Aerostat system

Abstract

The invention provides an aerostat system. The aerostat system comprises a capsule body, a first pod, a second pod and external equipment, external equipment is mounted on the outer surface of the bag body; the first nacelle and the second nacelle are respectively hoisted on the lower surface of the capsule body; the external equipment is connected with the first pod and / or the second pod through a shielding wire, and a magnetic ring is arranged at the joint of the shielding wire and the external equipment; the first pod and the second pod are each of a metal shell closed structure. The first nacelle and the second nacelle are connected through a grounded metal net; installing power supply and distribution equipment in the first pod; a flight control device is installed in the second pod; and the equipment cases in the first pod and the second pod are connected with a pod rack on the pod structure. According to the aerostat system provided by the invention, the aerostat system is integrally designed and is divided into a plurality of areas, and targeted protection measures are adopted for different areas, so that electromagnetic interference is avoided in all directions, and the reliability of the aerostat system is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aerostats, and in particular to an aerostat system. Background Art

[0002] Compared with other types of aircraft, aerostats have the advantages of low requirements for launch conditions, long-term fixed-point airborne, and low cost. At present, they are widely used in industries such as high-altitude radar detection, optical observation, and high-altitude environmental scientific experimental monitoring. The electrical system of aerostats mainly includes the power supply and distribution subsystem and the flight control subsystem, which respectively provide power to the system and ensure the normal posture of the floating body (ball, boat). The cloud layer where the aerostat is located has relatively active discharges, which can easily cause failures of the electronic equipment of the aerostat.

[0003] In the prior art, for key components such as motors, cables, servos, measurement and control devices, internal communication power supplies and communication signal circuits, measures such as lightning protection nets, shielding layers, protection circuits, lightning cables and grounding wires are taken to achieve protection against common-mode and differential-mode interference caused by lightning.

[0004] However, the electromagnetic field environment at high altitudes is relatively complex. Even with the above-mentioned solutions in the prior art, there is still a risk of failure of key equipment due to electromagnetic interference, and the reliability is not high. Summary of the invention

[0005] The present invention provides an aerostat system, which is used to solve the technical problems in the prior art that key equipment in the aerostat system has the risk of failure due to electromagnetic interference and the reliability is low.

[0006] The present invention provides an aerostat system, comprising: a capsule, a first pod, a second pod and external equipment; The external equipment is installed on the outer surface of the capsule; the first pod and the second pod are respectively hoisted on the lower surface of the capsule; The external device is connected to the first pod and / or the second pod via a shielded wire, and a magnetic ring is provided at the connection between the shielded wire and the external device; The first pod and the second pod both adopt a metal shell closed structure; the first pod and the second pod are connected by a grounded metal mesh; A power supply and distribution device is installed in the first pod; a flight control device is installed in the second pod; and the equipment boxes in the first pod and the second pod are connected to the pod rack on the pod structure.

[0007] In some embodiments, the primary power return line of the power supply and distribution equipment is single-point grounded at the input end of the distributor or power controller, and the single-point grounding point is connected to the main grounding pile on the pod structure through a grounding wire.

[0008] In some embodiments, the secondary power supply return line of the power supply and distribution equipment is single-point grounded at the output end of each isolated DC / DC converter, and the single-point grounding point is connected to the main grounding pile on the pod structure through a grounding wire.

[0009] In some embodiments, the flight control device includes a signal acquisition module; The signal acquisition module is connected to the external device via a shielded line; A magnetic ring is provided at the connection between the shielding wire and the external device; A signal acquisition protection circuit is provided at the connection between the shielding wire and the signal acquisition module.

[0010] In some embodiments, the signal acquisition protection circuit includes a first-stage subcircuit composed of a transient voltage suppressor diode and a capacitor connected in series to ground; the first-stage subcircuit is used to discharge common-mode interference; A second stage subcircuit consisting of a bidirectional transient voltage suppressor diode; the second stage subcircuit is used to suppress differential mode interference; A third-level subcircuit composed of a voltage-stabilizing diode; the third-level subcircuit is used to limit the level of input to the signal acquisition module.

[0011] In some embodiments, the flight control device includes a control module; The control module is connected to the external device via a shielded wire; A magnetic ring is provided at the connection between the shielding wire and the external device; A driving protection circuit is provided at the connection between the shielding wire and the control module.

[0012] In some embodiments, the driving protection circuit includes a resistor and a MOS tube; The first end of the resistor is connected to the output end of the control module; The second end of the resistor is connected to the gate of the MOS tube; The source of the MOS tube is grounded; the drain of the MOS tube is connected to the driving motor of the external device.

[0013] In some embodiments, a resistor and a capacitor are connected in parallel on the power supply return line of the control module to achieve resistance-capacitance grounding.

[0014] In some embodiments, a DC input protection circuit is further provided between the flight control device and the DC power supply of the power supply; An AC input protection circuit is also provided between the flight control device and the AC power supply of the power supply.

[0015] In some embodiments, shielded cables are used for input lines and output lines of the inverters in the first pod and the second pod, and the shielding layers of the shielded cables are connected to the grounding points of the pods.

[0016] The aerostat system provided by the present invention is designed as a whole, and the aerostat system is divided into multiple areas. Different areas adopt targeted protection measures, which avoids electromagnetic interference in all directions and improves the reliability of the aerostat system. 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 It is a schematic diagram of the overall design of the aerostat system provided by the present invention.

[0019] Figure 2 It is a structural schematic diagram of the extravehicular cable provided by the present invention.

[0020] Figure 3 It is a structural schematic diagram of the signal acquisition protection circuit provided by the present invention.

[0021] Figure 4 It is a structural schematic diagram of the driving protection circuit provided by the present invention.

[0022] Figure 5 It is a structural schematic diagram of the resistance-capacitance grounding circuit of the control module provided by the present invention.

[0023] Figure 6 It is a structural schematic diagram of the power supply and distribution power grounding method provided by the present invention.

[0024] Figure 7 It is a structural schematic diagram of the DC input protection circuit provided by the present invention.

[0025] Figure 8 It is a structural schematic diagram of the AC input protection circuit provided by the present invention. DETAILED DESCRIPTION

[0026] 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.

[0027] Figure 1 Schematic diagram of the overall design of the aerostat system provided by the present invention. Figure 1 As shown in the figure, the electromagnetic protection area of ​​the aerostat is divided into the capsule area, the pod area and the chassis area according to the order of exposure to the high-altitude electromagnetic environment. The capsule area directly faces the high-altitude electromagnetic environment, and this area contains external equipment and connecting harnesses, among which the harnesses are very easy to couple electromagnetic interference; the pod area includes the first pod and the second pod, and the equipment in the chassis area is installed in the pod.

[0028] The aerostat system provided by the present invention comprises: a capsule, a first pod, a second pod and external equipment; The external equipment is installed on the outer surface of the capsule; the first pod and the second pod are respectively hoisted on the lower surface of the capsule; The external device is connected to the first pod and / or the second pod via a shielded wire, and a magnetic ring is provided at the connection between the shielded wire and the external device; The first pod and the second pod both adopt a metal shell closed structure; the first pod and the second pod are connected by a grounded metal mesh; A power supply and distribution device is installed in the first pod; a flight control device is installed in the second pod; and the equipment boxes in the first pod and the second pod are connected to the pod rack on the pod structure.

[0029] It should be noted that the aerostat system provided by the present invention has at least two pods, and can also be divided into more than two pods according to actual needs.

[0030] In some embodiments, the external device includes a blower, a valve, and a sensor. The blower may be a pressure-controlled blower.

[0031] Sensors include temperature sensors, humidity sensors, wind speed sensors, tension sensors, etc.

[0032] External devices are distributed on the top, bottom, side walls, etc. of the capsule.

[0033] Signal and power cables of various lengths are connected between the pods and between the pods and the external devices of the capsule, and are distributed over the entire surface of the capsule.

[0034] The main body of the aerostat includes a tethered balloon and a stratospheric airship, that is, the capsule can be spherical or airship-shaped.

[0035] The pods all adopt a metal shell closed structure, for example, an aluminum shell closed structure, or an aluminum alloy shell closed structure. The pods with a metal shell closed structure have a certain shielding effect on electromagnetic interference. The electromagnetic interference inside the pod is weaker than that outside the pod, which further protects the equipment inside the pod from electromagnetic interference.

[0036] A grounding copper mesh is used between the pod shells to achieve equipotential connection, and each equipment chassis in the pod is fully electrically bonded to the pod rack.

[0037] Figure 2 Schematic diagram of the structure of the extravehicular cable provided by the present invention. Figure 2 As shown, shielded cables are used to connect the pod to external equipment, and the wire harness is wrapped in multiple strands in the same direction with amorphous nanocrystalline magnetic rings for common-mode filtering where the cables enter the fan and valve. Shielded signal lines are used between the sensor and the collection equipment in the chassis of the pod, and common-mode filtering is used on the sensor side to suppress the impact of voltage spikes generated by high-frequency electromagnetic pulses on the equipment on the pod.

[0038] In some embodiments, the flight control device includes a signal acquisition module; The signal acquisition module is connected to the external device via a shielded line; A magnetic ring is provided at the connection between the shielding wire and the external device; A signal acquisition protection circuit is provided at the connection between the shielding wire and the signal acquisition module.

[0039] In some embodiments, the signal acquisition protection circuit includes a first-stage subcircuit composed of a transient voltage suppressor diode and a capacitor connected in series to ground; the first-stage subcircuit is used to discharge common-mode interference; A second stage subcircuit consisting of a bidirectional transient voltage suppressor diode; the second stage subcircuit is used to suppress differential mode interference; A third-level subcircuit composed of a voltage-stabilizing diode; the third-level subcircuit is used to limit the level of input to the signal acquisition module.

[0040] Specifically, the signal acquisition protection circuit adopts three-level protection measures. The first level uses high-power transient voltage suppressor (TVS) diodes and capacitors to be grounded in series to discharge common-mode interference. TVS1 and C1 are grounded in series to achieve signal positive protection, and TVS2 and C2 are grounded in series to achieve signal negative protection. The secondary circuit is differential mode interference suppression, which is achieved using bidirectional TVS diode TVS3. Common-mode inductor CML1 and capacitor C3 are used for decoupling between the primary and secondary protections. When entering the acquisition circuit, Zener diodes D3 and D4 are used to limit the level to prevent overvoltage from causing damage to the internal core circuit. At the same time, R1 and C4 are used to filter the acquisition signal.

[0041] For example, Figure 3 Schematic diagram of the signal acquisition protection circuit provided by the present invention. Figure 3 As shown, from the end of the acquisition cable to the acquisition module, there are the first-level sub-circuit, the second-level sub-circuit, and the third-level sub-circuit in sequence, and the first-level sub-circuit, the second-level sub-circuit, and the third-level sub-circuit are connected in series.

[0042] A common mode inductor CML1 may be connected in series between the first and second sub-circuits. The first coil of the common mode inductor CML1 is connected in series to the first pole cable of the acquisition cable; and the second coil of the common mode inductor CML1 is connected in series to the second pole cable of the acquisition cable.

[0043] An amplification / adjustment circuit may be connected in series between the second-stage sub-circuit and the third-stage sub-circuit.

[0044] The first-stage sub-circuit includes a transient voltage suppressor diode TVS1, a capacitor C1, a transient voltage suppressor diode TVS2, and a capacitor C2.

[0045] The first end of the transient voltage suppressor diode TVS1 is connected to the first pole cable of the signal acquisition cable, the second end of the transient voltage suppressor diode TVS1 is connected to the first end of the capacitor C1, and the second end of the capacitor C1 is grounded. The first end of the transient voltage suppressor diode TVS2 is connected to the second pole cable of the signal acquisition cable, the second end of the transient voltage suppressor diode TVS2 is connected to the first end of the capacitor C2, and the second end of the capacitor C2 is grounded.

[0046] The second stage sub-circuit includes capacitor C3 and transient voltage suppressor diode TVS3.

[0047] The first end of capacitor C3 is connected to the first pole cable of the collection cable, and the second end of capacitor C3 is connected to the second pole cable of the collection cable. The first end of transient voltage suppressor diode TVS3 is connected to the first pole cable of the collection cable, and the second end of transient voltage suppressor diode TVS3 is connected to the second pole cable of the collection cable.

[0048] The third-stage sub-circuit includes a resistor R1, a voltage-stabilizing diode D3, a voltage-stabilizing diode D4 and a capacitor C4.

[0049] The resistor R1 is connected in series with the first pole cable of the acquisition cable, the first end of the resistor R1 is connected to the adjustment circuit, the second end of the resistor R1 is connected to the first end of the voltage-stabilizing diode D4, the second end of the voltage-stabilizing diode D3, and the first end of the capacitor C4; the second end of the voltage-stabilizing diode D4 is connected to the second end of the capacitor C4, and is connected to the second pole cable of the acquisition cable, and is grounded. The first end of the voltage-stabilizing diode D3 is connected to the power supply VCC.

[0050] In some embodiments, the flight control device includes a control module; The control module is connected to the external device via a shielded wire; A magnetic ring is provided at the connection between the shielding wire and the external device; A driving protection circuit is provided at the connection between the shielding wire and the control module.

[0051] In some embodiments, the driving protection circuit includes a resistor and a MOS tube; The first end of the resistor is connected to the output end of the control module; The second end of the resistor is connected to the gate of the MOS tube; The source of the MOS tube is grounded; the drain of the MOS tube is connected to the driving motor of the external device.

[0052] Specifically, a resistor R2 is connected in series between the output of the control signal of the control module and the gate of the MOS tube Q1. The value of the resistor is generally selected to be 10 ohms. The resistor can slow down the change rate of the drain-source resistance.

[0053] The gate source of MOS tube Q1 is connected in parallel with the voltage regulator D1 to limit the gate voltage below the voltage regulator value to protect the MOS tube from breakdown. The gate source of MOS tube is connected in parallel with the resistor R3 to release the gate charge and prevent charge accumulation. The Zener diode D2 clamp and the RC buffer circuit C1 and R1 are used in series to suppress the drain spike voltage caused by the sudden change of the instantaneous current of the device switch.

[0054] For example, Figure 4 Schematic diagram of the structure of the driving protection circuit provided by the present invention. Figure 4 As shown, the driving protection circuit includes a resistor R1, a resistor R2, a resistor R3, a MOS tube Q1, a Zener diode D1, a Zener diode D2, a voltage regulator diode D3 and a capacitor C1.

[0055] The output end of the control module is connected to the first end of the resistor R2 and the first end of the Zener diode D3; the second end of the resistor R2 is connected to the second end of the Zener diode D3, the first end of the resistor R3, the first end of the Zener diode D1, and the gate of the MOS tube Q1; the drain of the MOS tube Q1 is connected to the first end of the resistor R1, the first end of the Zener diode D2, and the drive motor; the second end of the resistor R1 is connected to the first end of the capacitor C1; the second end of the resistor R3, the second end of the Zener diode D1, the source of the MOS tube Q1, the second end of the capacitor C1, and the second end of the Zener diode D2 are all grounded.

[0056] In some embodiments, a resistor and a capacitor are connected in parallel on the power supply return line of the control module to achieve resistance-capacitance grounding.

[0057] Specifically, the control module power supply loop uses a resistor in parallel with a capacitor to achieve resistance-capacitance grounding, and the grounding of the same power supply system is grounded at one point. The capacitor is a high-voltage capacitor of 100nF / 3KV, and the resistance value is usually 1M.

[0058] For example, Figure 5 : is a schematic diagram of the structure of the resistance-capacitance grounding circuit of the control module provided by the present invention, such as Figure 5 As shown, after the resistor is connected in parallel with the capacitor, the first end is connected to the second pole of the control module power line, and the second end is grounded.

[0059] In some embodiments, the primary power return line of the power supply and distribution equipment is single-point grounded at the input end of the distributor or power controller, and the single-point grounding point is connected to the main grounding pile on the pod structure through a grounding wire.

[0060] In some embodiments, the secondary power supply return line of the power supply and distribution equipment is single-point grounded at the output end of each isolated DC / DC converter, and the single-point grounding point is connected to the main grounding pile on the pod structure through a grounding wire.

[0061] Specifically, Figure 6 Schematic diagram of the structure of the power supply grounding method provided by the present invention, such as Figure 6 As shown, the negative ends of the primary power supply (ACDC power supply) are gathered together and connected to the grounding stake of the equipment mounting plate through the electrical connector of the power controller or distributor, that is, the structural ground of the pod (main grounding stake). The grounding stake is set next to the power controller or distributor so that the grounding wire is as short as possible. The primary power supply line and return line must be arranged in pairs, and the structure is not allowed to be used as a return line.

[0062] The output of the secondary power supply (distributor or power controller) is isolated from the primary power supply. The ground wires of the secondary power supply in the same single-machine equipment are not connected to each other, but single-point grounding is adopted, and they are connected to the structural ground of the pod together with the primary power return line.

[0063] In some embodiments, a DC input protection circuit is also provided between the flight control device and the DC power supply of the power supply.

[0064] Specifically, in the DC input protection circuit, an SPD device is used between the input DC+ and DC-, generally a varistor SPD1 to achieve differential mode protection, while the common mode protection of DC- is connected to the discharge tube GDT1 to achieve high power discharge. The common mode protection of the positive pole is achieved by the varistor SPD1 and the gas discharge tube GDT1. The polymer positive temperature coefficient thermistor PPTC is used as a decoupling device between the two levels of protection to ensure that the bidirectional TVS diode TVS1 of the rear stage will limit the voltage only after most of the energy is discharged from the front stage.

[0065] For example, Figure 7Schematic diagram of the structure of the DC input protection circuit provided by the present invention. Figure 7 As shown, the DC input protection circuit includes a first-level subcircuit, a second-level subcircuit, and a third-level subcircuit. The first-level subcircuit, the second-level subcircuit, and the third-level subcircuit are connected in series.

[0066] The first-level subcircuit includes a varistor SPD1 and a discharge tube GDT1. The first end of the varistor SPD1 is connected to the DC+ end of the DC input power supply, and the second end of the varistor SPD1 is connected to the DC- end of the DC input power supply; the first end of the discharge tube GDT1 is connected to the DC- end of the DC input power supply, and the second end of the discharge tube GDT1 is grounded. The second-level subcircuit includes a polymer positive temperature coefficient thermistor PPTC. The polymer positive temperature coefficient thermistor PPTC is connected in series to the DC+ cable of the DC input power supply. The third-level subcircuit includes a bidirectional transient voltage suppressor diode TVS1. The first end of the bidirectional transient voltage suppressor diode TVS1 is connected to the DC+ end of the DC input power supply, and the second end of the bidirectional transient voltage suppressor diode TVS1 is connected to the DC- end of the DC input power supply.

[0067] In some embodiments, an AC input protection circuit is further provided between the flight control device and the AC power supply of the power supply.

[0068] Specifically, in the AC input protection circuit, the main protection is for single-phase AC input power supply. The common mode of the AC input phase line adopts varistors SPD2, SPD3 and high-voltage capacitors C1, C2 in series. The differential mode between the phase lines is protected by varistor SPD1, and the common-mode inductor CML1 is used for decoupling. The differential mode capacitor C3 and common-mode capacitors C4, C5 are used in the subsequent stage to improve electromagnetic interference.

[0069] For example, Figure 8 is a schematic diagram of the structure of the AC input protection circuit provided by the present invention, such as Figure 8 As shown, the AC input protection circuit includes a first-level subcircuit, a second-level subcircuit, and a third-level subcircuit. The first-level subcircuit, the second-level subcircuit, and the third-level subcircuit are connected in series.

[0070] The first-level subcircuit includes a varistor SPD1, a varistor SPD2, a varistor SPD3, a capacitor C1, and a capacitor C2. The first end of the varistor SPD1 is connected to the L end of the AC input power supply, and the second end of the varistor SPD1 is connected to the N end of the AC input power supply; the first end of the capacitor C1 is connected to the second end of the varistor SPD3, and the first end of the varistor SPD3 is connected to the N end of the AC input power supply. The second end of the capacitor C2 is connected to the first end of the varistor SPD2, and the second end of the varistor SPD2 is connected to the L end of the AC input power supply. The second end of the capacitor C1 and the first end of the capacitor C2 are both grounded. The second-level subcircuit includes a common-mode inductor CML1. The first coil of the common-mode inductor CML1 is connected in series to the L end cable of the AC input power supply; the second coil of the common-mode inductor CML1 is connected in series to the N end cable of the AC input power supply. The third-level subcircuit includes a capacitor C3, a capacitor C4, and a capacitor C5. The first end of capacitor C3 is connected to the second end of capacitor C4 and connected to the L end of the AC input power supply; the second end of capacitor C3 is connected to the first end of capacitor C5 and connected to the N end of the AC input power supply; the first end of capacitor C4 and the second end of capacitor C5 are both grounded.

[0071] In some embodiments, shielded cables are used for input lines and output lines of the inverters in the first pod and the second pod, and the shielding layers of the shielded cables are connected to the grounding points of the pods.

[0072] Specifically, the high-power power cables and signal cables in the pod are arranged separately, and shielded cables are used for the inverter input and output cables, with the shielding layer connected to the pod grounding point. Each cable is routed close to the pod wall.

[0073] The protection of the capsule equipment of the present invention is mainly aimed at the protection of valves, fans and external sensors, and voltage spike suppression is achieved by using shielded cables and magnetic ring common mode winding. The pod area is protected by grounding the pod structure of the power supply and distribution power supply and each device in the control cabin, equipotential bonding of the equipment chassis, pod shielding, and wiring methods in the pod, so as to weaken the external electromagnetic field and electrostatic interference. In the chassis area, protection design circuits are provided for the sensor signal processing circuit, and the input circuits of the DC input and AC input power supplies. The circuit is designed with a scheme of high-power discharge in the front stage, decoupling in the middle stage, and fast discharge and suppression in the rear stage. In addition, the valve and fan control drive circuits are protected by MOS drive tube gate-source overvoltage protection, fast channel suppression and charge discharge, and drain-source overvoltage absorption suppression.

[0074] In the pod area, the flight control equipment and power supply and distribution equipment are installed in independent pods. The pod uses an aluminum shell enclosure to minimize the impact of external electromagnetic radiation on the cables and equipment in the pod. The pod shells are connected with grounding copper mesh to achieve equipotential connection, and each equipment chassis is fully electrically bonded to the pod rack. The high-power power cables and signal cables in the pod are arranged separately, and shielded cables are used for the inverter input and output cables, with the shielding layer connected to the pod grounding point. Each cable is routed close to the pod wall.

[0075] In the power supply and distribution pod, the primary power loop is single-point grounded at the ball (boat) onboard distributor or power controller input, and the single-point grounding point is connected to the main grounding pile of the pod structure through the grounding wire. For the secondary power loop, including the isolated DC / DC output loops of the distributor, single-point grounding is used to connect to the main grounding pile of the pod structure.

[0076] In the control cabin, the output return lines of the isolated DC / DC modules in the control chassis should be single-point grounded, and high-resistance grounding should be achieved through resistance and capacitance.

[0077] In the chassis area, the power supply and distribution equipment chassis should be fully enclosed metal structure, and the honeycomb structure should be used for heat dissipation at the ventilation holes of the box wall. The socket should be electrically connected to the box wall through a conductive gasket or directly contacting the box body. At the external cable entry power connection, including the step-down input, AC / DC power input, fan power input, and inverter input interface, a three-level protection circuit is used to gradually reduce the impact of surges, including primary discharge, decoupling and secondary discharge circuits. In addition to the power supply equipment, the control chassis also adopts a fully enclosed metal structure. The control circuits connected to the capsule device in the control chassis, including fan control, valve control, etc., need to be equipped with protection circuits. For the MOS switch in the valve drive circuit, a voltage regulator and a resistor are used to prevent overvoltage between the gate and source during the drive input, slow down the conduction speed of the MOS tube and release the gate charge. An RC absorption circuit is used between the drain and the source to absorb the voltage spike when the MOS switch is switched. An RC absorption circuit is used for the mechanical relay contacts, and a freewheeling diode is used for the coil drive circuit to achieve protection. For the sensor signal input interface on the ball (boat), isolation and filtering are used for signal processing, and a voltage regulator circuit is used to achieve voltage clamping.

[0078] The aerostat system provided by the present invention is designed as a whole, and the aerostat system is divided into multiple areas. Different areas adopt targeted protection measures, which avoids electromagnetic interference in all directions and improves the reliability of the aerostat system.

[0079] It should also be noted that the terms "target", "first", "second", etc. in the embodiments of the present application are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the terms used in this way can be interchangeable under appropriate circumstances, so that the embodiments of the present application can be implemented in an order other than those illustrated or described here, and the objects distinguished by "first" and "second" are generally of the same type, and the number of objects is not limited. For example, the first object can be one or more.

[0080] In the embodiments of the present application, the term "and / or" describes the association relationship of the associated objects, indicating that three relationships may exist. For example, A and / or B may represent: A exists alone, A and B exist at the same time, and B exists alone. The character " / " generally indicates that the associated objects before and after are in an "or" relationship.

[0081] "Determine B based on A" in the embodiments of the present application means that the factor A should be considered when determining B. It is not limited to "B can be determined based on A alone", but should also include: "Determine B based on A and C", "Determine B based on A, C and E", "Determine C based on A, and further determine B based on C", etc. In addition, it can also include taking A as a condition for determining B, for example, "When A meets the first condition, use the first method to determine B"; for another example, "When A meets the second condition, determine B", etc.; for another example, "When A meets the third condition, determine B based on the first parameter", etc. Of course, it can also be a condition that takes A as a factor for determining B, for example, "When A meets the first condition, use the first method to determine C, and further determine B based on C", etc.

[0082] In the embodiments of the present application, the term "plurality" refers to two or more than two, and other quantifiers are similar.

[0083] 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. An aerostat system, characterized in that: include: The capsule, the first pod, the second pod and external equipment; The external device is installed on the outer surface of the capsule; The first pod and the second pod are respectively suspended on the lower surface of the capsule; The external device is connected to the first pod and / or the second pod via a shielded wire, and a magnetic ring is provided at the connection between the shielded wire and the external device; The first pod and the second pod both adopt a metal shell closed structure; the first pod and the second pod are connected by a grounded metal mesh; installing power supply and distribution equipment in the first pod; installing a flight control device in the second pod; The equipment chassis in the first pod and the second pod are connected to the pod rack on the pod structure.

2. The aerostat system according to claim 1, characterized in that: The primary power return line of the power supply and distribution equipment is single-point grounded at the input end of the distributor or power controller, and the single-point grounding point is connected to the main grounding pile on the pod structure through a grounding wire.

3. The aerostat system according to claim 2, characterized in that: The secondary power supply return line of the power supply and distribution equipment is single-point grounded at the output end of each isolated DC / DC converter, and the single-point grounding point is connected to the main grounding pile on the pod structure through a grounding wire.

4. The aerostat system according to claim 1, characterized in that: The flight control device includes a signal acquisition module; The signal acquisition module is connected to the external device via a shielded line; A magnetic ring is provided at the connection between the shielding wire and the external device; A signal acquisition protection circuit is provided at the connection between the shielding wire and the signal acquisition module.

5. The aerostat system according to claim 4, characterized in that: The signal acquisition protection circuit includes a first-stage subcircuit composed of a transient voltage suppressor diode and a capacitor connected in series to ground; the first-stage subcircuit is used to discharge common-mode interference; A second stage subcircuit consisting of a bidirectional transient voltage suppressor diode; the second stage subcircuit is used to suppress differential mode interference; A third-level subcircuit composed of a voltage-stabilizing diode; the third-level subcircuit is used to limit the level of input to the signal acquisition module.

6. The aerostat system according to claim 1, characterized in that: The flight control device includes a control module; The control module is connected to the external device via a shielded wire; A magnetic ring is provided at the connection between the shielding wire and the external device; A driving protection circuit is provided at the connection between the shielding wire and the control module.

7. The aerostat system according to claim 6, characterized in that: The driving protection circuit includes a resistor and a MOS tube; The first end of the resistor is connected to the output end of the control module; The second end of the resistor is connected to the gate of the MOS tube; The source of the MOS tube is grounded; the drain of the MOS tube is connected to the driving motor of the external device.

8. The aerostat system according to claim 6, characterized in that: A resistor and a capacitor are connected in parallel on the power supply loop of the control module to realize resistance-capacitance grounding.

9. The aerostat system according to claim 1, characterized in that: A DC input protection circuit is also provided between the flight control device and the DC power supply of the power supply; An AC input protection circuit is also provided between the flight control device and the AC power supply of the power supply.

10. The aerostat system according to any one of claims 1 to 9, characterized in that: The inverter input lines and output lines in the first pod and the second pod use shielded cables, and the shielding layers of the shielded cables are connected to the grounding points of the pods.

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