CN114238198A

CN114238198A - Remote sensing data processing and solid state power control system combined with aerospace application

Info

Publication number: CN114238198A
Application number: CN202111484858.6A
Authority: CN
Inventors: 刘朝杰; 曹爱华; 张艺凡
Original assignee: Beijing Remote Sensing Space Technology Co ltd
Current assignee: Beijing Remote Sensing Space Technology Co ltd
Priority date: 2021-12-07
Filing date: 2021-12-07
Publication date: 2022-03-25

Abstract

The invention provides a remote sensing data processing and solid state power control system for aerospace applications, which comprises a processing module (204), a Remote Data Concentrator (RDC) module (202) in communication with the processing module, wherein the RDC module (202) receives analog or discrete input loaded with sensor information and converts the analog or discrete input into an operational protocol. A remote sensing data processing and solid state power control system incorporating aerospace applications also includes a solid state power controller SSPC (208) in communication with the RDC and the processing module, the SSPC (208) receiving load sensor information from the RDC module and controlling at least one loading mechanism based on the load sensor information.

Description

Remote sensing data processing and solid state power control system combined with aerospace application

Technical Field

The invention belongs to the field of remote sensing, and particularly relates to a remote sensing data processing and solid-state power control system combined with aerospace application.

Background

Conventional aviation power distribution systems may include sensory inputs, communication inputs, processing, control logic, and power control switching. These power distribution systems are typically customized to support the power distribution needs of the communication, logic, and target aircraft. Conventional aircraft also include individual communications and sensor integration and processing, including protocol conversion functionality in the form of a remote data concentrator. Conventional systems have historically not integrated the system functions of power distribution into one unit with a remote data concentrator. In contrast, the inclusion of sensory input, control logic and power control switching systems as separate systems not only increases the weight of the aircraft, but also increases the complexity of routine maintenance of the aircraft.

Disclosure of Invention

In order to overcome the defects of the traditional system, the invention provides a remote sensing data processing and solid-state power control system combined with aerospace application.

The invention is realized by the following embodiments:

according to one embodiment of the present invention, a system that combines standalone space sensing with Solid State Power Controllers (SSPCs). The standalone space sensing and attached solid state power controller includes a processing module and a Remote Data Concentrator (RDC) in combination with the processing module and is configured to receive analog or discrete input including loaded sensor information, and convert the analog or discrete input to an operational protocol via the processing module. The stand-alone space sensing and solid state power controller may further comprise a solid state power controller in communication with the RDC and the processing module, configured to receive load sensor information from the RDC module and control at least one loading mechanism based on the load sensor information.

In accordance with another embodiment of the present invention, a method performed by a microcontroller of a standalone space sensing and Solid State Power Controller (SSPC) is provided. The method includes converting analog or discrete input to network communication with a Remote Data Concentrator (RDC) module by implementing an RDC module, the analog or discrete input having load sensor information received from at least one load sensor, converting the analog or discrete input to a protocol operated by a processing module, and controlling at least one load mechanism based on the load sensor with a solid state power controller.

Drawings

FIG. 1 is a diagram of a remote data concentrator and power distribution system used in conventional aerospace applications;

FIG. 2 is a block diagram of a combined remote data concentrator and power distribution SSPC, according to one embodiment;

FIG. 3 is a flow diagram of a method for controlling an aerospace remote sensing data processing and solid state power controller, according to one embodiment;

FIG. 4 is a block diagram of a computer system for practicing the embodiments described herein, according to one embodiment.

Detailed Description

Fig. 1 depicts a remote data concentrator and power distribution system 100 for use in conventional aerospace applications. Conventional system 100 includes one or more Remote Data Concentrators (RDCs), shown in FIG. 1 as RDC104 and RDC 106. Legacy system 100 also includes one or more communication buses, namely 108 and 110, operatively connected to RDC104 and RDC 106. The system 100 may also include a plurality of general purpose computing modules 112, secondary

distribution master modules

114 and 116, and a plurality of Solid State Power Controllers (SSPCs) 118 and 120. Each of the sub-modules described above is shown in fig. 1. Are independent custom design modules that are required by the communication bus. Accordingly, conventional aircraft solid state control systems may be maintenance challenging, particularly in remote maintenance facilities, as different systems and hardware must be included and supported.

As shown in FIG. 1, a conventional aerospace remote sensing and SSPC system includes separate RDCs and power distribution systems, such as RDC104 and RDC 106. The conventional system 100 includes a plurality of individual modules that are generally configured to interconnect and work together to support flight operations of the various systems. RDC104 and RDC106 are separate subsystems specifically configured to receive input 102. The inputs 102 include inputs from sensors, external communications, etc., and are incorporated onto the aircraft backbone communication bus.

Modern aircraft, while only two

communication buses

108 and 110 are shown, each communication bus includes a plurality of different RDCs. Each wire performs a specific task to support flight operations. The general purpose computing module 112 may be one or more single board computers used to carry aircraft software. A common general purpose computing module 112 may communicate with the

communication buses

108 and 110 to send and receive control information to secondary

distribution master modules

114 and 116.

Secondary distribution masters

114 and 116 are typically separate subsystems configured at one or

more SSPCs

118 and 120. The SSPCs 118 and 120 are connected to a plurality of loading machines 122, such as pumps, relays, heaters, and the like. Modern aircraft control systems may include any number of controller subsystems, so only 118 and 120 SSPCs are required.

The SSPC power distribution functions include sensory input, logic control, and power switch control. The individual sub-modules described in fig. 1 contribute to a greater weight load of the aircraft.

The conventional aerospace communications, sensing, control, and solid state power distribution system shown in fig. 1 includes various subsystems, each existing as a distinct unit or control system cabinet. The various solid state power control systems act as stand alone custom systems, resulting in increased weight loading of the aircraft and complexity of the aircraft design. Accordingly, it would be advantageous to provide an aerospace remote sensing and SSPC that unifies the components in the system 100 into one unit.

Figure 2 combines a remote data concentrator and a power distribution SSPC, according to one embodiment. As shown, the system 200 may include a Remote Data Concentrator (RDC)202 and a processing module 204 in communication therewith and configured to receive analog or discrete inputs containing loaded sensor information. According to one embodiment, RDC202 may be connected to one or more communication buses. For example, a primary communication bus, a secondary communication bus, a tertiary communication bus, etc., may be included. The system 200 further includes one or more SSPC output channels 214 for controlling various aspects of flight operations, such as a loading mechanism 218. According to one embodiment, the primary communication bus may be a CAN bus.

According to one embodiment, RDC202 may receive discrete inputs from sensors 211 and convert the analog or discrete inputs into a protocol operable by a processing module. RDC202 may connect a plurality of redundant internal communication buses 206 to one or more SSPCs 208. SSPC208 may receive load sensor information from the RDC module and control at least one loading mechanism 218 based on the load sensor information. The SSPC208 may receive power from a power input 216, which may also supply power to the RDC202 and the processing module 204.

According to one embodiment, RDC202 may include a plurality of input channels 212 that provide data transfer to RDC202 and processing modules 204. The system 200 includes a plurality of communication buses 206 for connecting to aircraft communication systems.

FIG. 3 is a flow diagram of a method 300 for controlling an aerospace remote sensing data processing and solid state power controller (system 200), according to one embodiment. As shown, the system 200 may be configured to receive analog or discrete inputs and convert the inputs via the processing module 204, as shown at 302. The analog or discrete input 210 may include loaded sensor information received from at least one sensor 211, as shown at 304. System 200 may convert analog or discrete inputs into a protocol operable with RDC202 communication processing modules. The processing module 204 may control one or more loading mechanisms based on the loading sensor information, as shown at 306. According to an embodiment, the system 200 may be configured on a single unit. Such as a single card. Or multiple cards within a single unit combining the RDC202, the processing module 204, and one or more SSPCs 208.

According to one embodiment, several performance advantages may be realized by combining sensory processing, logic processing, data integration, and control functions into one card or unit. As with all aerospace applications, weight is critical. By combining these three functions into one system, many system controllers and their redundancies are combined to reduce the net weight. In addition, various systems that unify into a single card or unit can be more easily routinely maintained and replaced. The system 200 may use a common communication network and processor to perform logic, control, and communication integration functions. As a single system, the power input 216 and the compression package (e.g., a control system cabinet, not shown) may be shared.

FIG. 4 is a block diagram of a computer system 400 (hereinafter "computer 400") for practicing the embodiments described herein. The methods described herein may be implemented in hardware, software, or a combination of hardware and software. In one embodiment, the methods described herein are implemented in hardware and are part of a microprocessor suitable for use with a digital computer or general purpose computer. And are used as a single computing card or unit in an aerospace control system. Or distributed across multiple cards in the system (such as the aerospace remote sensing and SSPC208 shown in figure 2). Computer 400 may thus be used as part of system 200 to represent a general purpose computer or aircraft computing system configuration.

In one embodiment, as far as the hardware architecture is concerned, fig. 4 is concerned. The computer 400 includes a processor 401. The computer 400 also includes a memory 402 to which the processor 401 may be coupled, and one or more input/output adapters 403 that may be communicatively coupled via a system bus 405. The memory 402 may be connected to one or more internal or external memory devices. Communications adapter 404 may connect computer 400 to one or more networks 415. The processor 401 is a hardware device for executing hardware instructions or software, in particular software stored in a non-transitory computer readable memory (e.g., memory 402). The processor 401 may be any custom made or commercially available processor, a Central Processing Unit (CPU), multiple CPUs, such as CPUs a-c, other auxiliary processors associated with the computer 400, a semiconductor-based microprocessor (in the form of a microchip or chip set), or generally any device for executing instructions. Processor 401 includes a memory cache 406 that may include, but is not limited to, an instruction cache to accelerate executable instruction fetching, a data cache to accelerate data fetching and storing, and a translation look-up buffer (TLB) to accelerate virtual-to-physical address translation of two execution files into instructions and data. Cache 406 may be organized as a hierarchy of more cache levels (L1, L2, etc.).

The memory 402 includes Random Access Memory (RAM)407 and Read Only Memory (ROM) 408. The RAM407 can be any one or combination of volatile memory elements (e.g., DRAM, SRAM, SDRAM, etc.). ROM408 may include any one or more non-volatile memories, such as erasable programmable read-only memory (EPROM), flash memory, electrically erasable programmable read-only memory (EEPROM), and the like. Also, the memory 402 may comprise an electronic, magnetic, optical, or other type of memory device. The memory 402 may also have a distributed architecture, where various components are remote from each other, but may be accessible to the processor 401.

The instructions in memory 402 may comprise one or more separate programs, each of which constitutes an ordered listing of computer-executable instructions for implementing logical functions. In fig. 4, the instructions in memory 402 may include an operating system 411. The operating system 411 may control the execution of other computer programs and provide scheduling, input-output control, file and data management, memory management, communication control, and related services.

The input/output adapter 403 may be, but is not limited to, one or more public lines or other wired or wireless connections. The input/output adapter 403 may have additional elements. Such as controllers, buffers (caches), drivers, repeaters, and receivers, to enable communications. In addition, the local interface includes address, control, or data connections to enable communication between the aforementioned components. The interface adapter 412 may be configured to connect one or more input/output devices to the computer 400. Input/output devices connectable to interface adapter 412 also include devices that communicate both input and output simultaneously. In an embodiment, the computer 400 may also include a communications adapter 404 for connecting to an aircraft or maintenance network 415.

The network 415 is for communication between the computer 400 and any external devices. The network 415 transmits and receives data between the computer 400 and devices or systems external to the computer 400. The network 415 may be an aircraft internal network, such as an avionics network or the like. The network 415 may be implemented wirelessly. For example, wireless protocols and technologies, such as WIFI, etc., are used. The network 415 may also be a wired network. Such as an ethernet network, ARINC429 network, CAN, etc. The network 415 may also be a packet switched network, such as a local area network. The network 415 may be a fixed wireless network, a wireless Local Area Network (LAN), a wireless Personal Area Network (PAN), a Virtual Private Network (VPN), or other suitable network system.

The computer program product of the present invention includes computer-readable program instructions with a computer-readable storage medium to cause a processor to perform various aspects of the present invention.

The above description of the embodiments is only intended to facilitate the understanding of the method of the invention and its core idea. Meanwhile, for a person skilled in the art, according to the idea of the present invention, the specific embodiments and the application range may be changed. In view of the above, the present disclosure should not be construed as limiting the invention.

Claims

1. A remote sensing data processing and solid state power control system for use in connection with aerospace applications, comprising a processing module, a remote data concentrator, RDC, in communication with the processing module and configured to receive analog or discrete inputs containing load sensor information and to convert the analog or discrete inputs into a protocol for operation by the processing module, a solid state power controller, SSPC, in communication with the RDC, the SSPC being operable to receive the load sensor information from the RDC module and to control at least one loading mechanism based on the load sensor information.

2. A remote sensing data processing and solid state power control system in combination with aerospace applications according to claim 1, wherein there is provided a computer implemented method for controlling an aerospace remote sensing data processing and solid state power controller, SSPC:

receiving, by a processor implementing a Remote Data Concentrator (RDC) module, an analog or discrete input having load sensor information received from at least one load sensor; converting the analog or discrete input to a protocol for communication by the processing module with the RDC module; and controlling at least one loading mechanism with the SSPC based on the loading sensor information.

3. A remote sensing data processing and solid state power control system in combination with aerospace applications according to claim 1, wherein the remote data concentrator RDC, processing module and SSPC may be combined into a single unit.

4. The remote data concentrator RDC and SSPC of claim 3, wherein the RDC module receives a plurality of communication signals over at least one communication bus and includes an analog or discrete input, a C primary communication bus, a secondary communication bus, and a tertiary communication bus.

5. The remote data concentrator RDC and SSPC as claimed in claim 3, wherein the SSPC is configurable as one or more SSPC modules.