A heat dissipation control device for a propulsion system of a low-speed UAV in near-space

Abstract

The present invention discloses a heat dissipation control device for a propulsion system of a low-speed unmanned aerial vehicle in near space, which relates to the technical field of heat dissipation of unmanned aerial vehicles, comprising: an air inlet and an air outlet, which are correspondingly arranged at both ends of a propulsion support rod; a heat dissipation cover plate, which is movably arranged on the inner wall of the propulsion support rod, and 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 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; a light sensing control unit, which is arranged on the inner wall of the propulsion support rod, and 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; the control device can alleviate the problem of energy shortage during the night flight of the unmanned aerial vehicle, and realizes the on-off of the heat dissipation path of the propulsion support rod by opening and closing the heat dissipation cover plate, so that the ambient temperature of the motor controller can be actively controlled to meet the heat dissipation requirements under different conditions.

Description

Technical Field

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

[0002] Near-space drones (UAVs) boast high altitudes and exceptionally long flight times, combining the characteristics of conventional aircraft and low-orbit satellites. They are primarily used for reconnaissance, surveillance, and communications relay, representing a new development in aerospace technology with significant strategic and economic benefits. As the optimal propulsion system for solar-powered UAVs, near-space propeller electric propulsion systems consume over 70% of the system's total energy. Their energy flow efficiency is crucial for maintaining energy balance and enabling day-night flight cycles. With the rapid development of the industrial and aerospace sectors, the number of near-space long-endurance aircraft is increasing. During nighttime flight, energy storage batteries are used to power the aircraft. Auxiliary heating is essential to ensure the proper operation of aircraft equipment in harsh environments. In addition to the propulsion power required for UAV flight, heating power accounts for a significant portion. Since UAVs have limited battery power at night, other methods are needed to maintain equipment temperature to conserve energy and alleviate power consumption. Summary of the Invention

[0003] The purpose of the present invention is to address the shortcomings of the existing technology and provide a heat dissipation control device for the propulsion system of a low-speed near-space UAV. The control device can alleviate the problem of energy shortage during the UAV's night flight. By opening and closing the heat dissipation cover, the heat dissipation path of the propulsion rod can be opened and closed, so that the ambient temperature of the motor controller can be actively controlled to meet the heat dissipation requirements under different conditions.

[0004] In order to achieve the above objectives, 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 respectively arranged at the two ends of the propulsion support rod;

[0006] a heat dissipation cover plate, movably disposed on the inner wall of the propulsion support rod, the heat dissipation cover plate being 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. 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, 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.

[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 controlled and 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 light sensing 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 face 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 to the support of the self-locking structure, and 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.

[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 the 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 communicating the air inlet and the air outlet corresponds to the fins 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 uses closed heat dissipation holes to reduce heat dissipation. The heat generated by the motor controller during normal operation heats the surrounding environment. During night flight, the airflow path is closed. Compared with traditional auxiliary heating, this improves energy utilization, saves power, and increases overnight flight time. When the auxiliary heating function fails, the heat dissipation control device can still achieve a heating effect through the heat of the motor controller itself, ensuring the normal operation of the motor controller at low temperatures. It also provides redundant temperature control.

[0018] 2. The heat dissipation control device uses the power module in the motor controller to power the heat dissipation control device. This can minimize the impact of the heat dissipation control device on the drone, reduce modification costs, make operation easier, 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. The electromagnet controls the sliding rod to press the heat dissipation cover 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 energized for a long time. It is controlled by a click trigger method to realize the alternating switching between open and closed.

[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 heat dissipation cover automatically closes or opens by identifying the solar radiation status through the light sensing element. Manual control 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 with reference to 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 Shown 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 sensor. 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. Instead, 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 near-space low-speed UAV, comprising:

[0031] The air inlet and the air outlet are respectively 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. The heat dissipation cover is connected to 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. When the heat dissipation cover is pressed again, the self-locking structure drives the heat dissipation cover to open the air outlet.

[0033] The 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. 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 both air holes are in the open state, the airflow in the propulsion strut can take away the heat emitted by the motor controller; when the heat exchange in the propulsion strut needs to be reduced, the heat dissipation cover can be pressed once, so that the heat dissipation cover will completely close the air outlet. The heat dissipation cover can also be pressed according to the radiation intensity through the light sensing control unit, so that the heat exchange mode can be turned off in 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 part is provided at one end of the sliding rod, a first return spring is provided between the limiting part and the end face 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 set 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 is cut off, the sliding rod retracts 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 to the support of the self-locking structure, and the other end of the guide rod is slidably set 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.

[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 the sliding direction of the heat dissipation cover.

[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, 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, 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 adopt manual control and automatic control: 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 realize the opening and closing of the cover. In the automatic control mode, the push-pull electromagnet is automatically controlled by the photosensitive element to realize 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 is automatic identification of day and night by the photosensitive element. 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 the 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 air flow 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 rod is wrapped with a foam insulation layer.

[0048] Specifically, an air intake hood is set outside the air inlet, which can collect a large amount of air into the propulsion support rod, facilitating 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 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 both ends of the propulsion support rod 4;

[0052] The heat dissipation cover 103 is movably arranged on the inner wall of the propulsion support rod 4. The heat dissipation cover 103 is connected to the self-locking structure 1. When the heat dissipation cover 103 is pressed, the self-locking structure 1 drives the heat dissipation cover 103 to close the air outlet 3. When the heat dissipation cover 103 is pressed again, the self-locking structure 1 drives the heat dissipation cover 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, greatly reducing heat exchange; 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, realizing heat exchange inside and outside the propulsion support rod 4.

[0056] While various embodiments of the present invention have been described above, the above description is intended to be illustrative, not exhaustive, and not limited to the disclosed embodiments. Many modifications and variations 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 respectively arranged at the two ends of the propulsion support rod; a heat dissipation cover plate, movably disposed on the inner wall of the propulsion support rod, the heat dissipation cover plate being 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. 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 provided 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; 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 controllably 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. The push-pull electromagnet includes a sliding rod and an electromagnetic coil, the electromagnetic coil is connected to the light sensing element, the middle portion of the sliding rod passes through the electromagnetic coil, one end of the sliding rod is provided with a limiting portion, 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 is engaged with the heat dissipation cover plate; 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, and 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.

2. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 1 is characterized in that: The guide groove is a closed polygon, and a first stop position and a second stop position are provided on the polygon. The connecting line of the first stop position and the second stop position is parallel to the sliding direction of the heat dissipation cover plate.

3. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 1, 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.

4. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 3, 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.

5. The heat dissipation control device for a near-space low-speed UAV propulsion system according to claim 3 is characterized in that: An air inlet cover is provided on the air inlet hole.

6. 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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