Ground system suitable for 360-degree rotary multi-cabin aircraft structure

Abstract

The invention discloses a structure ground system suitable for a 360-degree rotary multi-cabin aircraft. The structure ground system comprises a fixed end structure ground module, a structure ground transmission module and a rotary end structure ground module, wherein the fixed end structure ground module is connected with the structure ground transmission module; and the structural ground transmission module is connected with the rotating end structural ground module. The equipotential requirement of the structural ground system among the rotary multi-cabin sections is effectively met, the safety of the structural ground system after the high-voltage power supply equipment breaks down is guaranteed, the problems of electrostatic accumulation and electrostatic discharge of new equipment installed in orbit are solved, and the structural ground system of the space rotary multi-cabin section aircraft is guaranteed to be stable, safe and effective for a long time.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft structure construction, and in particular to a system suitable for a 360-degree rotating multi-cabin aircraft structure. Background Art

[0002] With the development of aerospace technology and the increasing demand for deep space exploration missions, higher requirements are placed on the safety of rotating multi-cabin aircraft. It is necessary to ensure the normal operation of the entire cabin power supply system in the event of a power supply failure in the equipment, to ensure that the structural ground between the rotating multi-cabins prevents space electrostatic discharge due to potential differences, to ensure the safety of the connection between the newly installed equipment in orbit and the cabin structure, and to ensure the normal operation of the aircraft power supply system through the structural ground system in all aspects.

[0003] In the existing aircraft structural systems, there is no structural technical method that can meet the structural system safety requirements of rotating multi-cabin spacecraft to ensure the normal operation of the power supply system. The negative effect brought about by this is that the structural system cannot be effectively constructed between the rotating cabins, resulting in structural mismatch between the cabins, static electricity accumulation without a release circuit to produce static electricity discharge, causing confusion in the signal of the power supply system, and ultimately damaging the equipment. Summary of the invention

[0004] The technical problem solved by the present invention is: to overcome the shortcomings of the prior art, to provide a structural ground system suitable for a 360° rotating multi-compartment aircraft, to effectively solve the equipotential requirements of the structural ground system between the rotating multi-compartments, to ensure the safety of the structural ground system after failure of the high-voltage power supply equipment and the problems of static electricity accumulation and static electricity discharge when installing new equipment in orbit, and to ensure the long-term stability, safety and effectiveness of the structural ground system of a space rotating multi-compartment aircraft.

[0005] The object of the present invention is achieved through the following technical scheme: a system suitable for a 360° rotating multi-chamber aircraft structure, comprising: a fixed end structural module, a structural transmission module and a rotating end structural module; wherein the fixed end structural module is connected to the structural transmission module; the structural transmission module is connected to the rotating end structural module.

[0006] In the above-mentioned system applicable to a 360° rotating multi-compartment aircraft structure, the fixed-end structural module includes a first power receiving device, a lithium-ion battery and a first structural confluence module; wherein the structural confluence module is connected to the first power receiving device; and the lithium-ion battery is connected to the first structural transmission module.

[0007] In the above-mentioned system applicable to a 360° rotating multi-cabin aircraft structure, the first power receiving device includes an in-cabin drive controller, a bus filter, a charge and discharge regulator and a power manager; wherein the first structure's busbar module is respectively connected to the in-cabin drive controller, the bus filter, the charge and discharge regulator, the power manager and the lithium-ion battery.

[0008] In the above-mentioned system applicable to the 360° rotating multi-compartment aircraft structure, the structural transmission module includes an electrical transmission component and an insulating layer; wherein the electrical transmission component is arranged in the insulating layer; the first structural confluence module is connected to the electrical transmission component; and the electrical transmission component is connected to the module of the rotating end structure.

[0009] In the above-mentioned system applicable to a 360° rotating multi-compartment aircraft structure, the electrical transmission component includes an empty ring, a first grounding ring and a second grounding ring; wherein the first structural ground confluence module is respectively connected to one end of the first grounding ring and one end of the second grounding ring; the other end of the first grounding ring and the other end of the second grounding ring are both connected to the module of the rotating end structure; the empty ring is connected to the module of the rotating end structure.

[0010] In the above-mentioned system applicable to the 360° rotating multi-compartment aircraft structure, the module of the rotating end structure includes a shunt regulator, a second structure merging module, a power receiving device, a driving mechanism, a solar wing and an on-orbit installation device; wherein the driving mechanism is connected to the solar wing; the shunt regulator is connected to the empty ring; the shunt regulator is connected to the driving mechanism; the second structure merging module is respectively connected to the other end of the first grounding ring and the other end of the second grounding ring; the second structure merging module is respectively connected to the shunt regulator, the driving mechanism, the power receiving device and the on-orbit installation device.

[0011] In the above-mentioned system applicable to a 360° rotating multi-cabin aircraft structure, the power receiving equipment includes an integrated drive controller, a thermistor converter, an extravehicular drive controller and an extravehicular temperature controller; wherein the integrated drive controller, the thermistor converter, the extravehicular drive controller and the extravehicular temperature controller are all connected to the second structure's confluence module.

[0012] In the above-mentioned system applicable to a 360° rotating multi-compartment aircraft structure, the on-orbit installation device includes an extended shunt regulator and an extension and retraction controller; wherein the extended shunt regulator and the extension and retraction controller are both connected to the confluence module of the second structure.

[0013] In the above-mentioned system applicable to the 360° rotating multi-cabin aircraft structure, the structural transmission module also includes an outboard flange drive assembly switching assembly; wherein the second structural confluence module is connected to the outboard flange drive assembly switching assembly.

[0014] In the above-mentioned system applicable to the 360° rotating multi-cabin aircraft structure, the structural transmission module also includes a cabin flange main load-bearing frame drive assembly switching assembly; wherein the second structural confluence module is connected to the cabin flange main load-bearing frame drive assembly switching assembly.

[0015] Compared with the prior art, the present invention has the following beneficial effects:

[0016] (1) The present invention realizes the connection between the rotating end structural module and the fixed end structural module through the structural transmission module. The rotating end structural module and the fixed end structural module are innovatively arranged at both ends of the 360° transmission channel as the common point for connecting the equipment in the two compartment space areas, and finally realizes that the equipment in each compartment can still realize effective structural connection when the aircraft is rotated 360°;

[0017] (2) The present invention realizes on-track maintainable operations through the connection of the transmission channel of the device electrical connector, and innovatively utilizes the performance of the electrical connector to disconnect the transmission path of the structure when the device electrical connector is disconnected, and connect the transmission path of the device structure when the electrical connector is plugged in. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference symbols are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0019] Figure 1 It is a structural block diagram of a system applicable to a 360° rotating multi-cabin aircraft structure provided by an embodiment of the present invention. DETAILED DESCRIPTION

[0020] Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments set forth herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to be able to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that, in the absence of conflict, the embodiments of the present invention and the features described in the embodiments can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0021] Figure 1 1 is a structural block diagram of a system applicable to a 360° rotating multi-cabin aircraft structure provided by an embodiment of the present invention. Figure 1 As shown, the system suitable for a 360° rotating multi-chamber aircraft structure includes: a fixed-end structural module, a structural transmission module and a rotating-end structural module; wherein the fixed-end structural module is connected to the structural transmission module; and the structural transmission module is connected to the rotating-end structural module.

[0022] The fixed-end structural module includes a first power receiving device, a lithium-ion storage battery and a first structural ground confluence module; wherein the structural ground confluence module is connected to the first power receiving device; and the lithium-ion storage battery is connected to the first structural ground transmission module.

[0023] The first power receiving device includes an in-cabin drive controller, a bus filter, a charge and discharge regulator and a power manager; wherein the first structure ground bus module is respectively connected to the in-cabin drive controller, the bus filter, the charge and discharge regulator, the power manager and the lithium-ion battery.

[0024] The structural ground transmission module includes an electric transmission component and an insulating layer; wherein the electric transmission component is arranged in the insulating layer; the first structural ground confluence module is connected to the electric transmission component; and the electric transmission component is connected to the rotating end structural ground module.

[0025] The electrical transmission component includes an empty ring, a first grounding ring and a second grounding ring; wherein the first structural ground confluence module is respectively connected to one end of the first grounding ring and one end of the second grounding ring; the other end of the first grounding ring and the other end of the second grounding ring are both connected to the rotating end structural ground module; the empty ring is connected to the rotating end structural ground module.

[0026] The rotating end structure ground module includes a shunt regulator, a second structure ground confluence module, a power receiving device, a driving mechanism, a solar wing and an on-track installation device; wherein the driving mechanism is connected to the solar wing; the shunt regulator is connected to the empty ring; the shunt regulator is connected to the driving mechanism; the second structure ground confluence module is respectively connected to the other end of the first grounding ring and the other end of the second grounding ring; the second structure ground confluence module is respectively connected to the shunt regulator, the driving mechanism, the power receiving device and the on-track installation device.

[0027] The powered equipment includes an integrated drive controller, a thermistor converter, an outboard drive controller and an outboard temperature controller; wherein the integrated drive controller, the thermistor converter, the outboard drive controller and the outboard temperature controller are all connected to the second structural ground confluence module.

[0028] The on-track installation device includes an extended shunt regulator and an extension and retraction controller; wherein the extended shunt regulator and the extension and retraction controller are both connected to the second structure ground confluence module.

[0029] The structural ground transmission module also includes an outboard flange drive assembly switching assembly; wherein the second structural ground confluence module is connected to the outboard flange drive assembly switching assembly.

[0030] The structural ground transmission module also includes a switching component of the driving component of the main load-bearing frame of the flange in the cabin; wherein the second structural ground confluence module is connected to the switching component of the driving component of the main load-bearing frame of the flange in the cabin.

[0031] The fixed end structural ground module is composed of overlapping electronic equipment, high resistance grounding equipment and the first structural ground confluence module;

[0032] Inside the system, powered devices such as "in-cabin drive controller", "bus filter", "charge and discharge regulator" and "power manager" are used as connecting electronic devices for equipment connection design.

[0033] "Lithium-ion battery" is a power supply device. The grounding terminal of the lithium-ion battery shell is designed with high-resistance grounding to prevent the power supply from leaking and still ensure the safety of the system through the high-resistance grounding path.

[0034] The "structural ground confluence module" is a fixed-end electronic device. The structural ground confluence module provides the overall confluence function of the structure, realizes a unified structural ground at the fixed end, and is finally connected to the structural ground confluence module at the rotating end through the transmission module.

[0035] The structural ground transmission module consists of a transmission slip ring and a transmission path. The structural ground transmission module is divided into a rotating end transmission path and a fixed end transmission path through the transmission slip ring. The transmission slip ring can realize the effective connection of the transmission paths when the transmission paths rotate 360°. The transmission slip ring adopts a high-resistance grounding design as a whole to prevent the power supply from leaking and still ensure the safety of the system through the high-resistance grounding path.

[0036] The rotating end structure ground module is composed of bonding electronic equipment, high-resistance grounding equipment and the second structure ground confluence module. The "integrated drive controller", "too sensitive converter", "outboard drive controller" and "outboard temperature controller" are used as power receiving equipment in the system, and are used as bonding electronic equipment for equipment bonding design.

[0037] The extended shunt regulator and the expansion and retraction controller are on-orbit installation equipment. As overlapping electronic equipment, they adopt the equipment overlapping design. In order to realize the maintainable operation on-orbit, the equipment structure is connected through the equipment electrical connector transmission channel, which is different from the direct equipment casing overlapping method at the fixed end.

[0038] The solar wing is a power supply device that requires a high-resistance grounding design, and the "shunt regulator" is a power transmission device that also uses a high-resistance grounding design. Both prevent the power supply from having a leakage fault and ensure the safety of the system through the high-resistance grounding path.

[0039] The second structural confluence module provides an overall structural confluence function for the rotating end electronic equipment, realizes a unified structural confluence at the rotating end, and is finally connected to the structural confluence module at the fixed end through the transmission module.

[0040] Aircraft power receiving equipment: Since the product draws power from the busbar, when the equipment power supply fails, the equipment fault can be isolated by disconnecting the power switch. Therefore, a direct bonding installation method is adopted in the grounding system.

[0041] Aircraft power supply equipment: According to product characteristics, power supply equipment is the power supply of aircraft. When the equipment fails, the equipment cannot be disconnected from the power supply path. Therefore, such equipment is installed in an insulated manner and grounded with high resistance in the grounding system. When the equipment fails, a small current can be released through the high resistance grounding path to protect the power supply system from working normally. Such as batteries and solar wings.

[0042] Aircraft on-orbit installation equipment: According to the characteristics of on-orbit installation of products, it is necessary to consider the establishment of a static electricity accumulation discharge circuit after the equipment is installed. Therefore, such equipment is directly overlapped and installed in the grounding system, and a structural ground is set inside the equipment and then connected to the cabin structure ground through wires. Such as extended shunt regulators and extended expansion and retraction controllers.

[0043] Aircraft power transmission equipment: According to the product characteristics, it needs to meet the requirements of 360° rotation and power transmission. The power transmission equipment is a single point link in the power supply path. When the equipment fails, the equipment cannot be disconnected from the power supply path. Therefore, such equipment is installed in an insulated manner and grounded with high resistance in the grounding system. When the equipment fails, a small current can be released through the high-resistance grounding path to protect the power supply system from working normally. Such as drive mechanism and solar orientation device.

[0044] This embodiment constructs a comprehensive safety structural ground system through technical measures such as overlapping, high-resistance grounding, and slip ring grounding.

[0045] The rotating multiple compartments of the aircraft are the working compartment, truss compartment and solar wing;

[0046] The rotating mechanism of the aircraft cabin wall includes a solar orientation device and a driving mechanism, wherein the solar orientation device connects the working cabin and the truss cabin, and the driving mechanism connects the truss cabin and the solar wing.

[0047] The equipment in the aircraft working compartment includes drive controller, bus filter, power manager, charge and discharge regulator, and battery;

[0048] The aircraft truss cabin equipment includes shunt regulator, integrated controller, deployment controller, outboard drive controller, outboard temperature controller, extended shunt regulator, and extended deployment controller;

[0049] The aircraft working cabin equipment drive controller, bus filter, power manager, and charge and discharge regulator are all powered devices, and are directly connected to the cabin structure for installation and overlap.

[0050] The battery of the aircraft working cabin equipment is the power supply equipment. It is insulated from the cabin and installed with high resistance connection measures. A 50KΩ high resistance is set inside the battery to connect to the grounding pile inside the equipment, and then led out to the working cabin structure ground through the connector.

[0051] The sun-directing device is directly overlapped with the installation surfaces of the truss cabin and the working cabin.

[0052] Grounding piles are set for the cabin flange, main load-bearing frame, and driving locking assembly and switching locking assembly installed on the cabin flange of the sun orientation device, and then the wires are led out to connect with the structural ground in the working cabin.

[0053] Grounding piles are arranged on the outer flange of the solar orientation device and the driving locking assembly and the switching locking assembly installed on the flange for collection, and then the wires are led out to be connected with the truss cabin structure.

[0054] The electric transmission component of the solar orientation device is the main power transmission equipment, and the shell is insulated from the main structure of the solar orientation device. A grounding stake is set on the shell of the electric transmission component, and an 80KΩ resistor is connected in series, and then connected to the grounding stake of the flange outside the solar orientation device cabin for collection.

[0055] The aircraft truss cabin is equipped with a structural ground in quadrants II and IV for grounding of each product. The structural grounds in quadrants II and IV are connected through truss cables, and then connected to the two grounding slip rings of the solar orientation device by the truss structural ground, and then connected to the cabin structure ground in the working cabin through the slip rings. The connection between the truss structural ground and the cabin structure ground in the working cabin is realized.

[0056] The thermal control multi-layer structure coated outside the aircraft truss cabin is connected to the structures of the truss quadrants II and IV through cables.

[0057] The aircraft truss cabin equipment shunt regulator, integrated controller, extension and retraction controller, extravehicular drive controller, and extravehicular temperature controller are all powered devices. The internal structure of the equipment is used to lead out two structural ground contacts through connectors, and they are respectively connected to the structural ground set in quadrants II and IV of the truss cabin through truss cables.

[0058] The driving mechanism is a power transmission device, which is insulated from the truss cabin and directly overlapped with the solar wing mounting surface.

[0059] The solar wing is a power supply device, with a high resistance of 80KΩ connected in series on its shell structure, and connected to the two grounding rings in the drive mechanism through connectors. The grounding ring of the drive mechanism is connected to the structural ground of the truss cabin through the truss cable.

[0060] The empty ring of the driving mechanism and the empty ring of the sun-directing device are connected to the 100KΩ high resistance set inside the shunt regulator through a connector, the high resistance is connected to the shunt regulator structure, and then led out to the truss structure through the connector.

[0061] The extended shunt regulator and extended expansion and retraction controller are products to be installed on-orbit later. The equipment is a power-receiving device, so a grounding pile is set inside the equipment, and two structural ground contacts are led out through connectors. After the installation on-orbit and the cabin is completed, the equipment structural ground is connected to the truss cabin structural ground through cables.

[0062] The extended solar wing is a power supply device, with a high resistance of 80KΩ connected in series on its shell. After being installed on the track, it is connected to the structural ground of the extended shunt regulator through a cable. The structural ground of the extended shunt is connected to the structural ground of the equipment with the structural ground of the truss cabin through a connector to lead out a cable.

[0063] This embodiment realizes the connection between the rotating end structural ground module and the fixed end structural ground module through the structural ground transmission module. The rotating end structural ground and the fixed end structural ground are innovatively set at both ends of the 360° transmission channel as the common point of the connection ground of the equipment in the two compartment space areas, and finally realizes that the equipment in each compartment can still realize effective structural connection when the aircraft is rotated 360°; this embodiment realizes on-orbit maintainable operation through the equipment electrical connector transmission channel connection, and innovatively utilizes the performance of the electrical connector to realize that the structural ground transmission path is disconnected when the equipment is disconnected from the electrical connector, and the structural ground transmission path of the equipment is connected when the electrical connector is plugged in.

[0064] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A system suitable for a 360° rotating multi-cabin aircraft structure, characterized in that include: The fixed end structure module, the structure transmission module and the rotating end structure module; wherein, The fixed end structural ground module is connected to the structural ground transmission module; The structural transmission module is connected to the rotating end structural module.

2. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 1, characterized in that: The module of the fixed end structure includes a first power receiving device, a lithium ion battery and a first structure bus module; wherein, The structural ground confluence module is connected to the first powered device; The lithium-ion battery is connected to the first structural transmission module.

3. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 2, characterized in that: The first power receiving device includes an in-cabin drive controller, a bus filter, a charge and discharge regulator, and a power manager; wherein, The first structured bus module is respectively connected to the in-cabin drive controller, the bus filter, the charge and discharge regulator, the power manager and the lithium-ion battery.

4. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 2, characterized in that: The structural transmission module includes an electrical transmission component and an insulating layer; wherein, The electrical transmission component is disposed in the insulating layer; The first structure ground confluence module is connected to the electrical transmission component; The electric transmission assembly is connected to a module of the rotating end structure.

5. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 4, characterized in that: The electric transmission assembly comprises an empty ring, a first grounding ring and a second grounding ring; wherein, The first structural ground confluence module is respectively connected to one end of the first grounding ring and one end of the second grounding ring; The other end of the first grounding ring and the other end of the second grounding ring are both connected to the module of the rotating end structure; The empty ring is connected to the module of the rotating end structure.

6. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 5, characterized in that: The module of the rotating end structure includes a shunt regulator, a second structure converging module, a power receiving device, a driving mechanism, a solar wing and an on-orbit installation device; wherein, The driving mechanism is connected to the solar wing; The shunt regulator is connected to the empty ring; The shunt regulator is connected to the driving mechanism; The second structure ground confluence module is respectively connected to the other end of the first grounding ring and the other end of the second grounding ring; The second structure of the current converging module is respectively connected to the shunt regulator, the driving mechanism, the power receiving device and the on-track installation device.

7. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 6, characterized in that: The power receiving equipment includes an integrated drive controller, a thermosensitive converter, an off-board drive controller and an off-board temperature controller; wherein, The integrated drive controller, the thermosensitive converter, the off-board drive controller and the off-board temperature controller are all connected to the second structural ground confluence module.

8. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 6, characterized in that: The on-track installation device includes an extended shunt regulator and an extension and retraction controller; wherein the extended shunt regulator and the extension and retraction controller are both connected to the second structure ground confluence module.

9. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 4, characterized in that: The structural ground transmission module also includes an outboard flange drive assembly switching assembly; wherein the second structural ground confluence module is connected to the outboard flange drive assembly switching assembly.

10. The system applicable to a 360° rotating multi-cabin aircraft structure according to claim 4, characterized in that: The structural ground transmission module also includes a cabin flange main load-bearing frame drive assembly switching assembly; wherein the second structural ground confluence module is connected to the cabin flange main load-bearing frame drive assembly switching assembly.

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