Aircraft nose landing gear loading device for torque condition test and method thereof

Abstract

The application belongs to the technical field of aircraft nose torque working condition test, and particularly relates to an aircraft nose torque working condition test front landing gear loading device and method, wherein two vertical loading actuators are used to apply vertical load to the front landing gear, a lateral loading actuator is used to apply lateral load to the front landing gear, and through the design of multiple pin shafts, joint bearings and strip-shaped sliding grooves, the vertical load and the lateral load applied to the front landing gear are decoupled to a certain extent, so that the front landing gear is prevented from being stuck and interfered, the accuracy of the load is ensured through the correction of the vertical and lateral loads, and the aircraft nose torque working condition test under a large torque condition is completed.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft front fuselage torque working condition test, and particularly relates to an aircraft front fuselage torque working condition test front landing gear loading device and a method thereof. BACKGROUND

[0002] The aircraft front fuselage torque working condition test belongs to the ground test of aircraft structure strength, and when the test is performed, the rear end of the front section of the fuselage is fixed, and a lateral load and a vertical load are simultaneously applied to the front landing gear on the front section of the fuselage, as shown in FIG. 1. Figure 1

[0003] When the aircraft front fuselage torque working condition test is performed, the front section of the fuselage will produce a rotational deformation along the horizontal structural center line, as shown in FIG. 2, and the rotational deformation has a relatively small influence on the lateral load applied to the front landing gear but has a relatively large influence on the vertical load. Figure 2

[0004] At present, when the aircraft front fuselage torque working condition test is performed, a crowbar system is usually used to load the front landing gear, and the technical scheme has the following defects:

[0005] 1) The crowbar system is easily affected by the rotational deformation of the front section of the fuselage, and is prone to be stuck or even collapsed, which has a major safety hazard;

[0006] 2) The crowbar system cannot provide a large lateral deformation of the front landing gear, and thus it is difficult to complete the aircraft front fuselage torque working condition test under a large torque working condition;

[0007] 3) When the crowbar system applies the vertical load to the front landing gear, the application of the lateral load is interfered, and it is difficult to ensure the accuracy of the loading.

[0008] The present application is proposed in view of the above technical defects.

[0009] It should be noted that the disclosure of the above background art content is only used to assist in understanding the inventive concept and technical solutions of the present application, and it does not necessarily belong to the prior art of the present application. In the absence of explicit evidence that the above content has been disclosed on the filing date of the present application, the above background art should not be used to evaluate the novelty and inventiveness of the present application. SUMMARY

[0010] The purpose of the present application is to provide an aircraft front fuselage torque working condition test front landing gear loading device and a method thereof, so as to overcome or alleviate at least one aspect of the known technical defects.

[0011] The technical scheme of the present application is as follows:

[0012] In one aspect, an aircraft front fuselage torque working condition test front landing gear loading device is provided, comprising: ​​

[0013] two vertical loading columns;

[0014] two vertical loading suspension seats, bolted on the two vertical loading columns, and having double ear structures formed thereon;

[0015] two vertical loading single ear sleeves, connected with the double ear structures on the two vertical loading suspension seats through pin shafts;

[0016] two vertical loading connecting rods, one end of each of which is threadedly connected to the two vertical loading single ear sleeves;

[0017] two vertical loading actuating cylinders, the cylinder body of each of which is threadedly connected to the other end of the two vertical loading connecting rods, and the piston rod of each of which has a single ear structure formed thereon;

[0018] two pairs of vertical loading pull plates, one end of each of which is connected with the single ear structure on the piston rod of each of the two vertical loading actuating cylinders through a pin shaft;

[0019] two vertical loading single ear seats, the single ear structure of each of which is connected with the other end of the two pairs of vertical loading pull plates through a pin shaft;

[0020] a vertical loading cross beam, on which the two vertical loading single ear seats are connected;

[0021] two vertical loading hanging ears, connected on the vertical loading cross beam;

[0022] two knuckle bearings, installed in the two vertical loading hanging ears and sleeved on the two ends of the front landing gear axle;

[0023] a lateral loading column, having a strip-shaped sliding slot thereon;

[0024] a lateral loading adapter rod, penetrating through the front landing gear axle and having a double ear structure formed on one end and a pad and a nut threadedly connected on the other end for limiting;

[0025] a lateral loading actuating cylinder, the piston rod of which has a single ear structure formed thereon, the single ear structure being connected with the double ear structure on the lateral loading adapter rod through a pin shaft;

[0026] a lateral loading connecting rod, penetrating through the strip-shaped sliding slot and having one end threadedly connected to the lateral loading actuating cylinder and the other end having a pad and a nut threadedly connected for limiting.

[0027] According to at least one embodiment of the present application, in the above-mentioned aircraft front fuselage torque working condition test front landing gear loading device, the vertical loading cross beam is formed by two channel steels and four steel plates, and a gap is left between the two channel steels;

[0028] the two vertical loading single ear seats have connecting pieces extending into the gap between the two channel steels and connected through pin shafts;

[0029] Two vertical loading lugs have connecting plates that extend into the gap between two channel steels and are connected by pins.

[0030] On the other hand, a method for loading the nose landing gear during aircraft nose fuselage torque condition testing is provided, including:

[0031] A 40% vertical load was applied to the nose landing gear using two vertical loading actuators; a 40% lateral load was applied to the nose landing gear using a lateral loading actuator; the lateral displacement L of the nose landing gear was measured. 40 Lifting height h 40 ;

[0032] A vertical load is applied to the nose landing gear using two vertical loading actuators. Where H is the suspension height of the nose landing gear, and P 40 The vertical load is 40%; the lateral loading actuator is used at the lifting height h. 40 Applying lateral load to the front landing gear Among them, F 40 The lateral load is 40%; the lateral displacement L of the nose landing gear is measured. 40 Lifting height h 40 ;

[0033] If the lateral displacement L of the nose landing gear is measured later compared to the measurement at the front... 40 Lifting height h 40 If the deviation exceeds 2mm, then the two vertical loading actuators are used again to apply a vertical load to the nose landing gear. Lifting height h using lateral loading actuator 40 Applying lateral load to the front landing gear And measure the lateral displacement L of the nose landing gear 40 Lifting height h 40 Until the lateral displacement L of the nose landing gear is measured laterally compared to the measurement at the front, ... 40 Lifting height h 40 The deviation is less than 2mm;

[0034] A vertical load is applied to the nose landing gear using two vertical loading actuators. Among them, L 100 The lateral displacement of the nose landing gear under 100% load is given by L. 40 The conversion yields h 100 The lift height of the nose landing gear under 100% load is given by h. 40 The conversion yields P 100 For 100% vertical load; using a lateral loading actuator at a lifting height h 100 Applying lateral load to the nose landing gear Among them, F100 100% lateral load

[0035] According to at least one embodiment of the present application, in the above-mentioned aircraft front fuselage torque working condition test before landing gear loading method, L 100 = 2.5L 40 ;

[0036] h 100 = 2.5h 40 . BRIEF DESCRIPTION OF DRAWINGS

[0037] Figure 1 is a schematic diagram of the existing aircraft fuselage torque working condition test;

[0038] Figure 2 is a schematic diagram of the existing aircraft fuselage torque working condition test fuselage segment producing rotation deformation along the horizontal configuration center line;

[0039] Figure 3 is a schematic diagram of the aircraft front fuselage torque working condition test before landing gear loading device provided by the embodiment of the present application;

[0040] Figure 4 is a reference schematic diagram of the vertical loading suspension seat provided by the embodiment of the present application;

[0041] Figure 5 is a reference schematic diagram of the vertical loading single ear bushing provided by the embodiment of the present application;

[0042] Figure 6 is a reference schematic diagram of the vertical loading actuating cylinder and the lateral loading actuating cylinder provided by the embodiment of the present application;

[0043] Figure 7 is a reference schematic diagram of the vertical loading pull plate provided by the embodiment of the present application;

[0044] Figure 8 is a reference schematic diagram of the vertical loading cross beam provided by the embodiment of the present application;

[0045] Figure 9 is a reference schematic diagram of the vertical loading hanging ear provided by the embodiment of the present application;

[0046] Figure 10 is a reference schematic diagram of the lateral loading transfer rod provided by the embodiment of the present application;

[0047] Figure 11 is a reference schematic diagram of the front fuselage segment provided by the embodiment of the present application;

[0048] Figure 12 is a reference schematic diagram of the front landing gear provided by the embodiment of the present application;

[0049] Figure 13 is a schematic diagram of the aircraft front fuselage torque working condition test before landing gear loading method provided by the embodiment of the present application;

[0050] Among them:

[0051] 1-vertical loading column; 2-vertical loading suspension seat; 3-front section of fuselage; 4-vertical loading single ear bushing; 5-vertical loading connecting rod; 6-vertical loading actuator cylinder; 7-vertical loading pull plate; 8-vertical loading single ear seat; 9-vertical loading cross beam; 10-vertical loading lug; 11-knuckle bearing; 12-front landing gear; 13-lateral loading column; 14-lateral loading adapter rod; 15-lateral loading actuator cylinder; 16-lateral loading connecting rod.

[0052] In order to better illustrate the embodiment, some components in the drawings may be omitted, enlarged or reduced, and do not represent the size of the actual product. In addition, the drawings are only used for illustrative description and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0053] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further clearly and completely described below in combination with the drawings. It can be understood that the specific embodiments described herein are only part of the embodiments of the present application, which are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design. In the case of no conflict, the embodiments in the present application and the technical features in the embodiments can be combined to obtain new embodiments.

[0054] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as having the common meaning to those of ordinary skill in the art to which the present application belongs. The words "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer" and the like, which express the relative position in the description of the present application, are only used to express the relative direction or position relationship, and not to imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the described object changes, the relative position relationship may also change accordingly, and therefore cannot be understood as a limitation on the present application. The "first", "second", "third" and the like used in the description of the present application are only for the purpose of description, in order to distinguish different components, and cannot be understood as indicating or implying relative importance. The "one", "an" or "the" and the like used in the description of the present application should not be understood as an absolute limitation on the quantity, but should be understood as the presence of at least one. The "includes" or "contains" and the like used in the description of the present application means that the elements or objects appearing before the word are covered by the elements or objects listed after the word and their equivalents, and other elements or objects are not excluded.

[0055] In addition, it should be further pointed out that, unless otherwise explicitly specified and limited, the "installation", "connection", "connection" and the like used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection, or detachable connection, or integral connection; can be mechanical connection, or electrical connection; can be directly connected, or indirectly connected through intermediate medium, or the internal communication of two elements, and those skilled in the art can understand the specific meaning of the present application according to the specific circumstances.

[0056] The following will be described in detail in combination with the accompanying drawings Figures 1 to 13 The present application is further described in detail.

[0057] In one aspect, an aircraft front fuselage torque working condition test before landing gear loading device is provided, comprising:

[0058] Two vertical loading columns 1;

[0059] Two vertical loading suspension seats 2 are connected by bolts on the two vertical loading columns 1, and a double ear structure is formed thereon;

[0060] Two vertical loading single ear sleeves 4 are connected with the double ear structure on the two vertical loading suspension seats 2 through a pin shaft;

[0061] Two vertical loading connecting rods 5 are threadedly connected at one end to the two vertical loading single ear sleeves 4;

[0062] Two vertical loading actuating cylinders 6, the cylinder body is screwed with the other end of two vertical loading connecting rods 5, the single ear structure is formed on the piston rod;

[0063] Two pairs of vertical loading pull plates 7, one end is connected with the single ear structure on the piston rod of two vertical loading actuating cylinders 6 through a pin shaft;

[0064] Two vertical loading single ear seats 8, the single ear structure on it is connected with the other end of two pairs of vertical loading pull plates 7 through a pin shaft;

[0065] A vertical loading crossbeam 9, on which two vertical loading single ear seats 8 are connected;

[0066] Two vertical loading hanging ears 10, connected on the vertical loading crossbeam 9;

[0067] Two joint bearings 11, installed in two vertical loading hanging ears 10, sleeved on both ends of the front landing gear 12 axle, when the front landing gear 12 is subjected to vertical load by two vertical loading actuating cylinders 6, the joint bearings 11 can provide a corner for the lateral deformation of the front landing gear 12;

[0068] A lateral loading upright column 13, which has a strip-shaped sliding slot;

[0069] A lateral loading adapter rod 14, which is arranged through the front landing gear 12 axle, one end is formed as a double ear structure, the other end is provided with a pad and screwed with a nut for limiting;

[0070] A lateral loading actuating cylinder 15, the piston rod of which is formed with a single ear structure, which is connected with the double ear structure on the lateral loading adapter rod 14 through a pin shaft;

[0071] A lateral loading connecting rod 16, which is arranged through the strip-shaped sliding slot, one end is screwed on the lateral loading actuating cylinder 15, the other end is provided with a pad and screwed with a nut for limiting, and can play a certain fastening role, when the front landing gear 12 is subjected to lateral load by the lateral loading actuating cylinder 15, the height of the lateral loading actuating cylinder 15 can be adjusted to match the height position of the front landing gear 12 through the sliding of the lateral loading connecting rod 16 along the strip-shaped sliding slot.

[0072] Based on the above-mentioned embodiment disclosed in the aircraft front fuselage torque working condition test front landing gear loading device, in the aircraft front fuselage torque working condition test, two vertical loading actuating cylinders 6 can be used to apply vertical load to the front landing gear 12, and the lateral loading actuating cylinder 15 can be used to apply lateral load to the front landing gear 12, through the design of multiple pin shafts, joint bearings and strip-shaped sliding slots, the vertical load and lateral load on the front landing gear 12 can be decoupled to a certain extent, so as to avoid jamming and interference, and through the correction of vertical and lateral loading, the accuracy of loading can be ensured, and the aircraft front fuselage torque working condition test under large torque working condition can be completed.

[0073] In some alternative embodiments, the above-mentioned aircraft front fuselage torque working condition test landing gear loading device, the vertical loading beam 9 is welded by two channel steel and four steel plates, and a gap is left between the two channel steels;

[0074] The two vertical loading single lug seats 8 have connecting pieces extending into the gap between the two channel steels and connected by a pin shaft;

[0075] The two vertical loading lug ears 10 have connecting pieces extending into the gap between the two channel steels and connected by a pin shaft.

[0076] In another aspect, an aircraft front fuselage torque working condition test landing gear loading method is provided, comprising:

[0077] applying 40% vertical load to the front landing gear 12 by using two vertical loading actuators 6; applying 40% lateral load to the front landing gear 12 by using a lateral loading actuator 15; measuring the lateral displacement L of the front landing gear 12 40 , the lifting height h 40 ;

[0078] applying vertical load to the front landing gear 12 by using two vertical loading actuators 6 wherein H is the suspension height of the front landing gear 12, P 40 is the 40% vertical load; applying lateral load to the front landing gear 12 at the lifting height h 40 by using a lateral loading actuator 15 wherein F 40 is the 40% lateral load; measuring the lateral displacement L of the front landing gear 12 40 , the lifting height h 40 ;

[0079] If the deviation of the lateral displacement L of the front landing gear 12 40 , the lifting height h 40 between the latter measurement and the former measurement exceeds 2 mm, then the vertical load is applied to the front landing gear 12 again by using two vertical loading actuators 6 the lateral load is applied to the front landing gear 12 at the lifting height h 40 by using a lateral loading actuator 15 and the lateral displacement L of the front landing gear 12 40 , the lifting height h 40 is measured, until the deviation of the lateral displacement L of the front landing gear 12 40 , the lifting height h 40 between the latter measurement and the former measurement is less than 2 mm;

[0080] Vertical loads are applied to the nose landing gear 12 using two vertical loading actuators 6. Among them, L 100 For the lateral displacement of the nose landing gear 12 under 100% load, L 40 The conversion yields h 100 The lift height of the nose landing gear 12 under 100% load is determined by h. 40 The conversion yields P 100 For 100% vertical load; using the lateral loading actuator 15 at the lifting height h 100 Lateral loads are applied to the front landing gear 12. Among them, F 100 The aircraft's forward fuselage torque test was completed under 100% lateral load.

[0081] In some optional embodiments, in the above-described method for loading the nose landing gear during the aircraft nose fuselage torque condition test, L 100 =2.5L 40 h 100 =2.5h 40 That is, utilizing the lateral displacement L of the nose landing gear 12 under 40% load. 40 Lifting height h 40 By using a factor amplification method, the lateral displacement L of the front landing gear 12 under 100% load can be estimated quickly and easily. 100 Lifting height h 100 This allows for the correction of vertical and lateral loads under 100% load conditions, which is convenient, effective, and ensures the accuracy of 100% load loading, thus efficiently completing the torque test of the aircraft's forward fuselage.

[0082] The method for loading the nose landing gear for the aircraft nose fuselage torque condition test disclosed in the above embodiments is implemented based on the aircraft nose fuselage torque condition test nose landing gear loading device disclosed in the above embodiments. The description is relatively simple. For specific details, please refer to the relevant description of the aircraft nose fuselage torque condition test nose landing gear loading device. The technical effects can also be referred to the technical effects of the relevant parts of the aircraft nose fuselage torque condition test nose landing gear loading device. It will not be repeated here.

[0083] 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.

[0084] The technical scheme of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to the related technical features without departing from the principles of the present application, and the technical schemes after the changes or replacements will fall within the protection scope of the present application.

Claims

1. A loading device for the nose landing gear during aircraft nose fuselage torque condition testing, characterized in that, It comprises: Two vertical loading columns (1); Two vertical loading suspension seats (2) are bolted on the two vertical loading columns (1), and a double ear structure is formed on the two vertical loading suspension seats (2); Two vertical loading single ear sleeves (4) are connected with the double ear structure on the two vertical loading suspension seats (2) through a pin shaft; Two vertical loading connecting rods (5) are threadedly connected at one end to the two vertical loading single ear sleeves (4); Two vertical loading cylinders (6) are threadedly connected at the other end to the two vertical loading connecting rods (5), and a single ear structure is formed on the piston rod; Two pairs of vertical loading pull plates (7) are connected at one end to the single ear structure on the piston rod of the two vertical loading cylinders (6) through a pin shaft; Two vertical loading single ear seats (8) are connected at the other end to the two pairs of vertical loading pull plates (7) through a pin shaft; A vertical loading cross beam (9) is connected to the two vertical loading single ear seats (8); Two vertical loading hanging ears (10) are connected to the vertical loading cross beam (9); Two knuckle bearings (11) are installed in the two vertical loading hanging ears (10) and are sleeved on the two ends of the front landing gear (12) axle; A lateral loading column (13) has a strip-shaped sliding groove thereon; A lateral loading adapter rod (14) is arranged through the front landing gear (12) axle, one end of which is formed as a double ear structure, and the other end is provided with a pad and a nut for limiting; A lateral loading cylinder (15) has a single ear structure formed on the piston rod, which is connected to the double ear structure on the lateral loading adapter rod (14) through a pin shaft; A lateral loading connecting rod (16) is arranged through the strip-shaped sliding groove, one end of which is threadedly connected to the lateral loading cylinder (15), and the other end is provided with a pad and a nut for limiting.

2. The front landing gear loading device for the aircraft front fuselage torque test of claim 1, wherein The vertical loading cross beam (9) is composed of two channel steels and four steel plates, and a gap is left between the two channel steels; The two vertical loading single ear seats (8) have connecting pieces that extend into the gap between the two channel steels and are connected by a pin shaft; The two vertical loading hanging ears (10) have connecting pieces that extend into the gap between the two channel steels and are connected by a pin shaft.

3. A method for loading the landing gear before the front fuselage torque condition test of an aircraft, implemented based on the landing gear loading device before the front fuselage torque condition test of an aircraft according to claim 1, characterized in that, It comprises: 40% vertical load is applied to the front landing gear (12) by using the two vertical loading cylinders (6); Apply 40% lateral load to the nose landing gear (12) using the lateral loading actuator cylinder (15); measure the lateral displacement L of the nose landing gear (12) 40 , the lifting height h 40 ; Applying vertical load to the nose landing gear (12) using two vertical loading rams (6) where H is the suspension height of the nose landing gear (12), P 40 is 40% vertical load; applying lateral load to the nose landing gear (12) at the lift height h 40 using the lateral loading ram (15) where F 40 is 40% lateral load; measuring the lateral displacement L 40 of the nose landing gear (12), the lift height h 40 ; if the lateral displacement L of the front landing gear (12) measured later is different from the lateral displacement L of the front landing gear (12) measured earlier by more than 2 mm 40 , the lifting height h 40 , the vertical load applied to the front landing gear (12) by the two vertical loading actuators (6) is applied again the lifting height h 40 is lifted by the lateral loading actuator (15) and the lateral displacement L of the front landing gear (12) is measured 40 , the lifting height h 40 , until the lateral displacement L of the front landing gear (12) measured later is different from the lateral displacement L of the front landing gear (12) measured earlier by less than 2 mm 40 , the lifting height h 40 ; The vertical load is applied to the nose landing gear (12) by two vertical loading rams (6) where L 100 is the lateral displacement of the nose landing gear (12) at 100% load, converted from L 40 where h 100 is the lift height of the nose landing gear (12) at 100% load, converted from h 40 where P 100 is 100% vertical load. The lateral load is applied to the nose landing gear (12) at the lift height h 100 by the lateral loading rams (15) where F 100 is 100% lateral load.

4. The front landing gear loading method for the aircraft front fuselage torque test of claim 3, wherein L 100 = 2.5L 40 ; h 100 = 2.5h 40 .

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