A method for determining the lifting load of an aircraft lifting joint

Abstract

The present application belongs to the technical field of aircraft lifting joints and slings design, and specifically relates to a method for determining the lifting load of an aircraft lifting joint, comprising: constructing an aircraft lifting scenario; calculating the load that each lifting joint needs to bear when the aircraft is lifted in each lifting scenario; based on the maximum load that each lifting joint needs to bear when the aircraft is lifted in each lifting scenario, the lifting load of each lifting joint is obtained. This lifting load is relatively small, and the lifting joint, sling and reinforced structure on the fuselage designed accordingly are relatively small in volume and weight, and can ensure the safe lifting of the aircraft in each lifting scenario.

Description

Technical Field

[0001] The present application belongs to the technical field of aircraft lifting joints and lifting equipment design, and specifically relates to a method for determining the lifting load of an aircraft lifting joint. Background Art

[0002] Aircraft production trials, flight tests, transfers, transportation, and maintenance support scenarios all involve lifting aircraft. For this purpose, the aircraft is designed with multiple lifting joints to lift the aircraft with corresponding lifting equipment.

[0003] To ensure safe lifting of aircraft in various scenarios, a relatively conservative approach is currently used to determine the lifting load of each lifting joint on the aircraft based on the maximum ground weight, and then design the lifting joints and lifting equipment. This technical solution has the following drawbacks:

[0004] 1) The lifting load of each lifting joint is large. Therefore, the lifting joint and the lifting device are designed accordingly. The resulting lifting joint and the lifting device are large in size and weight. The large size and weight of the lifting joint will occupy a large space on the aircraft, destroy the aerodynamic shape of the aircraft surface, increase the overall weight of the aircraft, and increase the aircraft load. The large size and weight of the lifting device are inconvenient to carry and install, and are not convenient to use in situations where space is limited. This problem is particularly prominent when used on ships.

[0005] 2) When the aircraft is lifted, the lifting joints bear concentrated loads, and corresponding reinforcement structures need to be designed at corresponding positions on the fuselage. Such reinforcement structures are designed based on the lifting loads of the lifting joints. When the lifting loads of the various lifting joints are large, the designed reinforcement structures on the fuselage will also have a relatively large volume and weight, further affecting the aerodynamic shape of the fuselage surface, and increasing the overall weight of the aircraft, thereby increasing the aircraft load.

[0006] This application is proposed in view of the above-mentioned technical defects.

[0007] It should be noted that the disclosure of the above background technology content is only used to assist in understanding the inventive concept and technical solution of the present invention, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above content has been disclosed on the filing date of this application, the above background technology should not be used to evaluate the novelty and creativity of this application. Summary of the Invention

[0008] The purpose of the present application is to provide a method for determining the lifting load of an aircraft lifting joint, so as to overcome or alleviate at least one of the technical deficiencies of the prior art.

[0009] The technical solution of this application is:

[0010] A method for determining a lifting load of an aircraft lifting joint, comprising:

[0011] Construct an aircraft lifting scene;

[0012] Calculate the load that each lifting joint needs to bear when lifting the aircraft in various lifting scenarios;

[0013] Based on the maximum load that each lifting joint needs to bear when lifting the aircraft in various lifting scenarios, the lifting load of each lifting joint is obtained.

[0014] According to at least one embodiment of the present application, in the above-mentioned method for determining the lifting load of an aircraft lifting joint, constructing an aircraft lifting scenario specifically includes:

[0015] Constructing the lifting scene during aircraft production trial;

[0016] Constructing the lifting scenario for aircraft flight tests;

[0017] Construct lifting scenarios for aircraft transfer and transportation;

[0018] Construct an aircraft lifting scenario during maintenance and support.

[0019] According to at least one embodiment of the present application, in the above-mentioned method for determining the lifting load of an aircraft lifting joint, the calculation of the load that each lifting joint needs to bear when the aircraft is lifted in each lifting scenario is specifically as follows:

[0020] Calculate the weight and center of gravity of the aircraft during lifting in various lifting scenarios;

[0021] Calculate the load that each lifting joint needs to bear based on the aircraft's weight and center of gravity in various lifting scenarios.

[0022] According to at least one embodiment of the present application, in the above-mentioned method for determining the lifting load of an aircraft lifting joint, the lifting load of each lifting joint is obtained based on the maximum load that each lifting joint needs to withstand when lifting the aircraft in various lifting scenarios, specifically:

[0023] Based on the aircraft in various lifting scenarios, the maximum load that each lifting joint needs to withstand during lifting is multiplied by the safe lifting and lifting overload factors to obtain the lifting load of each lifting joint.

[0024] According to at least one embodiment of the present application, in the above-mentioned method for determining the lifting load of the aircraft lifting joint, the safety lifting and lifting overload coefficients are within the range of 1.5 to 2.

[0025] This application has at least the following beneficial technical effects:

[0026] A method for determining the lifting load of an aircraft lifting joint is provided. The method is designed to construct an aircraft lifting scenario, calculate the maximum load that each lifting joint needs to bear when lifting the aircraft in each lifting scenario, and obtain the lifting load of each lifting joint. This lifting load is relatively small, and the lifting joint, sling, and reinforcement structure on the aircraft body designed based on this method have relatively small volume and weight, and can ensure the safe lifting of the aircraft in various lifting scenarios. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a schematic diagram of a method for determining the lifting load of an aircraft lifting joint provided in an embodiment of the present application.

[0028] In order to better illustrate this embodiment, some parts of 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 purposes and should not be understood as limitations on this patent. DETAILED DESCRIPTION

[0029] To make the technical solution and its advantages of the present application clearer, the technical solution of the present application will be described in further detail below in conjunction with the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of the present application and are only used to explain the present application, not to limit the present application. It should be noted that, for ease of description, only the parts related to the present application are shown in the accompanying drawings, and other related parts can refer to the general design. In the absence of conflict, the embodiments of the present application and the technical features in the embodiments can be combined with each other to obtain new embodiments.

[0030] In addition, unless otherwise defined, the technical or scientific terms used in the description of this application should have the ordinary meanings understood by those of ordinary skill in the art to which this application belongs. The words "upper," "lower," "left," "right," "center," "vertical," "horizontal," "inner," and "outer" used in the description of this application are only used to indicate relative directions or positional relationships, and do not imply that the device or component must have a specific orientation, be constructed, or operate in a specific orientation. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. Therefore, they should not be understood as limitations on this application. The words "first," "second," "third," and similar terms used in the description of this application are used only for descriptive purposes to distinguish different components and should not be understood to indicate or imply relative importance. The words "one," "an," or "the" used in the description of this application should not be understood as absolute limitations on quantity, but should be understood as meaning the presence of at least one. The words "include" or "comprises" used in the description of this application mean that the element or object listed before the word includes the elements or objects listed after the word and their equivalents, but does not exclude other elements or objects.

[0031] In addition, it should be noted that, unless otherwise clearly stipulated and limited, the words "install", "connect", "connect" and similar terms used in the description of this application should be understood in a broad sense. For example, the 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, an indirect connection through an intermediate medium, or a connection between two components. Technical personnel in the field can understand their specific meanings in this application according to the specific circumstances.

[0032] The following is combined with Figure 1 This application is described in further detail.

[0033] In different lifting scenarios, the weight and posture of an aircraft vary. Such differences result in different weight distribution and center of gravity positions of the aircraft during lifting in each lifting scenario. This, in turn, results in different loads that each lifting joint on the aircraft needs to bear. Based on this, an embodiment of the present application provides a method for determining the lifting load of an aircraft lifting joint, including:

[0034] Construct an aircraft lifting scene;

[0035] Calculate the load that each lifting joint needs to bear when lifting the aircraft in various lifting scenarios;

[0036] Based on the maximum load that each lifting joint needs to bear when lifting the aircraft in various lifting scenarios, the lifting load of each lifting joint is obtained.

[0037] As for the method for determining the lifting load of an aircraft lifting joint disclosed in the above-mentioned embodiment, it can be understood by those skilled in the art that its design is based on constructing an aircraft lifting scenario, calculating the maximum load that each lifting joint needs to bear when lifting the aircraft in each lifting scenario, and obtaining the lifting load of each lifting joint. This lifting load is relatively small, and the lifting joint, sling, and reinforced structure on the fuselage obtained by this design have relatively small volume and weight, and can ensure the safe lifting of the aircraft in each lifting scenario.

[0038] In some optional embodiments, in the above-mentioned method for determining the lifting load of an aircraft lifting joint, constructing an aircraft lifting scenario specifically includes:

[0039] Create a lifting scenario for aircraft production trials. In this scenario, calculate the load that each lifting joint needs to bear when lifting the aircraft. The weight of the aircraft fuel and its payload does not need to be considered. The empty weight of the aircraft can be used as the weight.

[0040] Constructing the lifting scenario for aircraft flight tests;

[0041] Construct a lifting scenario for aircraft transfer and transportation. In this scenario, the load that each lifting joint needs to bear when lifting the aircraft is calculated, without considering the weight of the aircraft's available fuel and its payload.

[0042] Construct an aircraft lifting scenario during maintenance and support. In this scenario, calculate the load that each lifting joint needs to bear when the aircraft is lifted. The aircraft weight can be taken as the aircraft's designed landing weight.

[0043] In some optional embodiments, in the above-mentioned method for determining the lifting load of an aircraft lifting joint, the calculation of the load that each lifting joint needs to bear when the aircraft is lifted in each lifting scenario is specifically as follows:

[0044] Calculate the weight and center of gravity of the aircraft during lifting in various lifting scenarios;

[0045] Calculate the load that each lifting joint needs to bear based on the aircraft's weight and center of gravity in various lifting scenarios.

[0046] In some optional embodiments, in the above-mentioned method for determining the lifting load of an aircraft lifting joint, the lifting load of each lifting joint is obtained based on the maximum load that each lifting joint needs to withstand when lifting the aircraft in various lifting scenarios, specifically:

[0047] Based on the aircraft in various lifting scenarios, the maximum load that each lifting joint needs to withstand during lifting is multiplied by the safe lifting and lifting overload factors to obtain the lifting load of each lifting joint.

[0048] In some optional embodiments, in the above-mentioned method for determining the lifting load of the aircraft lifting joint, the safety lifting and lifting overload coefficients are in the range of 1.5 to 2.

[0049] In order to make it easier for those skilled in the art to understand the technical solutions disclosed in this application, the following specific embodiments are provided:

[0050] A certain aircraft is designed with three lifting joints;

[0051] The aircraft lifting scenarios include the first lifting scenario, the second lifting scenario, the third lifting scenario, and the fourth lifting scenario.

[0052] Calculate the weight and center of gravity of the aircraft in the first lifting scenario, and obtain the load that the first lifting joint needs to bear as M 11 The second lifting joint needs to bear the load M 12 The third lifting joint needs to bear the load M 13 ;

[0053] Calculate the weight and center of gravity of the aircraft during the second lifting scenario, and obtain the load that the first lifting joint needs to bear as M 21 The second lifting joint needs to bear the load M 22 The third lifting joint needs to bear the load M 23 ;

[0054] Calculate the weight and center of gravity of the aircraft during the third lifting scenario, and obtain the load that the first lifting joint needs to bear as M 31 The second lifting joint needs to bear the load M 32 The third lifting joint needs to bear the load M 33 ;

[0055] Calculate the weight and center of gravity of the aircraft during lifting in the fourth lifting scenario, and obtain the load that the first lifting joint needs to bear as M 41 The second lifting joint needs to bear the load M 42 The third lifting joint needs to bear the load M 43 ;

[0056] In M 11 >M 21 ,M 31 ,M 41 In the case of 11 ;

[0057] In M 22 >M 12 ,M 32 ,M 42 In the case of 22 ;

[0058] In M 33 >M 13 ,M 23 ,M 43 In the case of 33 ;

[0059] in,

[0060] α is the safety lifting and lifting overload coefficient.

[0061] The various embodiments in the specification are described in a progressive manner, and each embodiment focuses on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to in detail.

[0062] So far, the technical solution of the present 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 the present application is obviously not limited to these specific embodiments. Without departing from the principles of the present application, those skilled in the art can make equivalent changes or replacements to the relevant technical features, and the technical solutions after these changes or replacements will fall within the scope of protection of the present application.

Claims

1. A method for determining the lifting load of an aircraft lifting joint, characterized in that: include: Construct an aircraft lifting scene; Calculate the load that each lifting joint needs to bear when lifting the aircraft in various lifting scenarios; Based on the maximum load that each lifting joint needs to bear during lifting in various lifting scenarios, the lifting load of each lifting joint is obtained; The lifting load of each lifting joint is obtained based on the maximum load that each lifting joint needs to bear when lifting the aircraft in various lifting scenarios, specifically: Based on the maximum load that each lifting joint needs to bear in each lifting scenario, multiply it by the safe lifting and lifting overload factors to obtain the lifting load of each lifting joint; The construction of the aircraft lifting scene specifically includes: Constructing the lifting scene during aircraft production trial; Constructing the lifting scenario for aircraft flight tests; Construct lifting scenarios for aircraft transfer and transportation; Construct an aircraft lifting scenario during maintenance and support.

2. The method for determining the lifting load of an aircraft lifting joint according to claim 1, wherein: The calculation of the load that each lifting joint needs to bear in each lifting scenario is as follows: Calculate the weight and center of gravity of the aircraft during lifting in various lifting scenarios; Calculate the load that each lifting joint needs to bear based on the aircraft's weight and center of gravity in various lifting scenarios.

3. The method for determining the lifting load of an aircraft lifting joint according to claim 1, wherein: The safety lifting and lifting overload coefficients are within the range of 1.5 to 2.

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