates with the heat dissipation cover.

4. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 1 is characterized in that: The self-locking structure includes a guide rod and a guide block, one end of the guide rod is hinged on the support of the self-locking structure, the other end of the guide rod is slidably arranged in the guide groove of the guide block, a second return spring is arranged between one side of the guide block and the support, and the other side of the guide block is connected to the heat dissipation cover plate.

5. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 4 is characterized in that: The guide groove is a closed polygon, a first stop position and a second stop position are arranged on the polygon, and a line connecting the first stop position and the second stop position is parallel to a sliding direction of the heat dissipation cover plate.

6. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 1 is characterized in that: The air inlet and the air outlet are respectively provided with a plurality of heat dissipation openings, and the air flow path communicating the air inlet and the air outlet corresponds to the fins of the motor controller.

7. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 6 is characterized in that: The heat dissipation cover plate and the self-locking structure are arranged between the motor controller and the inner wall of the propulsion support rod.

8. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 6 is characterized in that: An air inlet cover is arranged on the air inlet hole.

9. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 1, characterized in that: The outer side of the propulsion support rod is wrapped with a foam insulation layer.

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