Aerostat system

Abstract

The application provides a kind of aerostat system, comprising: capsule, first gondola, second gondola and external equipment;External equipment is installed on the outer surface of the capsule;First gondola and second gondola are respectively hoisted on the lower surface of the capsule;External equipment is connected with first gondola and / or second gondola through shielded wire and external equipment, and magnetic ring is arranged at the connection of shielded wire and external equipment;First gondola and second gondola are both closed structure with metal shell;Grounded metal mesh is used to connect between first gondola and second gondola;Power supply equipment is installed in first gondola;Flight control equipment is installed in second gondola;Equipment cabinet in first gondola and second gondola is connected with gondola rack on gondola structure.The aerostat system provided by the application is designed from the whole, divides the aerostat system into multiple areas, different areas use targeted protection measures, and electromagnetic interference is avoided in all directions, which improves the reliability of the aerostat system.

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 to other types of aircraft, aerostats offer advantages such as low launch requirements, the ability to maintain a fixed position for extended periods, and low cost. They are currently widely used in fields such as high-altitude radar detection, optical observation, and high-altitude environmental scientific experiment monitoring. The electrical system of an aerostat primarily consists of a power supply and distribution subsystem and a flight control subsystem, which respectively provide power and maintain the proper posture of the aerostat (sphere, boat). The cloud layer in which aerostats operate is prone to high electrical discharges, which can easily lead to malfunctions in the aerostat's electronic equipment.

[0003] In the existing technology, 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, protective circuits, lightning cables and grounding wires are taken to achieve protection against common-mode and differential-mode interference caused by lightning.

[0004] However, the high-altitude electromagnetic field environment is relatively complex. Even with the above-mentioned solutions in the existing technology, 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 for solving the technical problems in the prior art of the risk of failure of key equipment due to electromagnetic interference and low reliability.

[0006] The present invention provides an aerostat system, comprising: a capsule, a first pod, a second pod and external equipment;

[0007] 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;

[0008] 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;

[0009] The first pod and the second pod both adopt a metal shell enclosed structure; the first pod and the second pod are connected by a grounded metal mesh;

[0010] A power supply and distribution device is installed in the first pod; a flight control device is installed in the second pod; and the device chassis in the first pod and the second pod are connected to the pod rack on the pod structure.

[0011] 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.

[0012] In some embodiments, the secondary power 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.

[0013] In some embodiments, the flight control device includes a signal acquisition module;

[0014] The signal acquisition module is connected to the external device via a shielded wire;

[0015] providing a magnetic ring at the connection between the shielding wire and the external device;

[0016] A signal acquisition protection circuit is provided at the connection between the shielding wire and the signal acquisition module.

[0017] 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;

[0018] a second-stage subcircuit composed of a bidirectional transient voltage suppressor diode; the second-stage subcircuit is used to suppress differential mode interference;

[0019] 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.

[0020] In some embodiments, the flight control device includes a control module;

[0021] The control module is connected to the external device via a shielded wire;

[0022] providing a magnetic ring at the connection between the shielding wire and the external device;

[0023] A driving protection circuit is provided at the connection between the shielding wire and the control module.

[0024] In some embodiments, the driving protection circuit includes a resistor and a MOS tube;

[0025] The first end of the resistor is connected to the output end of the control module;

[0026] The second end of the resistor is connected to the gate of the MOS tube;

[0027] The source of the MOS tube is grounded; the drain of the MOS tube is connected to the driving motor of the external device.

[0028] 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.

[0029] 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;

[0030] An AC input protection circuit is also provided between the flight control device and the AC power supply of the power supply.

[0031] In some embodiments, 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.

[0032] The aerostat system provided by the present invention is designed from an overall perspective, and the aerostat system is divided into multiple areas. Different areas adopt targeted protection measures, thereby avoiding electromagnetic interference in all directions and improving the reliability of the aerostat system. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the technical solutions in the present invention or the prior art, a brief introduction is given below to 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 any creative work.

[0034] Figure 1 It is a schematic diagram of the overall design of the aerostat system provided by the present invention.

[0035] Figure 2 It is a structural schematic diagram of the extravehicular cable provided by the present invention.

[0036] Figure 3 It is a structural diagram of the signal acquisition protection circuit provided by the present invention.

[0037] Figure 4 It is a structural diagram of the driving protection circuit provided by the present invention.

[0038] Figure 5 It is a structural schematic diagram of the resistance-capacitance grounding circuit of the control module provided by the present invention.

[0039] Figure 6 It is a structural schematic diagram of the power supply and distribution power grounding method provided by the present invention.

[0040] Figure 7 It is a structural diagram of the DC input protection circuit provided by the present invention.

[0041] Figure 8 It is a structural diagram of the AC input protection circuit provided by the present invention. DETAILED DESCRIPTION

[0042] To make the objectives, technical solutions, and advantages of the present invention more clear, the technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts shall fall within the scope of protection of the present invention.

[0043] Figure 1 This is a 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 zones of an aerostat are divided into the capsule area, the pod area, and the chassis area, in the order of exposure to the high-altitude electromagnetic environment. The capsule area directly faces the high-altitude electromagnetic environment and contains external equipment and connecting wiring harnesses, the wiring harnesses of which are highly susceptible to electromagnetic interference. The pod area includes the first pod and the second pod, and the chassis area equipment is installed inside the pod.

[0044] The aerostat system provided by the present invention comprises: a capsule, a first pod, a second pod and external equipment;

[0045] 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;

[0046] 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;

[0047] The first pod and the second pod both adopt a metal shell enclosed structure; the first pod and the second pod are connected by a grounded metal mesh;

[0048] A power supply and distribution device is installed in the first pod; a flight control device is installed in the second pod; and the device chassis in the first pod and the second pod are connected to the pod rack on the pod structure.

[0049] 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.

[0050] In some embodiments, the external device includes a blower, a valve, and a sensor. The blower may be a pressure-controlled blower.

[0051] Sensors include temperature sensors, humidity sensors, wind speed sensors, tension sensors, etc.

[0052] External equipment is distributed on the top, bottom, side walls, etc. of the capsule.

[0053] 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.

[0054] The main body of the aerostat includes a tethered balloon and a stratospheric airship, that is, the capsule can be spherical or airship-shaped.

[0055] The pods all adopt a metal shell enclosed structure, for example, an aluminum shell enclosed structure, or an aluminum alloy shell enclosed structure. The pods with a metal shell enclosed structure have a certain shielding effect on electromagnetic interference. The electromagnetic interference inside the pod is weaker than that outside the pod, further protecting the equipment inside the pod from electromagnetic interference.

[0056] A grounding copper mesh is used between the pod shells to achieve equipotential connection, and each equipment chassis in the pod is fully electrically connected to the pod rack.

[0057] Figure 2 This is a 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 chassis acquisition equipment in 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.

[0058] In some embodiments, the flight control device includes a signal acquisition module;

[0059] The signal acquisition module is connected to the external device via a shielded wire;

[0060] providing a magnetic ring at the connection between the shielding wire and the external device;

[0061] A signal acquisition protection circuit is provided at the connection between the shielding wire and the signal acquisition module.

[0062] 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;

[0063] a second-stage subcircuit composed of a bidirectional transient voltage suppressor diode; the second-stage subcircuit is used to suppress differential mode interference;

[0064] 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.

[0065] Specifically, the signal acquisition protection circuit employs a three-level protection strategy. The first level uses a high-power transient voltage suppressor (TVS) diode and capacitor connected in series with ground to dissipate common-mode interference. TVS1 and C1 are connected in series with ground to protect the positive signal, while TVS2 and C2 are connected in series with ground to protect the negative signal. The second level suppresses differential-mode interference using a bidirectional TVS diode, TVS3. Common-mode inductor CML1 and capacitor C3 provide decoupling between the primary and secondary protection levels. Zener diodes D3 and D4 limit the voltage level before the signal enters the acquisition circuit to prevent damage to the internal core circuitry caused by overvoltage. R1 and C4 filter the acquired signal.

[0066] For example, Figure 3 This is a schematic diagram of the structure 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.

[0067] 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 to the first pole cable of the acquisition cable; and the second coil of the common mode inductor CML1 is connected to the second pole cable of the acquisition cable.

[0068] An amplification / adjustment circuit may be connected in series between the second-stage sub-circuit and the third-stage sub-circuit.

[0069] 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.

[0070] A first end of a transient voltage suppressor diode TVS1 is connected to the first pole of the signal acquisition cable, a second end of the transient voltage suppressor diode TVS1 is connected to the first end of a capacitor C1, and a second end of the capacitor C1 is grounded. A first end of a transient voltage suppressor diode TVS2 is connected to the second pole of the signal acquisition cable, a second end of the transient voltage suppressor diode TVS2 is connected to the first end of a capacitor C2, and a second end of the capacitor C2 is grounded.

[0071] The second stage sub-circuit includes capacitor C3 and transient voltage suppressor diode TVS3.

[0072] The first end of capacitor C3 is connected to the first pole of the acquisition cable, and the second end of capacitor C3 is connected to the second pole of the acquisition cable. The first end of transient voltage suppressor diode TVS3 is connected to the first pole of the acquisition cable, and the second end of transient voltage suppressor diode TVS3 is connected to the second pole of the acquisition cable.

[0073] The third-stage sub-circuit includes a resistor R1, a Zener diode D3, a Zener diode D4, and a capacitor C4.

[0074] Resistor R1 is connected in series with the first pole of the data acquisition cable. The first end of resistor R1 is connected to the adjustment circuit. The second end of resistor R1 is connected to the first end of Zener diode D4, the second end of Zener diode D3, and the first end of capacitor C4. The second end of Zener diode D4 is connected to the second end of capacitor C4, the second pole of the data acquisition cable, and ground. The first end of Zener diode D3 is connected to power supply VCC.

[0075] In some embodiments, the flight control device includes a control module;

[0076] The control module is connected to the external device via a shielded wire;

[0077] providing a magnetic ring at the connection between the shielding wire and the external device;

[0078] A driving protection circuit is provided at the connection between the shielding wire and the control module.

[0079] In some embodiments, the driving protection circuit includes a resistor and a MOS tube;

[0080] The first end of the resistor is connected to the output end of the control module;

[0081] The second end of the resistor is connected to the gate of the MOS tube;

[0082] The source of the MOS tube is grounded; the drain of the MOS tube is connected to the driving motor of the external device.

[0083] 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.

[0084] A voltage regulator diode D1 is connected in parallel with the gate-source of MOS transistor Q1 to limit the gate voltage to below the regulator's regulated voltage value, protecting the MOS transistor from breakdown. A resistor R3 is connected in parallel with the gate-source of the MOS transistor to release gate charge and prevent charge accumulation. A Zener diode D2 clamps the gate, and an RC snubber circuit C1 and R1 are connected in series to suppress the drain voltage spikes generated by sudden changes in the device's switching current.

[0085] For example, Figure 4 This is a 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 transistor Q1, a Zener diode D1, a Zener diode D2, a voltage regulator diode D3 and a capacitor C1.

[0086] The output end of the control module is connected to the first end of the resistor R2 and the first end of the voltage-stabilizing diode D3; the second end of the resistor R2 is connected to the second end of the voltage-stabilizing diode D3, the first end of the resistor R3, the first end of the Zener diode D1, and the gate of the MOS transistor Q1; the drain of the MOS transistor 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 transistor Q1, the second end of the capacitor C1, and the second end of the Zener diode D2 are all grounded.

[0087] 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.

[0088] Specifically, a resistor in parallel with a capacitor is used on the control module power supply line to achieve resistance-capacitance grounding, so that the grounding of the same power supply system is grounded at a single point. The capacitor is a high-voltage capacitor of 100nF / 3kV, and the resistance is usually 1M.

[0089] 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 power line of the control module, and the second end is grounded.

[0090] 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.

[0091] In some embodiments, the secondary power 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.

[0092] Specifically, Figure 6 This is a schematic diagram of the structure of the power supply grounding method provided by the present invention. Figure 6As shown, the negative terminals of the primary power supplies (ACDC power supplies) are combined and connected through the power controller or distributor's electrical connector to the grounding stake on the equipment mounting plate, which is the pod's structural ground (main grounding stake). The grounding stake should be located near the power controller or distributor to keep the grounding lead as short as possible. The primary power supply line and return line must be arranged in pairs; structural wires are not permitted to serve as return lines.

[0093] 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 are grounded at a single point and connected to the structural ground of the pod together with the primary power return line.

[0094] 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.

[0095] Specifically, in the DC input protection circuit, an SPD device is used between the DC+ and DC- inputs. Typically, a varistor (SPD1) provides differential-mode protection. Meanwhile, a discharge tube (GDT1) connects to the DC- common-mode circuit for high-power discharge. Common-mode protection for the positive terminal is achieved through both the varistor (SPD1) and the gas discharge tube (GDT1). A polymer positive temperature coefficient (PPTC) thermistor serves as a decoupling device between the two protection stages, ensuring that the bidirectional TVS diode (TVS1) in the subsequent stage only begins voltage limiting after the upstream stage has dissipated most of the energy.

[0096] For example, Figure 7 This is a schematic 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 sub-circuit, a second-level sub-circuit, and a third-level sub-circuit. The first-level sub-circuit, the second-level sub-circuit, and the third-level sub-circuit are connected in series.

[0097] The first-stage subcircuit includes a varistor SPD1 and a discharge tube GDT1. The first end of the varistor SPD1 is connected to the DC+ terminal of the DC input power supply, and the second end of the varistor SPD1 is connected to the DC- terminal of the DC input power supply. The first end of the discharge tube GDT1 is connected to the DC- terminal of the DC input power supply, and the second end of the discharge tube GDT1 is grounded. The second-stage subcircuit includes a polymer positive temperature coefficient thermistor (PPTC). The polymer positive temperature coefficient thermistor (PPTC) is connected in series with the DC+ cable of the DC input power supply. The third-stage subcircuit includes a bidirectional transient voltage suppressor (TVS1). The first end of the bidirectional transient voltage suppressor (TVS1) is connected to the DC+ terminal of the DC input power supply, and the second end of the bidirectional transient voltage suppressor (TVS1) is connected to the DC- terminal of the DC input power supply.

[0098] 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.

[0099] Specifically, in the AC input protection circuit, the main protection is for single-phase AC input power. The common mode of the AC input phase line adopts varistors SPD2, SPD3 and high-voltage capacitors C1 and 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 and C5 are used in the subsequent stage to improve electromagnetic interference.

[0100] For example, Figure 8 This is a schematic diagram of the structure of the AC input protection circuit provided by the present invention. Figure 8 As shown, the AC input protection circuit includes a first-level sub-circuit, a second-level sub-circuit, and a third-level sub-circuit. The first-level sub-circuit, the second-level sub-circuit, and the third-level sub-circuit are connected in series.

[0101] The first-stage subcircuit includes varistor SPD1, varistor SPD2, varistor SPD3, capacitor C1, and capacitor C2. The first end of varistor SPD1 is connected to the L-terminal of the AC input power supply, and the second end of varistor SPD1 is connected to the N-terminal of the AC input power supply. The first end of capacitor C1 is connected to the second end of varistor SPD3, and the first end of varistor SPD3 is connected to the N-terminal of the AC input power supply. The second end of capacitor C2 is connected to the first end of varistor SPD2, and the second end of varistor SPD2 is connected to the L-terminal of the AC input power supply. The second end of capacitor C1 and the first end of capacitor C2 are both grounded. The second-stage subcircuit includes common-mode inductor CML1. The first coil of common-mode inductor CML1 is connected in series to the L-terminal cable of the AC input power supply; the second coil of common-mode inductor CML1 is connected in series to the N-terminal cable of the AC input power supply. The third-stage subcircuit includes capacitors C3, C4, and 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.

[0102] In some embodiments, 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.

[0103] Specifically, high-power power cables and signal cables are laid separately inside the pod. Shielded cables are used for the inverter input and output cables, with the shield connected to the pod's ground point. All cables are routed close to the pod wall.

[0104] 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 control cabin and each device in the control cabin, equipotential bonding of the equipment chassis, pod shielding and wiring in the pod, so as to achieve the reduction of external electromagnetic fields 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 front-stage high-power discharge, intermediate-stage decoupling and rear-stage fast discharge and suppression. 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 to achieve protection of switching devices.

[0105] Within the pod area, flight control equipment and power supply and distribution equipment are installed in separate pods. The pods are enclosed in aluminum shells to minimize the impact of external electromagnetic radiation on the cabling and equipment within. A grounding copper mesh is used between the pod shells to achieve equipotential bonding, and each equipment chassis is fully electrically bonded to the pod rack. High-power power cables and signal cables are routed separately within the pod. Shielded cables are used for inverter input and output cables, with the shield connected to the pod ground point. All cables are routed close to the pod walls.

[0106] Within the power distribution pod, the primary power return line is single-point grounded at the spherical (or boat-mounted) distributor or power controller input. This single-point grounding point is connected to the pod structure's main grounding stake via a grounding conductor. Secondary power return lines, including the distributor's isolated DC / DC output lines, are single-point grounded to the pod structure's main grounding stake.

[0107] 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-capacitance method.

[0108] Within the enclosure, the power supply and distribution equipment chassis should be a fully enclosed metal structure, with honeycomb structures used for heat dissipation in the enclosure wall ventilation holes. Sockets should be electrically bonded to the enclosure wall via conductive gaskets or direct contact with the enclosure. A three-level protection circuit is implemented at the power supply connections, including the step-down (Buck) input, AC / DC power supply input, fan power input, and inverter input. This circuitry includes primary discharge, decoupling, and secondary discharge circuits to mitigate surges. In addition to the power supply equipment, the control chassis also features a fully enclosed metal structure. Within the control chassis, all control circuits connected to the capsule device, including fan control and valve control, require protection circuits. For MOS switches in the valve drive circuits, a voltage regulator diode and resistor are used at the drive input to prevent overvoltage between the gate and source, slowing the MOS transistor's conduction speed and dissipating gate charge. An RC snubber circuit is used between the drain and source to absorb voltage spikes during MOS switching. An RC snubber circuit is also used for mechanical relay contacts, and a freewheeling diode is used for coil drive circuit protection. For the sensor signal input interface on the ball (boat), isolation and filtering are adopted for signal processing and a voltage regulator circuit is used to achieve voltage clamping.

[0109] The aerostat system provided by the present invention is designed from an overall perspective, and the aerostat system is divided into multiple areas. Different areas adopt targeted protection measures, thereby avoiding electromagnetic interference in all directions and improving the reliability of the aerostat system.

[0110] It should also be noted that the terms "target," "first," and "second," etc., in the embodiments of this application are used to distinguish similar objects, and are not used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, so that the embodiments of this application can be implemented in an order other than that illustrated or described herein. Furthermore, the objects distinguished by "first" and "second" are generally of the same type, and do not limit the number of objects. For example, the first object can be one or more.

[0111] In the embodiments of this application, the term "and / or" describes the association relationship between associated objects, indicating that three relationships can exist. For example, A and / or B can represent three situations: A exists alone, A and B exist simultaneously, and B exists alone. The character " / " generally indicates that the associated objects are in an "or" relationship.

[0112] In the embodiments of the present application, "determine B based on A" means that the factor A must be considered when determining B. It is not limited to "B can be determined based on A alone", and 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. 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 example, "when A meets the second condition, determine B", etc.; for 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 in 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.

[0113] In the embodiments of the present application, the term "plurality" refers to two or more than two, and other quantifiers are similar.

[0114] 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 various embodiments of the present invention.

Claims

1. An aerostat system, characterized in that: include: capsule, a first pod, a 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 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 enclosed 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 flight control equipment 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, wherein: 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, wherein: 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, wherein: The flight control device includes a signal acquisition module; The signal acquisition module is connected to the external device via a shielded wire; providing a magnetic ring 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 composed 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, wherein: The flight control device includes a control module; The control module is connected to the external device via a shielded wire; providing a magnetic ring 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, wherein: 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, wherein: A resistor and a capacitor are connected in parallel on the power supply loop of the control module to achieve resistance-capacitance grounding.

9. The aerostat system according to claim 1, wherein: 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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