Aircraft head equivalent model fixture

Abstract

The invention relates to a device for fixing an equivalent model of an aircraft head, and relates to the field of structural strength testing of aircraft. To address the technical problem in the prior art that a device for testing and analyzing only the aircraft head structure has not yet been proposed, the present invention provides a technical solution: a device for fixing an equivalent model of an aircraft head, comprising: an aircraft head fixing cover, including a front fixing cover and two oppositely arranged fan-shaped tail fixing covers; the front fixing cover includes a circular flange, which is used to connect to the loading hole of the loading device; the tail fixing cover is connected to the front fixing cover via an end away from its own arc-shaped edge; and further comprising an aircraft head fixing bracket for fixing the aircraft head; the aircraft head fixing bracket is slidably arranged between the two tail fixing covers. The device can be used in an aircraft water impact test to fix an equivalent model of the aircraft head to simulate the effects of water impact at different angles.

Description

Technical Field

[0001] The invention relates to the field of structural strength testing of aircraft. Background Art

[0002] When a spacecraft crosses an air-water medium at high speed, its head is often subjected to enormous slamming loads, which can damage its structure and key internal components, potentially significantly impacting its ability to complete its mission objectives. Conducting high-slamming loading tests on spacecraft, especially on the head, is of great engineering significance.

[0003] Currently, common aircraft slam tests are categorized by the aircraft's motion state, typically into dynamic and static tests. Dynamic tests primarily involve high-speed impacts between aircraft and fixed structures, or high-speed crossings of air-water media. These tests often require acceleration and require larger, more complex test sites. Static tests primarily involve loading a stationary aircraft using a loading device, offering the advantages of lower site requirements and preparation costs. Furthermore, static tests allow for testing and analysis of only the aircraft's nose structure, further reducing costs. However, the prior art lacks a device for testing and analyzing only the aircraft's nose structure. Summary of the Invention

[0004] In order to solve the technical problem existing in the prior art that there is no device for testing and analyzing only the head structure of an aircraft, the technical solution provided by the present invention is as follows:

[0005] The equivalent model fixture of the aircraft head includes:

[0006] A fixed cover for the aircraft head, comprising a front fixed cover and two oppositely arranged fan-shaped tail fixed covers;

[0007] The front fixed cover includes a short cylinder and a circular flange, and the circular flange is used to connect with the loading hole of the loading device;

[0008] The tail fixed cover is connected to the short cylinder of the front fixed cover through one end away from the arc-shaped edge of the tail fixed cover;

[0009] Also included is an aircraft head fixing bracket, the aircraft head fixing bracket including an aircraft head mounting tube for fixing the aircraft head;

[0010] The aircraft head fixing support is slidably arranged between the two tail fixing covers.

[0011] Furthermore, a preferred embodiment is provided, wherein the front fixed cover is used to connect to a loading device.

[0012] Furthermore, a preferred embodiment is provided, wherein arc-shaped sliding grooves are symmetrically provided on the opposite side walls of the two tail fixed covers, the arc-shaped track of the sliding groove is consistent with the center of the circle of the fan-shaped arc edge, and two sliding blocks are relatively provided on the outer wall of the head fixed support for sliding cooperation with the sliding groove.

[0013] Furthermore, a preferred embodiment is provided, in which a limiting hole is provided at the connection between the short cylinder of the front fixed cover and the tail fixed cover, and the limiting hole is coaxial with the short cylinder of the front fixed cover and has a diameter smaller than the diameter of the aircraft head.

[0014] Furthermore, a preferred embodiment is provided in which the aircraft head fixing bracket further includes a tail sealing shell for covering the aircraft head between the two tail fixing covers.

[0015] Furthermore, a preferred embodiment is provided, in which positioning holes are evenly arranged along the arc edge on the tail fixed cover, and a positioning plate is provided on the aircraft head fixed support, and a through hole is provided on the positioning plate for cooperating with the positioning holes to fix the angle of the aircraft head relative to the short cylindrical axis of the front fixed cover.

[0016] Furthermore, a preferred embodiment is provided, wherein the device further comprises a base for supporting the aircraft head fixed cover.

[0017] Furthermore, a preferred embodiment is provided in which both the base and the aircraft head fixed cover are provided with mounting plates, and the aircraft head fixed cover is fixedly connected to the base through the mounting plates.

[0018] Furthermore, a preferred embodiment is provided, wherein the base comprises a semi-enclosed box, and the mounting plate is arranged on a side wall of the semi-enclosed box.

[0019] Furthermore, a preferred embodiment is provided in which a corner reinforcement plate is provided between the mounting piece and the semi-enclosed box.

[0020] Compared with the prior art, the technical solution provided by the present invention is beneficial in that:

[0021] The aircraft head equivalent model fixture provided by this invention addresses the need for securing the aircraft head structure and quickly adjusting the slamming angle during high-impact loading tests. Through the design of components such as the aircraft head fixing bracket, aircraft head fixing cover, and base, the aircraft head structure can be secured and the slamming angle can be adjusted according to test requirements. This allows for better simulation of the effects of slamming impacts at different angles.

[0022] The aircraft head equivalent model fixture provided by the present invention can protect sensors and their cables from the direct load of the loading device. This can prevent the loading device from damaging the sensors and their cables, thereby improving the reliability and safety of the test.

[0023] The aircraft head equivalent model fixture provided by the present invention is highly versatile and can simulate a wide range of aircraft water entry conditions. It can adapt to different load-applying devices and simulate water impacts at different angles, demonstrating high applicability and flexibility.

[0024] The aircraft head equivalent model fixture provided by this invention provides greater flexibility and convenience in addressing the issues of securing the aircraft head structure and adjusting the slamming angle. Traditional slamming testing methods often require large and complex test sites and equipment. However, this solution, through a rationally designed fixture, enables high-intensity slamming tests under static conditions, reducing test preparation costs and site requirements.

[0025] The aircraft head equivalent model fixing device provided by the present invention can only test and analyze the aircraft head structure, thereby further saving costs.

[0026] The device for securing an equivalent model of an aircraft head, provided by this invention, can be used in aircraft water impact tests to secure the equivalent model of the aircraft head and simulate the effects of impacts at different angles. This solution offers strong versatility and a wide range of simulations, making it suitable for work related to aircraft water impact tests. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] Figure 1 It is a three-dimensional schematic diagram of the fixture of the equivalent model of the aircraft head;

[0028] Figure 2 for Figure 1 Exploded diagram;

[0029] Figure 3 for Figure 1 The degree of elevation profile;

[0030] Figure 4 This is a three-dimensional schematic diagram of the aircraft head fixing bracket;

[0031] Figure 5 It is a three-dimensional schematic diagram of a head fixing cover;

[0032] Figure 6 for Figure 5 Front cross-sectional view of

[0033] Figure 7 A three-dimensional schematic diagram of the base.

[0034] Among them, 1 represents the aircraft head fixing bracket, 2 represents the aircraft head fixing cover, 3 represents the base, 4 represents the aircraft head mounting tube, 5 represents the slider, 6 represents the tail sealing shell, 7 represents the positioning plate, 8 represents the front fixing cover, 9 represents the tail fixing cover, 10 represents the limiting hole, 11 represents the sliding groove, 12 represents the positioning hole, 13 represents the mounting plate, and 14 represents the semi-enclosed box. DETAILED DESCRIPTION

[0035] In order to make the advantages and benefits of the technical solution provided by the present invention more clearly reflected, the technical solution provided by the present invention is now further described in detail with reference to the accompanying drawings, specifically:

[0036] Embodiment 1: This embodiment provides a device for fixing an equivalent model of a head of an aircraft, including:

[0037] A fixed cover for the aircraft head, comprising a front fixed cover and two oppositely arranged fan-shaped tail fixed covers;

[0038] The front fixed cover includes a short cylinder and a circular flange, and the circular flange is used to connect with the loading hole of the loading device;

[0039] The tail fixed cover is connected to the short cylinder of the front fixed cover through one end away from the arc-shaped edge of the tail fixed cover;

[0040] Also included is an aircraft head fixing bracket, the aircraft head fixing bracket including an aircraft head mounting tube for fixing the aircraft head;

[0041] The aircraft head fixing support is slidably arranged between the two tail fixing covers.

[0042] Embodiment 2: This embodiment further limits the aircraft head equivalent model fixing device provided in Embodiment 1, and the front fixing cover is used to connect the loading device.

[0043] Implementation method three. This implementation method further limits the aircraft head equivalent model fixing device provided in implementation method one. Arc-shaped sliding grooves are symmetrically provided on the opposite side walls of the two tail fixing covers. The arc-shaped track of the sliding groove is consistent with the center of the circle of the fan-shaped arc edge. Two sliding blocks are relatively provided on the outer wall of the head fixing support for sliding cooperation with the sliding groove.

[0044] Implementation method 4. This implementation method further limits the aircraft head equivalent model fixing device provided in implementation method 1. A limiting hole is provided at the connection between the short cylinder of the front fixed cover and the tail fixed cover. The limiting hole is coaxial with the short cylinder of the front fixed cover and has a diameter smaller than the diameter of the aircraft head.

[0045] Embodiment 5. This embodiment further limits the aircraft head equivalent model fixing device provided in embodiment 1. The aircraft head fixing bracket further includes a tail sealing shell for covering the aircraft head between the two tail fixing covers.

[0046] Implementation method six. This implementation method further limits the aircraft head equivalent model fixing device provided in implementation method one. The tail fixing cover is provided with positioning holes evenly arranged along the arc edge, and the aircraft head fixing support is provided with a positioning plate. The positioning plate is provided with a through hole for cooperating with the positioning hole to fix the angle of the aircraft head relative to the short cylindrical axis of the front fixing cover.

[0047] Embodiment 7: This embodiment further limits the aircraft head equivalent model fixing device provided in embodiment 1. The device further includes a base for supporting the aircraft head fixing cover.

[0048] Implementation 8. This implementation further limits the aircraft head equivalent model fixing device provided in Implementation 7. Both the base and the aircraft head fixing cover are provided with mounting plates, and the aircraft head fixing cover is fixedly connected to the base through the mounting plates.

[0049] Implementation method 9. This implementation method further limits the aircraft head equivalent model fixing device provided in implementation method 8. The base includes a semi-enclosed box, and the mounting plate is arranged on the side wall of the semi-enclosed box.

[0050] Implementation 10. This implementation further limits the aircraft head equivalent model fixing device provided in Implementation 9, wherein a corner reinforcement plate is provided between the mounting plate and the semi-enclosed box.

[0051] Implementation Method 11: Combination Figure 1-7 This embodiment is described in detail. The technical solution provided above is clearly and completely described through specific examples. Specifically:

[0052] The equivalent model fixture of the aircraft head includes:

[0053] Aircraft head fixing bracket 1, aircraft head fixing cover 2, and base 3. During testing, the aircraft head structure is screwed to the front of the aircraft head fixing bracket 1; the aircraft head structure and aircraft head fixing bracket 1 are installed from the rear into the sliding groove inside the head fixing cover 2; a square base 3 is set below the head fixing cover 2; a flange is set in front of the head fixing cover 2 to connect to the loading hole flange of the loading device.

[0054] The aircraft head fixing bracket 1 is composed of an aircraft head mounting tube 4, a slider 5, a tail sealing shell 6, and a positioning plate 7. The aircraft head mounting tube 4 is similar to the front end of the aircraft mid-section structure. Lateral threaded holes are arranged on the sidewall of the front end of the mounting tube, and the aircraft head structure can be installed on the front end of the aircraft head mounting tube 4 using screws. The slider 5 is located on the left and right sides of the aircraft head mounting tube 4. The tail sealing plate 6 is located at the tail end of the aircraft head mounting tube 4, and an opening is provided at the connection with the aircraft head mounting tube 4 to ensure that the sensors and cables arranged inside the aircraft head structure are not affected by the direct load of the loading device. The positioning plates 7 are located on both sides of the outside of the tail sealing plate 6.

[0055] The head fixing cover 2 is composed of a front fixing cover 8, a tail fixing cover 9, a limiting hole 10, a sliding groove 11, a positioning hole 12, and a mounting plate 13. The front fixing cover 8 is a short cylinder with a flange, and the tail fixing cover 9 is a semi-enclosed box; a limiting hole 10 is set between the front fixing cover 8 and the tail fixing cover 9; a sliding groove 11 is set on the side wall of the tail fixing cover 9 so that the slider 5 can slide freely inside. The sliding groove 11 is arc-shaped, and the center of the arc is on the same horizontal line as the center of the front structure of the aircraft, so that when the slider slides, the aircraft only rotates in the vertical plane without displacement; a positioning hole 12 is set on the rear side wall of the tail fixing cover 9. After the circular hole of the positioning plate 7 is aligned with the positioning hole 12, it is fixed by bolts, so that the aircraft head structure can be fixed at different angles.

[0056] The base 3 is composed of a mounting plate 13 and a box body 14, wherein the head fixing cover 2 and the base 3 can be fixedly installed by bolts through the circular holes on the mounting plate 13; the box body 14 is a semi-enclosed square box body; in order to ensure the strength of the connection structure, a gusset plate is provided between the bottom of the mounting plate 13 and the outer wall of the box body 14 for reinforcement.

[0057] During the test, the installation process of the aircraft head equivalent model fixing device of the present invention is as follows:

[0058] Step 1: The aircraft head structure is first fixed to the aircraft head mounting tube 4 of the aircraft head fixing bracket 1 through the side wall threaded holes;

[0059] Step 2: Place the connecting structure installed in step 1 horizontally, align the slider 5 with the notch of the sliding groove 11 of the head fixed cover 2, and push it into the sliding groove 11;

[0060] Step 3: According to the test working condition requirements, push the slider 5 in the sliding groove 11, select a suitable impact angle of the aircraft structure, and fix the aircraft equivalent structure through the positioning holes;

[0061] Step 4: Install the head fixing cover 2 on the base 3 through the mounting piece 13;

[0062] Step 5: Align the flange of the front fixed cover 8 with the loading hole of the loading device, and use bolts to fix the aircraft head equivalent device of the present invention to the loading device;

[0063] Step 6: Arrange the sensor inside the equivalent structure of the aircraft head through the opening at the rear of the aircraft head fixing bracket 1;

[0064] Step 7: The loading device releases the load to complete the slamming load loading.

[0065] In the above step 5, the schematic diagram of the aircraft head equivalent model fixture fixedly installed on the loading device is as follows: Figure 1 shown.

[0066] The above further describes the technical solution provided by the present invention in detail through several specific embodiments in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the several specific embodiments described above are not intended to limit the present invention. Any reasonable modification and improvement of the present invention, combination of embodiments and equivalent replacement based on the spirit and principles of the present invention should be included in the scope of protection of the present invention.

[0067] The descriptions in this specification refer only to preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Furthermore, reference to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples" implies that a specific feature, structure, material, or characteristic described in conjunction with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative descriptions of these terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in any one or N embodiments or examples. Furthermore, those skilled in the art may combine and integrate the different embodiments or examples described in this specification, as well as features from different embodiments or examples, unless otherwise specified. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed to indicate or imply relative importance or to implicitly specify the number of the technical features indicated. Therefore, features designated "first" or "second" may explicitly or implicitly include at least one of these features. In the description of the present invention, "N" means at least two, for example, two, three, etc., unless otherwise specifically defined. Any process or method description in a flowchart or otherwise described herein can be understood to represent a module, segment, or portion of code comprising one or more executable instructions for implementing a custom logic function or process, and the scope of the preferred embodiments of the present invention includes alternative implementations in which functions may be performed in a different order than shown or discussed, including substantially simultaneously or in reverse order depending on the functions involved, as will be understood by those skilled in the art to which the embodiments of the present invention pertain. The logic and / or steps represented in a flowchart or otherwise described herein, for example, can be considered as a sequenced list of executable instructions for implementing a logic function, can be embodied in any computer-readable medium for use by an instruction execution system, apparatus, or device (e.g., a computer-based system, a system including a processor, or other system that can fetch and execute instructions from an instruction execution system, apparatus, or device), or in conjunction with such instruction execution systems, apparatuses, or devices. For purposes of this specification, a "computer-readable medium" can be any device that can contain, store, communicate, propagate, or transmit a program for use by an instruction execution system, apparatus, or device, or in conjunction with such instruction execution systems, apparatuses, or devices. More specific examples (a non-exhaustive list) of computer-readable media include the following: an electrical connection having one or N wirings (electronic devices), a portable computer disk cartridge (magnetic devices), random access memory (RAM), read-only memory (ROM), erasable and programmable read-only memory (EPROM or flash memory), fiber optic devices, and portable compact disc read-only memory (CDROM).In addition, the computer-readable medium may even be paper or other suitable medium on which the program can be printed, because the program can be obtained electronically, for example, by optically scanning the paper or other medium, then editing, interpreting, or processing in other suitable ways as necessary, and then storing it in a computer memory. It should be understood that the various parts of the present invention can be implemented with hardware, software, firmware, or a combination thereof. In the above embodiment, the N steps or methods can be implemented with software or firmware stored in a memory and executed by a suitable instruction execution system. For example, if implemented with hardware, as in another embodiment, any one of the following technologies known in the art or their combination can be used to implement: a discrete logic circuit having a logic gate circuit for implementing a logic function on a data signal, a dedicated integrated circuit having a suitable combination of logic gate circuits, a programmable gate array (PGA), a field programmable gate array (FPGA), etc.

[0068] Those skilled in the art will appreciate that all or part of the steps carried out in the above-mentioned embodiment method can be completed by instructing the relevant hardware through a program, and the program can be stored in a computer-readable storage medium, which, when executed, includes one or a combination of the steps of the method embodiment. In addition, the functional units in the various embodiments of the present invention can be integrated into a processing module, or each unit can exist physically alone, or two or more units can be integrated into one module. The above-mentioned integrated module can be implemented in the form of hardware or in the form of a software functional module. If the integrated module is implemented in the form of a software functional module and sold or used as an independent product, it can also be stored in a computer-readable storage medium.

Claims

1. The aircraft head equivalent model fixture is characterized by: include: A fixed cover for the aircraft head, comprising a front fixed cover and two oppositely arranged fan-shaped tail fixed covers; The front fixed cover is used to connect the loading device; The front fixed cover includes a short cylinder and a circular flange, and the circular flange is used to connect with the loading hole of the loading device; The tail fixed cover is connected to the short cylinder of the front fixed cover through one end away from the arc-shaped edge of the tail fixed cover; Also included is an aircraft head fixing bracket, the head fixing bracket including an aircraft head mounting tube for fixing the aircraft head; The head fixing support is slidably arranged between the two tail fixing covers; Among them, a sliding groove is set on the side wall of the tail fixed cover so that the slider can slide freely inside. The sliding groove is arc-shaped, and the center of the arc is on the same horizontal line as the center of the front structure of the spacecraft; A positioning hole is set at the rear of the side wall of the tail fixed cover. After the circular hole of the positioning plate is aligned with the positioning hole, it is fixed with bolts; It also includes: a tail sealing plate, located at the tail end of the aircraft head mounting tube, and having an opening at the connection with the aircraft head mounting tube; The two tail fixing covers are symmetrically provided with arc-shaped sliding grooves on the opposite side walls, and the arc track of the sliding grooves is consistent with the center of the arc edge of the fan-shaped circle. The outer wall of the head fixing bracket is provided with two sliders for slidingly cooperating with the sliding grooves. The tail fixed cover is provided with positioning holes arranged evenly along the arc edge, and the aircraft head fixed support is provided with a positioning plate, and the positioning plate is provided with a through hole for cooperating with the positioning holes to fix the angle of the aircraft head relative to the short cylindrical axis of the front fixed cover.

2. The aircraft head equivalent model fixing device according to claim 1, characterized in that: A limiting hole is provided at the connection between the short cylinder of the front fixed cover and the tail fixed cover. The limiting hole is coaxial with the short cylinder of the front fixed cover and has a diameter smaller than the diameter of the aircraft head.

3. The aircraft head equivalent model fixing device according to claim 1, characterized in that: The aircraft head fixing bracket further comprises a tail sealing shell, which is used for covering the aircraft head between the two tail fixing covers.

4. The aircraft head equivalent model fixing device according to claim 1, characterized in that: The device further comprises a base for supporting the aircraft head fixed cover.

5. The aircraft head equivalent model fixing device according to claim 4, characterized in that: The base and the aircraft head fixing cover are both provided with mounting pieces, and the aircraft head fixing cover is fixedly connected to the base through the mounting pieces.

6. The aircraft head equivalent model fixing device according to claim 5, characterized in that: The base includes a semi-enclosed box body, and the mounting piece is arranged on a side wall of the semi-enclosed box body.

7. The aircraft head equivalent model fixing device according to claim 6, characterized in that: A corner reinforcement plate is provided between the mounting piece and the semi-enclosed box body.

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