Stacked aero-engine transportation bracket

Abstract

The utility model discloses a stacked aero-engine transportation bracket which comprises a chassis frame, four trundle assemblies, an inner frame, two supporting force arms and two supporting rods. Two front supporting positions are arranged at the front position of the inner frame, and two flush rear supporting positions are arranged at the rear position of the inner frame. The trundles can move, so that the transportation bracket can be switched between the mode that the trundles make contact with the ground and the mode that the chassis frame makes contact with the ground. The supporting force arms are folded around the hinge points, so that the supporting force arms are unfolded and folded. The supporting rods are folded around the hinge points, so that the supporting rods are unfolded and folded. After the chassis frame is in contact with the ground, the supporting force arms are folded and the supporting rods are folded, the transportation bracket is lifted up and placed on the two front supporting positions and the two rear supporting positions of another transportation bracket, and therefore stacking is carried out. The transportation bracket has the beneficial effects that when the transportation bracket is not used, the transportation bracket can be stacked, so that the occupied area is reduced.

Description

Technical Field

[0001] The utility model relates to a transport bracket, in particular to a stacked aircraft engine transport bracket. Background Art

[0002] Aircraft engines are the power that propels aircraft. Unlike the power plants of land and surface vehicles, which can be shut down or anchored for troubleshooting when problems arise, aircraft engines must operate continuously and stably at altitudes of thousands or even tens of thousands of meters. An engine failure in mid-air deprives the aircraft of its primary power source, making it unable to maintain altitude and speed. This can lead to mission failure at best, or even fatal accidents. Furthermore, compared to other mechanical devices, aircraft engines are highly complex, with tens of thousands of parts. Furthermore, the operating environment of their key components is extremely harsh, often subject to high temperatures (reaching nearly 2000 degrees Celsius), high pressures (tens of atmospheres), and high rotational speeds (reaching tens of thousands of revolutions per minute). A single component failure could cause the engine to shut down or fail, potentially leading to catastrophic consequences. Therefore, before any aircraft engine is officially put into service, it must undergo comprehensive testing to gain a thorough understanding of its performance, functionality, strength, and reliability, ensuring its safe, effective, and rational use.

[0003] For airlines, routine aircraft engine inspection, maintenance, servicing, and replacement are essential tasks. Replacing an aircraft engine requires disassembly, installation, transportation, and storage of the engine and the aircraft's suspension. Currently, a transport bracket is typically used to accommodate disassembled and hoisted aircraft engines. The bracket typically consists of two support arms with docking joints and two support rods with supporting joints. The center and rear casings of the aircraft engine are mounted to the docking and supporting joint mounting brackets, respectively. Caster assemblies are installed at each corner of the bracket's chassis frame for mobility. Utility Model Content

[0004] The present application provides a stackable aircraft engine transport bracket, which can solve the problem that existing transport brackets cannot be stacked and occupy a large area.

[0005] In the present application, a stackable aircraft engine transport bracket is provided, comprising:

[0006] chassis frame;

[0007] Four sets of caster assemblies are respectively arranged at the four corners of the chassis frame; the casters in the caster assemblies are movable so that the transport bracket can be switched between a loaded state with the casters touching the ground and a stacked state with the chassis frame touching the ground;

[0008] The inner frame is fixedly connected to the top surface of the chassis frame, and has two front support positions at the front position and two flush rear support positions at the rear position;

[0009] Two support arms can be hinged to the front two sides of the inner frame in a limited manner, so that the transport bracket can be switched between a loading state in which the support arms are extended and a stacking state in which the support arms are retracted;

[0010] The two support rods are respectively hinged to two sides of the rear portion of the inner frame, so that the transport bracket can be switched between a loading state in which the support rods are extended and a stacking state in which the support rods are folded.

[0011] In some embodiments, the caster assembly further includes a connecting arm and a quick-release pin for mounting the caster; each of the four corners of the chassis frame has a first hole for inserting the quick-release pin; the connecting arm is hinged to the chassis frame and has two second holes for inserting the quick-release pin, corresponding to the caster touching the ground and the chassis frame touching the ground respectively.

[0012] In some embodiments, at least one of the two support rods can be further adjusted in a front-to-rear direction to a connection position with the inner frame.

[0013] In some embodiments, a detachable upper pin is provided between the two support arms and the inner frame, and the upper pin is used to limit the hinge connection between the two.

[0014] In some embodiments, two gas springs are further included, which are respectively arranged between the two support arms and the inner frame, and are used to drive the corresponding support arms to fold.

[0015] In some embodiments, the chassis frame is provided with two forklift slots.

[0016] In summary, in the present application, a stackable aircraft engine transport bracket includes a chassis frame, four sets of caster assemblies, an inner frame, two support levers and two support rods. The inner frame has two front support positions at the front and two flush rear support positions at the rear. The casters are movable, so that the transport bracket can switch between the casters touching the ground and the chassis frame touching the ground. By folding the support levers around the hinge point, the support levers can be expanded and folded. By folding the support rods around the hinge point, the support rods can be expanded and folded. After the chassis frame touches the ground, the support levers are folded, and the support rods are folded, the transport bracket is lifted up and placed on the two front support positions and two rear support positions of another transport bracket for stacking. The beneficial effect is that when the transport brackets are not in use, they can be stacked to reduce the floor space. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the background technology, the drawings required for use in the embodiments of the present application or the background technology will be described below.

[0018] Figure 1 This is the rear view of the application;

[0019] Figure 2 A schematic diagram of this application;

[0020] Figure 3 for Figure 2 A magnified schematic diagram of part A;

[0021] Figure 4 for Figure 2 An enlarged schematic diagram of part B;

[0022] Figure 5 for Figure 2 Enlarged schematic diagram of part C.

[0023] In the figure,

[0024] 1. Chassis frame; 1a. Forklift slot;

[0025] 2. Caster assembly; 2a. Caster; 2b. Connecting arm; 2b1. First pin; 2b2. Second hole; 2c. Quick-release pin;

[0026] 3. Inner frame; 3a. Front support; 3b. Rear support;

[0027] 4. Support arm; 4a. Lower pin; 4b. Upper pin; 4c. Butt joint;

[0028] 5. Support rod; 5a. Fourth pin; 5b. Stop rod; 5c. Support joint;

[0029] 6. Gas spring. DETAILED DESCRIPTION

[0030] The following is further explained with reference to the accompanying drawings, which are provided for illustrative purposes only and are not drawn to scale. Unless otherwise defined, technical or scientific terms used in this disclosure should have the same ordinary meaning as those understood by persons of ordinary skill in the art to which this disclosure pertains. The terms "first," "second," and similar expressions used in this disclosure do not denote any order, quantity, or importance, but are used only to distinguish between different components. Terms such as "include" or "comprising" mean that the element or object preceding the term includes the elements or objects listed after the term, and their equivalents, without excluding other elements or objects. Terms such as "connected" or "connected" are not limited to physical or mechanical connections but may include electrical connections, whether direct or indirect. Terms such as "upper," "lower," "left," and "right" are used only to indicate relative positional relationships; if the absolute position of the described object changes, the relative positional relationship may also change accordingly. The embodiments of this application are combinable unless there is a conflict.

[0031] See also Figure 1 and Figure 2 A stackable aircraft engine transport bracket includes a chassis frame 1, four sets of caster assemblies 2, an inner frame 3, two support arms 4, and two support rods 5. In other words, the transport bracket has a normal loading state for loading and transferring aircraft engines, and a stacking state for stacking aircraft engines.

[0032] The chassis frame 1 can be frame-shaped, with four corners beveled to leave space for the subsequent four sets of caster assemblies 2.

[0033] Four sets of caster assemblies 2 are mounted at the four corners of the chassis frame 1. The casters 2a in the caster assemblies 2 are movable, allowing the transport bracket to switch between the casters 2a touching the ground and the chassis frame 1 touching the ground. Accordingly, the casters 2a touching the ground corresponds to the loading state, while the chassis frame 1 touching the ground corresponds to the stacking state. In other words, to stack multiple transport brackets, the casters 2a of the transport brackets are first retracted, allowing the chassis frame 1 to touch the ground, and then the transport brackets are lifted to begin stacking.

[0034] See also Figure 2 and Figure 3In some embodiments, the caster assembly 2 includes, in addition to the caster 2a mentioned above, a connecting arm 2b and a quick-release pin 2c. There is a first hole position for inserting the quick-release pin 2c at each of the four corners of the chassis frame 1. The connecting arm 2b is hinged to the chassis frame 1 and is also used for installing the caster 2a. More specifically, the connecting arm 2b and the chassis frame 1 can be hinged through a first pin shaft 2b1, and the caster 2a can use WICKE's 230210 model double-row shock-absorbing caster to ensure that the chassis does not produce too much vibration when moving. There are also two second holes 2b2 on the connecting arm 2b for inserting the quick-release pin 2c. These two second holes 2b2 correspond to the caster 2a touching the ground and the chassis frame 1 touching the ground. That is to say, when the transport bracket switches between the caster 2a touching the ground and the chassis frame 1 touching the ground, first lift the transport bracket, then remove the quick release pin 2c, release the connection between the first hole position and the current second hole position 2b2, swing the connecting arm 2b so that the other second hole position 2b2 corresponds to the first hole position, and finally reinsert the quick release pin 2c.

[0035] Compared with the method of using a screw module or a hydraulic system to make the caster 2a move, the method of using the connecting arm 2b and the quick-release pin 2c has the following characteristics: the structure is simpler; when the caster 2a touches the ground, it can provide good support for the transport bracket and ensure the stability of the connection between the connecting arm 2b and the chassis frame 1; when the caster 2a touches the ground, it can easily ensure that the four casters 2a extend to the same position relative to the chassis frame 1, so that the chassis frame 1 is at the required level.

[0036] See also Figure 2 In some embodiments, the chassis frame 1 is provided with two forklift slots 1 a.

[0037] The transport bracket can be lifted not only by hoisting but also by forklift.

[0038] See also Figure 1 、 Figure 2 and Figure 4 The inner frame 3 is fixedly connected to the top surface of the chassis frame 1. The inner frame 3 has two front support positions 3a at the front and two flush rear support positions 3b at the rear. More specifically, the two front support positions 3a and the two rear support positions 3b are stepped, with the inner side lower for supporting the chassis frame 1 of another transport bracket and the outer side higher for limiting the supported chassis frame 1.

[0039] The two support arms 4 are hinged to the front and sides of the inner frame 3. More specifically, the support arms 4 and the inner frame 3 are hinged via a second pin, designated as the lower pin 4a. The lower pin 4a is fixed, with nuts installed at both ends. This pin connects the support arms 4 to the inner frame 3 and also serves as the pivot for the support arms 4 to fold.

[0040] By folding the support arms 4 around the hinge point, the support arms 4 can be expanded and retracted. The hinge between the two support arms 4 and the inner frame 3 can also be limited, and this limitation can be used to keep the support arms 4 expanded. During the process of the two support arms 4 swinging inward and retracting, when the support arms 4 and the inner frame 3 come into contact, the support arms 4 are retracted, and the hinge can be removed, relying on the gravity of the support arms 4 to keep them retracted. Accordingly, the support arms 4 remaining expanded corresponds to the loading state, and the support arms 4 remaining retracted corresponds to the stacking state.

[0041] The two supporting arms 4 are also provided with butt joints 4c for mounting the aircraft engine.

[0042] The two supporting arms 4 are the main load-bearing structures connected to the aircraft engine and can be mainly formed by welding Q355 plates.

[0043] See also Figure 2 and Figure 4 In some embodiments, a third pin is detachably installed between both support arms 4 and the inner frame 3. The third pin is located above the second pin and is labeled upper pin 4b. Upper pin 4b is used to limit the articulation between the support arms 4 and the inner frame 3. In other words, the upper pin is a latch-type pin, and upper pin 4b is installed after the support arms 4 are folded into place.

[0044] The upper pin shaft 4b and the lower pin shaft 4a bear the force simultaneously, so that the support force wall remains stably fixed relative to the inner frame 3, providing protection for the support force arm 4 to serve as the main load-bearing structure connected to the aircraft engine.

[0045] See also Figure 2 and Figure 4 In some embodiments, the transport bracket further includes two gas springs 6. The two gas springs 6 are respectively disposed between the two support arms 4 and the inner frame 3. More specifically, the gas springs 6 and the support arms 4, as well as the gas springs 6 and the inner frame 3, can be hinged. The two gas springs 6 are used to drive the corresponding support arms 4 to fold.

[0046] See also Figure 1 and Figure 2 The two support rods 5 are hinged to the rear of the inner frame 3 on either side. More specifically, the support rods 5 and the inner frame 3 are hinged via a fourth pin 5a. The support rods 5 can be expanded and collapsed by folding around the hinge point. Accordingly, the expanded support rods 5 correspond to the loading state, while the collapsed support rods 5 correspond to the stacking state.

[0047] The two support rods 5 also have support joints 5c for mounting the aircraft engine. Because the two support arms 4 are the main load-bearing structures connected to the aircraft engine, the swing between the two support rods 5 and the inner frame 3 can be unrestricted, and there is no need to keep the support rods 5 extended. In other words, the joints 4c of the two support arms 4 are first installed with the aircraft engine, and then the positions of the two support rods 5 are adjusted, and the support joints 5c of the two support rods 5 are installed with the aircraft engine. Correspondingly, stop rods 5b can be fixedly connected to both sides of the rear of the inner frame 3. During the deployment process, the two support rods 5 can first swing to abut against the stop rods 5b so that the support rods 5 can be maintained in this position. At this time, the distance between the two support joints 5c is larger, which facilitates the entry of the hoisted aircraft engine. After the aircraft engine is entered, the positions of the two support rods 5 are adjusted.

[0048] In some embodiments, at least one of the two support rods 5 can be adjusted in the forward and backward direction relative to the inner frame 3. More specifically, the length of the fourth pin 5a is greater than the thickness of the support rod 5, allowing the support rod 5 to fold around the fourth pin 5a while also sliding along the axis of the fourth pin 5a. When the transport bracket is loaded, the two support rods 5 can be aligned. When the aircraft engine transport bracket is stacked, the two support rods 5 can be staggered.

Claims

1. A stackable aircraft engine transport bracket, characterized in that: include: Chassis frame (1); Four sets of caster assemblies (2) are respectively arranged at the four corners of the chassis frame (1); the casters (2a) in the caster assemblies (2) are movable, so that the transport bracket can be switched between a loading state in which the casters (2a) touch the ground and a stacking state in which the chassis frame (1) touches the ground; An inner frame (3) is fixedly connected to the top surface of the chassis frame (1), and has two front support positions (3a) at the front and two flush rear support positions (3b) at the rear; Two support arms (4) can be respectively hinged to the front two sides of the inner frame (3) in a limited manner, so that the transport bracket can be switched between a loading state in which the support arms (4) are kept extended and a stacking state in which the support arms (4) are kept retracted; The two support rods (5) are respectively hinged to the two rear sides of the inner frame (3), so that the transport bracket can be switched between a loading state in which the support rods (5) are unfolded and a stacking state in which the support rods (5) are folded.

2. The stackable aircraft engine transport bracket according to claim 1, characterized in that: The caster assembly (2) further comprises a connecting arm (2b) and a quick-release pin (2c) for mounting the caster (2a); each of the four corners of the chassis frame (1) has a first hole for inserting the quick-release pin (2c); the connecting arm (2b) is hinged to the chassis frame (1) and has two second holes (2b2) ​​for inserting the quick-release pin (2c), corresponding to the caster (2a) touching the ground and the chassis frame (1) touching the ground respectively.

3. The stackable aircraft engine transport bracket according to claim 1, characterized in that: At least one of the two support rods (5) can also be adjusted in the front-rear direction at its connection position on the inner frame (3).

4. The stackable aircraft engine transport bracket according to claim 1, characterized in that: An upper pin shaft (4b) is detachably provided between the two support arms (4) and the inner frame (3), and the upper pin shaft (4b) is used to limit the hinge connection between the two.

5. The stackable aircraft engine transport bracket according to claim 1, characterized in that: It also includes two gas springs (6), which are respectively arranged between the two support arms (4) and the inner frame (3) and are used to drive the corresponding support arms (4) to fold.

6. The stackable aircraft engine transport bracket according to claim 1, characterized in that: The chassis frame (1) is provided with two forklift slots (1a).

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