Temperature control box of unmanned aerial vehicle and unmanned aerial vehicle

Abstract

The invention provides a temperature control box of an unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle temperature control, the temperature control box comprises a heat preservation box body structure, an air inlet and an air outlet are formed in the bottom of the heat preservation box body structure at intervals, the heat preservation box body structure is used for being arranged in a vehicle body of the unmanned aerial vehicle, and the air inlet is formed in an internal-external interface of the vehicle body; the heat preservation box body structure is arranged in the machine body and is close to the head of the unmanned aerial vehicle, the air outlet is formed in the internal-external interface of the machine body and is close to the tail of the unmanned aerial vehicle, and the interior of the heat preservation box body structure is used for bearing airborne equipment of the unmanned aerial vehicle; the air inlet door and the air outlet door are respectively arranged at the air inlet position and the air outlet position; the driving device is connected with the air inlet door and the air outlet door; the temperature control box achieves heat dissipation and heat preservation, does not consume a large amount of electric energy of the unmanned aerial vehicle, and guarantees the endurance and lift performance of the unmanned aerial vehicle.

Description

Technical Field

[0001] The present invention belongs to the technical field of temperature control of unmanned aerial vehicles, and more specifically, relates to a temperature control box of an unmanned aerial vehicle and the unmanned aerial vehicle. Background Art

[0002] The flight altitude of near-space UAVs can reach more than 20km, and they need to experience the ambient temperature from the ground to the ceiling altitude. According to the ground and high-altitude temperatures recorded in the extreme values ​​of climate for military equipment of UAV GJB 1172, it can be known that the ambient temperature that the UAV needs to experience during the ground take-off and landing phase can be as high as +47.7, and the ambient temperature that it needs to experience during high-altitude flight can be as low as -88.2℃. According to the General Guidelines for Airborne Electronic Equipment GJB457, the operating temperature of Class 2 airborne equipment at sea level must be higher than -55℃ and lower than +70℃. According to GJB457, the low-temperature working temperature has nothing to do with the altitude, and the upper limit of the high-temperature working temperature gradually decreases with the increase of the altitude. At an altitude of 21.28km, the high-temperature working environment must be lower than 10℃; therefore, in the entire flight profile of the UAV, the airborne equipment needs to dissipate the heat when the ambient temperature is higher than the operating temperature requirement, and keep the equipment warm when the ambient temperature is lower than the operating temperature requirement.

[0003] At present, the heat dissipation surface of airborne equipment is directly exposed to the air. If the heat dissipation surface of airborne equipment is directly exposed to the air for heat dissipation, there will be no problem in heat dissipation. However, a large amount of energy will be required for compensatory heating of the airborne equipment when the ambient temperature is lower than the working temperature requirement, which will consume the electric energy of the UAV and will have an adverse effect on the UAV's performance such as flight time and lift.

[0004] Since near-space drones experience a wide range of ambient temperature variations, onboard equipment requires both heat dissipation and heat preservation, while energy usage is restricted. How to meet the operating temperature requirements of onboard equipment under these restrictions is a difficult problem that this application needs to solve. Summary of the invention

[0005] The purpose of the present invention is to provide a temperature control box for an unmanned aerial vehicle and an unmanned aerial vehicle in view of the deficiencies in the existing technology, so as to solve the problem raised in the above background technology that the heat dissipation surface of the current airborne equipment is directly exposed to the air, which can achieve heat dissipation but cannot keep warm. When the ambient temperature is low, a large amount of electric energy is required to compensate for the heating of the airborne equipment, which will have an adverse effect on the performance of the unmanned aerial vehicle, such as the flight time and lift.

[0006] In order to achieve the above object, the present invention provides a temperature control box for an unmanned aerial vehicle, the temperature control box comprising:

[0007] A heat preservation box structure, wherein an air inlet and an air outlet are arranged at intervals at the bottom of the heat preservation box structure, and the heat preservation box structure is used to be arranged inside the body of the drone, the air inlet is arranged at the inner and outer interface of the body, and is arranged near the nose position of the drone, the air outlet is arranged at the inner and outer interface of the body, and is arranged near the tail position of the drone, and the interior of the heat preservation box structure is used to carry the airborne equipment of the drone;

[0008] An air inlet door and an air exhaust door, wherein the air inlet door and the air exhaust door are respectively arranged at the air inlet position and the air exhaust position;

[0009] A driving device is arranged inside the heat preservation box structure, the driving device is connected to the air inlet door and the air exhaust door, the driving device can drive the air inlet door to cover or open the air inlet, and can synchronously drive the exhaust door to cover or open the air exhaust port.

[0010] Preferably, the inner side of the air inlet is hingedly connected to the air inlet door near the middle of the thermal insulation box structure, and the inner side of the air outlet is hingedly connected to the exhaust door near the middle of the thermal insulation box structure, and the top surface of the air inlet door and the top surface of the exhaust door can respectively form an inclined air inlet top surface and an inclined exhaust top surface when the driving device is driven.

[0011] Preferably, the driving device comprises:

[0012] A flip mechanism, wherein the flip mechanism is connected to the air inlet door and the air exhaust door, and the flip mechanism can drive the air inlet door and the air exhaust door to flip and open the air inlet and the air exhaust respectively;

[0013] A rotating mechanism is connected to the air inlet door and the air exhaust door, and the rotating mechanism can drive the air inlet door and the air exhaust door to rotate and cover the air inlet and the air exhaust respectively.

[0014] Preferably, the flipping mechanism comprises:

[0015] A steering gear, the steering gear being arranged between the air inlet and the air outlet;

[0016] A damper operating rod, the middle part of which is connected to the output end of the servo, both ends of the damper operating rod are bent to form pressure rods, the two pressure rods are respectively arranged above the air inlet door and above the air exhaust door, the servo is used to drive the damper operating rod to rotate, and the other ends of the two pressure rods can slide against the top surface of the air inlet door and the top surface of the air exhaust door respectively when the damper operating rod rotates.

[0017] Preferably, the slewing mechanism comprises:

[0018] Two shafts, the inner side of the air inlet is hingedly connected to the air inlet door via one of the shafts, and the inner side of the air outlet is hingedly connected to the air outlet door via the other of the shafts;

[0019] Two torsion springs, the two torsion springs are respectively sleeved on the two shafts, one end of the two torsion springs is connected to the bottom of the heat preservation box structure, and the other ends of the two torsion springs are respectively connected to the air inlet door and the air exhaust door.

[0020] Preferably, the thermal insulation box structure comprises:

[0021] A box body, wherein a box opening is provided at the bottom of the box body;

[0022] A bottom plate, two sides of which are respectively connected to the inner sides of the box opening, an air inlet is formed between one end of the bottom plate and one end of the box body, and an air outlet is formed between the other end of the bottom plate and the other end of the box body.

[0023] Preferably, the box body is a PMI material box body.

[0024] Preferably, the bottom plate is an aluminum honeycomb sandwich bottom plate.

[0025] Preferably, the temperature control box of the drone also includes a temperature control sensor and a controller, and the temperature control sensor and the controller are arranged inside the temperature control box. The controller is electrically connected to the temperature control sensor and the drive device, and the controller can receive the temperature signal detected by the temperature control sensor and control the operation of the drive device.

[0026] A drone comprises a temperature control box of the drone.

[0027] The present invention provides a temperature control box for an unmanned aerial vehicle and the unmanned aerial vehicle, which have the following beneficial effects: the heat preservation box structure of the temperature control box is arranged inside the body of the unmanned aerial vehicle, the air inlet and the air exhaust port of the heat preservation box structure are arranged outside the body of the unmanned aerial vehicle, the air inlet and the air exhaust port are arranged close to the nose and the tail of the unmanned aerial vehicle respectively, the driving device is connected with the air inlet door and the air exhaust door, when the unmanned aerial vehicle is flying, under high temperature conditions, the internal temperature of the temperature control box is close to the upper limit, the driving device can drive the air inlet door to open the air inlet, and can synchronously drive the air exhaust door to open the air exhaust port, the air in the atmospheric environment will be discharged from the air inlet door The air enters from the inlet and is discharged from the exhaust port, flowing through the thermal insulation box structure. The heat dissipation capacity of the thermal insulation box structure is enhanced, and the heat dissipation of the airborne equipment can be achieved. Under low temperature conditions, the internal temperature of the temperature control box is close to the lower limit, the driving device can drive the air inlet door to cover the air inlet, and can synchronously drive the exhaust door to cover the exhaust port. The air in the thermal insulation box structure has only natural convection, and the thermal insulation capacity of the thermal insulation box structure is enhanced, which can achieve heat preservation of the airborne equipment. Therefore, the temperature control box achieves both heat dissipation and heat preservation, and at the same time will not consume a large amount of electric energy of the UAV, thereby ensuring the flight time and lift performance of the UAV.

[0028] Other features and advantages of the present invention will be described in detail in the following detailed description. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] 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.

[0030] Figure 1 A schematic structural diagram of a temperature control box of a drone during heat preservation according to an embodiment of the present invention is shown;

[0031] Figure 2 A schematic structural diagram of a temperature control box of a drone during heat dissipation according to an embodiment of the present invention is shown.

[0032] Description of reference numerals:

[0033] 1. Insulation box structure; 2. Air inlet; 3. Air outlet; 4. Air inlet door; 5. Air exhaust door; 6. Servo; 7. Air door operating rod; 8. Pressure rod; 9. Box; 10. Bottom plate. DETAILED DESCRIPTION

[0034] 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.

[0035] like Figure 1 and Figure 2 As shown, the present invention provides a temperature control box for an unmanned aerial vehicle, the temperature control box comprising:

[0036] The heat preservation box structure 1 has an air inlet 2 and an air outlet 3 at intervals at the bottom thereof. The heat preservation box structure 1 is used to be arranged inside the body of the UAV. The air inlet 2 is arranged at the inner and outer interfaces of the body and is arranged near the nose of the UAV. The air outlet 3 is arranged at the inner and outer interfaces of the body and is arranged near the tail of the UAV. The interior of the heat preservation box structure 1 is used to carry the airborne equipment of the UAV.

[0037] The air inlet door 4 and the air exhaust door 5 are respectively arranged at the air inlet 2 and the air exhaust 3;

[0038] The driving device is arranged inside the heat preservation box structure 1, and the driving device is connected to the air inlet door 4 and the exhaust door 5. The driving device can drive the air inlet door 4 to cover or open the air inlet 2, and can synchronously drive the exhaust door 5 to cover or open the exhaust port 3.

[0039] Specifically, in order to solve the problem that the heat dissipation surface of the current airborne equipment is directly exposed to the air, which can achieve heat dissipation but cannot keep warm, when the ambient temperature is low, a large amount of electric energy is needed to compensate for the heating of the airborne equipment, which will have an adverse effect on the performance of the UAV such as the flight time and lift, the present invention provides a temperature control box for a UAV, the heat preservation box structure 1 of the temperature control box is fixed inside the belly of the UAV body, the air inlet 2 and the air exhaust 3 of the heat preservation box structure 1 are arranged on the outside of the UAV body, the air inlet 2 and the air exhaust 3 are respectively arranged close to the nose and the tail of the UAV, the driving device is connected to the air inlet door 4 and the exhaust door 5, when the UAV is flying, under high temperature conditions, the internal temperature of the temperature control box is close to the upper limit, and the driving device can The air inlet door 4 is driven to open the air inlet 2, and the exhaust door 5 can be driven to open the exhaust port 5 synchronously. The air in the atmospheric environment will enter from the air inlet 2 and be discharged from the exhaust port 5, flowing through the thermal insulation box structure 1. The heat dissipation capacity of the thermal insulation box structure 1 is enhanced, and the heat dissipation of the airborne equipment can be achieved; under low temperature conditions, the internal temperature of the temperature control box is close to the lower limit, the driving device can drive the air inlet door 4 to cover the air inlet 2, and can synchronously drive the exhaust door 5 to cover the exhaust port 3. The air in the thermal insulation box structure 1 has only natural convection, and the heat preservation capacity of the thermal insulation box structure 1 is enhanced, and the heat preservation of the airborne equipment can be achieved. Therefore, the temperature control box realizes both heat dissipation and heat preservation, and at the same time will not consume a large amount of electric energy of the UAV, thereby ensuring the flight time and lift performance of the UAV.

[0040] Preferably, the inner side of the air inlet 2 is hingedly connected to the air inlet door 4 near the middle of the thermal insulation box structure 1, and the inner side of the air outlet 3 is hingedly connected to the exhaust door 5 near the middle of the thermal insulation box structure 1. The top surface of the air inlet door 4 and the top surface of the exhaust door 5 can respectively form an inclined air inlet top surface and an inclined exhaust top surface when driven by the driving device.

[0041] Specifically, the airflow can enter the heat preservation box structure 1 along the inclined air inlet top surface, so that a large amount of external ambient airflow can enter the heat preservation box structure 1, thereby improving the heat dissipation effect.

[0042] Preferably, the driving device comprises:

[0043] The flip mechanism is connected to the air inlet door 4 and the air exhaust door 5, and the flip mechanism can synchronously drive the air inlet door 4 and the air exhaust door 5 to flip and open the air inlet 2 and the air exhaust 3 respectively;

[0044] The rotary mechanism is connected with the air inlet door 4 and the air exhaust door 5. The rotary mechanism can drive the air inlet door 4 and the air exhaust door 5 to rotate and cover the air inlet 2 and the air exhaust 3 respectively.

[0045] Preferably, the flipping mechanism comprises:

[0046] A steering gear 6, which is arranged between the air inlet 2 and the air outlet 3;

[0047] The damper operating rod 7 has its middle portion connected to the output end of the servo 6, and both ends of the damper operating rod 7 are bent to form pressure rods 8, and the two pressure rods 8 are respectively arranged above the air inlet door 4 and above the air exhaust door 5. The servo 6 is used to drive the damper operating rod 7 to rotate, and the other ends of the two pressure rods 8 can slide against the top surfaces of the air inlet door 4 and the top surfaces of the air exhaust door 5 respectively when the damper operating rod 7 rotates.

[0048] Specifically, the servo 6 is a small servo, the damper actuating rod 7 and the pressure rod 8 are arranged vertically, the servo 6 is arranged at the bottom of the heat preservation box structure 1, the damper actuating rod 7 is rotatably connected to the bottom of the heat preservation box structure 1, and a limit block is provided on the damper actuating rod 7 to limit the damper actuating rod 7 to only rotate 90 degrees. When the flip mechanism is in operation, the servo 6 can control the damper actuating rod 7 to rotate 90 degrees. At this time, the other ends of the two pressure rods 8 can synchronously slide and lean against the top surfaces of the air inlet door 4 and the top surfaces of the exhaust door 5 when the damper actuating rod 7 rotates, and can synchronously push the air inlet door 4 and the exhaust door 5 to flip downward to open the air inlet 2 and the exhaust port 3. The air inlet door 4 and the exhaust door 5 can be simultaneously actuated by the damper actuating rod 7 to ensure that the cooling airflow can smoothly and timely pass over the surface of the airborne equipment.

[0049] Preferably, the slewing mechanism comprises:

[0050] Two shafts, the inner side of the air inlet 2 is hingedly connected to the air inlet door 4 through one of the shafts, and the inner side of the air outlet 5 is hingedly connected to the air outlet door 5 through the other shaft;

[0051] Two torsion springs are respectively sleeved on the two shafts, one end of the two torsion springs is connected to the bottom of the heat preservation box structure 1, and the other ends of the two torsion springs are respectively connected to the air inlet door 4 and the air outlet door 5.

[0052] Specifically, when the servo stops running, the air inlet door 4 can close the air inlet 2 under the torsion of the torsion spring, and the exhaust door 5 is similar. A closed space will be formed inside the thermal insulation box structure 1 to ensure that the airborne equipment is kept warm inside the thermal insulation box structure 1.

[0053] Preferably, the thermal insulation box structure comprises:

[0054] A box body 9, wherein a box opening is provided at the bottom of the box body 9;

[0055] The bottom plate 10 has two sides connected to the inner sides of the box opening respectively, an air inlet 2 is formed between one end of the bottom plate 10 and one end of the box body 9, and an air outlet 3 is formed between the other end of the bottom plate 10 and the other end of the box body 9.

[0056] Specifically, one end of the box body 9 is arranged toward the nose direction, and the other end of the box body is arranged toward the tail direction. The bottom plate 10 is flush with the lower wing surface of the UAV, and the airborne equipment is installed above the bottom plate 10. When in the closed state, the air inlet door 4 and the exhaust door 5 are parallel to the bottom plate 10.

[0057] Preferably, the box body 9 is a box body made of PMI material.

[0058] Preferably, the bottom plate 10 is an aluminum honeycomb sandwich bottom plate.

[0059] Preferably, the temperature control box of the drone also includes a temperature control sensor and a controller, which are arranged inside the temperature control box. The controller is electrically connected to the temperature control sensor and the drive device. The controller can receive the temperature signal detected by the temperature control sensor and control the operation of the drive device.

[0060] Specifically, when the temperature control sensor detects that the temperature inside the temperature control box is high, the controller controls the flip mechanism to operate; when the temperature control sensor detects that the temperature inside the temperature control box is low, the controller controls the rotation mechanism to operate so that the air inlet door 4 and the exhaust door 5 have the ability to close automatically.

[0061] A drone comprises a temperature control box of the drone.

[0062] In summary, when the temperature control box of the drone of the present invention is applied to the drone, under high temperature conditions, the servo 6 can control the damper operating rod 7 to open the air inlet door 4 and the exhaust door 5, and the airflow in flight will enter the insulation box structure 1 along the air inlet door, and the heat dissipation capacity of the insulation box structure 1 is enhanced. The airflow entering the insulation box structure 1 cools the airborne equipment and then flows out from the exhaust door 5; under low temperature conditions, the servo 6 controls the damper operating rod 5 to close the air inlet door 2 and the exhaust door 6, and the airflow in flight cannot enter the insulation box structure 1, and the heat preservation capacity of the insulation box structure 1 is enhanced. The airborne equipment relies on its own heat generation during operation to maintain the temperature, and thus the temperature control box realizes both heat dissipation and heat preservation, and at the same time will not consume a large amount of electrical energy of the drone, thereby ensuring the flight time and lift performance of the drone.

[0063] 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 temperature control box for an unmanned aerial vehicle, characterized in that: The temperature control box includes: A heat preservation box structure, wherein an air inlet and an air outlet are arranged at intervals at the bottom of the heat preservation box structure, and the heat preservation box structure is used to be arranged inside the body of the drone, the air inlet is arranged at the inner and outer interfaces of the body and is arranged near the nose of the drone, the air outlet is arranged at the inner and outer interfaces of the body and is arranged near the tail of the drone, and the interior of the heat preservation box structure is used to carry the airborne equipment of the drone; An air inlet door and an air exhaust door, wherein the air inlet door and the air exhaust door are respectively arranged at the air inlet position and the air exhaust position; A driving device is arranged inside the heat preservation box structure, the driving device is connected to the air inlet door and the air exhaust door, the driving device can drive the air inlet door to cover or open the air inlet, and can synchronously drive the exhaust door to cover or open the air exhaust port.

2. The temperature control box of a drone according to claim 1, characterized in that: The inner side of the air inlet is hingedly connected to the air inlet door near the middle of the thermal insulation box structure, and the inner side of the air outlet is hingedly connected to the exhaust door near the middle of the thermal insulation box structure. The top surface of the air inlet door and the top surface of the exhaust door can respectively form an inclined air inlet top surface and an inclined exhaust top surface when the driving device is driven.

3. The temperature control box of a drone according to claim 2, characterized in that: The driving device comprises: A flip mechanism, wherein the flip mechanism is connected to the air inlet door and the air exhaust door, and the flip mechanism can drive the air inlet door and the air exhaust door to flip and open the air inlet and the air exhaust respectively; A rotating mechanism is connected to the air inlet door and the air exhaust door, and the rotating mechanism can drive the air inlet door and the air exhaust door to rotate and cover the air inlet and the air exhaust respectively.

4. The temperature control box of a drone according to claim 3, characterized in that: The turning mechanism comprises: A steering gear, the steering gear being arranged between the air inlet and the air outlet; A damper operating rod, the middle part of which is connected to the output end of the servo, both ends of the damper operating rod are bent to form pressure rods, the two pressure rods are respectively arranged above the air inlet door and above the air exhaust door, the servo is used to drive the damper operating rod to rotate, and the other ends of the two pressure rods can slide against the top surface of the air inlet door and the top surface of the air exhaust door respectively when the damper operating rod rotates.

5. The temperature control box of a drone according to claim 3, characterized in that: The rotary mechanism comprises: Two shafts, the inner side of the air inlet is hingedly connected to the air inlet door via one of the shafts, and the inner side of the air outlet is hingedly connected to the air outlet door via the other of the shafts; Two torsion springs, the two torsion springs are respectively sleeved on the two shafts, one end of the two torsion springs is connected to the bottom of the thermal insulation box structure, and the other ends of the two torsion springs are respectively connected to the air inlet door and the air exhaust door.

6. The temperature control box of a drone according to claim 1, characterized in that: The thermal insulation box structure comprises: A box body, wherein a box opening is provided at the bottom of the box body; A bottom plate, two sides of which are respectively connected to the inner sides of the box opening, an air inlet is formed between one end of the bottom plate and one end of the box body, and an air outlet is formed between the other end of the bottom plate and the other end of the box body.

7. The temperature control box of a drone according to claim 6, characterized in that: The box body is made of PMI material.

8. The temperature control box of a drone according to claim 6, characterized in that: The bottom plate is an aluminum honeycomb sandwich bottom plate.

9. The temperature control box of a drone according to claim 1, characterized in that: The temperature control box of the drone also includes a temperature control sensor and a controller, which are arranged inside the temperature control box. The controller is electrically connected to the temperature control sensor and the drive device, and the controller can receive the temperature signal detected by the temperature control sensor and control the operation of the drive device.

10. A drone, characterized in that: Comprising: a temperature control box for an unmanned aerial vehicle as described in any one of claims 1 to 9.

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