Low-speed dynamic wind tunnel test model considering jet influence

Abstract

The invention discloses a low-speed dynamic wind tunnel test model considering jet influence, and belongs to the technical field of wind tunnel test models. The invention provides a dynamic derivative wind tunnel test model capable of carrying out a dynamic derivative wind tunnel test under the condition of considering jet flow influence. Wing frameworks are connected to the two sides of a fuselage framework, the fuselage framework and the wing frameworks are wrapped with model outer profiles, steering engines and flow valves are symmetrically arranged on the fuselage framework, the steering engines are connected with flow valve connecting pieces through steering engine connecting pieces, the flow valve connecting pieces are connected with the flow valves, one ends of the flow valves are air source inlets, and the other ends of the flow valves are air source outlets. The other end of the flow valve is connected with a jet piece through an air supply pipeline, and the jet piece is installed on a wing framework. The low-speed dynamic wind tunnel test model considering the jet influence is stable in operation and convenient to mount and dismount when being applied to a dynamic derivative wind tunnel test. The model processing precision meets the requirement of dynamic derivative wind tunnel test data measurement precision.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel test models, and in particular relates to a low-speed dynamic wind tunnel test model taking jet influence into consideration. Background Art

[0002] The dynamic derivative wind tunnel test uses forced or free oscillation equipment to simulate the rigid body motion mode of the aircraft to obtain the dynamic stability derivative. It is the earliest single-degree-of-freedom test technology studied. In practice, the results of dynamic derivative wind tunnel tests are becoming more and more important and have become the most reliable data source for flight dynamics modal analysis.

[0003] The dynamic derivative is the derivative of the aerodynamic force coefficient and aerodynamic moment coefficient to the dimensionless rotation angular velocity or attitude angle change rate of the aircraft. It is an indispensable original aerodynamic parameter for the design of the aircraft control system and the dynamic quality analysis. It is an important aspect related to the flight quality of the aircraft, the design of the automatic driving control system law and safe flight. For a long time, aerodynamic research institutions at home and abroad have been committed to the research and numerical simulation analysis of the dynamic derivative wind tunnel test technology of aircraft, and have provided a large amount of basic test data for the development of various aerospace aircraft.

[0004] The expansion of the flight envelope of modern advanced fighters and missiles, including high angle of attack and side-slip maneuvers, has led to a greater focus on dynamic stability research in recent years. The nonlinear flow phenomena that occur under such flight conditions have a strong impact on the dynamic stability characteristics of aircraft and missiles. To predict the dynamic characteristics of aircraft under these conditions and to design flight control systems, as well as to perform stall / spin analysis, it is necessary to know its dynamic stability derivatives. In addition, the sensitivity analysis of the aircraft's high angle of attack stability to the aircraft's dynamic derivatives shows that the lateral derivatives generated by longitudinal motion, that is, the cross-coupled derivatives, have a significant impact on the aircraft's stability. This shows the necessity of measuring dynamic derivatives, including damping derivatives, cross derivatives, and cross-coupled derivatives.

[0005] Therefore, the present application proposes a low-speed dynamic wind tunnel test model that takes into account the influence of jets to solve the above problems. Summary of the invention

[0006] The purpose of the present invention is to provide a dynamic derivative wind tunnel test model that can carry out dynamic derivative wind tunnel tests while taking into account the influence of the jet. 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.

[0007] The technical solution of the present invention: A low-speed dynamic wind tunnel test model taking jet influence into consideration comprises a model outer shape surface, a fuselage frame, a wing frame, a steering gear, a flow valve, an air supply pipeline and a jet component, wherein the wing frame is connected to both sides of the fuselage frame, the fuselage frame and the wing frame are covered with the model outer shape surface, the fuselage frame is symmetrically provided with a steering gear and a flow valve, the steering gear is connected to a flow valve connecting component via a steering gear connecting component, the flow valve connecting component is connected to the flow valve, one end of the flow valve is an air source inlet, the other end of the flow valve is connected to the jet component via an air supply pipeline, and the jet component is mounted on the wing frame.

[0008] Furthermore, a ventilation control assembly mounting plate is installed on the fuselage frame, the servo is symmetrically mounted on the ventilation control assembly mounting plate through a servo mounting seat, and the flow valve is symmetrically mounted on the ventilation control assembly mounting plate.

[0009] Furthermore, quick-connect connectors are installed at both ends of the air supply pipeline, one end of the air supply pipeline is connected to the flow valve through the quick-connect connector, and the other end of the air supply pipeline is connected to the jet component through the quick-connect connector.

[0010] Furthermore, the jet component is processed with a jet outlet, a jet cavity is provided inside the jet component, a quick-connect socket is processed at the tail end of the jet component, the jet component is connected to the quick-connect connector of the air supply pipeline through the quick-connect socket, and the quick-connect socket is connected to the jet outlet through the jet cavity.

[0011] Furthermore, the fluidic component is mounted on the wing frame via a fluidic component mounting plate.

[0012] Furthermore, a rectifying baffle is arranged in the jet cavity, and the rectifying baffle divides the jet cavity into a plurality of jet channels.

[0013] Furthermore, the jet outlet is a rectangular outlet, the jet cavity is a fan-shaped diffusion cavity, and the quick-connect socket is a circular socket.

[0014] Furthermore, the steering gear connector and the flow valve connector are made of stainless steel.

[0015] The present invention has the following beneficial effects: The aircraft model jet proposed by the low-speed dynamic wind tunnel test model taking into account the jet influence of the present invention can be controlled, meets the requirements of processing technology and test equipment, is applied to the dynamic derivative wind tunnel test, runs stably, and is easy to install and disassemble. The model processing accuracy meets the measurement accuracy requirements of dynamic derivative wind tunnel test data. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] Figure 1 It is a schematic diagram of a low-speed dynamic wind tunnel test model that takes into account the influence of the jet; Figure 2 It is a schematic diagram of the matching relationship between the jet component and the flow valve; Figure 3 is a cross-sectional view of the jet component; Figure 4 It is a schematic diagram of the quick-connect socket, jet cavity and jet outlet of the jet component.

[0017] In the figure: 1-model outer surface, 2-fuselage frame, 3-installation interface, 4-wing frame, 5-servo mounting seat, 6-servo, 7-quick plug connector, 8-ventilation control component mounting plate, 9-servo connector, 10-flow valve connector, 11-flow valve, 12-air supply pipeline, 13-jet component, 14-jet component mounting plate, 15-jet cavity, 16-quick connector, 17-jet outlet, 18-rectifier baffle. DETAILED DESCRIPTION

[0018] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is described below by the specific embodiments shown in the accompanying drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present invention. In addition, in the following description, the description of well-known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present invention.

[0019] The connection mentioned in the present invention is divided into fixed connection and detachable connection. The fixed connection (i.e., non-detachable connection) includes but is not limited to conventional fixed connection methods such as folding connection, rivet connection, bonding connection and welding connection. The detachable connection includes but is not limited to conventional detachable methods such as threaded connection, snap connection, pin connection and hinge connection. When the specific connection method is not clearly defined, it is assumed that at least one connection method can always be found in the existing connection methods to achieve the function. Those skilled in the art can choose according to their needs. For example: welding connection is selected for fixed connection, and hinge connection is selected for detachable connection.

[0020] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0021] Embodiment 1, combination Figure 1-Figure 4The present embodiment is described. The present embodiment is a low-speed dynamic wind tunnel test model that takes into account the influence of jets, comprising a model outer surface 1, a fuselage frame 2, a wing frame 4, a steering gear 6, a flow valve 11, an air supply pipeline 12 and a jet component 13. The wing frame 4 is connected to both sides of the fuselage frame 2. The fuselage frame 2 and the wing frame 4 are covered with the model outer surface 1. The fuselage frame 2 is symmetrically provided with a steering gear 6 and a flow valve 11. The steering gear 6 is connected to the flow valve connector 10 through the steering gear connector 9. The flow valve connector 10 is connected to the flow valve 11. One end of the flow valve 11 is an air source inlet. The other end of the flow valve 11 is connected to the jet component 13 through the air supply pipeline 12. The jet component 13 is installed on the wing frame 4.

[0022] In order to reduce the weight of the model as much as possible and reserve space inside the model, the main body of the model adopts a hybrid structure of metal and composite materials, which consists of a model outer surface 1 and an internal support frame. Carbon fiber materials with high specific strength and specific stiffness are used as the model outer surface 1 through compression molding, and reinforcing ribs are arranged inside the model to form the model skeleton. The key load-bearing frames and connectors of the model, the fuselage skeleton 2, the wing skeleton 4 and other components are made of high-strength super-hard aluminum. The two material components are firmly connected into one by bonding and screw connection. The fuselage skeleton 2 is provided with a mounting interface 3, and the model balance is installed on the fuselage skeleton 2 through the mounting interface 3; The model jet is controlled by driving the flow valve 11 through the steering gear 6, and the steering gear connector 9 is connected to the flow valve connector 10 to achieve linkage. The ventilation control component of the model includes an air supply pipe 12, a quick-connect connector 7, a ventilation control component mounting plate 8, a steering gear 6, a steering gear mounting seat 5, a steering gear connector 9, a flow valve 11 and a flow valve connector 10. The steering gear connector 9 and the flow valve connector 10 are made of stainless steel. One end of the air supply pipeline 12 is connected to the flow valve 11 through the quick-plug connector 7, and the input end of the flow valve 11 is connected to the air source for supplying air to the air supply pipeline. The other end of the air supply pipeline 12 is connected to the jet component 13 through the quick-plug connector 7. The airflow provided by the air source flows through the air supply pipeline 12 through the flow valve 11 and is finally ejected through the outlet of the jet component 13. The ventilation control component mounting plate 8 is connected to the fuselage frame 2 by pre-embedding, bonding, screw fastening, etc. according to the internal space of the model. The air supply pipeline 12 inside the model is reasonably arranged to ensure that it does not interfere with the model body. The servo 6 is symmetrically installed on the ventilation control component mounting plate 8 through the servo mounting seat 5, and the flow valve 11 is symmetrically installed on the ventilation control component mounting plate 8.

[0023] The gas flow direction inside the jet component 13 is perpendicular to the front lapel rotation axis. The internal structure of the jet component 13 includes a quick-connect socket 16, a jet cavity 15 and a jet outlet 17. The external gas source enters the air supply pipeline 12 through the flow valve 11. The air supply pipeline 12 is connected to the quick-connect interface 16 of the jet component 13 through the quick-connect connector 7, and the air flow is input into the jet cavity 15 of the jet component 13 and ejected through the jet outlet 17. According to the direction of the quick-connect socket 16 and the jet outlet, the jet flow direction inside the jet cavity 15 is reasonably designed. The quick-connect interface 16 is a circular inlet, and the quick-connect interface 16 has a reserved internal thread that is threadedly connected to the quick-connect connector 7. The quick-connect interface 16 and the jet cavity 15 have a smooth transition to ensure smooth ventilation. The interior of the jet cavity 15 is divided into four jet channels by three rectifying baffles 18, the jet outlet 17 is a rectangular opening, and the jet cavity 15 is a fan-shaped diffusion cavity.

[0024] According to the actual installation position of the ventilation control assembly and the jet component 13, it is necessary to reserve an installation channel for the air supply pipe 12 in the fuselage frame 2 and the wing frame 4, and design an installation platform for the ventilation control assembly mounting plate 8. The jet component 13 is arranged at the front end of the wing frame 4. The air supply pipe 12 passes through the fuselage frame 2 and the wing frame 4 and is connected to the jet component 13 through the quick-connect connector 7 and the quick-connect socket 16. A corresponding cover plate is designed for the corresponding installation position of the jet component 13 to facilitate installation and disassembly.

[0025] This embodiment is only an exemplary description of the present invention and does not limit its protection scope. Those skilled in the art may also make partial changes thereto. As long as they do not exceed the spirit of the present invention, they are within the protection scope of the present invention.

Claims

1. A low-speed dynamic wind tunnel test model taking into account the influence of jet flow, characterized in that: The invention comprises a model outer profile (1), a fuselage frame (2), a wing frame (4), a steering gear (6), a flow valve (11), an air supply pipeline (12) and a jet component (13). The wing frame (4) is connected to both sides of the fuselage frame (2). The model outer profile (1) is covered on the fuselage frame (2) and the wing frame (4). The steering gear (6) and the flow valve (11) are symmetrically arranged on the fuselage frame (2). The steering gear (6) is connected to the flow valve connecting component (10) through a steering gear connecting component (9). The flow valve connecting component (10) is connected to the flow valve (11). One end of the flow valve (11) is an air source inlet. The other end of the flow valve (11) is connected to the jet component (13) through an air supply pipeline (12). The jet component (13) is mounted on the wing frame (4).

2. A low-speed dynamic wind tunnel test model taking into account the jet effect according to claim 1, characterized in that: A ventilation control assembly mounting plate (8) is mounted on the fuselage frame (2); the steering gear (6) is symmetrically mounted on the ventilation control assembly mounting plate (8) via a steering gear mounting seat (5); and the flow valve (11) is symmetrically mounted on the ventilation control assembly mounting plate (8).

3. A low-speed dynamic wind tunnel test model taking into account the jet effect according to claim 1, characterized in that: Quick-connect connectors (7) are respectively installed at both ends of the air supply pipeline (12); one end of the air supply pipeline (12) is connected to the flow valve (11) via the quick-connect connector (7); and the other end of the air supply pipeline (12) is connected to the jet component (13) via the quick-connect connector (7).

4. A low-speed dynamic wind tunnel test model taking into account the jet effect according to claim 3, characterized in that: The jet component (13) is machined with a jet outlet (17), the jet component (13) has a jet cavity (15) inside, the tail end of the jet component (13) is machined with a quick-connect socket (16), the jet component (13) is connected to the quick-connect connector (7) of the air supply pipeline (12) via the quick-connect socket (16), and the quick-connect socket (16) is connected to the jet outlet (17) via the jet cavity (15).

5. A low-speed dynamic wind tunnel test model taking into account the jet effect according to claim 4, characterized in that: The jet component (13) is mounted on the wing frame (4) via a jet component mounting plate (14).

6. A low-speed dynamic wind tunnel test model taking into account the jet effect according to claim 4, characterized in that: A rectifying baffle (18) is arranged in the jet cavity (15), and the rectifying baffle (18) divides the jet cavity (15) into a plurality of jet channels.

7. A low-speed dynamic wind tunnel test model taking into account the jet effect according to claim 6, characterized in that: The jet outlet (17) is a rectangular outlet, the jet cavity (15) is a fan-shaped diffusion cavity, and the quick-connect socket (16) is a circular socket.

8. The low-speed dynamic wind tunnel test model taking into account the jet effect according to claim 1, characterized in that: The steering gear connecting piece (9) and the flow valve connecting piece (10) are made of stainless steel.

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