CN112959957A - Aircraft fuelling vehicle - Google Patents

Abstract

The utility model relates to an aircraft refueling equipment technical field, in particular to aircraft tank service truck, it includes: the device comprises a cab (1), a loading device and a control device, wherein the loading device comprises a plurality of actuating mechanisms (2), each actuating mechanism (2) is provided with a detection component (3) and is configured to detect the working state of the actuating mechanism (2); wherein, the controlling means includes: an internal controller (4) provided in the cab (1); and an external controller (5) arranged outside the cab (1) and connected with the internal controller (4) through a lead (6); the external controller (5) is connected with the plurality of detection parts (3) through a lead (6) and is configured to receive detection signals of the plurality of detection parts (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 the lead (6) and is configured to drive the plurality of actuators (2) to work.

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 refueling truck is special equipment and comprises a cab and upper equipment, wherein the upper equipment is provided with various detection components for detecting the working state of the refueling truck, and a main controller is arranged in the cab for receiving data transmitted by the detection components.

In the related art, each of the detecting units is connected to the main controller through a signal line to transmit data to the main controller. The wiring harness is thick, the occupied space is large, a large wire inlet needs to be formed in the cab for the wiring harness to enter, and the wiring harness layout difficulty is increased.

Disclosure of Invention

The utility model provides an aircraft tank service truck can reduce the degree of difficulty of pencil overall arrangement between facial make-up equipment and driver's cabin.

The aircraft tank service truck that this disclosure provided includes: the device comprises a cab, a loading device and a control device, wherein the loading device comprises a plurality of actuating mechanisms, each actuating mechanism is provided with a detection component and is configured to detect the working state of the actuating mechanism; wherein, the controlling means includes:

an internal controller provided in the cab; and

the external controller is arranged outside the cab and is connected with the internal controller through a lead; 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

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

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 aircraft refuelling vehicle further comprises a chassis frame on which the external controller is provided.

In some embodiments, the aircraft refuelling vehicle further comprises an explosion proof tank, the external controller being provided within the explosion proof tank.

In some embodiments, the aircraft refuelling vehicle further comprises a chassis frame and a mounting bracket fixed to the chassis frame, the explosion proof tank being removably mounted in suspension on the mounting bracket.

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.

In some embodiments, the control device further comprises: an indicator light assembly, the indicator light assembly comprising:

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 interlocking signals sent out when the corresponding actuating mechanisms act are received;

an interlock light disposed within the cab and electrically connected to the internal controller, configured to illuminate upon the presence of the illuminated interlock light;

the override interlock indicator lamp is arranged in the cab, is electrically connected with the internal controller, is configured to be turned on when the plurality of execution mechanisms are reset and the plurality of interlock indicator lamps are still turned on, and is turned on 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 internal controller 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 external controller is configured to send interlock signals of the plurality of actuators to the internal controller, and the internal controller is configured to deactivate the aircraft fuelling vehicle when the override interlock indicator is illuminated and to deactivate the aircraft fuelling vehicle when the power take-off indicator is illuminated.

In some embodiments, the control device further comprises: a plurality of switching amplifiers configured to amplify the interlock signal;

the interlocking signals sent out by the actuating mechanisms during action are electrically connected with an external controller after passing through a switching amplifier;

the plurality of interlock indicator lamps are connected with the plurality of switching amplifiers in a one-to-one correspondence, or the plurality of interlock indicator lamps are all connected with an external controller.

The aircraft refueling truck of the embodiment is simultaneously provided with the internal controller positioned in the cab and the external controller arranged outside the cab, wherein the plurality of actuating mechanisms and the plurality of detection parts on the aircraft refueling truck are connected with the external controller through wires, and then the external controller is connected with the internal controller through wires, so that the wire harness led into the cab from the outside can be reduced, the occupied space is small, the wiring is flexible, the layout is easy, and the risk that more wires are exposed outside can be reduced.

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 mounting location of an external controller in some embodiments of the 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 external controller is disposed within the explosion proof tank.

Fig. 3 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. 4 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. 5 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.

FIG. 6 is a schematic view of the arrangement and connection of indicator light assemblies in some embodiments of the aircraft fuelling vehicle of 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, in some embodiments, the aircraft fuelling vehicle comprises a cab 1, a chassis frame 9, a loading device and a control device, wherein the cab 1 is arranged on the chassis frame 9, the loading device comprises an oil pumping system, an oil tank assembly, a lifting mechanism and the like, in order to realize the operation of the loading device, the loading device comprises a plurality of actuators 2, and each actuator 2 is provided with a detection component 3 configured to detect the operation state of the actuator 2.

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 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.

The aircraft fuelling vehicle of the embodiment of the present disclosure is provided with an internal controller 4 located in the cab 1 and an external controller 5 located outside the cab 1, wherein a plurality of actuators and a plurality of detection components on the aircraft fuelling vehicle are connected with the external controller 5 through wires, and then the external controller 5 is connected with the internal controller 4 through wires. Therefore, detection signals obtained by a plurality of detection components can be transmitted to the internal controller 4 through the external controller 5, so that the internal controller 4 adjusts control signals according to the working states of a plurality of actuating mechanisms 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.

The arrangement mode can reduce the wiring harness 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 harness becomes thin, wiring is flexible, layout is easy, and the danger that more wires are exposed outside can be reduced, so that the working reliability of the control device is improved, and the safety of the operation of the aircraft refueling truck is improved.

In some embodiments, as shown in fig. 4 and 5, 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.

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.

For embodiments in which the external controller 5 comprises a first sub-controller 51 and a second sub-controller 52, as in fig. 4 and 5, 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. 4, 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 to the internal controller 4 through the first sub-controller 51, and the control signal issued by the internal controller 4 is sent to the second sub-controller 52 through the first sub-controller 51.

As shown in fig. 5, 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 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 conducting 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. 4 and 5, the connection between the internal controller 4 and the external controller 5 is via only 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.

In some embodiments, as shown in fig. 1, the external controller 5 is provided on a chassis frame 9 of an aircraft fuelling vehicle. The chassis frame 9 is provided with a beam on which the external controller 5 can be mounted. 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 some embodiments, as shown in fig. 1 and 2, the aircraft fuelling vehicle further comprises an explosion proof tank 10, the external controller 5 being provided within the explosion proof tank 10. In the process of replenishing fuel oil to an aircraft refueling truck, the fuel oil may leak, the aircraft refueling truck may explode in a high-temperature environment, the external controller 5 is arranged in the explosion-proof box 10 for protection, explosion is prevented, and the working reliability and safety are improved.

The explosion-proof case 10 can perform a dispersion of the wire harness to connect the wires at the inlet of the explosion-proof case 10 to the plurality of actuators 2 and the plurality of detection members 3 through the plurality of outlets, in addition to the explosion-proof function.

Further, a protective cover is arranged outside the explosion-proof box 10, and the protective cover is used for preventing oil and water so as to improve the working reliability and safety of the external controller 5.

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. 6, the control device further comprises: an indicator lamp assembly 7, the indicator lamp assembly 7 comprising: 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 light 72, which is provided in cab 1, for example, may be provided at the top of cab 1, and is electrically connected to internal controller 4, is configured to be lit when lit interlock indicator light 71 appears, i.e., interlock total indicator light 72 is lit as long as one actuator 2 is not returned to its home position. The interlock signal S is transmitted to the internal controller 4 through the external controller 5, and the internal controller 4 determines whether the interlock total indicator lamp 72 is on or off based on the plurality of interlock signals 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 internal controller 4, 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 is provided in the cab 1, for example, may be provided at the top of the cab 1, and is electrically connected to the interior controller 4, and is configured to be illuminated 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.

This embodiment is through making operating personnel can observe the operating condition of tank service truck outside the driver's cabin 1 and inside, and it is nimble convenient to observe. 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 external controller 5 is configured to send interlock signals for the plurality of actuators 2 to the internal controller 4, and the internal controller 4 is configured to deactivate the aircraft refuelling vehicle when the override interlock indicator lamp 73 is illuminated and to deactivate the aircraft refuelling vehicle 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. 6, 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 external controller 5 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 external controller 5 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 external controller 5 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 external controller 5 may transmit the received interlock signal S to the internal controller 4 through the wire 6 to control the vehicle to be in a braking state.

Alternatively, the interlock signals S generated by the plurality of actuators 2 during operation are electrically connected to the external controller 5 through one switching amplifier 8, and the plurality of interlock indicator lamps 71 are connected to the external controller 5. This embodiment transmits the amplified interlock signal S to the external controller 5, and controls the state of the interlock indicator lamp 71 through the external controller 5.

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 (11)

1. An aircraft fuelling vehicle comprising a cab (1), a loading apparatus and a control device, the loading apparatus comprising a plurality of actuators (2), each actuator (2) being provided with a detection member (3) configured to detect an operating state of the actuator (2); wherein the control device includes:

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

the external controller (5) is arranged outside the cab (1) and is connected with the internal controller (4) through a lead (6); 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.

2. Aircraft fuelling vehicle according to claim 1, 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 actuators (2) and the remaining parts of the detection elements (3) by wires (6).

3. Aircraft fueller vehicle according to claim 1, 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).

4. Aircraft fuelling vehicle according to claim 1, characterized in that the conductor (6) between the internal controller (4) and the external controller (5) employs a CAN bus.

5. Aircraft fuelling vehicle according to claim 1, further comprising a chassis frame (9), wherein the external controller (5) is provided on the chassis frame (9).

6. Aircraft fuelling vehicle according to claim 1, further comprising an explosion-proof tank (10), wherein the external controller (5) is provided inside the explosion-proof tank (10).

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

8. Aircraft fuelling vehicle according to claim 1, 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.

9. An aircraft fuelling vehicle according to any one of claims 1 to 8, wherein the control apparatus further comprises: 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 turned on when interlock signals (S) sent out when the corresponding actuators (2) are operated are received;

an interlock total indicator lamp (72) provided in the cab (1) and electrically connected to the interior controller (4), configured to be lit when the lit interlock indicator lamp (71) appears;

an override interlock indicator lamp (73) provided in the cab (1), electrically connected to the internal controller (4), configured to be lit after the plurality of actuators (2) are all returned 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; and

a power takeoff indicator lamp (74) disposed within the cab (1) and electrically connected to the interior controller (4), configured to illuminate when the plurality of actuators (2) are powered by the engine of the aircraft fuelling vehicle.

10. Aircraft fueller vehicle according to claim 9, wherein said external controller (5) is configured to send an interlock signal (S) of said plurality of actuators (2) to said internal controller (4), said internal controller (4) being configured to deactivate the braking of the aircraft fueller vehicle when said override interlock indicator lamp (73) is illuminated and to brake the aircraft fueller vehicle when said power take-off indicator lamp (74) is illuminated.

11. An aircraft fuelling vehicle according to claim 9, wherein the control apparatus further comprises: a plurality of switching amplifiers (8) configured to amplify the interlock signal (S);

the interlocking signals (S) sent out when the plurality of actuating mechanisms (2) act are electrically connected with the external controller (5) after passing through one switching amplifier (8);

the plurality of interlock indicator lamps (71) are connected in one-to-one correspondence with the plurality of switching amplifiers (8), or the plurality of interlock indicator lamps (71) are all connected with the external controller (5).

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