A structure of a bilateral support balance for measuring the influence of intake and exhaust

Abstract

A structure of a bilateral support balance for measuring the influence of intake and exhaust, belonging to the field of aerodynamics. It includes an aircraft fuselage shell, an upper cover of the intake duct, a double support balance, a bellows and a fixed support; the double support balance includes a front shell fitting section, a front intake duct, a lower cover of the intake duct, a support balance and a rear shell fitting section. The aircraft fuselage shell is connected to the double support balance through the shell fitting section. The lower cover of the intake duct is connected to the front shell fitting section. Both sides of the front shell fitting section and the rear shell fitting section are connected through the support balance. The lower cover of the intake duct is equipped with an upper cover of the intake duct. The upper cover of the intake duct and the lower cover of the intake duct jointly form a middle intake duct. The rear shell fitting section is equipped with a fixed support. The rear intake duct of the rear shell fitting section is communicated with the intake passage through a bellows. It solves the problem that there is a complete intake duct in the middle of the aircraft wing and fuselage, the internal space is narrow, the balance cannot be installed, and the measurement requirements of six-component loads cannot be met.

Description

Technical Field

[0001] The present invention relates to a double - supported balance structure for measuring the influence of intake and exhaust, belonging to the field of aerodynamics. Background Art

[0002] The wind tunnel force measurement test is the most basic test item in wind tunnel tests, and the wind tunnel balance is the direct measurement device for aerodynamic loads therein. During the development of an aircraft, the intake and exhaust of the aircraft will directly affect its aerodynamic performance. The intake duct is the interface of the aircraft propulsion system, and the influence of the intake effect on the flow of the lifting surface is particularly obvious. Through the wind tunnel test of the intake and exhaust effect, the influence amount of the intake and exhaust on the overall aerodynamic performance of the aircraft can be obtained.

[0003] Modern new - type aircraft mostly present a flattened layout with a large lifting surface, but the middle part of the fuselage is occupied by the intake duct, resulting in insufficient space for installing the balance. Therefore, in view of the flattened layout and limited middle space, the present invention proposes a double - supported balance structure for measuring the influence of intake and exhaust, which can achieve high - precision measurement of the wind tunnel test load of the intake and exhaust effect of the aircraft. Summary of the Invention

[0004] The research and development purpose of the present invention is to solve the problem that there is a complete intake duct in the middle of the wing - body of the aircraft, the internal space is narrow, the balance cannot be installed, and the measurement requirements of six - component loads cannot be met. A brief overview of the present invention is given below to provide a basic understanding of certain aspects of the present invention. It should be understood that this overview is not an exhaustive overview of the present invention. It is not intended to identify the key or important parts of the present invention, nor is it intended to limit the scope of the present invention.

[0005] The technical solution of the present invention:

[0006] A double - supported balance structure for measuring the influence of intake and exhaust includes an aircraft fuselage shell, an intake duct upper cover, a double - supported balance, a bellows, and a fixed support;

[0007] The double - supported balance includes a front shell mating section, a front intake duct, an intake duct lower cover, a support balance, and a rear shell mating section. The aircraft fuselage shell is connected and installed with the double - supported balance through the front shell mating section. The front side of the intake duct lower cover is connected to the rear side of the front shell mating section. The left and right sides of the front shell mating section and the rear shell mating section are both connected through the support balance. The support balances are symmetrically arranged on both sides of the air path as double - supports. An intake duct upper cover is installed on the top of the intake duct lower cover. The intake duct upper cover and the intake duct lower cover jointly form a middle intake duct. The front intake duct is communicated with the middle intake duct. A rear intake duct is arranged inside the rear shell mating section. A fixed support is installed at the bottom of the rear shell mating section. The bellows is installed between the intake duct upper cover and the rear shell mating section. A ventilation hole is processed on the fixed support. The front end of the rear intake duct is communicated with the middle intake duct through the bellows, and the rear end of the rear intake duct is communicated with the ventilation hole.

[0008] Preferably, a fixed end assembly surface is provided at the bottom of the rear housing fitting section, an assembly surface is machined on the fixed support, and the fixed support and the rear housing fitting section are fitted through the fixed end assembly surface and the assembly surface.

[0009] Preferably, a sealing ring is provided at the joint of the rear air inlet duct and the vent hole.

[0010] Preferably, front and rear flanges are respectively provided on both sides of the corrugated pipe. The front flange is fixedly connected to the rear ends of the upper cover and the lower cover of the air inlet duct, and the rear flange is fixedly connected to the front end of the rear housing fitting section.

[0011] Preferably, the front air inlet duct, the middle air inlet duct, the corrugated pipe, the rear air inlet duct and the vent hole together form an air intake and exhaust passage.

[0012] Preferably, there are at least two exhaust passages.

[0013] The present invention has the following beneficial effects:

[0014] 1. The corrugated pipe structure adopted by the present invention connects the rear air inlet duct and the air intake passage, avoiding affecting the stiffness of the supported balance, and realizing the ventilation function.

[0015] 2. The present invention can respectively realize the measurement of the air intake effect and the exhaust effect by changing the blocking positions of the front and rear air inlet ducts of the supported balance. By adopting the method of front air intake and rear blocking, the measurement of the air intake effect can be realized. When the front is blocked and the rear is ventilated, the measurement of the exhaust effect can be realized.

[0016] 3. The present invention integrates the balance with the air inlet duct and the outer shape of the aircraft to form an integrated balance, and realizes the measurement of the six-component aerodynamic load of the aircraft with a flat layout and a middle air inlet duct structure in a limited space.

[0017] 4. The double-supported balance of the present invention is arranged on both sides of the air inlet duct, symmetric about the neutral plane. The measured load has no eccentricity. The strain gauge pasting positions are arranged at the same cross-section before and after, and the strain gauges at the same cross-section are grouped and bridged to eliminate the internal stress of the front and rear temperature gradients. By adopting the method of combining and bridging the double-supported balances on both left and right sides, the accuracy of the balance is improved.

[0018] 5. The whole of the present invention adopts a frame-type double-supported structure, and the double-supported balance is enclosed before and after by using the outer shape. The overall rigidity is strong. Compared with the double-supported split structure, the installation repeatability error is reduced, and the repeatability of different-period tests is ensured.

[0019] 6. The present invention adopts a calibration method with fuselage loading. Different from the conventional calibration method of calibrating the balance body first and then installing the test when calibrating a balance, in the present invention, after all components such as the fuselage and bellows are assembled, the real measurement state is simulated for calibration. The assembly stress of components such as bellows is converted into internal force and eliminated during calibration, improving the accuracy of test measurement. Brief Description of the Drawings

[0020] Figure 1 is the front view of a double - support balance structure for measuring the influence of inlet and exhaust;

[0021] Figure 2 is the three - dimensional view of a double - support balance structure for measuring the influence of inlet and exhaust;

[0022] Figure 3 is the mating installation drawing of a double - support balance structure for measuring the influence of inlet and exhaust;

[0023] Figure 4 is Figure 1 the A - A sectional view of

[0024] Figure 5 is the mating installation drawing of the upper cover of the inlet duct and the double - support balance of the present invention;

[0025] Figure 6 is the mating installation drawing of the fixed support and the double - support balance of the present invention;

[0026] Figure 7 is the structural schematic diagram of the double - support balance of the present invention;

[0027] Figure 8 is the three - dimensional view of the bellows of the present invention;

[0028] Figure 9 is the three - dimensional view of the fixed support of the present invention;

[0029] Figure 10 is the three - dimensional view of the upper cover of the inlet duct of the present invention;

[0030] In the figures, 1 - outer shell of the aircraft fuselage, 2 - upper cover of the inlet duct, 3 - double - support balance, 4 - bellows, 5 - fixed support, 31 - front outer shell mating section, 32 - front inlet duct, 33 - lower cover of the inlet duct, 34 - support balance, 35 - rear outer shell mating section, 36 - middle inlet duct, 37 - rear inlet duct, 41 - front flange, 42 - rear flange, 51 - ventilation hole, 52 - assembly surface, 53 - sealing ring. Detailed Embodiments

[0031] To make the objectives, technical solutions, and advantages of the present invention more clear and understandable, the present invention will be described below through specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are merely exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, descriptions of well-known structures and technologies are omitted to avoid unnecessarily confusing the concepts of the present invention.

[0032] The connections mentioned in the present invention are divided into fixed connections and detachable connections. The fixed connection is an inseparable connection, including but not limited to conventional fixed connection methods such as hemming connection, riveting connection, bonding connection, and welding connection. The detachable connection includes but is not limited to conventional disassembly methods such as threaded connection, snap connection, pin connection, and hinge connection. When the specific connection method is not clearly defined, it is defaulted that at least one connection method can always be found among the existing connection methods to achieve this function, and those skilled in the art can choose according to their needs. For example: welding connection is selected for the fixed connection, and hinge connection is selected for the detachable connection.

[0033] Specific Embodiment 1: In combination with Figures 1 - 10 This embodiment will be described. A bilateral support balance structure for measuring the influence of intake and exhaust includes an aircraft fuselage outer shell 1, an intake duct upper cover 2, a double support balance 3, a bellows 4, and a fixed support 5;

[0034] The double support balance 3 includes a front outer shell mating section 31, a front intake duct 32, an intake duct lower cover 33, a support balance 34, and a rear outer shell mating section 35. The aircraft fuselage outer shell 1 is connected and installed with the double support balance 3 through the front outer shell mating section 31. The front side of the intake duct lower cover 33 is connected to the rear side of the front outer shell mating section 31. The left and right sides of the front outer shell mating section 31 and the rear outer shell mating section 35 are both connected through the support balance 34. The support balance 34 is symmetrically arranged on both sides of the gas path as a double support. An intake duct upper cover 2 is installed on the top of the intake duct lower cover 33. The intake duct upper cover 2 and the intake duct lower cover 33 together form a middle intake duct 36. The front intake duct 32 is communicated with the middle intake duct 36. A rear intake duct 37 is arranged inside the rear outer shell mating section 35. A fixed support 5 is installed at the bottom of the rear outer shell mating section 35. The bellows 4 is installed between the intake duct upper cover 2 and the rear outer shell mating section 35. A ventilation hole 51 is machined on the fixed support 5. The front end of the rear intake duct 37 is communicated with the middle intake duct 36 through the bellows 4, and the rear end of the rear intake duct 37 is communicated with the ventilation hole 51. The overall structure of the combination of the aircraft fuselage outer shell 1, the intake duct upper cover 2, the double support balance 3, the bellows 4, and the fixed support 5 is closed front and rear. Strain gauges are pasted on the support balances 34 on both sides to measure the six-component load, and the form of combining bridges on both sides is adopted to reduce the influence of assembly internal stress.

[0035] The front housing mating section 31 and the intake duct lower cover 33 are integrally formed, and a gap for installing a bellows is reserved between the intake duct lower cover 33 and the rear housing mating section 35.

[0036] A fixed end assembly surface is provided at the bottom of the rear housing mating section 35. An assembly surface 52 is machined on the fixed support 5. The fixed support 5 and the rear housing mating section 35 are fitted through the fixed end assembly surface and the assembly surface 52.

[0037] A sealing ring 53 is provided at the mating portion of the rear intake duct 37 and the vent hole 51 for sealing.

[0038] The front intake duct 32, the middle intake duct 36, the bellows 4, the rear intake duct 37 and the vent hole 51 together form an intake and exhaust passage, and the intake and exhaust passage diverts the air in the front intake duct 32. The exhaust passage is at least two.

[0039] The front flange 41 and the rear flange 42 are respectively provided on the front and rear sides of the bellows 4. The front flange 41 is fixedly connected to the rear ends of the intake duct upper cover 2 and the intake duct lower cover 33, and the rear flange 42 is fixedly connected to the front end of the rear housing mating section 35. Each intake and exhaust passage is connected by a bellows 4 in the middle. The bellows 4 eliminates the influence of the bellows stiffness on the measurement of the support balance 34, and at the same time seals the air flow passing through the intake and exhaust passage to prevent air leakage.

[0040] When the intake and exhaust influence measurement double support balance structure of this embodiment is used for a force measurement test, the specific method is as follows:

[0041] Combined with Figure 7 : First, complete the pasting of the support balance 34, calibrate the body of the support balance 34, and then perform the overall structure installation;

[0042] Combined with Figures 7 - 10 : During installation, first install the intake duct upper cover 2 and the double support balance 3, then compress the two bellows 4 and place them in the corresponding positions on both sides and then release, and tighten the front flange 41 and the rear flange 42.

[0043] Combined with Figures 2 - 10 : Install the sealing ring 53 on the fixed support 5, assemble it with the installed double support balance 3, complete the installation of the overall device, and perform overall calibration on the installed structure to eliminate the influence of each part of the assembly and the bellows 4 on the double support balance 3 and ensure the accuracy of the measurement result.

[0044] It should be noted that in the above embodiments, as long as the technical solutions are not contradictory, they can be arranged and combined. Those skilled in the art can exhaust all possibilities according to the mathematical knowledge of permutation and combination. Therefore, the present invention will no longer describe the technical solutions after permutation and combination one by one, but it should be understood that the technical solutions after permutation and combination have been disclosed by the present invention.

[0045] The above are only the preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included within the protection scope of the present invention.

Claims

1. A bilateral support balance structure for measuring the influence of intake and exhaust, characterized in that: It includes an aircraft fuselage outer shell (1), an upper inlet duct cover (2), a double-support balance (3), a corrugated pipe (4), and a fixed support (5); The double-support balance (3) includes a front outer shell mating section (31), a front inlet duct (32), a lower inlet duct cover (33), a support balance (34), and a rear outer shell mating section (35). The aircraft fuselage outer shell (1) is connected and installed with the double-support balance (3) through the front outer shell mating section (31). The front side of the lower inlet duct cover (33) is connected to the rear side of the front outer shell mating section (31). The left and right sides of the front outer shell mating section (31) and the rear outer shell mating section (35) are both connected through the support balance (34). The support balances (34) are symmetrically arranged on both sides of the air path as double supports. The upper inlet duct cover (2) is installed on the top of the lower inlet duct cover (33). The upper inlet duct cover (2) and the lower inlet duct cover (33) together form a middle inlet duct (36). The front inlet duct (32) is communicated with the middle inlet duct (36). A rear inlet duct (37) is arranged inside the rear outer shell mating section (35). A fixed support (5) is installed at the bottom of the rear outer shell mating section (35). The corrugated pipe (4) is installed between the upper inlet duct cover (2) and the rear outer shell mating section (35). A ventilation hole (51) is machined on the fixed support (5). The front end of the rear inlet duct (37) is communicated with the middle inlet duct (36) through the corrugated pipe (4), and the rear end of the rear inlet duct (37) is communicated with the ventilation hole (51); A fixed-end assembly surface is arranged at the bottom of the rear outer shell mating section (35). An assembly surface (52) is machined on the fixed support (5). The fixed support (5) and the rear outer shell mating section (35) are matched through the fixed-end assembly surface and the assembly surface (52); A sealing ring (53) is arranged at the mating part of the rear inlet duct (37) and the ventilation hole (51); Front flanges (41) and rear flanges (42) are respectively arranged on the front and rear sides of the corrugated pipe (4). The front flange (41) is fixedly connected to the rear ends of the upper inlet duct cover (2) and the lower inlet duct cover (33). The rear flange (42) is fixedly connected to the front end of the rear outer shell mating section (35). The intake effect measurement is realized by the way of front intake and rear blockage. When the front is blocked and the rear is ventilated, the measurement of the exhaust effect is realized.

2. The structure of a bilateral support balance for measuring the influence of intake and exhaust according to claim 1, characterized in that: The front inlet duct (32), the middle inlet duct (36), the corrugated pipe (4), the rear inlet duct (37), and the ventilation hole (51) together constitute an intake and exhaust channel.

3. A bilateral support balance structure for measuring the influence of intake and exhaust according to claim 2, characterized in that: There are at least two exhaust channels.

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