Aircraft refueling truck

Abstract

The present disclosure relates to the technical field of aircraft refueling equipment, and in particular to an aircraft refueling vehicle, comprising: a cab (1), an upper device and a control device, wherein the upper device comprises a plurality of actuators (2), each actuator (2) being provided with a detection component (3) configured to detect the working state of the actuator (2); wherein the control device comprises: an internal controller (4), which is arranged in the cab (1); and an external controller (5), which is arranged outside the cab (1) and connected to the internal controller (4) via a wire (6); the external controller (5) is connected to the plurality of detection components (3) via a wire (6), and is configured to receive detection signals from the plurality of detection components (3) and send the detection signals to the internal controller (4), and the external controller (5) is connected to the plurality of actuators (2) via a wire (6), and is configured to drive the plurality of actuators (2) to work.

Description

Technical Field

[0001] The present disclosure relates to the technical field of aircraft refueling equipment, and in particular to an aircraft refueling truck. Background Art

[0002] The aircraft refueling truck is a special equipment, including a cab and upper equipment. The upper equipment is equipped with a variety of detection components to detect the working status of the refueling truck, and a main controller is set in the cab to receive the data transmitted by each detection component.

[0003] In the prior art, each detection component is connected to a main controller via a signal line to transmit data to the main controller. This approach results in a thicker wiring harness, occupies a large space, requires a larger inlet in the cab for the wiring harness to enter, and increases the difficulty of wiring harness layout. Summary of the Invention

[0004] The present disclosure provides an aircraft refueling vehicle, which can reduce the difficulty of wiring harness layout between upper equipment and a cab.

[0005] The aircraft refueling vehicle provided by the present disclosure includes: a cab, upper equipment and a control device, wherein the upper equipment includes multiple actuators, each actuator is provided with a detection component configured to detect the working status of the actuator; wherein the control device includes:

[0006] Internal controls, located in the cab; and

[0007] The external controller is arranged outside the cab and is connected to the internal controller through wires; the external controller is connected to multiple detection components through wires, and is configured to receive detection signals from the multiple detection components and send them to the internal controller, and the external controller is connected to multiple actuators through wires, and is configured to receive control signals from the internal controller to drive the multiple actuators to work.

[0008] In some embodiments, the external controller includes:

[0009] A first sub-controller connected to a portion of the plurality of actuators and the plurality of detection components via wires; and

[0010] The second sub-controller is connected to the rest of the plurality of actuators and the plurality of detection components through wires.

[0011] In some embodiments, the wire between the internal controller and the external controller includes a first wire and a second wire;

[0012] The first sub-controller is connected to the internal controller via a first wire, the second sub-controller is connected to the first sub-controller via a second wire, or the second sub-controller is connected to the part of the first wire outside the cab via a second wire.

[0013] In some embodiments, the wires between the internal controller and the external controller use a CAN bus.

[0014] In some embodiments, the aircraft refueling vehicle further comprises a chassis frame, and the external controller is disposed on the chassis frame.

[0015] In some embodiments, the aircraft refueling truck further includes an explosion-proof box, and the external controller is disposed in the explosion-proof box.

[0016] In some embodiments, the aircraft refueling vehicle further includes a chassis frame and a mounting bracket, wherein the mounting bracket is fixed to the chassis frame, and the explosion-proof box is detachably suspended and mounted on the mounting bracket.

[0017] In some embodiments, the wiring between the internal controller and the external controller is routed so as to bypass the engine of the aircraft tanker.

[0018] In some embodiments, the control device further comprises: an indicator light assembly, the indicator light assembly comprising:

[0019] a plurality of interlock indicator lights, disposed outside the cab, corresponding one to each of the plurality of actuators and configured to illuminate upon receiving an interlock signal emitted when the corresponding actuator is actuated;

[0020] a master interlock indicator light, located in the cab and electrically connected to the internal controller, configured to illuminate when a lit interlock indicator light appears;

[0021] an override interlock indicator light located in the cab and electrically connected to the internal controller, configured to illuminate when the plurality of actuators have been reset but the plurality of interlock indicator lights remain illuminated and when the override interlock function is manually forcibly opened; and

[0022] The power take-off indicator light is located in the cab and is electrically connected to the internal controller, and is configured to illuminate when the engine of the aircraft refueling vehicle provides power to the plurality of actuators.

[0023] 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 release the brakes of the aircraft refueling truck when the override interlock indicator light is on and to apply the brakes of the aircraft refueling truck when the power take-off indicator light is on.

[0024] In some embodiments, the control device further comprises: a plurality of switching amplifiers configured to amplify the interlock signal;

[0025] The interlocking signals generated when multiple actuators are in motion are all electrically connected to the external controller after passing through a switching amplifier;

[0026] The plurality of interlock indicator lights are connected to the plurality of switch amplifiers in a one-to-one correspondence, or the plurality of interlock indicator lights are all connected to an external controller.

[0027] The aircraft refueling vehicle of the disclosed embodiment is provided with an internal controller located inside the cab and an external controller located outside the cab. Multiple actuators and multiple detection components on the aircraft refueling vehicle are connected to the external controller via wires, and the external controller is then connected to the internal controller via wires. This reduces the number of wiring harnesses introduced into the cab from the outside, occupies less space, provides flexible wiring, facilitates layout, and reduces the risk of having a large number of wires exposed. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present disclosure or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present disclosure. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative labor.

[0029] Figure 1 Schematic diagram of the installation location of the external controller in some embodiments of the aircraft refueling vehicle disclosed herein.

[0030] Figure 2 This is a schematic structural diagram of some embodiments of the aircraft refueling vehicle disclosed herein in which an external controller is disposed in an explosion-proof box.

[0031] Figure 3 Schematic diagram of some embodiments of the layout and wiring of the control device in the aircraft refueling vehicle disclosed herein.

[0032] Figure 4 Schematic diagrams of other embodiments of the layout and wiring of control devices in the aircraft refueling vehicle disclosed herein.

[0033] Figure 5 Schematic diagrams of some further embodiments of the layout and wiring of the control device in the aircraft refueling vehicle disclosed herein.

[0034] Figure 6 The figure is a schematic diagram of the arrangement and connection relationship of the indicator light assembly in some embodiments of the aircraft refueling vehicle disclosed herein.

[0035] Description of reference numerals:

[0036] 1. Cab;

[0037] 2. Executive body;

[0038] 3. Detection components;

[0039] 4. Internal controller;

[0040] 5. External controller; 51. First sub-controller; 52. Second sub-controller;

[0041] 6. Wire; 61. First wire; 62. Second wire;

[0042] 7. Indicator lamp assembly; 71. Interlock indicator lamp; 72. Interlock master indicator lamp; 73. Override interlock indicator lamp; 74. Power take-off indicator lamp; S. Interlock signal;

[0043] 8. Switching amplifier;

[0044] 9. Chassis frame;

[0045] 10. Explosion-proof box; 101. Mounting lug; 102. First mounting hole;

[0046] 11. Mounting bracket; 111. Mounting edge; 112. Second mounting hole. DETAILED DESCRIPTION

[0047] The following will be combined with the drawings in the embodiments of the present disclosure to clearly and completely describe the technical solutions in the embodiments of the present disclosure. Obviously, the described embodiments are only part of the embodiments of the present disclosure, rather than all the embodiments. The following description of at least one exemplary embodiment is actually only illustrative and is in no way intended to limit the present disclosure and its application or use. Based on the embodiments in the present disclosure, all other embodiments obtained by ordinary technicians in this field without carrying out creative work are within the scope of protection of the present disclosure.

[0048] Technologies, methods, and equipment known to ordinary technicians in the relevant art may not be discussed in detail, but where appropriate, the technologies, methods, and equipment should be considered part of the specification.

[0049] In the description of the present disclosure, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "horizontal, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present disclosure and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the scope of protection of the present disclosure; the directional words "inside and outside" refer to the inside and outside relative to the outline of each component itself.

[0050] In the description of the present disclosure, it should be understood that the use of words such as "first" and "second" to limit components is only for the convenience of distinguishing the corresponding components. Unless otherwise stated, the above words have no special meaning and therefore cannot be understood as limiting the scope of protection of the present disclosure.

[0051] In addition, the technical features involved in different embodiments of the present disclosure described below can be combined with each other as long as they do not conflict with each other.

[0052] Aircraft refueling trucks are important ground special vehicles used by airports to refuel aviation fuel. Figure 1 As shown, in some embodiments, the aircraft refueling vehicle includes a cab 1, a chassis frame 9, upper equipment and a control device. The cab 1 is arranged on the chassis frame 9. The upper equipment includes an oil pumping system, an oil tank assembly and a lifting mechanism, etc. In order to realize the operation of the upper equipment, the upper equipment includes a plurality of actuators 2, and each actuator 2 is provided with a detection component 3, which is configured to detect the working status of the actuator 2.

[0053] like Figure 3 As shown, the control device includes: an internal controller 4 and an external controller 5. The internal controller 4 is located inside the cab 1, and the external controller 5 is located outside the cab 1. The internal controller 4 and the external controller 5 are connected by a wire 6. For example, the wire 6 may include a single wire or multiple wires, cables, or a bus. The external controller 5 is connected to multiple detection components 3 via wires 6, such as signal lines, and is configured to receive detection signals from the multiple detection components 3 and send them to the internal controller 4. The external controller 5 is also connected to multiple actuators 2 via wires 6. The external controller 5 is configured to receive control signals from the internal controller 4 to drive the multiple actuators 2 to operate.

[0054] The aircraft refueling vehicle of the disclosed embodiment is equipped with both an internal controller 4 located within the cab 1 and an external controller 5 located outside the cab 1. Multiple actuators and detection components on the aircraft refueling vehicle are connected to the external controller 5 via wires, which in turn are connected to the internal controller 4 via wires. As a result, detection signals obtained by the multiple detection components can be transmitted to the internal controller 4 via the external controller 5, allowing the internal controller 4 to adjust control signals based on the operating status of the multiple actuators or control whether the aircraft refueling vehicle should travel. Furthermore, control signals from the internal controller 4 can also be transmitted to the multiple actuators via the external controller 5 to control their operation.

[0055] For example, when the internal controller 4 receives a signal that the actuator is in working state, it needs to keep the aircraft refueling truck in a brake state. Due to the special environment and operation objects of aviation fuel replenishment, the vehicle needs to be kept braked during the entire vehicle operation to prevent safety accidents caused by abnormal vehicle movement during operation.

[0056] This setting method can reduce the number of wiring harnesses introduced from outside the cab into the cab, takes up less space, and does not require a large wiring opening on the cab, which is beneficial to the sealing of the cab. The thinner wiring harness makes the wiring more flexible and easy to layout, and can reduce the risk of more wires being exposed, thereby improving the reliability of the control device and further improving the safety of aircraft refueling truck operations.

[0057] In some embodiments, as Figure 4 and Figure 5 As shown, the external controller 5 includes a first sub-controller 51 and a second sub-controller 52. The first sub-controller 51 is connected to a portion of the plurality of actuators 2 and the plurality of detection components 3 via a wire 6, and the second sub-controller 52 is connected to the remaining portion of the plurality of actuators 2 and the plurality of detection components 3 via a wire 6.

[0058] Since the aircraft refueling truck needs to perform many functions, the number of actuators 2 and detection components 3 is large, resulting in more leads. By setting the external controller 5 as two separate sub-controllers, it is convenient for external layout and wiring, and the accuracy of wiring can also be improved.

[0059] Optionally, the first sub-controller 51 and the second sub-controller 52 may be arranged side by side at the same position in the vehicle, or may be arranged at different positions according to the positions of the actuator 2 and / or detection component 3 connected thereto, to facilitate wiring.

[0060] Optionally, during wiring, multiple actuators 2 may be connected to the first sub-controller 51 via wires 6, and multiple detection components 3 may be connected to the second sub-controller 52 via wires 6. Alternatively, some actuators 2 and their corresponding detection components 3 may be connected to the first sub-controller 51 via wires 6, and the remaining actuators 2 and their corresponding detection components 3 may be connected to the second sub-controller 52 via wires 6.

[0061] For an embodiment in which the external controller 5 includes a first sub-controller 51 and a second sub-controller 52, as shown in FIG. Figure 4 and Figure 5 The wire 6 between the internal controller 4 and the external controller 5 includes a first wire 61 and a second wire 62 .

[0062] like Figure 4As shown, the first sub-controller 51 is connected to the internal controller 4 via a first wire 61, and the second sub-controller 52 is connected to the first sub-controller 51 via a second wire 62. Thus, the second sub-controller 52 sends the received detection signal to the internal controller 4 via the first sub-controller 51, and the control signal sent by the internal controller 4 is sent to the second sub-controller 52 via the first sub-controller 51.

[0063] like Figure 5 As shown, the second sub-controller 52 is connected to the portion of the first wire 6 located outside the cab 1 via the second wire 6. As a result, the detection signals received by the first sub-controller 51 and the second sub-controller 52 are combined and sent to the internal controller 4 via the first wire 61. The control signals sent by the internal controller 4 are sent to the first sub-controller 51 and the second sub-controller 52 respectively according to the preset address allocation rules.

[0064] The wiring method of this embodiment can further reduce the number of wirings between the internal controller 4 and the external controller 5, making the wiring more flexible and easy to layout, and can reliably protect the wires, thereby improving the reliability of the control device and further improving the safety of the aircraft refueling truck operation.

[0065] Optionally, the first sub-controller 51 and the second sub-controller 52 may also be connected to the internal controller 4 via independent wires 6 respectively.

[0066] In some embodiments, the wire 6 between the internal controller 4 and the external controller 5 adopts a CAN bus. Each CAN bus includes two lines, CAN high and CAN low. Figure 4 and Figure 5 In the embodiment, the internal controller 4 and the external controller 5 are connected via only one CAN bus.

[0067] This embodiment is connected via the CAN bus, which is beneficial to reducing the number of wires and transmitting multiple signals. It also has the advantages of strong real-time performance, long transmission distance, strong anti-electromagnetic interference ability, and low cost.

[0068] In some embodiments, as Figure 1 As shown, the external controller 5 is mounted on the aircraft refueling truck's chassis frame 9. The chassis frame 9 is provided with a beam, upon which the external controller 5 can be mounted. This arrangement eliminates the need to alter the layout of the aircraft refueling truck's onboard equipment and prevents the operation of the external controller 5 from being affected by the operation of the onboard equipment.

[0069] In some embodiments, as Figure 1 and Figure 2As shown, the aircraft refueling truck further includes an explosion-proof box 10, and the external controller 5 is disposed within the explosion-proof box 10. During the refueling process, the aircraft refueling truck may experience fuel leakage, which may cause explosions in high-temperature environments. Placing the external controller 5 within the explosion-proof box 10 can protect it from explosions and improve operational reliability and safety.

[0070] In addition to the explosion-proof function, the explosion-proof box 10 can also achieve the dispersion of the wiring harness, so that the wires at the entrance of the explosion-proof box 10 are connected to multiple actuators 2 and multiple detection components 3 through multiple exits.

[0071] Furthermore, a protective cover is provided outside the explosion-proof box 10 , and the protective cover is used to be oil-proof and waterproof, so as to improve the reliability and safety of the operation of the external controller 5 .

[0072] like Figure 2 As shown, the aircraft refueling vehicle also includes a mounting bracket 11, which is mounted on the chassis frame 9 of the aircraft refueling vehicle. The explosion-proof container 10 is detachably suspended from the mounting bracket 11. Specifically, the mounting bracket 11 includes a bracket body and a mounting edge 111. The mounting edge 111 is provided with a second mounting hole 112 for fastening the mounting bracket 11 to the chassis frame 9 via fasteners. The mounting edge 111 is arranged vertically. The explosion-proof container 10 is provided with mounting lugs 101 on both sides. The mounting lugs 101 are provided with first mounting holes 102 for fasteners to suspend the explosion-proof container 10 from the mounting bracket 11.

[0073] In this embodiment, the explosion-proof box 10 is detachably mounted by means of the mounting bracket 11 , which makes it easy to disassemble and facilitate maintenance of the external controller 5 .

[0074] In some embodiments, the wiring 6 between the internal controller 4 and the external controller 5 is routed so as to bypass the engine of the aircraft refueling truck. If the cab 1 is located far from the installation location of the external controller 5, the wiring distance between the internal controller 4 and the external controller 5 is longer, allowing the wiring 6 to avoid the heat source of the engine and prevent damage to the wiring 6.

[0075] In some embodiments, as Figure 6 As shown, the control device further includes an indicator light assembly 7, which includes a plurality of interlock indicator lights 71, a total interlock indicator light 72, an overriding interlock indicator light 73, and a power take-off indicator light 74. When the indicator lights are on, they can remain on or flash.

[0076] A plurality of interlock indicator lights 71 are provided outside the cab 1 and are provided in one-to-one correspondence with the plurality of actuators 2. The interlock indicator lights 71 are configured to light up when receiving an interlock signal S sent when the corresponding actuator 2 is in operation. Figure 2As shown, multiple interlock indicator lights 71 can be installed on the explosion-proof box 10. For example, multiple holes can be opened in the explosion-proof box 10 to allow the interlock indicator lights 71 to be exposed through the holes. To facilitate observation by the operator, the explosion-proof box 10 can be located near one side of the chassis frame 9, with the interlock indicator lights 71 facing the side of the vehicle. The operator can observe the operating status of the tanker truck without entering the cab.

[0077] The main interlock indicator light 72 is located within the cab 1, for example, on the top of the cab 1, and is electrically connected to the internal controller 4. It is configured to illuminate when an illuminated interlock indicator light 71 appears. That is, as long as at least one actuator 2 is not in its home position, the main interlock indicator light 72 will illuminate. An interlock signal S is transmitted to the internal controller 4 via the external controller 5. The internal controller 4 determines whether the main interlock indicator light 72 is illuminated based on multiple interlock signals S. This configuration allows the operator in the cab 1 to quickly determine whether any actuator 2 is in its home position. If an actuator 2 is in its home position, the vehicle brakes are maintained.

[0078] The override interlock indicator light 73 is located within the cab 1, for example, on the top of the cab 1, and is electrically connected to the internal controller 4. The indicator light 73 is configured to illuminate even when the multiple actuators 2 have returned to their original positions but the multiple interlock indicator lights 71 remain illuminated, and to illuminate after the override interlock function is manually forcibly engaged. Upon manually forcibly engaging the override interlock function, the vehicle's brakes are released, allowing the vehicle to be driven to a repair location.

[0079] A power take-off indicator light 74 is located within cab 1, for example, on the top of cab 1, and is electrically connected to internal controller 4. The indicator light 74 is configured to illuminate when the aircraft refueling vehicle's engine is providing power to the plurality of actuators 2. Illumination of the power take-off indicator light 74 indicates that the engine is providing power to the actuators in the upper body equipment, and the vehicle needs to be braked.

[0080] This embodiment allows the operator to observe the operating status of the refueling truck from both outside and inside the cab 1, providing flexible and convenient observation. Furthermore, due to the unique environment and operational requirements of aviation fuel refueling, operating status signals are required to control the vehicle to remain stationary during operation to prevent safety accidents caused by abnormal vehicle movement during operation. Accurately understanding the operating status of the upper equipment improves the safety of aircraft refueling truck operations.

[0081] In some embodiments, the external controller 5 is configured to send interlock signals of the plurality of actuators 2 to the internal controller 4, and the internal controller 4 is configured to release the brakes of the aircraft refueling truck when the override interlock indicator light 73 is on, and to brake the aircraft refueling truck when the power take-off indicator light 74 is on.

[0082] This embodiment ensures that the vehicle remains in a braked state when any actuator in the upper equipment is not in its original position or when the engine is providing power to the upper equipment, thereby improving the safety of the aircraft refueling vehicle. Furthermore, if multiple actuators 2 have been returned to their original positions but multiple interlock indicator lights 71 remain illuminated, the aircraft refueling vehicle can be released from its brakes for maintenance by manually forcibly opening the override interlock.

[0083] In some embodiments, as Figure 6 As shown, the control device also includes: multiple switching amplifiers 8, which are configured to amplify the interlocking signal S; the interlocking signals S emitted when the multiple actuators 2 are in action are all electrically connected to the external controller 5 after passing through a switching amplifier 8, and multiple interlocking indicator lights 71 are connected to the multiple switching amplifiers 8 in a one-to-one correspondence.

[0084] This embodiment can generate an interlock signal S when the actuator 2 is actuated. The interlock signal S is amplified by the switching amplifier 8, allowing it to be more accurately captured by the external controller 5 or illuminated by the interlock indicator 71, thus preventing erroneous sensing of the interlock signal S. The amplified interlock signal S is simultaneously transmitted to the external controller 5 and the interlock indicator 71, directly controlling the state of the interlock indicator 71 through the switching amplifier 8. The external controller 5 can then transmit the received interlock signal S to the internal controller 4 via the wire 6, thereby controlling the vehicle's braking state.

[0085] Optionally, the interlock signals S generated by the multiple actuators 2 when in operation are all electrically connected to the external controller 5 through a switching amplifier 8, and the multiple interlock indicator lights 71 are all connected to the external controller 5. In this embodiment, the amplified interlock signal S is sent to the external controller 5, which then controls the state of the interlock indicator lights 71.

[0086] In some embodiments, the controller described above may 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 devices, discrete gate or transistor logic devices, discrete hardware components, or any appropriate combination thereof, for performing the functions described in the present disclosure.

[0087] The above description is merely an exemplary embodiment of the present disclosure and is not intended to limit the present disclosure. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present disclosure shall be included in the scope of protection of the present disclosure.

Claims

1. An aircraft refueling vehicle, characterized in that: The invention comprises a cab (1), a superstructure and a control device, wherein the superstructure comprises a plurality of actuators (2), each of the actuators (2) being provided with a detection component (3) configured to detect the working state of the actuator (2); wherein the control device comprises: an internal controller (4) disposed in the cab (1); and An external controller (5) is provided outside the cab (1) and is connected to the internal controller (4) via a wire (6), wherein the wire (6) includes a first wire (61) and a second wire (62); the external controller (5) is connected to a plurality of detection components (3) via the wire (6), and is configured to receive detection signals from the plurality of detection components (3) and send the detection signals to the internal controller (4); and the external controller (5) is connected to the plurality of actuators (2) via the wire (6), and is configured to receive control signals from the internal controller (4) to drive the plurality of actuators (2) to operate; Wherein, the external controller (5) comprises: a first sub-controller (51) connected to the plurality of actuators (2) and a portion of the plurality of detection components (3) via a wire (6), and the first sub-controller (51) is connected to the internal controller (4) via the first wire (61); and The second sub-controller (52) is connected to the rest of the plurality of actuators (2) and the plurality of detection components (3) through a wire (6). The second sub-controller (52) is connected to the first sub-controller (51) through the second wire (62). 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 sent by the internal controller (4) is sent to the second sub-controller (52) through the first sub-controller (51); or, the second sub-controller (52) is connected to the portion of the first wire (61) located outside the cab (1) through the second wire (62). The detection signals received by the first sub-controller (51) and the second sub-controller (52) are converged and sent to the internal controller (4) through the first wire (61). The control signal sent by the internal controller (4) is sent to the first sub-controller (51) and the second sub-controller (52) respectively according to a preset address allocation rule.

2. The aircraft refueling vehicle according to claim 1, characterized in that: The wire (6) between the internal controller (4) and the external controller (5) adopts a CAN bus.

3. The aircraft refueling vehicle according to claim 1, characterized in that: It also includes a chassis frame (9), and the external controller (5) is arranged on the chassis frame (9).

4. The aircraft refueling vehicle according to claim 1, characterized in that: It also includes an explosion-proof box (10), wherein the external controller (5) is arranged in the explosion-proof box (10).

5. The aircraft refueling vehicle according to claim 4, characterized in that: It also includes a chassis frame (9) and a mounting bracket (11), wherein the mounting bracket (11) is fixed on the chassis frame (9) of the aircraft refueling vehicle, and the explosion-proof box (10) is detachably suspended and mounted on the mounting bracket (11).

6. The aircraft refueling 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 refueling vehicle.

7. The aircraft refueling vehicle according to any one of claims 1 to 6, characterized in that: The control device further comprises: an indicator light assembly (7), wherein the indicator light assembly (7) comprises: A plurality of interlock indicator lights (71) are provided outside the cab (1), are provided in one-to-one correspondence with the plurality of actuators (2), and are configured to light up when receiving an interlock signal (S) issued when a corresponding actuator (2) is actuated; An interlocking indicator light (72) is provided in the cab (1) and is electrically connected to the internal controller (4), and is configured to light up when the interlocking indicator light (71) is lit; an override interlock indicator light (73), disposed in the cab (1) and electrically connected to the internal controller (4), configured to illuminate when the plurality of actuators (2) are in their original positions but the plurality of interlock indicator lights (71) remain illuminated, and to illuminate after the override interlock function is manually forcibly opened; and A power take-off indicator light (74) is provided in the cab (1) and is electrically connected to the internal controller (4), and is configured to light up when the engine of the aircraft refueling vehicle provides power to the plurality of actuators (2).

8. The aircraft refueling vehicle according to claim 7, characterized in that: The external controller (5) is configured to send interlock signals (S) of the plurality of actuators (2) to the internal controller (4), and the internal controller (4) is configured to release the brakes of the aircraft refueling truck when the override interlock indicator light (73) is on, and to brake the aircraft refueling truck when the power take-off indicator light (74) is on.

9. The aircraft refueling vehicle according to claim 7, characterized in that: The control device further comprises: a plurality of switching amplifiers (8) configured to amplify the interlock signal (S); The interlocking signals (S) emitted when the plurality of actuators (2) are in action are all electrically connected to the external controller (5) after passing through a switching amplifier (8); The plurality of interlock indicator lights (71) are connected to the plurality of switch amplifiers (8) in a one-to-one correspondence, or the plurality of interlock indicator lights (71) are all connected to the external controller (5).

Images