Wireless charging system for near space aircraft

Abstract

The invention provides a wireless charging system for a near space aircraft, and belongs to the technical field of near space detection. The system comprises an energy transmitting end and an energy receiving end, the energy transmitting end is arranged on a ground device, and the energy receiving end is arranged at the bottom in a pod of the near space aircraft; the energy transmitting end comprises a transmitting unit and an energy transmitting circuit, and the energy receiving end comprises a receiving unit and an energy receiving circuit; the energy transmitting circuit is connected with the transmitting unit and is used for transmitting electric energy to the transmitting unit; magnetic coupling is formed between the transmitting unit and the receiving unit, and the transmitting unit transmits electric energy to the receiving unit through the magnetic coupling; the energy receiving circuit is connected with the receiving unit and used for receiving electric energy from the receiving unit.

Description

Technical Field

[0001] The present invention relates to the field of near-space detection technology, and in particular to a wireless charging system for near-space aircraft. Background Art

[0002] Common near-space aircraft, such as high-altitude balloons, have energy storage batteries installed in their cabins as the main energy supply, which plays a key role in their endurance.

[0003] Due to the low temperature environment in near-space, the cabin needs to be insulated and sealed, making it inconvenient to charge the energy storage battery in the cabin. In addition, some high-altitude balloons with scientific payloads (such as those used for solar cell calibration, astronomical observation, etc.) need to lift the cabin while waiting for launch. The cabin is connected to the balloon by a certain length of soft rope and suspended under the balloon. When the cabin is lifted by the launch vehicle, it will rotate or swing.

[0004] For the wired charging system of the energy storage battery, the rotation or swing of the pod will cause the wired charging cable to get tangled, causing operational difficulties and potential dangers. For the wireless charging system of the energy storage battery, the energy receiving structure is located inside the pod. When the pod rotates or swings, the receiving structure inside the pod is offset from the ground transmitting structure, affecting the power transmission efficiency of the charging system. Summary of the invention

[0005] The present invention provides a wireless charging system for a near-space aircraft, which is used to solve the defect in the prior art that the rotation or swing of a pod causes difficulty in charging the near-space aircraft, and realizes efficient charging of the near-space aircraft.

[0006] In a first aspect, the present invention provides a wireless charging system for a near-space aircraft, comprising an energy transmitting end and an energy receiving end; the energy transmitting end is arranged on a ground device, and the energy receiving end is arranged at the bottom of a cabin of the near-space aircraft; The energy transmitting end includes a transmitting unit and an energy transmitting circuit, and the energy receiving end includes a receiving unit and an energy receiving circuit; The energy transmitting circuit is connected to the transmitting unit and is used to transmit electrical energy to the transmitting unit; A magnetic coupling is formed between the transmitting unit and the receiving unit, and the transmitting unit transmits electrical energy to the receiving unit through the magnetic coupling; The energy receiving circuit is connected to the receiving unit and is used to receive electric energy from the receiving unit.

[0007] In one embodiment, the transmitting unit includes a first curved magnetic core, and the receiving unit includes a second curved magnetic core; A first coil is disposed on the concave edge of the first curved magnetic core; a cylindrical coil is disposed outwardly from the concave center of the second curved magnetic core; The concave surface of the first curved magnetic core is arranged opposite to the concave surface of the second curved magnetic core, and when the pod rotates or swings, the projection of the cylindrical coil toward the ground falls within the concave surface of the first curved magnetic core.

[0008] In one embodiment, the first curved magnetic core is centrally symmetrical to the second curved magnetic core.

[0009] In one embodiment, the circumscribed circle radius of the first curved magnetic core is determined according to a target swing radius; The target swing radius is the radius of the energy receiving end swinging along with the pod when the energy receiving end is located at a preset height above the energy transmitting end.

[0010] In one embodiment, the preset height is less than or equal to the target height; The target height is a vertical height between the transmitting unit and the receiving unit when the electric energy conversion efficiency corresponding to the magnetic coupling between the transmitting unit and the receiving unit is equal to a conversion efficiency threshold.

[0011] In one embodiment, the energy transmitting circuit includes an inverter circuit and a first resonant circuit; The input end of the inverter circuit is connected to a power supply, and the output end is connected to the first resonant circuit; The input end of the first resonant circuit is connected to the inverter circuit, and the output end is connected to the transmitting unit.

[0012] In one embodiment, the energy receiving circuit includes a second resonant circuit and a rectifier circuit; The input end of the second resonant circuit is connected to the receiving unit, and the output end is connected to the rectifier circuit; The input end of the rectifier circuit is connected to the output end of the second resonant circuit, and the output end is connected to the energy storage battery.

[0013] In one embodiment, a concave diameter of the first curved magnetic core is larger than a radius of a circumscribed circle of the first curved magnetic core, and smaller than a diameter of a circumscribed circle of the first curved magnetic core.

[0014] In one embodiment, the length of the cylindrical coil is smaller than the radius of the circumscribed circle of the first curved magnetic core.

[0015] In a second aspect, the present invention provides a near-space aircraft, comprising any one of the wireless charging systems for near-space aircraft described in the first aspect.

[0016] The wireless charging system for near-space aircraft provided by the present invention can ensure that electric energy is smoothly transmitted from the energy transmitting end to the energy receiving end when the pod rotates or swings by forming magnetic coupling between the energy transmitting end and the energy receiving end, thereby realizing normal charging of the near-space aircraft and effectively improving the charging efficiency of the near-space aircraft under various conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the present invention or the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0018] Figure 1 This is one of the structural schematic diagrams of the wireless charging system for near-space aircraft provided by the present invention.

[0019] Figure 2 It is a structural schematic diagram of a transmitting unit and a receiving unit provided by the present invention.

[0020] Figure 3 It is a schematic diagram of the pod swinging in an embodiment of the present invention.

[0021] Figure 4 It is a vertical cross-sectional schematic diagram of the first curved magnetic core and the second curved magnetic core provided by the present invention.

[0022] Figure 5 It is a schematic diagram of the radius of the circumscribed circle of the first curved magnetic core provided by the present invention.

[0023] Figure 6 This is the second structural schematic diagram of the wireless charging system for near-space aircraft provided by the present invention.

[0024] Figure 7 It is a schematic diagram of the circuit structure of a wireless charging system for near-space aircraft provided by the present invention.

[0025] Figure 8 It is a front view of the first curved magnetic core provided by the present invention.

[0026] Fig. 9 It is a three-dimensional diagram of the cylindrical coil provided by the present invention. DETAILED DESCRIPTION

[0027] In order to make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be clearly and completely described below in conjunction with the drawings of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] Figure 1 FIG. 1 is one of the structural schematic diagrams of the wireless charging system for near-space aircraft provided by the present invention. Figure 1 As shown, the system may include: An energy transmitting end 110 and an energy receiving end 120; The energy transmitting end 110 is arranged on a ground device, and the energy receiving end 120 is arranged at the bottom of a cabin of a near-space vehicle; The energy transmitting end 110 includes a transmitting unit 111 and an energy transmitting circuit 112, and the energy receiving end 120 includes a receiving unit 121 and an energy receiving circuit 122; The energy transmitting circuit 112 is connected to the transmitting unit 111 and is used to transmit electrical energy to the transmitting unit 111; A magnetic coupling is formed between the transmitting unit 111 and the receiving unit 121, and the transmitting unit 111 transmits electric energy to the receiving unit 121 through the magnetic coupling; The energy receiving circuit 122 is connected to the receiving unit 121 and is used to receive electrical energy from the receiving unit 121 .

[0029] Specifically, the energy transmitting end 110 may be disposed on various ground devices such as distribution vehicles, charging stations, etc. that can supply power to energy storage batteries for near-space vehicles.

[0030] It should be noted that when the energy receiving end 120 is arranged at the bottom of the pod of the near-space vehicle, it is necessary to ensure that magnetic coupling is formed between the receiving unit 121 and the transmitting unit 111. Specifically, the receiving unit 121 can extend from the bottom of the pod so as to be in direct contact with the transmitting unit 111. Alternatively, the receiving unit 121 can also be arranged as a whole inside the pod so as not to be in direct contact with the transmitting unit 111.

[0031] When the near-space vehicle is not released, it can be placed on a release vehicle, for example. At this time, the energy transmitting circuit 112 can transmit electric energy to the transmitting unit 111. Since magnetic coupling is formed between the transmitting unit 111 and the receiving unit 121, the transmitting unit 111 can transmit electric energy to the receiving unit 121 through magnetic coupling. The receiving unit 121 will transmit the electric energy to the energy receiving circuit 122, and the energy receiving circuit 122 can specifically transmit the electric energy to the energy storage battery of the near-space vehicle, thereby completing the charging of the near-space vehicle.

[0032] When the near-space vehicle is waiting to be launched, the pod will be lifted (by a launch vehicle or by an inflated high-altitude balloon), at which time the receiving unit 121 and the transmitting unit 111 will be out of contact (when the receiving unit 121 extends from the bottom of the pod), and the pod will rotate or swing. However, since magnetic coupling is formed between the transmitting unit 111 and the receiving unit 121, when the receiving unit 121 and the transmitting unit 111 are out of contact or the receiving unit 121 rotates or swings with the pod, as long as the distance between the transmitting unit 111 and the receiving unit 121 can ensure the formation of effective magnetic coupling, the transmitting unit 111 can still transmit electrical energy to the receiving unit 121 through magnetic coupling, thereby ensuring normal charging of the near-space vehicle.

[0033] The wireless charging system for near-space aircraft provided by the present invention can ensure that electric energy is smoothly transmitted from the energy transmitting end 110 to the energy receiving end 120 when the pod rotates or swings by forming a magnetic coupling between the energy transmitting end 110 and the energy receiving end 120, thereby realizing normal charging of the near-space aircraft and effectively improving the charging efficiency of the near-space aircraft under various conditions.

[0034] In one embodiment, Figure 2 As shown, the transmitting unit 111 may include a first curved magnetic core 211, and the receiving unit 121 may include a second curved magnetic core 221; A first coil 212 is disposed on the concave edge of the first curved magnetic core 211 ; a cylindrical coil 222 is disposed outwardly from the concave center of the second curved magnetic core 221 ; The concave surface of the first curved magnetic core 211 is arranged opposite to the concave surface of the second curved magnetic core 221 , and when the pod rotates or swings, the projection of the cylindrical coil 222 toward the ground falls within the concave surface of the first curved magnetic core 211 .

[0035] It should be noted that Figure 2It can be seen that the first curved magnetic core 211 and the second curved magnetic core 221 of the present invention can be a bowl-shaped structure, which can reduce the change in the air gap when the energy receiving end 120 swings with the pod, thereby weakening the fluctuation of the magnetic coupling coefficient between the energy receiving end 120 and the energy transmitting end 110.

[0036] Specifically, the cylindrical coil 222 may be a solenoid cylindrical coil, or other types of coils, such as a cylindrical coil, a quadrangular prism coil, etc., which is not specifically limited in the present invention.

[0037] The concave surface of the first curved magnetic core 211 and the concave surface of the second curved magnetic core 221 are arranged opposite to each other. The first coil 212 is arranged at the edge of the concave surface of the first curved magnetic core 211, and the cylindrical coil 222 is arranged outward from the center of the concave surface of the second curved magnetic core 221. This can make the transmission efficiency and stability of the magnetic coupling between the energy receiving end 120 and the energy transmitting end 110 higher.

[0038] When the pod rotates or swings, Figure 3 As shown, the projection of the cylindrical coil 222 toward the ground falls within the concave surface of the first curved magnetic core 211, which can minimize the impact of the magnetic coupling between the energy receiving end 120 and the energy transmitting end 110 caused by the swing of the pod, thereby ensuring the smooth transmission of electrical energy.

[0039] In one embodiment, the first curved magnetic core 211 is symmetrical to the second curved magnetic core 221. That is, the size and shape of the first curved magnetic core 211 and the second curved magnetic core 221 can be consistent. For example, the vertical cross-sections of the first curved magnetic core 211 and the second curved magnetic core 221 can be circles of the same size, such as Figure 4 shown.

[0040] By arranging the first curved magnetic core 211 and the second curved magnetic core 221 into a centrally symmetrical structure, the magnetic coupling process between the energy receiving end 120 and the energy transmitting end 110 does not change when the energy receiving end 120 rotates with the pod, thereby reducing the impact of the pod rotation on the charging performance of the system.

[0041] In one embodiment, the radius of the circumscribed circle of the first curved magnetic core 211 is determined according to the target swing radius; The target swing radius is the radius of the energy receiving end 120 swinging along with the pod when the energy receiving end 120 is located at a preset height above the energy transmitting end 110 .

[0042] In a specific application scenario of the wireless charging system for near-space aircraft provided by the present invention, such as Figure 5As shown, when the pod is suspended at a certain height (i.e., the energy receiving end 120 is located at a preset height above the energy transmitting end 110), the energy receiving end 120 will have a swing radius R when it swings with the pod. Using the circle formed by this swing radius R as the circumscribed circle of the first curved magnetic core 211 can effectively ensure that when the energy receiving end 120 swings with the pod within a certain range, the magnetic coupling between the energy receiving end 120 and the energy transmitting end 110 can effectively transmit electrical energy.

[0043] Further, in one embodiment, the preset height may be less than or equal to the target height; The target height is the vertical height between the transmitting unit 111 and the receiving unit 121 when the power conversion efficiency corresponding to the magnetic coupling between the transmitting unit 111 and the receiving unit 121 is equal to the conversion efficiency threshold.

[0044] It is understandable that when the distance between the transmitting unit 111 and the receiving unit 121 is larger, the electric energy conversion efficiency corresponding to the magnetic coupling between the transmitting unit 111 and the receiving unit 121 will be lower. By using the target height between the transmitting unit 111 and the receiving unit 121 as the preset height when the electric energy conversion efficiency corresponding to the magnetic coupling between the transmitting unit 111 and the receiving unit 121 is equal to the conversion efficiency threshold, it can be ensured that the magnetic coupling between the energy receiving end 120 and the energy transmitting end 110 meets the actual application requirements, thereby improving the practicality of the wireless charging system of the near-space aircraft.

[0045] Furthermore, in one embodiment, the concave diameter of the first curved magnetic core 211 is larger than the radius of the circumscribed circle of the first curved magnetic core 211 , and smaller than the diameter of the circumscribed circle of the first curved magnetic core 211 .

[0046] It can be understood that by setting the concave diameter PD of the first curved magnetic core 211 to be larger than the circumscribed circle radius R of the first curved magnetic core 211 and smaller than the circumscribed circle diameter 2R of the first curved magnetic core 211, that is, the value range of the concave diameter PD of the first curved magnetic core 211 is (R, 2R), it can ensure that effective magnetic coupling is formed between the transmitting unit 111 and the receiving unit 121 on the one hand, and avoid the first curved magnetic core 211 and the cylindrical coil 222. Direct contact to cause adverse effects.

[0047] It can be understood that after the circumscribed circle radius R of the first curved magnetic core 211 and the concave diameter PD of the first curved magnetic core 211 are determined, the height CH of the first curved magnetic core 211 can be determined. Figure 5 shown.

[0048] Furthermore, in one embodiment, the length of the cylindrical coil 222 is smaller than the radius of the circumscribed circle of the first curved magnetic core 211 .

[0049] It can be understood that by setting the length SH of the cylindrical coil 222 to be smaller than the circumscribed circle radius R of the first curved magnetic core 211, it is possible to ensure effective magnetic coupling between the transmitting unit 111 and the receiving unit 121 while avoiding adverse effects caused by direct contact between the first curved magnetic core 211 and the cylindrical coil 222.

[0050] In one embodiment, Figure 6 As shown (the arrows in the figure indicate the direction of electric energy flow), the energy transmitting circuit 112 includes an inverter circuit 1121 and a first resonant circuit 1122; The input end of the inverter circuit 1121 is connected to the power supply 1120, and the output end is connected to the first resonant circuit 1122; An input end of the first resonant circuit 1122 is connected to the inverter circuit 1121 , and an output end of the first resonant circuit 1122 is connected to the transmitting unit 111 .

[0051] It can be understood that by specifically configuring the energy transmitting circuit to include the inverter circuit 1121 and the first resonant circuit 1122 , smooth transmission of electric energy can be ensured.

[0052] Further, in one embodiment, if Figure 6 As shown (the arrows in the figure indicate the direction of electric energy flow), the energy receiving circuit 122 includes a second resonant circuit 1221 and a rectifier circuit 1222; The input end of the second resonant circuit 1221 is connected to the receiving unit 121, and the output end is connected to the rectifier circuit 1222; The input end of the rectifier circuit 1222 is connected to the output end of the second resonant circuit 1221 , and the output end is connected to the energy storage battery 1223 .

[0053] The second resonant circuit 1221 can realize efficient power transmission, and the rectifier circuit 1222 can convert the received alternating current into direct current for charging the energy storage battery 1223 .

[0054] It can be understood that by specifically configuring the energy receiving circuit 122 to include the second resonant circuit 1221 and the rectifier circuit 1222 , it is possible to ensure smooth reception of electric energy, thereby enabling charging of the energy storage battery 1223 .

[0055] In an example of applying the wireless charging system for near-space aircraft provided by the present invention, the specific circuit structure of the system can be as follows: Figure 7 shown.

[0056] in, V in The energy transmitting end 110 of the circuit is composed of a full-bridge inverter composed of four MOSFETs (S1-S4), a resonant capacitor C p1 and Cp2 , resonant inductor L p2 And the transmitting coil L p1 The energy receiving end 120 of the circuit is composed of a full-bridge rectifier composed of four diodes (D1-D4), a resonant capacitor C s And receiving coil L s The output side of the full-bridge rectifier passes through a large-capacity filter capacitor C o Connected to the energy storage battery load R in the pod L . R p1 , R p2 and R s L p1 , L p2 and L s The internal resistance.

[0057] In this example, the following process is used to determine specific parameters of the energy transmitting end 110 and the energy receiving end 120: Step 1: Determine the parameters such as the pod size, the preset pod suspension height, the offset, and the minimum air gap corresponding to the concave diameter PD of the first curved magnetic core 211 .

[0058] Step 2: Determine the concave diameter PD of the first curved magnetic core 211 and the diameter SD of the cylindrical coil 222 by combining the anti-deviance characteristic and the magnetic coupling characteristic, as shown in FIG. Figure 8 and 9 shown.

[0059] Step 3: Determine the coil height PH of the first curved magnetic core 211 and the height SH of the cylindrical coil 222 by comprehensively considering the anti-offset characteristic and the magnetic coupling characteristic.

[0060] Step 4: Analyze the anti-offset characteristics to determine the curvature radius QR of the first curved magnetic core 211 .

[0061] Step 5: Calculate the coil internal resistance and transmission efficiency assuming the quality factor.

[0062] Step 6: Determine the number of coil turns based on the transmission efficiency.

[0063] Step 7: Calculate other system parameters based on input voltage, voltage gain ratio, and output power.

[0064] Step 8: Determine whether the system requirements are met. If yes, proceed to step 9. If no, return to step 6.

[0065] Step 9: Calculate the magnetic field intensity distribution inside the pod based on the coil current simulation.

[0066] Step 10: Determine whether the electromagnetic interference standard is met. If yes, proceed to step 11. If no, return to step 6.

[0067] Step 11: Determine the number of turns in the coil.

[0068] According to the above steps 1-11, the scene specific parameters and the specific parameters of the transmitting unit 111 and the receiving unit 121 can be determined, as shown in Table 1 and Table 2 respectively.

[0069] Table 1 List of scene parameters

[0070] Table 2 Specific parameters of the transmitting unit and the receiving unit

[0071] Furthermore, the present invention also provides a near-space aircraft, which includes the wireless charging system for near-space aircraft described in any of the above embodiments, and has the beneficial effects of the wireless charging system for near-space aircraft described in any of the above embodiments, which will not be repeated here.

[0072] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein. However, these modifications or replacements do not deviate the essence of the corresponding technical solutions from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A wireless charging system for near-space aircraft, characterized in that: include: An energy transmitting end and an energy receiving end; the energy transmitting end is arranged on a ground device, and the energy receiving end is arranged at the bottom of a pod in a near-space aircraft; The energy transmitting end includes a transmitting unit and an energy transmitting circuit, and the energy receiving end includes a receiving unit and an energy receiving circuit; The energy transmitting circuit is connected to the transmitting unit and is used to transmit electrical energy to the transmitting unit; A magnetic coupling is formed between the transmitting unit and the receiving unit, and the transmitting unit transmits electrical energy to the receiving unit through the magnetic coupling; The energy receiving circuit is connected to the receiving unit and is used to receive electric energy from the receiving unit.

2. The wireless charging system for near-space aircraft according to claim 1, characterized in that: The transmitting unit includes a first curved magnetic core, and the receiving unit includes a second curved magnetic core; A first coil is disposed on the concave edge of the first curved magnetic core; a cylindrical coil is disposed outwardly from the concave center of the second curved magnetic core; The concave surface of the first curved magnetic core is arranged opposite to the concave surface of the second curved magnetic core, and when the pod rotates or swings, the projection of the cylindrical coil toward the ground falls within the concave surface of the first curved magnetic core.

3. The wireless charging system for near-space aircraft according to claim 2, characterized in that: The first curved magnetic core is centrally symmetrical to the second curved magnetic core.

4. The wireless charging system for near-space aircraft according to claim 3, characterized in that: The radius of the circumscribed circle of the first curved magnetic core is determined according to the target swing radius; The target swing radius is the radius of the energy receiving end swinging along with the pod when the energy receiving end is located at a preset height above the energy transmitting end.

5. The wireless charging system for near-space aircraft according to claim 4, characterized in that: The preset height is less than or equal to the target height; The target height is a vertical height between the transmitting unit and the receiving unit when the electric energy conversion efficiency corresponding to the magnetic coupling between the transmitting unit and the receiving unit is equal to a conversion efficiency threshold.

6. The wireless charging system for near-space aircraft according to claim 1, characterized in that: The energy transmitting circuit includes an inverter circuit and a first resonant circuit; The input end of the inverter circuit is connected to a power supply, and the output end is connected to the first resonant circuit; The input end of the first resonant circuit is connected to the inverter circuit, and the output end is connected to the transmitting unit.

7. The wireless charging system for near-space aircraft according to claim 6, characterized in that: The energy receiving circuit includes a second resonant circuit and a rectifier circuit; The input end of the second resonant circuit is connected to the receiving unit, and the output end is connected to the rectifier circuit; The input end of the rectifier circuit is connected to the output end of the second resonant circuit, and the output end is connected to the energy storage battery.

8. The wireless charging system for near-space aircraft according to claim 4, characterized in that: The concave diameter of the first curved magnetic core is larger than the radius of the circumscribed circle of the first curved magnetic core, and smaller than the diameter of the circumscribed circle of the first curved magnetic core.

9. The wireless charging system for near-space aircraft according to claim 8, characterized in that: The length of the cylindrical coil is smaller than the radius of the circumscribed circle of the first curved magnetic core.

10. A near-space aircraft, characterized in that: A wireless charging system for a near-space vehicle comprising the wireless charging system as described in any one of claims 1 to 9.

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