A device for checking the opening and closing movement of an aircraft spoiler

Abstract

This application belongs to the technical field of aircraft spoiler opening and retraction movement inspection and testing technology, specifically relating to an aircraft spoiler opening and retraction movement inspection and testing device. Its design utilizes the loading and unloading of the actuator cylinder, combined with the elastic reset function of the return spring, to transmit power through a pull plate, transmission beam, steel cable, transmission rocker arm, lower rocker arm, and upper rocker arm, replacing the spoiler control mechanism. This drives the spoiler to deflect between the open and retracted positions, completing the inspection and testing of the aircraft spoiler opening and retraction movement. The overall structure is simple, the force transmission path is clear, the action is smooth, rapid, and reliable, and the overall space occupied is small, making it easy to install. It can well meet the needs of aircraft spoiler opening and retraction movement inspection and testing.

Description

Technical Field

[0001] This application belongs to the technical field of aircraft spoiler opening and retraction movement inspection test technology, specifically relating to an aircraft spoiler opening and retraction movement inspection test device. Background Technology

[0002] The aircraft spoiler has two fork-shaped control joints in the middle and single-ear suspension joints at both ends. The single-ear suspension joints at both ends are hinged to the wing via pins. The supporting ends of the two fork-shaped control joints are also hinged to the wing via pins. The hinged ends are hinged to the spoiler control mechanism on the wing via pins. The pilot drives the spoiler to deflect through the spoiler control mechanism, causing the spoiler to open and close, thereby increasing wing drag and reducing lift, thus achieving the purpose of deceleration and controlling the aircraft's attitude. It is an important component related to aircraft flight safety. Conducting retraction and retrieval operation inspection tests to verify whether the joints will jam and whether the spoiler will deform after repeated retraction and retrieval is of great significance.

[0003] Currently, most tests on the opening and retraction of aircraft spoilers use the spoiler control mechanism on real aircraft to open and retract the spoilers. This mechanism is complex, inconvenient to install, occupies a lot of space, and has high testing costs.

[0004] This application is made in view of the aforementioned technical deficiencies.

[0005] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this invention, and it does not necessarily belong to the prior art of this application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0006] The purpose of this application is to provide a test device for checking the opening and closing motion of an aircraft spoiler, so as to overcome or mitigate at least one of the known technical defects.

[0007] The technical solution of this application is:

[0008] An aircraft spoiler opening and retraction movement inspection test device, comprising:

[0009] Two supporting columns;

[0010] The upper load-bearing beam is connected at both ends to two load-bearing columns;

[0011] Two double-ear suspension joints are connected to both ends of the upper load-bearing beam and are hinged to the single-ear suspension joints at both ends of the spoiler via pins.

[0012] Two double-ear control joints are connected to the upper load-bearing beam, located between the two double-ear suspension joints, and are hinged to the support ends of the two double-ear control joints in the middle of the spoiler via pins.

[0013] The lower load-bearing beam is connected at both ends to two load-bearing columns;

[0014] Two double-eared load-bearing joints are connected to the lower load-bearing beam;

[0015] Two lower rocker arms, one end of which is formed as a single-ear joint, which is hinged to two double-ear load-bearing joints by a pin, and the other end is formed as a double-ear joint;

[0016] The two upper rocker arms are formed into single-ear joints at both ends. The single-ear joint at one end is hinged to the double-ear joints on the two lower rocker arms by a pin. The single-ear joint at the other end is hinged to the hinged ends of the two double-ear control joints in the middle of the spoiler by a pin.

[0017] Two return springs, one end of which is connected to the double-ear joint on the two lower rocker arms by a pin, and the other end is connected to the support column;

[0018] Two transmission rocker arms, with double-ear joints at both ends, and one end is hinged to the two lower rocker arms by a pin.

[0019] Two transmission beams;

[0020] Two steel cables, one end of which is connected to the double-ear joint at the other end of the two transmission rocker arms by a pin, and the other end of which is connected between the two ends of the two transmission beams by a pin;

[0021] The pull plate has single-ear joints at both ends, and one end is hinged between two transmission beams by a pin.

[0022] Loading columns;

[0023] The actuator cylinder is hinged to the loading column by a pin through a single and double lug structure, and the piston rod is hinged to the single lug joint at the other end of the pull plate by bolts.

[0024] in,

[0025] When the actuator is loaded, the pull plate, two transmission beams, two steel cables, and two transmission rocker arms pull the two lower rocker arms to overcome the elastic swing of the two return springs, causing the two upper rocker arms to swing, which in turn drives the spoiler to deflect to the open position.

[0026] When the actuator is unloaded, the two return springs rely on their elastic force to pull the two lower rocker arms to swing, causing the two upper rocker arms to swing, which in turn drives the spoiler to deflect to the retracted position.

[0027] According to at least one embodiment of this application, the above-mentioned aircraft spoiler opening and retraction movement inspection test device further includes:

[0028] A force gauge is connected between the piston rod of the actuator cylinder and the single-ear connector at the corresponding end of the pull plate.

[0029] According to at least one embodiment of this application, in the above-described aircraft spoiler opening and retraction movement inspection test device, a force gauge is screwed to the piston rod of the actuator cylinder.

[0030] According to at least one embodiment of this application, the above-mentioned aircraft spoiler opening and retraction movement inspection test device further includes:

[0031] The load-bearing floor is connected to two load-bearing columns and their loading columns via anchor bolts.

[0032] According to at least one embodiment of this application, the above-mentioned aircraft spoiler opening and retraction movement inspection test device further includes:

[0033] The connecting rod has double-ear connectors at both ends that pass through the two lower rocker arms and single-ear connectors at the corresponding ends of the two upper rocker arms, connecting the two upper rocker arms.

[0034] According to at least one embodiment of this application, in the above-mentioned aircraft spoiler opening and retraction movement inspection test device, the double-ear joints on the two lower rocker arms have arc-shaped limiting grooves.

[0035] The aircraft spoiler opening and retraction movement inspection test device also includes:

[0036] Two limiting pins are set in two arc-shaped limiting grooves and connected to the single-ear connectors at the corresponding ends of the two upper rocker arms, so as to limit the deflection angle of the spoiler between the open and retracted positions. Attached Figure Description

[0037] Figure 1 This is a schematic diagram of the aircraft spoiler opening and retraction movement inspection test device provided in the embodiments of this application;

[0038] Figure 2 This is a schematic diagram of a portion of the structure of the aircraft spoiler opening and retraction movement inspection test device provided in the embodiments of this application;

[0039] Figure 3 This is a schematic diagram of another part of the aircraft spoiler opening and retraction movement inspection test device provided in the embodiments of this application;

[0040] Figure 4 This is a schematic diagram of another part of the structure of the aircraft spoiler opening and retraction movement inspection test device provided in the embodiments of this application;

[0041] Figure 5 This is a schematic diagram of the upper load-bearing beam provided in an embodiment of this application;

[0042] Figure 6This is a schematic diagram of the double-ear suspension connector provided in an embodiment of this application;

[0043] Figure 7 This is a schematic diagram of the dual-ear control connector provided in an embodiment of this application;

[0044] Figure 8 This is a schematic diagram of the double-ear bearing connector provided in an embodiment of this application;

[0045] Figure 9 This is a schematic diagram of the lower rocker arm provided in an embodiment of this application;

[0046] Figure 10 This is a schematic diagram of the upper rocker arm provided in an embodiment of this application;

[0047] Figure 11 This is a schematic diagram of the loading column provided in an embodiment of this application;

[0048] Figure 12 This is a schematic diagram of the connecting rod provided in an embodiment of this application;

[0049] in:

[0050] 1-Bearing column; 2-Upper bearing beam; 3-Double-ear suspension joint; 4-Spoiler; 5-Double-ear control joint; 6-Lower bearing beam; 7-Double-ear bearing joint; 8-Lower rocker arm; 9-Upper rocker arm; 10-Reset spring; 11-Transmission rocker arm; 12-Transmission beam; 13-Steel cable; 14-Pull plate; 15-Loading column; 16-Actuator cylinder; 17-Force gauge; 18-Bearing ground; 19-Connecting rod; 20-Limit pin.

[0051] To better illustrate this embodiment, some parts in the accompanying drawings may be omitted, enlarged, or reduced, and do not represent the actual product dimensions. Furthermore, the drawings are for illustrative purposes only and should not be construed as limiting this application. Detailed Implementation

[0052] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0053] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer," etc., used in this application description to indicate relative direction or positional relationship are used only to indicate relative orientation or positional relationship, and do not imply that the device or component must have a specific orientation, or be constructed and operated in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly, and therefore should not be construed as a limitation on this application. The terms "first," "second," "third," and similar terms used in this application description are used only for descriptive purposes to distinguish different components, and should not be construed as indicating or implying relative importance. The terms "a," "one," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but should be construed as indicating the existence of at least one. The terms "including," "comprising," etc., used in this application description mean that the element or object preceding the word covers the element or object listed after the word and its equivalents, without excluding other elements or objects.

[0054] Furthermore, it should be noted that, unless otherwise explicitly specified and limited, terms such as “installation,” “connection,” and “linkage” used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0055] The following is in conjunction with the appendix Figures 1 to 12 This application will be described in further detail.

[0056] An aircraft spoiler opening and retraction movement inspection test device, comprising:

[0057] Two supporting columns 1;

[0058] The upper load-bearing beam 2 is connected at both ends to two load-bearing columns 1;

[0059] Two double-eared suspension joints 3 are connected to both ends of the upper load-bearing beam 2 and are hinged to the single-eared suspension joints at both ends of the spoiler 4 via pins.

[0060] Two double-ear control joints 5 are connected to the upper load-bearing beam 2, located between two double-ear suspension joints 3, and are hinged to the support ends of the two double-ear control joints in the middle of the spoiler 4 via pins.

[0061] The lower load-bearing beam 6 is connected at both ends to two load-bearing columns 1;

[0062] Two double-eared load-bearing joints 7 are connected to the lower load-bearing beam 6;

[0063] Two lower rocker arms 8, one end of which is formed as a single-ear joint, which is hinged to two double-ear bearing joints 7 by a pin, and the other end is formed as a double-ear joint;

[0064] Two upper rocker arms 9 are formed into single-ear joints at both ends. The single-ear joint at one end is hinged to the double-ear joints on the two lower rocker arms 8 by a pin. The single-ear joint at the other end is hinged to the hinged ends of the two double-ear control joints in the middle of the spoiler 4 by a pin.

[0065] Two return springs 10 are connected at one end to the double-ear joints on the two lower rocker arms 8 via pins, and at the other end to the supporting column 1.

[0066] Two transmission rocker arms 11 are formed into double-ear joints at both ends, and one end is hinged to the two lower rocker arms 8 by a pin.

[0067] Two transmission beams, 12;

[0068] Two steel cables 13 are connected at one end to the double-ear joints at the other end of the two transmission rocker arms 11 via pins, and at the other end to the two transmission beams 12 via pins.

[0069] The pull plate 14 has single-ear joints at both ends, and one end is hinged between the two transmission beams 12 by a pin.

[0070] Load column 15;

[0071] The actuator cylinder 16 is hinged to the loading column 15 by a pin through a single and double ear structure, and the piston rod is hinged to the single ear joint at the other end of the pull plate 14 by bolts.

[0072] in,

[0073] When the actuator cylinder 16 is loaded, it pulls the two lower rocker arms 8 through the pull plate 14, two transmission beams 12, two steel cables 13, and two transmission rocker arms 11 to overcome the elastic swing of the two return springs 10, causing the two upper rocker arms 9 to swing, which in turn drives the deflector 4 to the open position.

[0074] When the actuator 16 is unloaded, the two return springs 10 rely on elastic force to pull the two lower rocker arms 8 to swing, causing the two upper rocker arms 9 to swing, which in turn drives the spoiler 4 to deflect to the retracted position.

[0075] For the aircraft spoiler opening and retraction movement inspection test device disclosed in the above embodiments, those skilled in the art will understand that its design utilizes the loading and unloading of the actuator 16, combined with the elastic reset function of the return spring 10, to transmit power through the pull plate 14, transmission beam 12, steel cable 13, transmission rocker arm 11, lower rocker arm 8, and upper rocker arm 9, replacing the spoiler control mechanism, driving the spoiler 4 to deflect between the open and retracted positions, and completing the inspection test of the aircraft spoiler opening and retraction movement. The overall structure is simple, the force transmission path is clear, the action is stable, fast, and reliable, and the overall space occupied is small, making it easy to install, and it can well meet the needs of aircraft spoiler opening and retraction movement inspection test.

[0076] In some optional embodiments, the above-described aircraft spoiler opening and retraction movement inspection test device further includes:

[0077] Force gauge 17 is connected between the piston rod of actuator cylinder 16 and the single-ear connector at the corresponding end of pull plate 14;

[0078] The actuator 16 and the force gauge 17 can be connected to the controller to form negative feedback regulation. The deflection speed and angle of the spoiler 4 can be controlled by programming, and the aircraft spoiler opening and retraction movement inspection test can be completed automatically.

[0079] In some alternative embodiments, in the above-described aircraft spoiler opening and retraction movement inspection test device, the force gauge 17 is screwed to the piston rod of the actuator cylinder 16.

[0080] In some optional embodiments, the above-described aircraft spoiler opening and retraction movement inspection test device further includes:

[0081] The load-bearing floor 18 is connected to two load-bearing columns 1 and their loading columns 15 by anchor bolts.

[0082] In some optional embodiments, the above-described aircraft spoiler opening and retraction movement inspection test device further includes:

[0083] The connecting rod 19 has double-ear connectors on both ends of the two lower rocker arms 8 and single-ear connectors on the corresponding ends of the two upper rocker arms 9, connecting the two upper rocker arms 9.

[0084] In some optional embodiments, the above-mentioned aircraft spoiler opening and retraction movement inspection test device has arc-shaped limiting grooves on the double-ear joints on the two lower rocker arms 8.

[0085] The aircraft spoiler opening and retraction movement inspection test device also includes:

[0086] Two limiting pins 20 are set in two arc-shaped limiting grooves and connected to the single-ear connectors at the corresponding ends of the two upper rocker arms 9, so as to limit the deflection angle of the spoiler 4 between the open and retracted positions and prevent the spoiler 4 from deflecting beyond the limit.

[0087] In the aircraft spoiler opening and retraction movement inspection test device disclosed in the above embodiments, some components can be connected by screws or bolts, and a strip guide groove can be configured so that the spacing between components can be adjusted according to the size of the spoiler, thereby enhancing the versatility of the device. In addition, in order to avoid jamming during use, joint bearings can be configured in some single and double ear structures. The specific configuration can be referred to the accompanying drawings of this application, and will not be described in more detail here.

[0088] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0089] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A test device for inspecting the opening and retraction movement of an aircraft spoiler, characterized in that, include: Two supporting columns (1); The upper load-bearing beam (2) is connected at both ends to two load-bearing columns (1); Two double-eared suspension joints (3) are connected to both ends of the upper load-bearing beam (2) and are hinged to the single-eared suspension joints at both ends of the spoiler (4) by pins; Two double-ear control joints (5) are connected to the upper bearing beam (2) and located between two double-ear suspension joints (3). The support ends of the two double-ear control joints in the middle of the spoiler (4) are hinged by pins. The lower load-bearing beam (6) is connected at both ends to two load-bearing columns (1); Two double-eared load-bearing joints (7) are connected to the lower load-bearing beam (6); Two lower rocker arms (8), one end of which is formed as a single-ear joint, which is hinged to two double-ear bearing joints (7) by a pin, and the other end is formed as a double-ear joint; Two upper rocker arms (9) are formed into single-ear connectors at both ends. The single-ear connector at one end is hinged to the double-ear connectors on the two lower rocker arms (8) by a pin. The single-ear connector at the other end is hinged to the hinged ends of the two double-ear control connectors in the middle of the spoiler (4) by a pin. Two return springs (10) are connected at one end to the double-ear joints on the two lower rocker arms (8) by a pin, and at the other end to the support column (1); Two transmission rocker arms (11) are formed into double-ear joints at both ends, and one end is hinged to the two lower rocker arms (8) by a pin. Two transmission beams (12); Two steel cables (13) are connected at one end to the double-ear joints at the other end of the two transmission rocker arms (11) by a pin, and at the other end to the two transmission beams (12) by a pin. The pull plate (14) is formed into single-ear joints at both ends, and one end is hinged between two transmission beams (12) by a pin. Load the column (15); The actuator cylinder (16) is hinged to the loading column (15) by a pin through a single and double ear structure, and the piston rod is hinged to the single ear joint at the other end of the pull plate (14) by bolts. in, When the actuator (16) is loaded, it pulls the two lower rocker arms (8) through the pull plate (14), two transmission beams (12), two steel cables (13), and two transmission rocker arms (11) to overcome the elastic swing of the two return springs (10), causing the two upper rocker arms (9) to swing, thereby driving the pull spoiler (4) to deflect to the open position; When the actuator (16) is unloaded, the two return springs (10) rely on elastic force to pull the two lower rocker arms (8) to swing, causing the two upper rocker arms (9) to swing, which in turn drives the spoiler (4) to deflect to the retracted position.

2. The aircraft spoiler opening and retraction movement inspection test device according to claim 1, characterized in that, Also includes: A force gauge (17) is connected between the piston rod of the actuator cylinder (16) and the single-ear connector at the corresponding end of the pull plate (14).

3. The aircraft spoiler opening and retraction movement inspection test device according to claim 2, characterized in that, The force gauge (17) is screwed onto the piston rod of the actuator (16).

4. The aircraft spoiler opening and retraction movement inspection test device according to claim 1, characterized in that, Also includes: A load-bearing floor (18) is provided, on which two load-bearing columns (1) and their loading columns (15) are connected by anchor bolts.

5. The aircraft spoiler opening and retraction movement inspection test device according to claim 1, characterized in that, Also includes: The connecting rod (19) is connected to the two upper rocker arms (9) by passing through the double-ear connectors on the two lower rocker arms (8) and the single-ear connectors on the corresponding ends of the two upper rocker arms (9).

6. The aircraft spoiler opening and retraction movement inspection test device according to claim 1, characterized in that, The two lower rocker arms (8) have arc-shaped limiting grooves on their double-ear joints; The aircraft spoiler opening and retraction movement inspection test device also includes: Two limiting pins (20) are set in two arc-shaped limiting grooves and connected to the single-ear connectors at the corresponding ends of the two upper rocker arms (9) so as to limit the deflection angle of the spoiler (4) between the open and retracted positions.

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