A device for measuring a twin-engine ventilation model with both tension wire support and tail support

Abstract

A device that takes into account both wire support and tail support for the measurement of a twin-engine ventilated model, belonging to the technical field of special support model design for wind tunnel tests. The present invention includes a model body and a support device. The support device includes a wire support and a tail support. A wire support is arranged on the model body, and a tail support is detachably installed at the tail of the model body. The tail support includes a tail support mechanism and a tail support rod. The model body includes a wing assembly, a front fuselage assembly, a middle fuselage assembly, an inlet duct assembly, and a rear fuselage assembly. The front fuselage assembly and the rear fuselage assembly are respectively installed on the front and rear sides of the middle fuselage assembly. Wing assemblies are installed on both the left and right sides of the middle fuselage assembly. The inlet duct assembly is placed inside the middle fuselage assembly, and a balance installation assembly is also arranged inside the middle fuselage assembly. The research and development purpose of the present invention is to solve the problem of simultaneously installing a wire support and a tail support under the condition of limited internal space in a twin-engine ventilated model, so that the support interference can be measured and deducted from each other.

Description

Technical Field

[0001] The present invention relates to a device that combines wire support and tail support for dual-engine ventilation model measurement, belonging to the technical field of special support model design for wind tunnel tests. Background Art

[0002] Wind tunnel tests can usually provide aerodynamic characteristic parameters for aircraft design and control system design. With the continuous development of aircraft maneuvering characteristics, higher requirements are put forward for the simulation ability and data quality of aircraft tests, which requires new requirements for the authenticity of aircraft test simulations. For example, components such as aircraft inlets that could be replaced by plugs in previous tests need to be accurately simulated, and at the same time, more accurate deductions of the strut interference and various interferences in the support system during wind tunnel tests are required.

[0003] In traditional wind tunnel tests, the wire-tail support combined support system is a commonly used support system. Among them, the wire support serves as the basic support, and the tail support serves as the auxiliary support to achieve mutual measurement of strut interference. It can utilize the advantages of the wire support, such as a large angle of attack range, no damage to the tail shape during the test, and high natural frequency, avoiding problems such as geometric dissimilarity of the afterbody and easy vibration of the model during the test caused by using only the tail support alone, and also avoiding the disadvantage of large interference when using ventral struts or dorsal struts for wind tunnel tests, effectively improving the accuracy of experimental data. However, there are blockage requirements in the wind tunnel, which requires restrictions on the size of the model. The existing wire-tail support combined support system has the disadvantages of large volume, difficult structural layout, and interference between the tension axis and the inlet. Especially for a dual-engine ventilation model with inlets on both sides, the inlets on both sides of the fuselage occupy too much space, and the space is narrow after the model is scaled down. It is very difficult to simultaneously consider wire support and tail support in such models without changing the ventilation of the inlets using the previous design methods.

[0004] In summary, how to reasonably and effectively design a dual-engine ventilation model to achieve both wire support and tail support in the limited space of the model has become an urgent technical problem to be solved. Summary of the Invention

[0005] The research and development purpose of the present invention is to solve the problem of simultaneously installing wire support and tail support under the condition of limited internal space of the dual-engine ventilation model. 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.

[0006] The technical solution of the present invention:

[0007] A device for double - engine ventilation model measurement that takes into account wire bracing and tail bracing, comprising a model body and a support device. The support device includes a wire bracing and a tail bracing. A wire bracing is provided on the model body, and a tail bracing is detachably installed at the tail of the model body. The tail bracing includes a tail bracing mechanism and a tail bracing strut. The model body includes a wing assembly, a front fuselage assembly, a middle fuselage assembly, an inlet duct assembly, and a rear fuselage assembly. The front fuselage assembly and the rear fuselage assembly are respectively installed on the front and rear sides of the middle fuselage assembly. Wing assemblies are installed on both the left and right sides of the middle fuselage assembly. The inlet duct assembly is placed inside the middle fuselage assembly, and a balance installation assembly is also provided inside the middle fuselage assembly;

[0008] The wire bracing includes a wire - angle - changing suspension point assembly and a wire main suspension point assembly. The wire - angle - changing suspension point assembly is provided inside the front fuselage assembly. The wire - angle - changing suspension point assembly is connected to a wire - angle - changing mechanism through a front steel wire rope. The middle fuselage assembly is connected to the main steel wire rope and the steel rod respectively through the wire main suspension point assembly. The rear fuselage assembly includes a rear body for tail bracing test and a real rear body. The real rear body is installed with the rear body for tail bracing test behind it. One end of the installed tail bracing strut is fixedly installed with the tail bracing mechanism. After the other end of the installed tail bracing strut passes through the rear body for tail bracing test and the real rear body in sequence, it penetrates into the middle fuselage assembly and is detachably installed with the balance installation assembly.

[0009] Preferably: The wing assembly includes a wing stabilizer, a control surface, and an angle block. The wing stabilizer is fixedly installed on the middle fuselage assembly, and the control surface is installed at the tail of the wing stabilizer through the angle block.

[0010] Preferably: The front fuselage assembly includes a front nose, a front fuselage, an upper cover plate of the front fuselage, an upper wire installation cover plate for angle - changing suspension point, and a lower wire installation cover plate for angle - changing suspension point. The front nose is installed on the front side of the front fuselage. The rear of the front fuselage is fixedly connected to the middle fuselage assembly. The upper cover plate of the front fuselage is installed with the upper wire installation cover plate for angle - changing suspension point at the top, and the lower wire installation cover plate for angle - changing suspension point is installed at the bottom of the front fuselage.

[0011] Preferably: The middle fuselage assembly includes a middle fuselage, an upper cover plate of the middle fuselage, an upper slotted cover plate for the wire main suspension point, and a lower slotted cover plate for the wire main suspension point. The upper cover plate of the middle fuselage is installed on the top of the middle fuselage. The upper slotted cover plate for the wire main suspension point is provided on the upper cover plate of the middle fuselage. The lower slotted cover plate for the wire main suspension point is provided at the bottom of the middle fuselage. First and second detachable stiffeners are provided between the middle fuselage and the upper cover plate of the middle fuselage. The inlet duct assembly passes through the first and second detachable stiffeners.

[0012] Preferably: The inlet duct assembly includes a front section of the inlet duct, a middle section of the inlet duct, and a rear section of the inlet duct. The front and rear sides of the middle section of the inlet duct are respectively connected to the front section of the inlet duct and the rear section of the inlet duct.

[0013] Preferably, the balance mounting assembly includes a front balance cone sleeve, a balance, and a rear balance cone sleeve. The front side of the balance is fixedly installed in the middle fuselage through the front balance cone sleeve. The tail of the balance is connected with a rear balance cone sleeve through a taper connection, and the rear balance cone sleeve and the tail support rod are connected through a taper connection and tightened with a positive and negative nut.

[0014] Preferably, the main wire suspension point assembly includes a lower wire connection frame, an upper wire connection frame, a tension shaft, a steel rod connection sleeve, a tension shaft connection seat, and a tapered roller bearing. The lower wire connection frame is connected to the rear balance cone sleeve. Tension shafts are arranged on the left and right sides of the lower wire connection frame. One end of the tension shaft is rotatably connected to the lower wire connection frame through a spigot. The other end of the tension shaft is connected to the lower wire connection frame through a tapered roller bearing and a tension shaft connection seat. The tension shaft is fixedly connected to the main steel wire rope through a stepped hole. The tension shaft is fixedly connected to the steel rod through a steel rod connection sleeve. The upper wire connection frame is installed on the top of the lower wire connection frame. The middle section of the air inlet duct is placed between the upper wire connection frame and the lower wire connection frame and does not contact each other.

[0015] Preferably, the variable angle wire suspension point assembly includes a front steel wire rope, a front wire vertical plate, a variable angle suspension upper threaded pin, a positioning key, and a front wire vertical plate connecting piece. The front wire vertical plate is fixedly connected to the front wire vertical plate connecting piece through the positioning key. The front wire vertical plate connecting piece is fixedly connected to the lower wire connection frame. The front wire vertical plate is fixedly connected to the front steel wire rope through the variable angle suspension upper threaded pin.

[0016] Preferably, a steel wire rope is connected to the bottom of the front wire vertical plate through a variable angle suspension lower threaded pin. After passing through the variable angle suspension lower wire installation cover plate, the steel wire rope is connected to a counterweight.

[0017] Preferably, slits are provided on the variable angle suspension upper wire installation cover plate, the main wire suspension upper slotted cover plate, the variable angle suspension lower wire installation cover plate, and the main wire suspension lower slotted cover plate.

[0018] The present invention has the following beneficial effects:

[0019] 1. Even under the conditions of limited internal space and extremely compact structure in the twin-engine ventilation model, the present invention can solve the problem of simultaneous installation of wire support and tail support, enabling mutual measurement and deduction of bracket interference.

[0020] 2. By arranging the tension shafts on both sides of the air inlet duct, the present invention solves the interference problem that the tension shafts of the conventional wire support device penetrate the air inlet duct.

[0021] 3. Both sides of the tension shaft of the present invention are connected to other components of the support device through tapered roller bearings, enabling smooth operation of the model angle of attack during the test.

[0022] 4. The present invention designs the air intake assembly and the reinforcing ribs to be detachable, and the reinforcing ribs, namely the first detachable reinforcing ribs and the second detachable reinforcing ribs, are installed in the order of the tensioning wire support device-reinforcing ribs and the air intake-connecting frame on the tensioning wire, so that the model structure can be easily installed and disassembled;

[0023] 5. The present invention realizes the connection between the wire support, the tail support and the balance through the novel design of the rear cone sleeve of the balance, so as to achieve multiple uses of one piece. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a stereoscopic diagram of a device that combines the tension wire support and the tail support for the measurement of the twin-engine ventilation model;

[0025] Figure 2 It is a coordination installation diagram of a device that takes into account both the tensioning wire support and the tail support for measuring the twin-engine ventilation model;

[0026] Figure 3 It is a three-dimensional diagram of the model body and the supporting device;

[0027] Figure 4 It is a top view of a device that combines the tension wire support and the tail support for measuring the twin-engine ventilation model;

[0028] Figure 5 is a three-dimensional diagram of the air intake assembly;

[0029] Figure 6 yes Figure 4 AA section view;

[0030] Figure 7 This is the matching installation diagram of the real rear body and mid-fuselage components;

[0031] Figure 8 yes Figure 4 BB cross-section diagram;

[0032] Figure 9 This is the installation diagram of the steel rod and the tension shaft;

[0033] Figure 10 yes Figure 4 CC profile of ;

[0034] In the figure: 1 - front nose, 2 - front fuselage, 3 - upper cover plate of front fuselage, 4 - installation cover plate of upper wire of variable - angle suspension point, 5 - wing stabilizer, 6 - upper cover plate of middle fuselage, 7 - slotted cover plate of upper main suspension point of wire, 8 - steel rod, 9 - steel wire rope, 10 - angle block, 11 - rudder surface, 12 - rear body for tail - strut test, 13 - tail - strut mechanism, 14 - tail - strut support rod, 15 - rear section of intake duct, 16 - detachable stiffener, 17 - middle fuselage, 18 - middle section of intake duct, 19 - detachable stiffener, 20 - front section of intake duct, 21 - steel wire rope, 22 - threaded pin of upper variable - angle suspension point, 23 - front vertical plate of wire, 24 - threaded pin of lower variable - angle suspension point, 25 - positioning key, 26 - connecting piece of front vertical plate of wire, 27 - front cone sleeve of balance, 28 - lower connecting frame of wire, 29 - connecting seat of tension shaft, 30 - tapered roller bearing, 31 - tension shaft, 32 - steel - rod connecting sleeve, 33 - internal bar - type balance, 34 - rear cone sleeve of balance, 35 - positive and negative nuts, 36 - upper connecting frame of wire, 37 - steel wire rope, 38 - installation cover plate of lower wire of variable - angle suspension point, 39 - real rear body, 40 - slotted cover plate of lower main suspension point of wire, 101 - wing assembly, 102 - front - fuselage assembly, 103 - middle - fuselage assembly, 104 - intake - duct assembly, 105 - rear - fuselage assembly, 201 - balance installation assembly, 202 - variable - angle suspension - point assembly of wire, 203 - main - suspension - point assembly of wire. Detailed implementation manners

[0035] To make the objectives, technical solutions and advantages of the present invention clearer and more explicit, the present invention will be described below through specific embodiments shown in the 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.

[0036] 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 flanging connection, riveting connection, bonding connection, and welding connection, etc. The detachable connection includes but not limited to conventional disassembly methods such as threaded connection, snap - connection, pin connection, and hinge connection, etc. 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: for the fixed connection, welding connection is selected; for the detachable connection, hinge connection is selected.

[0037] Detailed implementation manner one: Combine Figures 1 - 10This embodiment describes a device for dual - engine ventilation model measurement that combines wire - rope support and tail support. The device includes a model body and a support device. The support device includes a wire - rope support and a tail support. A wire - rope support is provided on the model body, and a tail support is detachably installed at the tail of the model body. The tail support includes a tail - support mechanism 13 and a tail - support strut 14. The model uses the wire - rope support as the basic support and the tail support as the auxiliary support. Both supports use the same internal - type rod - type balance 33 and are in the normal installation state during the test, with the installation method unchanged, so as to reduce the influence of different balances and different installation methods on the experimental data.

[0038] The model body includes a wing assembly 101, a front - fuselage assembly 102, a middle - fuselage assembly 103, an inlet - duct assembly 104, and a rear - fuselage assembly 105. The front - fuselage assembly 102 and the rear - fuselage assembly 105 are respectively installed on the front and rear sides of the middle - fuselage assembly 103. Wing assemblies 101 are installed on both the left and right sides of the middle - fuselage assembly 103. The inlet - duct assembly 104 is placed inside the middle - fuselage assembly 103. A balance - installation assembly 201 is also provided inside the middle - fuselage assembly 103. Since the model bears aerodynamic loads during the test and there is relative deformation between components, sufficient gaps are set during the model development process to ensure that the two do not collide during the test.

[0039] The wire - rope support includes a wire - rope variable - angle suspension - point assembly 202 and a wire - rope main - suspension - point assembly 203. The wire - rope variable - angle suspension - point assembly 202 is provided inside the front - fuselage assembly 102. The wire - rope variable - angle suspension - point assembly 202 is connected to the wire - rope variable - angle - of - attack mechanism through a front steel wire 21. The middle - fuselage assembly 103 is connected to the main steel wire 9 and the steel rod 8 through the wire - rope main - suspension - point assembly 203 respectively. The rear - fuselage assembly 105 includes a rear body 12 for tail - support test and a real rear body 39. The rear body 12 for tail - support test is installed behind the real rear body 39. One end of the installed tail - support strut 14 is fixedly installed with the tail - support mechanism 13. The other end of the installed tail - support strut 14 passes through the rear body 12 for tail - support test and the real rear body 39 in sequence, then extends into the middle - fuselage assembly 103 and is detachably installed with the balance - installation assembly 201. The rear body 12 for tail - support test is for the existence of the strut and has a certain geometric dissimilarity compared with the real rear body, and is installed when installing the tail - support strut 14. The real rear body 39 is installed during the wire - rope support. The installation position of the wire - rope support needs to ensure that the balance centering point coincides with the moment reference point in the X - direction, and is appropriately adjusted in the Y - direction according to the model space to ensure that there is enough clearance between the model body and the wire - rope support.

[0040] When it is necessary to deduct the interference of the wire - rope support, install the tail - support strut 14, the tail - support mechanism 13, and the rear body 12 for tail - support test, and conduct a comparative test through the states with and without the wire - rope to deduct the interference of the wire - rope support. Conduct a comparative test through the states of installing the wire - rope support and with and without the tail support to deduct the interference of the tail - support strut 14, the tail - support mechanism 13, and its rear body 12 for tail - support test on the experimental data.

[0041] The wing assembly 101 includes a wing stabilizer 5, a control surface 11, and an angle block 10. The wing stabilizer 5 is fixedly installed on the middle fuselage assembly 103. The control surface 11 is installed at the tail of the wing stabilizer 5 through the angle block 10. The wing stabilizer 5, the control surface 11, and the angle block 10 are made by conventional metal material removal processing methods;

[0042] The front fuselage assembly 102 includes a front nose 1, a front fuselage 2, an upper cover plate 3 of the front fuselage, an upper wire installation cover plate 4 of the variable-angle suspension point, and a lower wire installation cover plate 38 of the variable-angle suspension point. The front nose 1 is installed on the front side of the front fuselage 2. The tail of the front fuselage 2 is fixedly connected to the middle fuselage assembly 103. The upper wire installation cover plate 4 of the variable-angle suspension point is installed on the top of the front fuselage 2 through the upper cover plate 3 of the front fuselage. The lower wire installation cover plate 38 of the variable-angle suspension point is installed at the bottom of the front fuselage 2. The components of the front fuselage assembly 102 are mainly disassembled according to the processing manufacturability of the parts; the front fuselage assembly 102 is designed as a hollow shell structure to facilitate reducing the total weight of the model and leaving enough space for the clearance with the support device; the front nose 1, the front fuselage 2, the upper cover plate 3 of the front fuselage, the upper wire installation cover plate 4 of the variable-angle suspension point, and the lower wire installation cover plate 38 of the variable-angle suspension point are all made of high-strength super-hard aluminum;

[0043] The middle fuselage assembly 103 includes a middle fuselage 17, an upper cover plate 6 of the middle fuselage, a slotted cover plate 7 of the main wire suspension point at the upper part, and a slotted cover plate 40 of the main wire suspension point at the lower part. The upper cover plate 6 of the middle fuselage is installed on the top of the middle fuselage 17. The middle fuselage 17 and the upper cover plate 6 of the middle fuselage are designed as thin-shell structures and are connected by screws. The slotted cover plate 7 of the main wire suspension point at the upper part is arranged on the upper cover plate 6 of the middle fuselage. The slotted cover plate 40 of the main wire suspension point at the lower part is arranged at the bottom of the middle fuselage 17. Connection interfaces with the first detachable reinforcing rib 16 and the second detachable reinforcing rib 19 are arranged inside the two components of the middle fuselage 17 and the upper cover plate 6 of the middle fuselage. The first detachable reinforcing rib 16 and the second detachable reinforcing rib 19 are installed between the two components of the middle fuselage 17 and the upper cover plate 6 of the middle fuselage. The air intake duct assembly 104 is arranged through the first detachable reinforcing rib 16 and the second detachable reinforcing rib 19. As Figure 8 shown, the wing stabilizer 5 is connected by extending a square stop through the upper cover plate 6 of the middle fuselage; the middle fuselage 17, the first detachable reinforcing rib 16, and the second detachable reinforcing rib 19 of the middle fuselage assembly 103 are used as the core load-bearing components and are made of stainless steel, and the remaining components are all made of high-strength super-hard aluminum. As Figure 8 shown, slotted channels are reserved on the slotted cover plate 7 of the main wire suspension point at the upper part and the slotted cover plate 40 of the main wire suspension point at the lower part to facilitate the main wire rope 9 passing through the slotted channels during the test.

[0044] For ease of machining and installation, the inlet duct assembly 104 is divided into three detachable sections, namely, the front section 20 of the inlet duct, the middle section 18 of the inlet duct, and the rear section 15 of the inlet duct. The front and rear sides of the middle section 18 of the inlet duct are respectively connected to the front section 20 of the inlet duct and the rear section 15 of the inlet duct. Each section extends downward to form an installation platform and is connected to the middle fuselage 17. The sections of the front section 20 of the inlet duct, the middle section 18 of the inlet duct, and the rear section 15 of the inlet duct are not directly connected to each other, but are indirectly connected through detachable reinforcing ribs; the middle section 18 of the inlet duct straddles the slots inside the lower wire connection frame 28 and the upper wire connection frame 36.

[0045] The balance mounting assembly 201 includes a balance front cone sleeve 27, a balance 33, and a balance rear cone sleeve 34. The front side of the balance 33 is fixedly installed in the middle fuselage 17 through the balance front cone sleeve 27. The tail of the balance 33 is connected to the balance rear cone sleeve 34 in a conical manner. The front flange of the balance rear cone sleeve 34 is connected to the tail support strut 14 in a conical manner and tightened with positive and negative nuts 35. Through this component, the wire support and the tail support can be installed inside the model at the same time.

[0046] The main wire suspension point assembly 203 includes a lower wire connection frame 28, an upper wire connection frame 36, a tension shaft 31, a steel rod connection sleeve 32, a tension shaft connection seat 29, and a tapered roller bearing 30. The lower wire connection frame 28 is connected to the balance rear cone sleeve 34. Tension shafts 31 are arranged on the left and right sides of the lower wire connection frame 28. The tension shafts 31 avoid the middle section 18 of the inlet duct and are the rotating components of the main wire suspension point assembly 203. One end of the tension shaft 31 is rotatably connected to the lower wire connection frame 28 through a spigot. The other end of the tension shaft 31 is connected to the lower wire connection frame 28 through a tapered roller bearing 30 and a tension shaft connection seat 29. After the tension shaft connection seat 29 and the lower wire connection frame 28 are positioned by the spigot, they are fixedly connected with screws. By connecting the tapered roller bearing 30 and the tension shaft connection seat 29 to the lower wire connection frame 28, the angle of attack of the model during the test runs smoothly. Step holes are provided on both sides of the tension shaft 31. The tension shaft 31 is fixedly connected to the main steel wire rope 9 through the step holes. A semi-circular inner cavity is provided in the middle of the tension shaft 31 to facilitate the installation of the steel rod connection sleeve 32, that is, the tension shaft 31 is fixedly connected to the steel rod 8 through the steel rod connection sleeve 32. At the same time, a square groove is provided at the end of the semi-circular inner cavity of the tension shaft 31, and the width of the groove is greater than the maximum diameter of the steel rod, so that the steel rod 8 can pass through it. The upper wire connection frame 36 is installed on the top of the lower wire connection frame 28. The middle section 18 of the inlet duct is placed between the upper wire connection frame 36 and the lower wire connection frame 28 and does not contact each other.

[0047] The steel rod connection sleeve 32 is embedded inside the tension shaft 31. The steel rod connection sleeve 32 is not only provided with an inner cavity larger than the diameter of the steel rod ball head, but also provided with a wire groove larger than the diameter of the steel rod 8 but smaller than the diameter of the ball head. By putting the steel rod ball head into the inner cavity, the tension shaft 31 is assisted to fix the steel rod 8, solving the installation and fastening problems of the steel rod 8 in the tension shaft.

[0048] The number of the steel rods 8 is two, and the number of the main steel wire ropes 9 is four. Every two main steel wire ropes 9 and one steel rod 8 form a group, and there are two groups in total, which are respectively installed on the tension shafts 31 on both sides. During the test process, the position remains constant. The model can only rotate along the axis of the tension shaft 31 itself, and cannot move up and down or left and right. Through the real-time feedback of the angle-of-attack sensor installed on the front fuselage 2, precise control of the model angle of attack can be achieved.

[0049] The cable-variable-angle suspension point assembly 202 includes a front steel wire rope 21, a cable front vertical plate 23, a variable-angle suspension point upper threaded pin 22, a positioning key 25 and a cable front vertical plate connecting piece 26. The cable front vertical plate 23 is fixedly connected to the cable front vertical plate connecting piece 26 through a circular stop and the positioning key 25. During the installation process, guiding by the positioning key 25 can facilitate positioning. The cable front vertical plate connecting piece 26 is fixedly connected to the lower cable connecting frame 28. The cable front vertical plate 23 is fixedly connected to the front steel wire rope 21 through the variable-angle suspension point upper threaded pin 22. The front steel wire rope 21 drives the cable-variable-angle suspension point assembly 202 to rotate, realizing the change of the angle of attack.

[0050] The sizes of the square grooves are set in the lower cable connecting frame 28 and the upper cable connecting frame 36 to facilitate the passage of the middle section 18 of the air inlet duct and reserve enough clearance to ensure that no rubbing occurs during the test process; after the installation of the middle section 18 of the air inlet duct is completed, the upper cable connecting frame 36 is installed together with the lower cable connecting frame 28, and is positioned by the stop and connected by screws. The air inlet duct and the reinforcing ribs are designed to be detachable and installed in the order of the cable support device - the reinforcing ribs and the air inlet duct - the upper cable connecting frame, so that the model structure can be conveniently installed and disassembled;

[0051] A steel wire rope 37 is connected to the bottom of the cable front vertical plate 23 through a variable-angle suspension point lower threaded pin 24. After passing through the variable-angle suspension point lower cable installation cover plate 38, the steel wire rope 37 is connected to a counterweight.

[0052] The variable-angle suspension point upper cable installation cover plate 4, the cable main suspension point upper slotted cover plate 7, the variable-angle suspension point lower cable installation cover plate 38, and the cable main suspension point lower slotted cover plate 40 are all provided with slots. The size of the slots needs to be determined according to the cable position, cable size, and test angle of attack range in the support device. Using 3D CAD software to simulate the movement profile of the cable at the main suspension point, during the simulation process, the axis of the cable (steel rod 8 and steel wire rope 9) is extracted as the profile. Taking the axis of the tension axis as the rotation axis and the test angle of attack range as the angle limit, the movement trajectory surface of the axis of the cable (steel rod 8 and steel wire rope 9) can be obtained. This surface is a rotational surface; extend both ends of this surface by a length equal to the radius of the cable (steel rod 8 and steel wire rope 9); perform bilateral offset on the extended surface, and suture and round the corners of the offset surface. The fillet radius is the radius of the cable (steel rod 8 and steel wire rope 9), and the movement profiles of the steel rod 8 and the steel wire rope 9 during the movement can be obtained. According to this simulation result, sufficient clearance is reserved to facilitate the steel rod 8 and the steel wire rope 9 to pass through the middle of the cover plate, ensuring that the cable does not interfere with the model during the test. As Figure 8 shown, there is a tension axis component blocking in the middle of the upper and lower slotted cover plates, which not only reduces the influence of the air flow cross-flow caused by the slotted flow, but also reduces the interference of the aerodynamic characteristics caused by the damage of the aerodynamic shape of the model due to the movement of the cable, providing more real and stable data for the development of the aircraft.

[0053] When the preliminary design of the structure of a device that combines cable support and tail support for the measurement of a twin-engine ventilation model is completed in this embodiment, it is necessary to optimize the structure according to the aerodynamic load using the analysis results of finite element analysis software, and finally ensure that the model structure meets the requirements of strength, stiffness, and anti-collision requirements;

[0054] As Figure 9 shown, a clearance needs to be reserved between the variable-angle suspension point upper cable slotted cover plate 4 and the variable-angle suspension point lower cable installation cover plate 38 and the variable-angle suspension point upper threaded pin 22 and the variable-angle suspension point lower threaded pin 24 to prevent rubbing during the test;

[0055] For all slotted cover plate components that facilitate the passage of the cable, namely the variable-angle suspension point upper cable slotted cover plate 4, the cable main suspension point upper slotted cover plate 7, the variable-angle suspension point lower cable installation cover plate 38, and the cable main suspension point lower slotted cover plate 40, backup cover plates without slots are required for the installation of the model in the cable-free state.

[0056] As Figure 5 shown, the front section 20 of the intake duct, the middle section 18 of the intake duct, and the rear section 15 of the intake duct require the pipes to be special-shaped pipes, and the inner surface needs to be accurately machined. They are processed using 3D printing forming technology, and then the inner surface is treated with abrasive flow to ensure that the inner surface roughness meets the standard.

[0057] 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 based on the mathematical knowledge of permutations and combinations. 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.

[0058] 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 can have various changes and modifications. 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 device for dual-engine ventilation model measurement that takes into account both wire bracing and tail bracing, comprising a model body and a support device. The support device includes wire bracing and tail bracing. A wire bracing is provided on the model body, and a tail bracing is detachably installed at the tail of the model body. The tail bracing includes a tail bracing mechanism (13) and a tail bracing rod (14), and is characterized in that: The model body includes a wing assembly (101), a front fuselage assembly (102), a middle fuselage assembly (103), an air intake assembly (104), and a rear fuselage assembly (105). The front fuselage assembly (102) and the rear fuselage assembly (105) are respectively installed on the front and rear sides of the middle fuselage assembly (103). Wing assemblies (101) are installed on both the left and right sides of the middle fuselage assembly (103). The air intake assembly (104) is placed inside the middle fuselage assembly (103), and a balance installation assembly (201) is also provided inside the middle fuselage assembly (103). The wire support includes a wire variable-angle suspension point assembly (202) and a wire main suspension point assembly (203). The wire variable-angle suspension point assembly (202) is arranged inside the front fuselage assembly (102). The wire variable-angle suspension point assembly (202) is connected to the wire variable angle-of-attack mechanism through a front steel wire rope (21). The middle fuselage assembly (103) is connected to the main steel wire rope (9) and the steel rod (8) respectively through the wire main suspension point assembly (203). The rear fuselage assembly (105) includes a rear body for tail support test (12) and a real rear body (39). The rear body for tail support test (12) is installed behind the real rear body (39). One end of the installed tail support strut (14) is fixedly installed with the tail support mechanism (13). The other end of the installed tail support strut (14) passes through the rear body for tail support test (12) and the real rear body (39) in sequence, then extends into the middle fuselage assembly (103), and is detachably installed with the balance installation assembly (201).

2. The device for dual-engine ventilation model measurement that takes into account both wire support and tail support according to claim 1, characterized in that: The wing assembly (101) includes a wing stabilizer (5), a control surface (11), and an angle block (10). The wing stabilizer (5) is fixedly installed on the middle fuselage assembly (103). The control surface (11) is installed at the tail of the wing stabilizer (5) through the angle block (10).

3. The device for dual-engine ventilation model measurement that takes into account wire support and tail support according to claim 2, wherein: The front fuselage assembly (102) includes a front nose (1), a front fuselage (2), a front fuselage upper cover plate (3), a variable-angle suspension point upper wire installation cover plate (4), and a variable-angle suspension point lower wire installation cover plate (38). The front nose (1) is installed on the front side of the front fuselage (2). The tail of the front fuselage (2) is fixedly connected to the middle fuselage assembly (103). The variable-angle suspension point upper wire installation cover plate (4) is installed on the top of the front fuselage (2) through the front fuselage upper cover plate (3). The variable-angle suspension point lower wire installation cover plate (38) is installed at the bottom of the front fuselage (2).

4. The device for dual-engine ventilation model measurement that takes into account both wire support and tail support according to claim 3, wherein: The middle fuselage assembly (103) includes a middle fuselage (17), a middle fuselage upper cover plate (6), a wire main suspension point upper slotted cover plate (7), and a wire main suspension point lower slotted cover plate (40). The middle fuselage upper cover plate (6) is installed on the top of the middle fuselage (17). The wire main suspension point upper slotted cover plate (7) is arranged on the middle fuselage upper cover plate (6). The wire main suspension point lower slotted cover plate (40) is arranged at the bottom of the middle fuselage (17). A first detachable reinforcing rib (16) and a second detachable reinforcing rib (19) are arranged between the middle fuselage (17) and the middle fuselage upper cover plate (6). The air intake assembly (104) is arranged through the first detachable reinforcing rib (16) and the second detachable reinforcing rib (19).

5. The device for dual-engine ventilation model measurement that takes into account wire support and tail support according to claim 4, characterized in that: The intake duct assembly (104) includes a front section of the intake duct (20), a middle section of the intake duct (18), and a rear section of the intake duct (15). The front and rear sides of the middle section of the intake duct (18) are respectively connected to the front section of the intake duct (20) and the rear section of the intake duct (15).

6. The device for dual-engine ventilation model measurement that takes into account both wire support and tail support according to claim 5, wherein: The balance mounting assembly (201) includes a front balance cone sleeve (27), a balance (33), and a rear balance cone sleeve (34). The front side of the balance (33) is fixedly installed in the middle fuselage (17) through the front balance cone sleeve (27). The tail of the balance (33) is connected to the rear balance cone sleeve (34) by a taper connection, and the rear balance cone sleeve (34) and the tail support strut (14) are connected by a taper connection and tightened with a positive and negative nut (35).

7. A device for dual-engine ventilation model measurement that takes into account wire support and tail support, characterized in that: The main cable suspension point assembly (203) includes a lower cable connection frame (28), an upper cable connection frame (36), a tension shaft (31), a steel rod connection sleeve (32), a tension shaft connection seat (29), and a tapered roller bearing (30). The lower cable connection frame (28) is connected to the rear balance cone sleeve (34). Tension shafts (31) are arranged on the left and right sides of the lower cable connection frame (28). One end of the tension shaft (31) is rotatably connected to the lower cable connection frame (28) through a spigot. The other end of the tension shaft (31) is connected to the lower cable connection frame (28) through a tapered roller bearing (30) and a tension shaft connection seat (29). The tension shaft (31) is fixedly connected to the main wire rope (9) through a stepped hole. The tension shaft (31) is fixedly connected to the steel rod (8) through a steel rod connection sleeve (32). The upper cable connection frame (36) is installed on the top of the lower cable connection frame (28). The middle section of the intake duct (18) is placed between the upper cable connection frame (36) and the lower cable connection frame (28) and does not contact each other.

8. A device for dual-engine ventilation model measurement that takes into account wire support and tail support, characterized in that: The variable-angle cable suspension point assembly (202) includes a front wire rope (21), a front cable vertical plate (23), a variable-angle suspension point upper threaded pin (22), a positioning key (25), and a front cable vertical plate connecting piece (26). The front cable vertical plate (23) is fixedly connected to the front cable vertical plate connecting piece (26) through the positioning key (25). The front cable vertical plate connecting piece (26) is fixedly connected to the lower cable connection frame (28). The front cable vertical plate (23) is fixedly connected to the front wire rope (21) through the variable-angle suspension point upper threaded pin (22).

9. The device for dual-engine ventilation model measurement that takes into account both wire support and tail support according to claim 8, wherein: The bottom of the front cable vertical plate (23) is connected to a wire rope (37) through a variable-angle suspension point lower threaded pin (24). After the wire rope (37) passes through the variable-angle suspension point lower cable mounting cover plate (38), it is connected to a counterweight block.

10. A device for dual-engine ventilation model measurement that takes into account wire support and tail support, characterized in that: Slits are provided on the variable-angle suspension point upper cable mounting cover plate (4), the main cable suspension point upper slotted cover plate (7), the variable-angle suspension point lower cable mounting cover plate (38), and the main cable suspension point lower slotted cover plate (40).

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