A powered dynamic test model structure

Abstract

A kind of power dynamic test model structure belongs to the technical field of wind tunnel test aircraft design.It solves the problem that dynamic and power simulation wind tunnel test cannot be carried out simultaneously in the prior art.The technical points are as follows: the central wing is installed on the fuselage, the left and right sides of the central wing are connected with outer wings, the nacelle mechanism is installed on the bottom of the central wing, the vertical tail is installed at the tail end of the fuselage, the central wing framework is connected to the square platform of the middle fuselage framework, the central wing framework is provided with a motor installation groove and a motor wiring groove, the upper part of the central wing framework is covered with a central wing pipeline cover plate, the central wing front skin covers the central wing front lightening groove, and the central wing rear skin covers the central wing rear lightening groove.The present application strengthens the local strength of the model, ensures the firm connection between the nacelle mechanism and the model, and ensures that the model itself can withstand the gravity of the nacelle mechanism and the shaking generated during operation, on the basis of ensuring that the reference center of the aircraft model coincides with the actual center of mass of the model and the overall weight reduction of the model.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of wind tunnel test aircraft design, in particular to a dynamic test model structure with power. BACKGROUND

[0002] With the continuous development of wind tunnel test technology at home and abroad, dynamic wind tunnel test and power simulation wind tunnel test, two kinds of special wind tunnel test, are also more and more mature. Dynamic wind tunnel test requires the test mechanism to force the model to vibrate, so the weight and inertia of the model are strictly limited. Inside the power simulation wind tunnel test model, a motor or a motor is needed to be installed to provide power for the propeller, which often brings additional weight and vibration load to the model as a whole, and also has greater requirements for the structural strength of the model.

[0003] In the prior art, it is difficult to develop a model that can simultaneously meet the requirements of dynamic wind tunnel test and power simulation wind tunnel test. Dynamic test requires lightweight and low rotational inertia of the model, and power test needs to integrate power devices, so the installation and connection of the power devices and the arrangement of the corresponding pipelines are often considered, which often increases the additional weight burden of the model. With the development of science and technology, the requirements for wind tunnel test data in the field of aviation and aerospace are also gradually improving, and the research problem of dynamic aerodynamic characteristics under the influence of slipstream needs to be broken through.

[0004] Therefore, it is urgent to propose a dynamic test model structure with power to solve the problem that the prior art cannot simultaneously perform dynamic and power simulation wind tunnel tests. SUMMARY

[0005] In view of the above facts, the present application is designed to solve the problem that the prior art cannot simultaneously perform dynamic and power simulation wind tunnel tests, and further designs a dynamic test model structure with power.

[0006] To achieve the above purpose, the present application adopts the following technical solutions:

[0007] A dynamic test model structure with power, comprising a fuselage, a central wing, an outer wing, a nacelle mechanism, and a vertical tail.

[0008] The central wing is installed on the fuselage, and the left and right sides of the central wing are connected to the outer wing. The nacelle mechanism is installed on the bottom of the central wing, and the vertical tail is installed at the tail end of the fuselage.

[0009] The central wing comprises a central wing skeleton, a central wing pipeline cover plate, a central wing front skin, a central wing rear skin, a central wing front weight reduction groove, a motor installation groove, a central wing rear weight reduction groove, a central wing back weight reduction groove, and a motor wiring groove.

[0010] The central wing skeleton is provided with a motor wiring slot in the middle, a motor installation slot is arranged below the motor wiring slot, a central wing front lightening slot is arranged on both sides of the front area of the central wing skeleton, a central wing pipeline cover plate is arranged above the motor wiring slot, a central wing back lightening slot is arranged in the middle area of the central wing, and a central wing rear lightening slot is arranged on both sides of the rear area of the central wing.

[0011] The motor installation slot, the central wing front lightening slot, the central wing back lightening slot and the central wing rear lightening slot all penetrate the upper and lower surfaces of the central wing skeleton, the central wing front skin is attached to the upper and lower surfaces of the central wing front lightening slot, and the central wing rear skin is attached to the upper and lower surfaces of the central wing rear lightening slot.

[0012] The nacelle mechanism comprises a nacelle shell, a motor support plate, a motor, a steel hoop and a propeller.

[0013] The motor is fixed with the motor support plate through the steel hoop, the front end of the motor is connected with the propeller, the hub and the prop cap, the nacelle shell is wrapped around the motor, the tail end of the motor support plate extends from the rear end of the motor, and the motor support plate is inserted with the central wing skeleton.

[0014] Further, the fuselage comprises a front fuselage, a middle fuselage and a rear fuselage, the front fuselage comprises a front fuselage shell and a front fuselage skeleton, the middle fuselage comprises a middle fuselage shell and a middle fuselage skeleton, and the rear fuselage comprises a rear fuselage shell and a rear fuselage skeleton.

[0015] The front fuselage skeleton, the middle fuselage skeleton and the rear fuselage skeleton are sequentially connected through caulking, the front fuselage shell is wrapped on the front fuselage skeleton, the middle fuselage shell is wrapped on the middle fuselage skeleton, the rear fuselage shell is wrapped on the rear fuselage skeleton, and the vertical tail is installed at the tail end of the rear fuselage.

[0016] Further, the middle fuselage skeleton is provided with a square caulking, and the central wing is fixed on the square caulking.

[0017] Further, the outer wing comprises an outer wing skeleton, an outer wing skin and an outer wing mounting seat, the left and right sides of the central wing skeleton are connected with the outer wing skeleton through the outer wing mounting seat, and the outer wing skin is wrapped on the outer wing skeleton.

[0018] Further, the steel hoop is two.

[0019] Further, two steel hoop slots are arranged on the motor support plate to prevent the steel hoop from slipping off, and three mounting bosses are arranged at the tail end of the motor support plate.

[0020] Further, the motor support plate and the central wing skeleton are made of alloy steel.

[0021] Further, the front fuselage shell, the middle fuselage shell and the rear fuselage shell are all carbon fiber skin shells.

[0022] Further, the outer wing is made of aluminum alloy.

[0023] Further: the outer wing skin, the central wing front skin and the central wing rear skin are all carbon fiber skin shells.

[0024] The beneficial effects of the present application are:

[0025] 1. The present application strengthens the local strength of the model on the basis of ensuring that the reference center of the aircraft model coincides with the actual mass center of the model and the model as a whole is as light as possible, ensures the firm connection between the nacelle mechanism and the model, and makes the model itself able to withstand the gravity of the nacelle mechanism and the shaking generated during operation.

[0026] 2. Compared with traditional dynamic test models and dynamic simulation test models, the present application does not need to design and manufacture two independent models for dynamic test and dynamic simulation test, can realize the simultaneous performance of dynamic simulation and dynamic derivative test, is beneficial to the exploration of dynamic aerodynamic characteristics under the influence of slipstream, makes up for the blank of test data in this field, the model structure has been successfully developed and applied in actual wind tunnel test.

[0027] 3. The present application can reduce repeated investment in the links of material procurement, processing and manufacturing, tooling and die, reduce processing cost, and shorten the model development cycle.

[0028] 4. The same model of the present application is used in two types of tests, which avoids the aerodynamic characteristic deviation caused by the processing error and structural difference of different models. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 is a general structure diagram of the present application;

[0030] Figure 2 is a structure schematic diagram of the central wing of the present application;

[0031] Figure 3 is an outline structure schematic diagram of the nacelle mechanism of the present application;

[0032] Figure 4 is an internal structure schematic diagram of the nacelle mechanism of the present application;

[0033] Figure 5 is a connection schematic diagram of the middle fuselage framework and the rear fuselage framework of the present application.

[0034] In the figure: 1 - front fuselage, 2 - nacelle shell, 3 - central wing skeleton, 4 - outer wing skin, 5 - central wing pipeline cover plate, 6 - central wing front skin, 7 - central wing rear skin, 8 - vertical tail, 9 - rear fuselage, 10 - middle fuselage, 11 - outer wing skeleton, 13 - central wing front weight-reducing groove, 14 - motor mounting groove, 15 - central wing rear weight-reducing groove, 16 - central wing back weight-reducing groove, 17 - motor wiring groove, 18 - outer wing mounting seat, 19 - motor support plate, 20 - motor, 21 - steel hoop, 22 - middle fuselage skeleton, 23 - rear fuselage skeleton, 24 - propeller. DETAILED DESCRIPTION

[0035] In order to make the personnel in the technical field better understand the scheme of the present application, the technical scheme in the embodiments of the present application will be clearly and completely described below in combination with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by the person of ordinary skill in the art without creative labor should belong to the protection scope of the present application.

[0036] The terms "arranged", "connected", and "fixed" should be understood in a broad sense. For example, "connected" can be fixed connection, detachable connection, or integral configuration; can be mechanical connection, can be direct connection, or indirect connection through an intermediate medium, or internal communication between two devices, elements, or components. The person of ordinary skill in the art can understand the specific meaning of the above terms in the present application according to the specific circumstances.

[0037] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict. The present application will be described in detail below with reference to the drawings and in combination with the embodiments.

[0038] The preferred embodiments of the present application will be described in detail below according to the drawings.

[0039] Embodiment 1: A powered dynamic test model structure in this embodiment includes a fuselage, a central wing, an outer wing, a nacelle mechanism, and a vertical tail 8;

[0040] The central wing is mounted on the fuselage, the left and right sides of the central wing are connected with the outer wing, the nacelle mechanism is mounted on the bottom of the central wing, and the vertical tail 8 is mounted at the tail end of the fuselage;

[0041] The central wing includes a central wing skeleton 3, a central wing pipeline cover plate 5, a central wing front skin 6, a central wing rear skin 7, a central wing front weight-reducing groove 13, a motor mounting groove 14, a central wing rear weight-reducing groove 15, a central wing back weight-reducing groove 16, and a motor wiring groove 17;

[0042] The central wing skeleton 3 is provided with a motor wiring slot 17 in the middle, a motor installation slot 14 is provided below the motor wiring slot 17, a central wing pipeline cover plate 5 is covered above the motor wiring slot 17, a central wing front lightening slot 13 is provided on both sides of the front area of the central wing skeleton 3, a central wing back lightening slot 16 is provided in the middle area of the central wing, and a central wing rear lightening slot 15 is provided on both sides of the rear area of the central wing.

[0043] The motor installation slot 14, the central wing front lightening slot 13, the central wing back lightening slot 16 and the central wing rear lightening slot 15 all penetrate the upper and lower surfaces of the central wing skeleton 3, the central wing front skin 6 is attached to the upper and lower surfaces of the central wing front lightening slot 13, and the central wing rear skin 7 is attached to the upper and lower surfaces of the central wing rear lightening slot 15, thereby maintaining the original appearance of the aircraft.

[0044] The nacelle mechanism includes a nacelle shell 2, a motor support plate 19, a motor 20, a steel hoop 21 and a propeller 24.

[0045] The motor 20 is fixed with the motor support plate 19 through the steel hoop 21, the front end of the motor 20 is connected with the propeller 24, a hub and a propeller cap, the nacelle shell 2 is wrapped around the motor 20, the tail end of the motor support plate 19 extends from the rear end of the motor 20, the motor support plate 19 is inserted into the central wing skeleton 3 and fastened by screws.

[0046] More specifically, the fuselage includes a front fuselage 1, a middle fuselage 10 and a rear fuselage 9, the front fuselage 1 includes a front fuselage shell and a front fuselage skeleton, the middle fuselage 10 includes a middle fuselage shell and a middle fuselage skeleton 22, and the rear fuselage 9 includes a rear fuselage shell and a rear fuselage skeleton 23.

[0047] The front fuselage skeleton, the middle fuselage skeleton 22 and the rear fuselage skeleton 23 are sequentially connected by a butt joint, the front fuselage shell is wrapped on the front fuselage skeleton, the middle fuselage shell is wrapped on the middle fuselage skeleton 22, the rear fuselage shell is wrapped on the rear fuselage skeleton 23, and the vertical tail 8 is installed at the tail end of the rear fuselage 9.

[0048] More specifically, the middle fuselage skeleton 22 is provided with a square butt joint, and the central wing is fixed on the square butt joint.

[0049] More specifically, the outer wing includes an outer wing skeleton 11, an outer wing skin 4 and an outer wing mounting seat 18, the left and right sides of the central wing skeleton 3 are connected with the outer wing skeleton 11 by port connection through the outer wing mounting seat 18, and the outer wing skin 4 is wrapped on the outer wing skeleton.

[0050] More specifically, the steel hoop 21 is two.

[0051] More specifically, the motor support plate 19 is provided with two steel hoop slots to prevent the steel hoop 21 from slipping off, and the tail end of the motor support plate 19 is provided with three mounting bosses to ensure the stability of the installation of the motor 20 and avoid loosening of the connection due to vibration of the motor 20.

[0052] More specifically: the motor bracket 19 and the central wing skeleton 3 are made of alloy steel, bearing the vibration load of the motor 20 during operation.

[0053] More specifically: the front fuselage shell, the middle fuselage shell, and the rear fuselage shell are all carbon fiber skin shells.

[0054] More specifically: the outer wing is made of aluminum alloy.

[0055] More specifically: the outer wing skin 4, the central wing front skin 6, and the central wing rear skin 7 are all carbon fiber skin shells.

[0056] More specifically: the wires and cooling water pipes at the tail of the motor 20 enter the motor wiring groove 17 through the motor mounting groove 14, and after the wiring is completed, the upper cover is covered with the central wing pipeline cover plate 5, and the wires and cooling water pipes enter the middle fuselage skeleton 22 inside the central wing skeleton 3, and are connected to the outside together with the support strut.

[0057] More specifically: the nacelle mechanism, the central wing pipeline cover plate 5, the motor mounting groove 14, and the motor wiring groove 17 are components designed for the need of powered slipstream test;

[0058] The central wing skeleton 3 is made of alloy steel, meeting the needs of powered slipstream test;

[0059] The fuselage, the outer wing skin 4, the central wing front skin 6, the central wing rear skin 7, the central wing front weight reduction groove 13, the central wing back weight reduction groove 16, and the central wing rear weight reduction groove 15 are components designed for the need of dynamic test.

[0060] Finally, it should be noted that the above examples are only used to illustrate the technical solutions of the present application, and are not limiting; although the present application has been described in detail with reference to the foregoing examples, the technical solutions described in the foregoing examples can be modified, or some or all of the technical features can be replaced by equivalents; as long as there is no structural conflict, each feature in the specific embodiments disclosed in the present application can be used in combination with any other feature, and the corresponding technical solution will not deviate from the scope of the technical solutions of the present application.

[0061] In addition, it should be understood that although the present specification is described in terms of embodiments, not every embodiment contains only one independent technical solution, and the description manner of the specification is only for the sake of clarity, and those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that those skilled in the art can understand.

Claims

1. A dynamic test model structure with a drive, characterized in that, Including fuselage, center wing, outer wings, nacelle mechanism, and vertical tail (8); The central wing is mounted on the fuselage, and the left and right sides of the central wing are connected to the outer wings. The nacelle mechanism is mounted on the bottom sides of the central wing, and the vertical tail (8) is mounted on the tail end of the fuselage. The central wing includes a central wing frame (3), a central wing pipe cover (5), a central wing front skin (6), a central wing rear skin (7), a central wing front weight reduction groove (13), a motor mounting groove (14), a central wing rear weight reduction groove (15), a central wing back weight reduction groove (16), and a motor wiring groove (17). The central wing frame (3) has a motor wiring groove (17) in the middle, a motor mounting groove (14) is provided below the motor wiring groove (17), a central wing pipe cover plate (5) is provided above the motor wiring groove (17), a central wing front weight reduction groove (13) is provided on both sides of the front area of ​​the central wing frame (3), a central wing back weight reduction groove (16) is provided in the middle area of ​​the central wing, and a central wing rear weight reduction groove (15) is provided on both sides of the rear area of ​​the central wing. The motor mounting slot (14), the front weight reduction slot (13), the back weight reduction slot (16), and the rear weight reduction slot (15) all penetrate the upper and lower surfaces of the central wing frame (3). The front skin (6) of the central wing is attached to the upper and lower surfaces of the front weight reduction slot (13), and the rear skin (7) of the central wing is attached to the upper and lower surfaces of the rear weight reduction slot (15). The nacelle mechanism includes a nacelle shell (2), a motor support plate (19), a motor (20), a steel hoop (21), and a propeller (24). The motor (20) and the motor support plate (19) are fixed by steel hoops (21). The front end of the motor (20) is connected to the propeller (24), the hub and the cap. The nacelle shell (2) covers the motor (20). The tail end of the motor support plate (19) extends from the rear end of the motor (20). The motor support plate (19) is inserted into the central wing frame (3).

2. The dynamic test model structure according to claim 1, characterized in that, The fuselage includes a front fuselage (1), a middle fuselage (10), and a rear fuselage (9). The front fuselage (1) includes a front fuselage shell and a front fuselage frame. The middle fuselage (10) includes a middle fuselage shell and a middle fuselage frame (22). The rear fuselage (9) includes a rear fuselage shell and a rear fuselage frame (23). The front fuselage frame, the middle fuselage frame (22), and the rear fuselage frame (23) are connected in sequence with a stop. The front fuselage shell covers the front fuselage frame, the middle fuselage shell covers the middle fuselage frame (22), and the rear fuselage shell covers the rear fuselage frame (23). The vertical tail (8) is installed at the tail end of the rear fuselage (9).

3. The dynamic test model structure according to claim 2, characterized in that, A square stop is provided on the mid-fuselage frame (22), and the central wing is fixed on the square stop.

4. The dynamic test model structure according to claim 1, characterized in that, The outer wing includes an outer wing frame (11), an outer wing skin (4), and an outer wing mounting base (18). The left and right sides of the central wing frame (3) are connected to the ports of the outer wing frame (11) through the outer wing mounting base (18), and the outer wing skin (4) covers the outer wing frame.

5. The dynamic test model structure according to claim 1, characterized in that, The steel hoop (21) consists of two sections.

6. The dynamic test model structure according to claim 1, characterized in that, The motor support plate (19) is provided with two steel hoop grooves to prevent the steel hoop (21) from slipping off, and the tail end of the motor support plate (19) is provided with three mounting bosses.

7. The dynamic test model structure according to claim 1, characterized in that, The motor support plate (19) and the central wing frame (3) are made of alloy steel.

8. The dynamic test model structure according to claim 2, characterized in that, The front fuselage shell, middle fuselage shell, and rear fuselage shell are all made of carbon fiber skin.

9. The dynamic test model structure according to claim 3, characterized in that, The outer wing is made of aluminum alloy.

10. The dynamic test model structure according to claim 4, characterized in that, The outer wing skin (4), the front skin of the central wing (6), and the rear skin of the central wing (7) are all carbon fiber skin shells.

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