CN214450599U - Aircraft fuelling vehicle - Google Patents

Abstract

The present disclosure relates to an aircraft fuelling vehicle comprising a cab (1), a top-loading device comprising a plurality of actuators (2), a control device and an indicator light assembly (7), the indicator light assembly (7) comprising: a plurality of interlock indicator lamps (71) which are arranged outside the cab (1), correspond to the plurality of actuators (2) and are used for lighting when the actuators (2) act to send out interlock signals; an interlock total indicator lamp (72) which is provided in the cab (1), is electrically connected to the control device, and is turned on when the interlock indicator lamp (71) is turned on; the override interlock indicator lamp (73) is arranged in the cab (1), is electrically connected with the control device, and is used for turning on the plurality of interlock indicator lamps (71) when the actuating mechanism (2) is reset and the override interlock function is manually and forcibly turned on; and a power takeoff indicator lamp (74) disposed in the cab (1) and electrically connected to the control device for lighting when the engine powers the actuator (2).

Description

Aircraft fuelling vehicle

Technical Field

The utility model relates to an aircraft refueling equipment technical field, in particular to aircraft tank service truck.

Background

The aircraft fuelling vehicle is a special equipment, including driver's cabin and top-mounted equipment, and the top-mounted equipment includes several actuating mechanisms, and in order to make operating personnel know the working state of actuating mechanism, the interior of driver's cabin is equipped with indicator lamp.

When the actuating mechanism acts, an interlocking signal related to the action is sent to a controller in a cab, and the working state of the indicator light is controlled through the controller, so that an operator can observe and know the working condition of the actuating mechanism. However, whether the aircraft fuelling vehicle is performing a fuelling operation or any other action, the operator is required to enter the cab to be able to see the operation by viewing the indicator light.

SUMMERY OF THE UTILITY MODEL

The utility model provides an aircraft tank service truck can make operating personnel know the operating condition of facial make-up equipment more nimble conveniently.

The aircraft tank service truck that this disclosure provided includes driver's cabin, facial make-up equipment, controlling means and pilot lamp subassembly, and facial make-up equipment includes a plurality of actuating mechanism, and the pilot lamp subassembly includes:

the interlocking indicator lamps are arranged outside the cab, are in one-to-one correspondence with the actuating mechanisms and are configured to be lightened when the corresponding actuating mechanisms act to send out interlocking signals;

an interlock total indicator lamp disposed in the cab and electrically connected to the control device, configured to be lit upon occurrence of the lit interlock indicator lamp;

the override interlock indicator lamp is arranged in the cab, is electrically connected with the control device, is configured to be lightened when the plurality of executing mechanisms are reset and the plurality of interlock indicator lamps are still lightened, and is lightened after the override interlock function is manually and forcibly turned on; and

and the power takeoff indicator lamp is arranged in the cab, is electrically connected with the control device and is configured to be lightened when an engine of the aircraft refueling truck provides power for the plurality of actuating mechanisms.

In some embodiments, the control device is configured to deactivate the aircraft refueler when the override interlock indicator is illuminated and to deactivate the aircraft refueler when the power take-off indicator is illuminated.

In some embodiments, the control device comprises: a plurality of switching amplifiers, respective input ends of which are connected with the plurality of actuators in a one-to-one correspondence, respective output ends of which are connected with the control device, the switching amplifiers being configured to amplify the corresponding interlock signals and transmit the same to the control device;

the plurality of interlock indicator lamps are connected with the output ends of the plurality of switching amplifiers in a one-to-one correspondence manner, or the plurality of interlock indicator lamps are all connected with the control device.

In some embodiments, an interlock summary indicator light, an override interlock indicator light, and a power takeoff indicator light are provided at the interior roof of the cab.

In some embodiments, the control device comprises:

an internal controller provided in the cab; and

and the external controller is arranged outside the cab, is connected with the internal controller through a lead, is configured to receive the interlocking signals sent out when the plurality of actuating mechanisms act, and transmits the interlocking signals to the internal controller.

In some embodiments, the vehicle body further comprises a chassis frame and an explosion-proof box, wherein the explosion-proof box is installed on the chassis frame, the external controller is arranged in the explosion-proof box, a plurality of holes are formed in the side wall of the explosion-proof box, and the plurality of interlocking indicator lamps are exposed out of the plurality of holes in a one-to-one correspondence mode.

In some embodiments, the anti-explosion tank further comprises a mounting bracket fixed on a chassis frame of the aircraft fuelling vehicle, and the anti-explosion tank is detachably suspended on the mounting bracket.

In some embodiments, each actuator is provided with a detection component configured to detect an operating state of the actuator;

the external controller is connected with the plurality of detection components through leads, is configured to receive detection signals of the plurality of detection components and send the detection signals to the internal controller, is connected with the plurality of execution mechanisms through leads, and is configured to receive control signals of the internal controller and drive the plurality of execution mechanisms to work.

In some embodiments, the external controller comprises:

a first sub-controller connected to some of the plurality of actuators and the plurality of detection parts through a wire; and

the second sub-controller is connected with the rest parts of the plurality of actuating mechanisms and the plurality of detection components through leads;

wherein the interlock signal is received by at least one of the first sub-controller and the second sub-controller.

In some embodiments, the wires between the internal controller and the external controller include a first wire and a second wire;

the first sub-controller is connected with the internal controller through a first lead, the second sub-controller is connected with the first sub-controller through a second lead, or the second sub-controller is connected with the part of the first lead, which is located outside the cab, through the second lead.

In some embodiments, the wires between the internal controller and the external controller employ a CAN bus.

In some embodiments, the extended path of the wire between the internal controller and the external controller is configured to bypass the engine of the aircraft fuelling vehicle.

The aircraft refueling truck of the embodiment of the disclosure has the advantages that the operating state of the refueling truck can be observed by operators both outside and inside the cab, the observation is flexible and convenient, and when any one executing mechanism is abnormal in the working process, the aircraft refueling truck is easy to position and can stop working in time. Moreover, due to the special environment and the operation object of aviation fuel supply, the vehicle needs to be controlled to be static by the operation state signal in the whole vehicle operation process, safety accidents caused by abnormal vehicle movement in operation are prevented, and the safety of the operation of the airplane refueling truck can be improved by accurately knowing the operation state of the loading equipment.

Drawings

In order to more clearly illustrate the embodiments of the present disclosure or the technical solutions in the prior art, the drawings needed to be used in the description of the embodiments or the prior art will be briefly introduced below, it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and for those skilled in the art, other drawings can be obtained according to the drawings without inventive exercise.

FIG. 1 is a schematic illustration of the installation location of an indicator light assembly and an external control in some embodiments of an aircraft fuelling vehicle of the present disclosure.

FIG. 2 is a schematic structural view of some embodiments of the aircraft fuelling vehicle of the present disclosure in which the indicator light assembly and external controls are located in an explosion proof enclosure.

FIG. 3 is a schematic diagram of the arrangement and connection of indicator light assemblies in some embodiments of the aircraft fuelling vehicle of the present disclosure.

Fig. 4 is a schematic structural diagram of some embodiments of the layout and routing of control devices in an aircraft fuelling vehicle according to the present disclosure.

Fig. 5 is a schematic structural diagram of other embodiments of the layout and routing of the control device in the aircraft fuelling vehicle of the present disclosure.

Fig. 6 is a schematic structural diagram of further embodiments of the layout and routing of control devices in an aircraft fuelling vehicle according to the present disclosure.

Description of reference numerals:

1. a cab;

2. an actuator;

3. a detection section;

4. an internal controller;

5. an external controller; 51. a first sub-controller; 52. a second sub-controller;

6. a wire; 61. a first conductive line; 62. a second conductive line;

7. an indicator light assembly; 71. an interlock indicator light; 72. an interlock general indicator light; 73. an override interlock indicator light; 74. a power takeoff indicating lamp; s, interlocking signals;

8. a switching amplifier;

9. a chassis frame;

10. an explosion-proof box; 101. mounting a lug; 102. a first mounting hole;

11. mounting a bracket; 111. installing edges; 112. and a second mounting hole.

Detailed Description

The technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure, and it is obvious that the described embodiments are only a part of the embodiments of the present disclosure, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the disclosure, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments disclosed herein without any inventive step, are intended to be within the scope of the present disclosure.

Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate.

In the description of the present disclosure, it is to be understood that the orientation or positional relationship indicated by the directional terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal" and "top, bottom", etc., are generally based on the orientation or positional relationship shown in the drawings, and are presented only for the convenience of describing and simplifying the disclosure, and in the absence of a contrary indication, these directional terms are not intended to indicate and imply that the device or element being referred to must have a particular orientation or be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the disclosure; the terms "inner and outer" refer to the inner and outer relative to the profile of the respective component itself.

In the description of the present disclosure, it should be understood that the terms "first", "second", etc. are used to define the components, and are used only for convenience of distinguishing the corresponding components, and if not otherwise stated, the terms have no special meaning, and thus, should not be construed as limiting the scope of the present disclosure.

In addition, technical features involved in different embodiments of the present disclosure described below may be combined with each other as long as they do not conflict with each other.

An airplane refueling truck is an important ground special vehicle for realizing aviation fuel supply at an airport. As shown in fig. 1 to 3, in some embodiments, the aircraft refueling truck comprises a cab 1, a chassis frame 9, a top-mounted device, a control device and an indicator lamp assembly 7, wherein the cab 1 is arranged on the chassis frame 9, the top-mounted device comprises an oil pumping system, an oil tank assembly, a lifting mechanism and the like, and the top-mounted device comprises a plurality of actuating mechanisms 2 for realizing the operation of the top-mounted device.

As shown in fig. 3, the indicator lamp assembly 7 includes: a plurality of interlock indicator lights 71, interlock total indicator light 72, override interlock indicator light 73, and power take off indicator light 74. The indicator light may remain constantly on or flash when illuminated.

A plurality of interlock lamps 71, which are provided outside the cab 1, are provided in one-to-one correspondence with the plurality of actuators 2, and are configured to be lit when receiving an interlock signal S that is issued when the corresponding actuator 2 is operated. As shown in fig. 2, a plurality of interlock lamps 71 may be provided on the explosion-proof case 10, for example, a plurality of holes may be opened in the explosion-proof case 10 so that the interlock lamps 71 are exposed from the holes. To facilitate the operator's view, the explosion-proof case 10 may be provided on the chassis frame 9 near one side with the interlock indicator lamp 71 facing the vehicle side. The operator can observe the working state of the refueling truck without entering the cab.

Interlock total indicator lamp 72, which is provided in cab 1, for example, may be provided at the top of cab 1, and is electrically connected to the control device, is configured to be turned on when the turned-on interlock indicator lamp 71 appears, that is, as long as one actuator is not returned to its home position, interlock total indicator lamp 72 is turned on. The control device is configured to determine whether the interlock total indicator lamp 72 is lit based on the plurality of interlock signals S after receiving the interlock signal S. This arrangement facilitates the operator to quickly know whether or not the actuator 2 is not returned in the cab 1, and if there is an actuator 2 that is actuated, the vehicle is kept in a braking state.

The override interlock indicator lamp 73 is provided in the cab 1, for example, may be provided at the top of the cab 1, and is electrically connected to the control device, and is configured to be lit after the plurality of actuators 2 are all returned to their original positions but the plurality of interlock indicator lamps 71 are still lit, and to be lit after the override interlock function is manually forcibly turned on. After the override interlock function is manually forcibly turned on, the braking function of the vehicle is released to allow the vehicle to be driven to a service location.

A power take-off indicator lamp 74, provided in the cab 1, for example, may be provided at the top of the cab 1, and electrically connected to the control device, configured to light up when the engine of the aircraft fuelling vehicle powers the plurality of actuators 2. The power take-off indicator lamp 74 is illuminated to indicate that the engine is powering the actuators in the upper-mounted equipment and that it is desired to keep the vehicle braked.

According to the embodiment, the working states of the actuating mechanisms in the refueling truck can be observed by an operator both outside and inside the cab 1, the observation is flexible and convenient, and when any actuating mechanism is abnormal in the working process, the positioning is easy and the operation can be stopped in time. In addition, due to the special environment and the operation object of aviation fuel supply, the vehicle needs to be controlled to be static by the operation state signal in the whole vehicle operation process, safety accidents caused by abnormal vehicle movement in operation are prevented, and the safety of the operation of the airplane refueling truck is improved by accurately knowing the operation state of the loading equipment.

In some embodiments, the control device is configured to deactivate the aircraft refueler when the override interlock indicator lamp 73 is illuminated and to deactivate the aircraft refueler when the power take-off indicator lamp 74 is illuminated.

The embodiment can ensure that the vehicle is in a braking state when an actuating mechanism in the loading equipment is not returned or the engine provides power for the loading equipment, and improves the safety of the operation of the airplane refueling truck. When the plurality of actuators 2 are all returned to their original positions but the plurality of interlock lamps 71 are still on, the override interlock is manually forcibly turned on to release the brake of the aircraft refueling truck for maintenance.

In some embodiments, as shown in fig. 3, the control device further comprises: a plurality of switching amplifiers 8 configured to amplify the interlock signal S; the interlock signals S generated when the actuators 2 are operated are electrically connected to the control device through one switching amplifier 8, and the interlock indicator lamps 71 are connected to the switching amplifiers 8 in a one-to-one correspondence.

The embodiment can send the interlocking signal S when the actuating mechanism 2 acts, and amplify the interlocking signal S through the switching amplifier 8, so as to be more accurately acquired by the control device or enable the interlocking indicator lamp 71 to be lightened, and the condition of induction error of the interlocking signal S is prevented. The amplified interlock signal S is sent to the control device and the interlock indicator lamp 71 at the same time, i.e. the state of the interlock indicator lamp 71 is directly controlled by the switching amplifier 8. The control device may control the vehicle to be in a braking state after receiving the interlock signal S.

Alternatively, the interlock signals S sent by the plurality of actuators 2 during operation are all electrically connected to the external controller 5 through a switching amplifier 8, and the plurality of interlock indicator lamps 71 are all connected to the control device. This embodiment sends the amplified interlock signal S to the control device, which controls the state of the interlock indicator lamp 71.

In some embodiments, interlock total indicator light 72, override interlock indicator light 73, and power take off indicator light 74 are provided on the interior top of cab 1. The arrangement mode is convenient for operators to observe. Alternatively, these three indicator lights may be provided at other positions in cab 1.

In some embodiments, as shown in fig. 3, the control device includes: an internal controller 4 and an external controller 5. Wherein, interior controller 4 is established in driver's cabin 1, and external controller 5 is established outside driver's cabin 1, and interior controller 4 passes through wire 6 with external controller 5 and connects, and for example, wire 6 can include single or many wires, cables or bus etc.. The external controller 5 is configured to receive the interlock signal S issued when the plurality of actuators 2 are actuated, and transmit the interlock signal S to the internal controller 4 to control the braking state of the vehicle by the internal controller 4.

The aircraft fuelling vehicle provided by the embodiment of the disclosure is simultaneously provided with an internal controller 4 positioned in the cab 1 and an external controller 5 arranged outside the cab 1, wherein signal lines of a plurality of actuating mechanisms on the aircraft fuelling vehicle, which are used for sending the interlocking signal S, are all connected with the external controller 5 through a lead, and then the external controller 5 is connected with the internal controller 4 through a lead. Thus, the operating states of the actuators 2 can be transmitted to the internal controller 4 via the external controller 5, so that the internal controller 4 controls the state of the indicator lights in the cab 1 according to the operating states of the actuators and controls whether the aircraft fuelling vehicle needs to be in a braking state.

For example, when the internal controller 4 receives the interlock signal S, it is described that the actuator is not returned, the interlock light 72 needs to be turned on, and the aircraft fuelling vehicle needs to be kept in a braking state.

Because the number of the actuating mechanisms on the aircraft fuelling vehicle is large, the arrangement mode can reduce wiring harnesses led into the cab from the outside of the cab, the occupied space is small, a large wiring port does not need to be formed in the cab, the cab is sealed, the wiring harnesses become thin, wiring is flexible, layout is easy, the danger that more wires are exposed outside can be reduced, the working reliability of the control device is improved, and the operation safety of the aircraft fuelling vehicle is improved.

In some embodiments, as shown in fig. 1 and 2, the aircraft fuelling vehicle further comprises a chassis frame 9 and an explosion-proof tank 10, the explosion-proof tank 10 is mounted on a beam of the chassis frame 9, the external controller 5 is provided in the explosion-proof tank 10, a side wall of the explosion-proof tank 10 is provided with a plurality of holes, and a plurality of interlock indicator lamps 71 are exposed from the plurality of holes in a one-to-one correspondence.

The arrangement mode does not need to change the layout of the equipment on the aircraft fuelling vehicle, and can also prevent the work of the external controller 5 from being influenced by the operation of the equipment on the aircraft fuelling vehicle. In addition, in the process of replenishing fuel for the aircraft refueling truck, the fuel may leak, and the aircraft refueling truck may explode in a high-temperature environment, so that the electric connection parts of the plurality of interlock indicator lamps 71 and the external controller 5 are arranged in the explosion-proof box 10 for protection, thereby preventing explosion and improving the working reliability and safety.

Further, as shown in fig. 2, the explosion-proof box 10 is externally provided with a protective cover for preventing oil and water, so as to improve the reliability and safety of the operation of the external controller 5 and the plurality of interlock indicator lamps 71.

As shown in fig. 2, the aircraft fuelling vehicle further comprises a mounting bracket 11 mounted to the chassis frame 9 of the aircraft fuelling vehicle, the explosion proof tank 10 being removably mounted in suspended relation to the mounting bracket 11. Specifically, the mounting bracket 11 includes a bracket main body and a mounting edge 111, a second mounting hole 112 is provided on the mounting edge 111 to fix the mounting bracket 11 on the chassis frame 9 by a fastener, and the mounting edge 111 is vertically disposed. Mounting lugs 101 are arranged on two sides of the explosion-proof box 10, and first mounting holes 102 are formed in the mounting lugs 101 so that the explosion-proof box 10 can be mounted on the mounting bracket 11 in a hanging mode through fasteners.

This embodiment is through installing support 11 with explosion-proof box 10 detachable installation, easily dismantles, conveniently maintains external control ware 5.

In some embodiments, the extended path of the wire 6 between the internal controller 4 and the external controller 5 is configured to bypass the engine of the aircraft fuelling vehicle. If the cab 1 is installed at a position far from the external controller 5, the wiring distance between the internal controller 4 and the external controller 5 is long, and the extended path of the wire 6 is kept away from the heat source of the engine, thereby preventing the wire 6 from being damaged.

In some embodiments, as shown in fig. 4, each actuator 2 is provided with a detection member 3 configured to detect an operating state of the actuator 2. The external controller 5 is connected to the plurality of detection parts 3 through a wire 6, for example, a signal line, and configured to receive detection signals of the plurality of detection parts 3 and transmit the detection signals to the internal controller 4. And the external controller 5 is connected with the plurality of actuators 2 through a lead 6, and the external controller 5 is configured to receive control signals sent by the internal controller 4 to drive the plurality of actuators 2 to work.

According to the aircraft fuelling vehicle disclosed by the embodiment of the disclosure, a plurality of actuating mechanisms and a plurality of detection components on the aircraft fuelling vehicle are connected with the external controller 5 through the conducting wires, and then the external controller 5 is connected with the internal controller 4 through the conducting wires. Therefore, the detection signals obtained by the plurality of detection components 3 can be transmitted to the internal controller 4 through the external controller 5, so that the internal controller 4 adjusts the control signals according to the working states of the plurality of actuators or controls whether the aircraft fuelling vehicle runs or not; furthermore, the control signals of the internal controller 4 can also be transmitted to a plurality of actuators via the external controller 5 to control the operation of the actuators.

For example, when the internal controller 4 receives a signal that the actuator is in the operating state, the aircraft fuelling vehicle needs to be kept in the braking state, and due to the special environment and the operating object of aviation fuel supply, the vehicle needs to be kept in the braking state during the entire vehicle operation, so that safety accidents caused by abnormal vehicle movement during operation are prevented.

Because actuating mechanism and the detection part total number that corresponds are more, this kind of mode of setting can greatly reduce the pencil of leading into the driver's cabin from the driver's cabin outside, and occupation space is little to it is more nimble to make the line of walking, easily overall arrangement, and can reduce the danger that more wire exposes outside, thereby improves the reliability of controlling means work, further improves the security of aircraft tank service truck operation.

In some embodiments, as shown in fig. 5 and 6, the external controller 5 includes: a first sub-controller 51 and a second sub-controller 52. Wherein, the first sub-controller 51 is connected with a part of the plurality of actuators 2 and the plurality of detection components 3 through a lead 6, and the second sub-controller 52 is connected with the rest of the plurality of actuators 2 and the plurality of detection components 3 through a lead 6. Wherein the interlock signal S is received by at least one of the first sub-controller 51 and the second sub-controller 52.

Because the aircraft tank service truck needs a lot of functions to be executed, the number of the actuating mechanisms 2 and the detecting parts 3 is large, so that a lot of lead wires are caused, the external controller 5 is set into two split sub-controllers through the arrangement, the external layout wiring is convenient, and the wiring accuracy can be improved.

Alternatively, the first sub-controller 51 and the second sub-controller 52 may be provided side by side at the same position in the vehicle, or may be provided at different positions depending on the position of the actuator 2 and/or the detection member 3 connected thereto, in order to facilitate wiring.

Alternatively, when wired, the plurality of actuators 2 may each be connected to the first sub-controller 51 through the wire 6, and the plurality of detection parts 3 may each be connected to the second sub-controller 52 through the wire 6. Alternatively, some of the actuators 2 and their corresponding detection components 3 are connected to the first sub-controller 51 by the wires 6, and the rest of the actuators 2 and their corresponding detection components 3 are connected to the second sub-controller 52 by the wires 6. The signal line for issuing the interlock signal S can be connected to the first partial controller 51 and also to the second partial controller 52.

For embodiments in which the external controller 5 comprises a first sub-controller 51 and a second sub-controller 52, as in fig. 5 and 6, the conductor 6 between the internal controller 4 and the external controller 5 comprises a first conductor 61 and a second conductor 62.

As shown in fig. 5, the first subcontroller 51 is connected to the internal controller 4 via a first line 61, and the second subcontroller 52 is connected to the first subcontroller 51 via a second line 62. Thereby, the second sub-controller 52 sends the received detection signal and interlock signal S to the internal controller 4 through the first sub-controller 51, and the control signal sent from the internal controller 4 is sent to the second sub-controller 52 through the first sub-controller 51.

As shown in fig. 6, the second sub-controller 52 is connected to a portion of the first wire 6 located outside the cab 1 through the second wire 6. Therefore, the detection signals and the interlock signal S received by the first sub-controller 51 and the second sub-controller 52 are converged and then sent to the internal controller 4 through the first wire 61, and the control signals sent by the internal controller 4 are respectively sent to the first sub-controller 51 and the second sub-controller 52 according to the preset address allocation rule.

The wiring mode of this embodiment can further reduce the quantity of wiring between internal control ware 4 and the external control ware 5, makes to walk the line more nimble, easily overall arrangement, and can carry out reliable protection to the wire to improve the reliability of controlling means work, and then improve the security of aircraft tank service truck operation.

Alternatively, the first sub-controller 51 and the second sub-controller 52 may be connected to the internal controller 4 via separate lines 6.

In some embodiments, the conductor 6 between the internal controller 4 and the external controller 5 employs a CAN bus. Each CAN bus includes two CAN high and CAN low lines. For the embodiments of fig. 5 and 6, the connection between the internal controller 4 and the external controller 5 is only via one CAN bus.

The embodiment is connected through the CAN bus, is beneficial to reducing the number of conducting wires and transmitting multi-channel signals, and also has the advantages of strong real-time performance, long transmission distance, strong anti-electromagnetic interference capability, low cost and the like.

The explosion-proof case 10 in the above embodiment can achieve, in addition to the explosion-proof function, the dispersion of the wire harness to connect the lead wires at the inlet of the explosion-proof case 10 to the plurality of actuators 2, the plurality of detection members 3, and the signal wires transmitting the interlock signal S through the plurality of outlets.

In some embodiments, the Controller described above can be a general purpose Processor, a Programmable Logic Controller (PLC), a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA) or other Programmable Logic device, discrete Gate or transistor Logic, discrete hardware components, or any suitable combination thereof for performing the functions described in this disclosure.

The above description is only exemplary of the present disclosure and is not intended to limit the present disclosure, and any modification, equivalent replacement, or improvement made within the spirit and principle of the present disclosure should be included in the scope of the present disclosure.

Claims (12)

1. An aircraft fuelling vehicle comprising a cab (1), a top-loading apparatus comprising a plurality of actuators (2), a control device and an indicator light assembly (7), the indicator light assembly (7) comprising:

a plurality of interlock indicator lamps (71) which are arranged outside the cab (1), are arranged in one-to-one correspondence with the plurality of actuators (2), and are configured to be lighted when the corresponding actuators (2) act to send out interlock signals (S);

an interlock light (72) disposed within the cab (1) and electrically connected to the control device, configured to be illuminated upon the presence of the illuminated interlock light (71);

an override interlock indicator (73) provided in the cab (1), electrically connected to the control device, and configured to be lit when the plurality of actuators (2) are all returned but the plurality of interlock indicators (71) are still lit, and to be lit after the override interlock function is manually forcibly turned on; and

a power take-off indicator (74) disposed within the cab (1) and electrically connected to the control device, configured to light up when the plurality of actuators (2) are powered by the engine of the aircraft fuelling vehicle.

2. An aircraft fuelling vehicle according to claim 1, wherein the control device is configured to deactivate the aircraft fuelling vehicle when the override interlock indicator (73) is illuminated and to deactivate the aircraft fuelling vehicle when the power take-off indicator (74) is illuminated.

3. An aircraft fuelling vehicle according to claim 1, wherein the control device comprises: a plurality of switching amplifiers (8), respective input ends of which are connected with the plurality of actuators (2) in a one-to-one correspondence, respective output ends of which are connected with the control device, the switching amplifiers (8) being configured to amplify and send the corresponding interlock signals (S) to the control device;

the plurality of interlock indicator lamps (71) are connected with the output ends of the plurality of switching amplifiers (8) in a one-to-one correspondence manner, or the plurality of interlock indicator lamps (71) are all connected with the control device.

4. Aircraft fuelling vehicle according to claim 1, wherein said interlocking general indicator light (72), said override interlocking indicator light (73) and said power take-off indicator light (74) are provided at the inner top of said cabin (1).

5. An aircraft fuelling vehicle according to claim 1, wherein the control device comprises:

an internal controller (4) provided in the cab (1); and

and the external controller (5) is arranged outside the cab (1), is connected with the internal controller (4) through a lead (6), and is configured to receive the interlocking signal (S) sent out when the plurality of actuators (2) act and transmit the interlocking signal (S) to the internal controller (4).

6. The aircraft fuelling vehicle according to claim 5, further comprising a chassis frame (9) and an explosion-proof tank (10), wherein the explosion-proof tank (10) is mounted to the chassis frame (9), the external controller (5) is arranged in the explosion-proof tank (10), a plurality of holes are formed in a side wall of the explosion-proof tank (10), and the plurality of interlocking indicator lights (71) are exposed from the plurality of holes in a one-to-one correspondence manner.

7. An aircraft fuelling vehicle according to claim 6, further comprising a mounting bracket (11), said mounting bracket (11) being secured to a chassis frame (9) of the aircraft fuelling vehicle, said tank (10) being removably suspension mounted to said mounting bracket (11).

8. Aircraft fueller vehicle according to claim 5, characterized in that each actuator (2) is provided with a detection member (3) configured to detect the operating state of the actuator (2);

wherein, the external controller (5) is connected with the plurality of detection components (3) through a lead (6), is configured to receive detection signals of the plurality of detection components (3) and send the detection signals to the internal controller (4), and the external controller (5) is connected with the plurality of actuators (2) through a lead (6), and is configured to receive control signals of the internal controller (4) and drive the plurality of actuators (2) to work.

9. Aircraft fuelling vehicle according to claim 8, characterized in that said external controller (5) comprises:

a first sub-controller (51) connected to the plurality of actuators (2) and a part of the plurality of detection parts (3) by a lead (6); and

a second sub-controller (52) connected to the plurality of actuators (2) and the rest of the plurality of detection members (3) by a lead (6);

wherein the interlock signal (S) is received by at least one of the first sub-controller (51) and the second sub-controller (52).

10. Aircraft fueller vehicle according to claim 9, wherein the conductor (6) between the internal controller (4) and the external controller (5) comprises a first conductor (61) and a second conductor (62);

wherein the first sub-controller (51) is connected with the interior controller (4) by the first wire (61), the second sub-controller (52) is connected with the first sub-controller (51) by the second wire (62), or the second sub-controller (52) is connected with a portion of the first wire (61) located outside the cab (1) by the second wire (62).

11. Aircraft fuelling vehicle according to claim 5, characterized in that the conductor (6) between the internal controller (4) and the external controller (5) employs a CAN bus.

12. Aircraft fuelling vehicle according to claim 5, characterized in that the extension path of the wire (6) between the internal controller (4) and the external controller (5) is configured to bypass the engine of the aircraft fuelling vehicle.

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