Multifunctional airborne integrated controller

Abstract

The invention belongs to the technical field of airplane control system design, and particularly relates to a multifunctional airborne comprehensive controller which has the functions of comprehensive hanging object control management, electromechanical control driving, external lighting control and anti-skid brake control. The comprehensive controller comprises a central processing module, a hanging object putting control module, a power supply module, a lighting control module, an electromechanical control module, an anti-skid brake control module and a case welding part; wherein the case welding assembly has a radio frequency signal processing function; the central processing module is the core of the multifunctional airborne comprehensive controller and is used for controlling the working logic of the whole multifunctional airborne comprehensive controller; the hanging object putting control module is used for controlling and managing hanging objects; the power supply module is mainly used for supplying power to each module in the multifunctional airborne integrated controller; the illumination control module is used for illumination and state indication; the electromechanical control module is used for outputting related electromechanical control signals; and the anti-skid brake control module is used for realizing output control of brake related signals.

Description

Technical Field

[0001] This invention belongs to the field of aircraft control system design technology, specifically relating to an airborne integrated controller with functions of suspended object control and management, electromechanical control and drive, external lighting control and anti-skid braking control. Background Technology

[0002] Currently, most airborne systems supporting domestic trainer aircraft platforms adopt a distributed system architecture. Suspension control and management, electromechanical control and drive, external lighting control, and anti-skid braking control functions are all implemented by corresponding independent field replaceable units (LRUs). Each unit has similar processing modules, power modules, and chassis welded components, requiring cabling between the unit and the airborne integrated processor and execution equipment. This hinders weight reduction of the aircraft platform and results in low equipment integration. Summary of the Invention

[0003] Objective: To improve the equipment integration of current airborne systems on trainer aircraft platforms, reduce the number of onboard cables, lighten the weight of the aircraft platform, and lower hardware system costs, this invention proposes a multi-functional airborne integrated controller that integrates external attachments control and management, electromechanical control and drive, external lighting control, and anti-skid braking control functions. It provides electromechanical drive control signals and external lighting control signals, and features normal braking control, anti-skid function, and stop braking function. It monitors and reports the status information of aircraft-mounted attachments, enables the launch / release control of various types of attachments, and has the function of outputting emergency attachment release signals. This invention proposes a multi-functional airborne integrated controller.

[0004] Technical Solution: This invention designs a multi-functional airborne integrated controller, which has integrated suspended object control and management, electromechanical control and drive, external lighting control and anti-skid braking control functions. The integrated controller includes a central processing module, a suspended object deployment control module, a power supply module, a lighting control module, an electromechanical control module, an anti-skid braking control module, and a chassis welding component; wherein the chassis welding component has radio frequency signal processing function. The central processing module is the core of the multi-functional airborne integrated controller, used to control the working logic of the entire multi-functional airborne integrated controller; the suspended object deployment control module is used for the control and management of suspended objects; the power supply module is mainly used to supply power to the various modules inside the multi-functional airborne integrated controller; the lighting control module is used for lighting and status indication; the electromechanical control module is used to realize the output of electromechanical control related signals; and the anti-skid brake control module is used to realize the output control of brake related signals.

[0005] Furthermore, the central processing module communicates with the airborne integrated processor via two HB6096 buses for mission data exchange; it manages and controls all suspended objects via one dual-redundant GJB289A bus; it receives discrete signals from the cockpit, landing gear, and attachment point interlocks, processes them through logic and software, and outputs power supply and deployment permission commands for each attachment point; it also outputs a selection control signal to the suspended object deployment control module to realize power supply and deployment control of the suspended objects; it outputs discrete control signals to realize radio frequency signal gain adjustment; and it retrieves the power supply control output and emergency deployment status of the suspended objects.

[0006] Furthermore, the suspended object deployment control module is used to complete the control and management of the selection and deployment of suspended objects at 6 attachment points and the emergency complete disposal; the suspended object deployment control module realizes the selection and deployment of suspended objects by receiving the selection control signal from the central processing module and DC power supply; by receiving the emergency complete disposal signal from the cabin and emergency power supply, and through the delay processing of the internal hardware interlock and delay control unit, the orderly emergency complete disposal of suspended objects at 6 attachment points is realized.

[0007] Furthermore, the lighting control module communicates with the airborne integrated processor via one RS-422 line to enable the illumination of fuselage formation lights, vertical tail formation lights, navigation formation lights, tail lights, collision avoidance lights, landing taxi lights, landing gear indicator lights, brightness adjustment, and switching between friendly / concealed modes.

[0008] Furthermore, the electromechanical control module communicates with the airborne integrated processor via one RS-422 interface to exchange electromechanical control task data; it also communicates with the external remote interface device via one RS-422 interface to collect electromechanical status data; and it outputs power control, electromechanical control, and atmospheric sensor power supply related signals.

[0009] Furthermore, the anti-skid brake control module communicates with the external remote interface device via one RS-422 interface to exchange brake control task data, output anti-skid brake control related signals, and collect wheel speed.

[0010] Furthermore, the radio frequency signal processing function of the chassis welding component is specifically as follows: the satellite navigation signal processing circuit is laid out on the motherboard, the satellite navigation signal uses a power divider to realize the forwarding and power distribution of one satellite navigation signal to the six hardpoints on the left and right wings, and the signal gain is adjusted by receiving the gain control command sent by the central processing module.

[0011] Furthermore, the power module processes the input 28VDC voltage of the carrier through an internal spike suppression circuit, surge suppression circuit, filter circuit, and power-off retention circuit, and converts it into the 5VDC and 28VDC power supply voltages required by each module through a DC-DC conversion circuit.

[0012] Furthermore, of the two HB6096 buses, one is the main channel and the other is the backup channel, which is used to ensure the reliability of data interaction with the airborne integrated processor.

[0013] Furthermore, the chassis welding components are also used to provide physical protection for each module, ensure electromagnetic shielding effect and heat dissipation performance, and guarantee the stability and reliability of equipment operation.

[0014] Technical Effects: This invention integrates suspended object control and management, electromechanical control and drive, external lighting control, and anti-skid braking control functions, reducing the need for multiple independent devices. It significantly reduces the number and weight of long-distance cables between the airborne controller interface and the airborne integrated processor interface, as well as the task execution module interface, lowering hardware costs and reducing the load on the carrier platform. Parallel processing capabilities enable collaborative operation of real-time and non-real-time tasks, improving the control system's response speed and efficiency. Adhering to standards as a system design principle, the interfaces for the launch vehicle and mission suspended objects are rigorously designed, improving the versatility of the launch device and suspended object control and management. The integration of multiple safety mechanisms, including overload protection, short-circuit protection, and over / under voltage protection, extends equipment lifespan and improves mission reliability and safety. Attached Figure Description

[0015] Figure 1 This is a principle block diagram of the present invention; Figure 2 This is a schematic diagram of a product structure according to the present invention; Among them, 1-Central processing module, 2-Suspended object deployment control module, 3-Power supply module, 4-Lighting control module, 5-Electromechanical control module, 6-Anti-skid brake control module, 7-Chassis welding components, and 8-Multi-functional airborne integrated controller. Detailed Implementation

[0016] To more clearly illustrate the technical solutions of the embodiments of the present invention, the present invention will be described in detail below with reference to the accompanying drawings or specific implementation examples. It should be noted that some (but not all) of the disclosed examples are shown in the drawings. In fact, many different examples can be described, and these examples should not be construed as limited to the examples set forth herein. Rather, these examples are described to better demonstrate the positive effects of the present invention, and all aspects not detailed herein are considered to be well-known or conventional techniques in the art.

[0017] See Figure 1 As shown, the present invention specifically includes a multi-functional airborne integrated controller, comprising a central processing module 1, a suspended object deployment control module 2, a power supply module 3, a lighting control module 4, an electromechanical control module 5, an anti-skid brake control module 6, and a chassis welding component 7. The chassis welding component 7 has radio frequency signal processing capabilities.

[0018] The central processing module 1 is the core of the multi-functional airborne integrated controller, used to control the working logic of the entire multi-functional airborne integrated controller. It communicates with the airborne integrated processor via two HB 6096 buses for task data exchange, one as the primary channel and the other as a backup channel; it manages and controls all suspended objects via one dual-redundant GJB 289A bus; it receives discrete signals from the cockpit, landing gear, and hardpoint interlocks through its internal discrete quantity interface unit, processes these signals through logic and software, outputs power supply and deployment permission commands for each hardpoint, and outputs selective deployment control signals to the suspended object deployment control module to achieve selective deployment control; it outputs discrete quantity control signals to achieve radio frequency signal gain adjustment; and it tracks the power supply control output and emergency deployment / abandonment status of the suspended objects.

[0019] The suspended object deployment control module 2 is mainly used to control and manage the selection and deployment of suspended objects at six attachment points and the emergency complete disposal. It selects and deploys suspended objects by receiving the selection control signal and DC power supply from the central processing module; and it receives the emergency complete disposal signal and emergency power supply from the cabin, and through the delay processing of the internal hardware interlock and delay control unit, it achieves the orderly emergency complete disposal of suspended objects at the six attachment points.

[0020] The power module 3 is mainly used to supply power to the various modules inside the multi-functional airborne integrated controller. It processes the spikes, surges, filtering, and power-off retention circuits internally, and then converts the 28VDC of the carrier aircraft into the 5VDC and 28VDC power required by each module through a DC-DC conversion circuit.

[0021] The lighting control module 4 communicates with the airborne integrated processor via one RS-422 line, receives lighting control commands issued by the aircraft, and realizes the illumination of fuselage formation lights, vertical tail formation lights, navigation formation lights, tail lights, collision avoidance lights, landing taxi lights, landing gear indicator lights, brightness adjustment, and friendly / concealed mode switching.

[0022] The electromechanical control module 5 is used to output electromechanical control related signals: it communicates with the airborne integrated processor through one RS-422 to exchange electromechanical control task data; it communicates with the external remote interface device through one RS-422 to collect electromechanical status; and it outputs power control, electromechanical control and atmospheric sensor power supply related signals.

[0023] The anti-skid brake control module 6 is used to realize the output control of brake-related signals. It communicates with the external remote interface device through one RS-422 to perform brake control task data exchange, output anti-skid brake control related signals, and collect wheel speed.

[0024] The aforementioned chassis welding component 7 has radio frequency signal processing function: the satellite navigation signal processing circuit is laid out on the motherboard, and the satellite navigation signal uses a power divider to realize the forwarding and power distribution of one satellite navigation signal to the left and right wing 6 hardpoints. The signal gain is adjusted by receiving the gain control command sent by the central processing module.

[0025] For the product composition and internal installation location of this invention, please refer to [link / reference]. Figure 2 As shown, the chassis welding component 7 is mainly used to provide physical protection, ensure electromagnetic shielding and heat dissipation performance, and at the same time ensure the stability and reliability of the equipment.

[0026] This invention integrates functions such as suspended object control and management, electromechanical control and drive, external lighting control, and anti-skid braking control. It provides electromechanical drive control signals and external lighting control signals, and has normal braking control, anti-skid, and stop braking functions. It monitors and reports the status information of the suspended objects mounted on the aircraft, realizes the launch / deployment control of various types of suspended objects mounted on the aircraft, and has the function of outputting emergency dropping signals for suspended objects.

[0027] The above specific embodiments or examples are only used to explain the technical solutions of the present invention and are not intended to limit the present application. Parts not described in detail are considered to be conventional technical means or common knowledge in the field. It can be understood by those skilled in the art that, based on the design concept of the present application, the technical solutions described in the foregoing embodiments can be adapted or some or all of the technical features can be equivalently replaced. These modifications, equivalent replacements, and adaptive improvements do not depart from the technical essence of the present invention and should all be covered within the protection scope of the present application.

Claims

1. A multi-functional airborne integrated controller, characterized in that, It has integrated functions of suspended object control and management, electromechanical control and drive, external lighting control and anti-skid brake control. The integrated controller includes a central processing module, a suspended object deployment control module, a power supply module, a lighting control module, an electromechanical control module, an anti-skid brake control module, and chassis welding components. The chassis welding components have radio frequency signal processing capabilities; the central processing module is the core of the multi-functional airborne integrated controller, used to control the working logic of the entire multi-functional airborne integrated controller; the suspended object deployment control module is used for the control and management of suspended objects; the power supply module is mainly used to supply power to the various modules inside the multi-functional airborne integrated controller; the lighting control module is used for lighting and status indication; the electromechanical control module is used to realize the output of electromechanical control related signals; and the anti-skid brake control module is used to realize the output control of brake-related signals.

2. The multi-functional airborne integrated controller according to claim 1, characterized in that, The central processing module communicates with the airborne integrated processor via two HB6096 buses for mission data exchange; it manages and controls all suspended objects via one dual-redundant GJB289A bus; it receives discrete signals from the cockpit, landing gear, and attachment point interlocks, processes them through logic and software, and outputs power supply and deployment permission commands for each attachment point; it also outputs a selection control signal to the suspended object deployment control module to realize power supply and deployment control of the suspended objects; it outputs discrete control signals to realize radio frequency signal gain adjustment; and it retrieves the power supply control output and emergency deployment status of the suspended objects.

3. The multi-functional airborne integrated controller according to claim 1, characterized in that, The suspended object deployment control module is used to complete the control and management of the selection and deployment of suspended objects at 6 attachment points and the emergency complete disposal. The suspended object deployment control module realizes the selection and deployment of suspended objects by receiving the selection control signal from the central processing module and DC power supply. By receiving the emergency complete disposal signal from the cockpit and emergency power supply, and through the delay processing of the internal hardware interlock and delay control unit, the orderly emergency complete disposal of suspended objects at 6 attachment points is realized.

4. The multi-functional airborne integrated controller according to claim 1, characterized in that, The lighting control module communicates with the airborne integrated processor via one RS-422 line to enable the illumination of fuselage formation lights, vertical tail formation lights, navigation formation lights, tail lights, collision avoidance lights, landing taxi lights, landing gear indicator lights, brightness adjustment, and switching between friendly / concealed modes.

5. The multi-functional airborne integrated controller according to claim 1, characterized in that, The electromechanical control module communicates with the airborne integrated processor via one RS-422 interface to exchange electromechanical control task data; it also communicates with the external remote interface device via one RS-422 interface to collect electromechanical status data; and it outputs power control, electromechanical control, and atmospheric sensor power supply related signals.

6. The multi-functional airborne integrated controller according to claim 1, characterized in that, The anti-skid brake control module communicates with the external remote interface device via one RS-422 interface to exchange brake control task data, output anti-skid brake control related signals, and collect wheel speed.

7. The multi-functional airborne integrated controller according to claim 1, characterized in that, The radio frequency signal processing function of the chassis welding component is as follows: the satellite navigation signal processing circuit is laid out on the motherboard, and the satellite navigation signal is implemented by a power divider to forward and distribute the power of one satellite navigation signal to the six hardpoints on the left and right wings. The signal gain is adjusted by receiving the gain control command sent by the central processing module.

8. The multi-functional airborne integrated controller according to claim 1, characterized in that, The power module processes the input 28VDC voltage from the carrier through internal spike suppression circuit, surge suppression circuit, filter circuit, and power failure retention circuit, and then converts it into the 5VDC and 28VDC power supply voltages required by each module through a DC-DC conversion circuit.

9. The multi-functional airborne integrated controller according to claim 2, characterized in that, Of the two HB6096 buses, one is the primary channel and the other is the backup channel, used to ensure the reliability of data interaction with the airborne integrated processor.

10. The multi-functional airborne integrated controller according to claim 1 or 7, characterized in that, The chassis welding components are also used to provide physical protection for each module, ensure electromagnetic shielding and heat dissipation performance, and guarantee the stability and reliability of equipment operation.

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