Dynamic impact energy measuring device, aircraft flap assembly and dynamic impact energy measuring method

Abstract

The dynamic impact energy measuring device is used for measuring impact energy generated by relative movement between a first component and a second component, and comprises a first connecting piece used for being connected with the first component; the second connecting piece is used for being connected with a second component, and the first connecting piece and the second connecting piece can generate impact movement relative to each other in the impact direction; the energy absorption device is arranged between the first connecting piece and the second connecting piece, can bear load due to relative movement of the first connecting piece and the second connecting piece in at least one part of stroke of relative movement of the first connecting piece and the second connecting piece, and is constructed to be capable of absorbing impact energy due to at least partial deformation of the load; and the sensing assembly is arranged to measure the borne load amount and the generated deformation amount of the energy absorption device respectively. The device can design the diameter / height and thickness of the energy absorption core body based on the bearing capacity of the machine body structure so as to realize overload protection of the machine body structure. The invention also relates to an aircraft flap assembly and a dynamic impact energy measurement method.

Description

Technical Field

[0001] The invention relates to the field of aircraft design and manufacturing, and more specifically to a dynamic impact energy measuring device with overload protection, which is used for measuring dynamic impact energy, and to an aircraft flap assembly and a method for measuring dynamic impact energy. Background Art

[0002] The failure of a single actuator of a civil aircraft flap to be disengaged is a scenario that must be considered during the aircraft design process. Airworthiness regulations require that single failures of such systems must be considered in the design, no matter how low the probability of failure is. Generally, a cross-linking device can be added between the inner and outer flaps, and the inner and outer flaps can be connected by the cross-linking device, which can reduce the inclination of the flap surface, thereby reducing the impact of the rolling moment on the control stability and achieving safe flight of the aircraft.

[0003] When designing the flap cross-linking device, it is necessary to obtain the dynamic impact energy that the flap cross-linking device needs to absorb after the aircraft flap actuator is disengaged. This is an important input for designing the flap cross-linking device. Because the flap wing surface and its supporting mechanism will undergo complex deformation in this fault scenario, the current desktop simulation cannot accurately simulate this fault scenario. The fault scenario can be simulated through ground tests. In the test, a device needs to be designed to measure the dynamic impact energy of the flap cross-linking device after the single flap actuator is disengaged. At the same time, it is necessary to ensure that the impact loads of the inner and outer flaps are limited to a safe range to ensure the structural safety of the inner and outer flaps.

[0004] The impact energy can be measured on a special drop hammer test bench, that is, the impact energy of the drop hammer is calculated based on the weight and height of the drop hammer. It can also be measured based on the impact energy calculation formula, that is, the impact energy is equal to the impact load multiplied by the displacement of the object caused by the impact. Usually, force sensors and high-speed displacement sensors are used to measure the impact load and displacement respectively, and the impact energy can be obtained by integrating the load-displacement.

[0005] The above two methods are not suitable for measuring the impact energy after the single flap actuator of a civil aircraft is disengaged. Due to the effect of the aerodynamic load of this fault scenario, the flap wing surface will generate a huge impact force. If the impact load and displacement information of the flap actuator disengagement process are directly measured, the inner and outer flap structures may be damaged. In order to ensure the structural safety, the present invention designs an impact energy measurement device with overload protection between the inner and outer flaps to measure the energy during the impact process, which is safe and efficient.

[0006] In the prior art, there is no device that can realize dynamic measurement after the single flap actuator is disengaged. For example, the inner and outer flap cross-linking device of CN107161325B and the inter-flap cross-linking device of CN112678151A can only realize the energy absorption and stopping function, but do not have the dynamic impact energy measurement function, and the energy absorption method is also difficult to meet the measurement requirements. Summary of the invention

[0007] The present invention therefore provides a dynamic impact energy measuring device, which is used to measure the impact energy generated by the relative movement between a first component and a second component.

[0008] Wherein, the measuring device comprises:

[0009] a first connecting member, the first connecting member being used to connect with the first component;

[0010] a second connecting member, the second connecting member being used to connect with the second component, wherein the first connecting member and the second connecting member are configured to be able to generate an impact movement relative to each other along an impact direction;

[0011] an energy absorbing device, the energy absorbing device being disposed between the first connecting member and the second connecting member and being capable of bearing a load due to the relative movement of the first connecting member and the second connecting member during at least a portion of the stroke of the relative movement of the first connecting member and the second connecting member, and being configured to absorb the impact energy by at least partially deforming due to the load; and

[0012] A sensing component is arranged to respectively measure the load borne and the deformation occurred by the energy absorbing device.

[0013] According to a preferred embodiment of the measuring device of the present invention, the second connecting member includes a shaft section, a flange is provided at one end of the shaft section close to the first connecting member, the first connecting member is provided with a bridging section which spans the flange and is sleeved on the shaft section, and the energy absorbing device is arranged between the shaft section and the bridging section.

[0014] According to a preferred embodiment of the measuring device of the present invention, the energy absorbing device comprises a segmented tubular member sleeved on the shaft section, the segmented tubular member comprises at least two segments with different diameters, and steps are provided between different segments.

[0015] According to a preferred embodiment of the measuring device of the present invention, the energy absorbing device comprises an energy absorbing pad disposed at at least one end of the segmented tubular member.

[0016] According to a preferred embodiment of the measuring device of the present invention, the sensing component includes a strain gauge arranged on the first connecting member and / or the second connecting member.

[0017] According to a preferred embodiment of the measuring device of the present invention, the sensing component comprises a laser displacement sensing component, and the laser displacement sensing component comprises:

[0018] A laser emitting portion fixedly mounted on one of the first connecting member and the second connecting member and used for emitting laser light along a laser direction;

[0019] a laser receiving unit fixed relative to the laser emitting unit and configured to receive laser light; and

[0020] A reflector is fixedly mounted on the other of the first connecting member and the second connecting member, wherein the reflector is configured to reflect the laser light from the laser emitting portion to the laser receiving portion.

[0021] According to a preferred embodiment of the measuring device of the present invention, it further comprises at least one set of positioning pins, wherein the positioning pins are detachably inserted into the bridging section.

[0022] The positioning pin is configured to respectively abut against two side surfaces of the flange in the impact direction so that the first connecting member can be fixed relative to the second connecting member in the impact direction through the positioning pin.

[0023] In addition, the present invention also provides an aircraft flap assembly, comprising:

[0024] Inner flaps;

[0025] an outer flap located outboard of the inner flap in the spanwise direction; and

[0026] Measuring device according to the preceding paragraph, wherein the first component is the inner flap and the second component is the outer flap.

[0027] According to a preferred embodiment of the aircraft flap assembly of the present invention, the first connecting member is pivotally connected to the span-wise outer end of the inner flap, and the second connecting member is pivotally connected to the span-wise inner end of the outer flap.

[0028] Furthermore, the invention also relates to a method for dynamic impact energy measurement using a measuring device according to the above,

[0029] The method comprises the following steps in sequence:

[0030] installing the measuring device between the first component and the second component;

[0031] After the installation is completed, the positioning pin is removed so that the first connecting member can move freely relative to the second connecting member;

[0032] performing a relative impact movement of the first component with respect to the second component; and

[0033] During the impact movement, the load borne by the energy absorbing device and the deformation occurred are measured respectively by the sensing component.

[0034] In summary, the present invention designs a flip tube energy-absorbing core with a polyurethane gasket, which can easily design the diameter / height and thickness of the energy-absorbing core based on the bearing capacity of the body structure, so that the load can be quickly increased to near the design load after bearing, and a load platform is formed to ensure that the dynamic impact load does not exceed the bearing capacity of the body structure strength, thereby realizing overload protection of the body structure.

[0035] In addition, the present invention forms a set of dynamic impact energy measuring devices. The measuring device of the present invention can measure the impact energy between adjacent structures. Since the measuring device is designed with a free stroke, it can ensure that the adjacent rudder surfaces are not constrained by the device under normal circumstances. When any structure fails to disengage, the free stroke decreases until it disappears, and the energy absorbing core begins to absorb energy by impact. At this time, the deformation and load of the energy absorbing core are measured respectively by a high-speed laser displacement sensor and a strain gauge, and the impact energy is obtained by load-displacement integration.

[0036] In the aircraft flap single actuator disengagement failure scenario, direct energy measurement cannot be achieved due to the large flap wing surface load and limited modification space. For this reason, the present invention collects the displacement and load of the impact energy measuring device through high frequency, obtains the impact energy after the flap single actuator is disengaged by integrating the displacement and load, and cleverly designs a dynamic impact energy measuring device with overload protection. The device of the present invention has a simple structure and has the advantages of convenient modification, accurate measurement, and easy operation. At the same time, it can realize the free stroke measurement of the flap cross-linking device and the dynamic impact energy measurement function, and the accuracy is sufficient to meet the test requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] This document includes the accompanying drawings to provide a further understanding of the various embodiments, and the accompanying drawings are incorporated in and constitute a part of this specification.

[0038] The drawings illustrate the various embodiments described herein, and together with the description serve to explain the principles and operations of the claimed subject matter.

[0039] With reference to the above objects, the technical features of the present invention are clearly described hereinafter, and advantages thereof are apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the present invention by way of example without limiting the scope of the present invention.

[0040] In the attached figure:

[0041] Figure 1 1 is a schematic plan view of a preferred embodiment of a dynamic impact energy measuring device according to the present invention.

[0042] Figure 2 yes Figure 1 A three-dimensional schematic diagram of the energy absorption device of a preferred embodiment of the dynamic impact energy measuring device shown in FIG.

[0043] Figure 3 1 is a schematic top view of an aircraft flap assembly including a dynamic impact energy measuring device according to the present invention.

[0044] Figure 4 The load-time diagram is shown during an exemplary operation of the measuring device according to the invention.

[0045] Figure 5 A load-displacement diagram is shown during an exemplary operation of the measuring device according to the invention.

[0046] Reference numerals list

[0047] 10 Inner flap

[0048] 20 Outer flaps

[0049] 100 Measuring devices

[0050] 110 First connecting piece

[0051] 111 Crossover section

[0052] 120 Second connecting piece

[0053] 121 Shaft section

[0054] 122 Flange

[0055] 130 Energy absorbing device

[0056] 131 pipe section

[0057] 132 pipe section

[0058] 133 Steps

[0059] 134 Energy absorbing pad

[0060] 141 Strain gauge

[0061] 142 Laser emission unit

[0062] 143 Laser receiving unit

[0063] 144 Reflective parts

[0064] 150 Locating pin

[0065] X impact direction DETAILED DESCRIPTION

[0066] Reference will now be made in detail to embodiments of the present invention, examples of which are illustrated in the accompanying drawings and described below.

[0067] Although the present invention will be described in conjunction with exemplary embodiments, it should be appreciated that this specification is not intended to limit the present invention to those exemplified embodiments. On the contrary, the present invention is intended to cover not only these exemplary embodiments, but also various alternative forms, modifications, equivalent forms and other embodiments that may be included within the spirit and scope of the present invention.

[0068] To facilitate explanation and accurately define the technical solutions of the present invention, the terms “upper”, “lower”, “inner” and “outer” are used to describe features of the exemplary embodiments shown in the drawings with reference to their positions.

[0069] Various preferred but non-limiting embodiments of the measuring device, the flap assembly including the measuring device, and the measuring method of the present invention are described in detail below with reference to the accompanying drawings.

[0070] like Figure 1 As shown in the figure, the present invention provides a dynamic impact energy measuring device 100. The measuring device 100 is used to measure the impact energy generated by the relative movement between the first component and the second component. The measuring device 100 includes: a first connecting member 110, a second connecting member 120, an energy absorbing device 130 and a sensing component.

[0071] The first connecting member 110 is used to connect with the first component.

[0072] The second connecting member 120 is used to be connected to the second component, wherein the first connecting member 110 and the second connecting member 120 are configured to be able to generate an impact movement along the impact direction X relative to each other.

[0073] The second connecting member 120 may preferably include a shaft section 121, and a flange 122 is provided at one end of the shaft section 121 close to the first connecting member 110. The first connecting member 110 is provided with a bridging section 111 which is sleeved on the shaft section 121 across the flange 122, and the energy absorbing device 130 is arranged between the shaft section 121 and the bridging section 111.

[0074] The energy absorbing device 130 is arranged between the first connecting member 110 and the second connecting member 120, and can bear the load due to the relative movement of the first connecting member 110 and the second connecting member 120 during at least a part of the stroke of the relative movement between the two, and is configured to absorb impact energy by at least partially deforming due to the load.

[0075] The energy absorbing device 130 may preferably include a segmented tubular member sleeved on the shaft section 121 , wherein the segmented tubular member includes at least two tube sections 131 , 132 with different diameters, and a step portion 133 is provided between different tube sections.

[0076] The energy absorbing device 130 may further include an energy absorbing pad 134 disposed at at least one end of the segmented tubular member.

[0077] The sensing assembly is arranged to respectively measure the amount of load borne and the amount of deformation occurring to the energy absorbing device.

[0078] The sensing component may preferably include a strain gauge 141 disposed on the first connector 110 and / or the second connector 120 .

[0079] The sensing component may also preferably include a laser displacement sensing component, which includes: a laser emitting unit 142 , a laser receiving unit 143 and a reflective element 144 .

[0080] The laser emitting portion 142 is fixedly mounted on one of the first connecting member 110 and the second connecting member 120 and is used for emitting laser light along a laser direction.

[0081] The laser receiving unit 143 is fixed relative to the laser emitting unit 142 and is used to receive laser light.

[0082] The reflector 144 is fixed on the other of the first connecting member 110 and the second connecting member 120 . The reflector 144 is configured to reflect the laser light from the laser emitting portion 142 to the laser receiving portion 143 .

[0083] The measuring device 100 may also preferably include at least one group of positioning pins 150, which can be detachably inserted into the bridging section 111, wherein the positioning pins 150 are configured to keep the first connecting member 110 fixed relative to the second connecting member 120 in the impact direction X by respectively abutting against the two side surfaces of the flange 122 in the impact direction X.

[0084] refer to Figure 2 The present invention also provides an aircraft flap assembly, comprising: an inner flap 10 , an outer flap 20 and the aforementioned measuring device 100 .

[0085] The reflector 144 is located outside the inner flap 10 in the span direction. The first component is the inner flap 10 , and the second component is the outer flap 20 .

[0086] Preferably, the first connection member 110 is pivotally connected to the span-wise outer end of the inner flap 10 , and the second connection member 120 is pivotally connected to the span-wise inner end of the outer flap 20 .

[0087] A method for measuring dynamic impact energy using the measuring device 100 according to the present invention is described below.

[0088] The method comprises the following steps in sequence:

[0089] Installing the measuring device 100 between the first component and the second component;

[0090] After the installation is completed, the positioning pin 150 is removed so that the first connecting member 110 can move freely relative to the second connecting member 120;

[0091] Implementing a relative impact movement of the first component with respect to the second component; and

[0092] During the impact movement, the load borne by the energy absorbing device 130 and the deformation occurred are measured respectively by the sensing component.

[0093] In summary, the structure diagram of a dynamic impact energy measuring device 100 with overload protection designed by the present invention is as follows: Figure 1 The measuring device 100 is installed between the inner and outer flaps 10 and 20 through the first joint and the second joint. The installation diagram is shown in Figure 2 . The first joint of the measuring device 100 is installed on the inner flap 10, and the second joint is installed on the outer flap 20. After the installation is completed, the positioning pin 150 is pulled out. When the test load reaches the predetermined load, the crank loses the rotation constraint through the flap actuator disengagement device to simulate the flap single actuator disengagement failure. After disengagement, the second connecting rod 120 can move axially within the free travel range. When the flange 120 at the bottom of the second connecting rod 120 contacts the energy absorption device 130 including the flip tube and the polyurethane gasket 134 in the bridging section 111 in the form of a sleeve, under the huge transient impact load, the initial load peak is reduced by the polyurethane gasket 134, and the initial deformation of the flip tube The zone begins to deform and absorb energy. At this time, the strain gauge 141 can measure the axial load on the cross-linking device. The laser displacement sensor emits laser and hits the reflective member 144, such as a reflective board, and then reflects. The reflective board is fixed by a reflective board bracket. The data transmission end of the laser displacement sensor transmits data to the data acquisition system for high-frequency acquisition, thereby measuring the stroke change of the cross-linking device and the deformation data of the energy-absorbing core. Based on the displacement and load data of the energy-absorbing core, the impact energy between the inner and outer flaps after the flap single actuator is disengaged can be finally obtained by integrating the displacement and the load.

[0094] The following briefly describes the preferred measurement method according to the present invention:

[0095] 1) The inventive device is installed between the inner and outer flaps, such as Figure 3 As shown;

[0096] 2) After installation, pull out the positioning pin of the flap cross-linking device;

[0097] 3) Apply aerodynamic loads to the flap surface;

[0098] 4) When the wing surface load reaches the test setting value, the flap single actuator is controlled to disengage;

[0099] 5) The flap cross-linking device starts continuous high-speed acquisition (including displacement and strain).

[0100] By implementing the present invention, the energy absorbing core can bear load stably, the load can be quickly increased and form a load platform. Figure 4 , the impact energy can be obtained by integrating the load-displacement, that is, Figure 5 The area enclosed by the curve.

[0101] Preferred embodiments of the present invention have been described above in detail, but it should be understood that aspects of the embodiments can be modified, if necessary, to employ aspects, features and concepts of the various patents, applications and publications to provide further embodiments.

[0102] Various changes can be readily appreciated in light of the above detailed description, and can be made to the embodiments described herein.

[0103] In general, in the claims, the terms used should not be considered limited to the specific embodiments disclosed in the specification and the claims, but should be construed to include all possible embodiments along with the full scope of equivalents to which the claims are entitled.

Claims

1. A dynamic impact energy measuring device (100), the measuring device (100) being used to measure the impact energy generated by the relative movement between a first component and a second component, in, The measuring device (100) comprises: A first connecting member (110), the first connecting member (110) being used to connect to the first component; a second connecting member (120), the second connecting member (120) being used for connecting to the second component, wherein the first connecting member (110) and the second connecting member (120) are configured to be capable of performing an impact movement relative to each other along an impact direction (X); an energy absorbing device (130), the energy absorbing device (130) being arranged between the first connecting member (110) and the second connecting member (120), and being capable of bearing a load due to the relative movement of the first connecting member (110) and the second connecting member (120) during at least a portion of the stroke of the relative movement of the first connecting member (110) and the second connecting member (120), and being configured to absorb the impact energy by at least partially deforming due to the load; and A sensing component is arranged to respectively measure the load borne and the deformation occurred by the energy absorbing device.

2. The measuring device (100) according to claim 1, It is characterized in that The second connecting member (120) comprises a shaft section (121), and a flange (122) is provided at one end of the shaft section (121) close to the first connecting member (110). The first connecting member (110) is provided with a bridging section (111) which spans over the flange (122) and is sleeved on the shaft section (121). The energy absorbing device (130) is arranged between the shaft section (121) and the bridging section (111).

3. The measuring device (100) according to claim 2, It is characterized in that The energy absorbing device (130) comprises a segmented tubular member sleeved on the shaft section (121), wherein the segmented tubular member comprises at least two tube sections (131, 132) with different diameters, and a step portion (133) is provided between different tube sections.

4. The measuring device (100) according to claim 3, It is characterized in that The energy absorbing device (130) comprises an energy absorbing pad (134) arranged at at least one end of the segmented tubular member.

5. The measuring device (100) according to claim 1, It is characterized in that The sensing component comprises a strain gauge (141) arranged on the first connecting member (110) and / or the second connecting member (120).

6. The measuring device (100) according to claim 1, It is characterized in that The sensing component includes a laser displacement sensing component, and the laser displacement sensing component includes: a laser emitting portion (142) fixedly mounted on one of the first connecting member (110) and the second connecting member (120) and used for emitting laser light along a laser direction; a laser receiving unit (143) fixed relative to the laser emitting unit (142) and used for receiving laser light; and A reflective member (144) is fixedly mounted on the other of the first connecting member (110) and the second connecting member (120), wherein the reflective member (144) is configured to reflect laser light from the laser emitting portion (142) to the laser receiving portion (143).

7. The measuring device (100) according to claim 2, It is characterized in that It also includes at least one set of positioning pins (150), wherein the positioning pins (150) are detachably inserted into the bridging section (111). The positioning pin (150) is configured to respectively abut against two side surfaces of the flange (122) in the impact direction (X), thereby enabling the positioning pin (150) to keep the first connecting member (110) fixed relative to the second connecting member (120) in the impact direction (X).

8. An aircraft flap assembly, comprising: Inner flap (10); An outer flap (20) located outside the inner flap (10) in the span direction; as well as The measuring device (100) according to any one of claims 1 to 7, wherein the first component is the inner flap (10) and the second component is the outer flap (20).

9. The aircraft flap assembly according to claim 8, It is characterized in that The first connecting member (110) is pivotally connected to the span-wise outer end of the inner flap (10), and the second connecting member (120) is pivotally connected to the span-wise inner end of the outer flap (20).

10. A method for measuring dynamic impact energy using the measuring device (100) according to claim 7, in, The method comprises the following steps in sequence: Installing the measuring device (100) between the first component and the second component; After the installation is completed, the positioning pin (150) is removed so that the first connecting member (110) can move freely relative to the second connecting member (120); performing a relative impact movement of the first component with respect to the second component; and During the impact movement, the load amount borne by the energy absorbing device (130) and the deformation amount occurred are respectively measured by the sensing component.

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