Multi-angle airfoil pneumatic structure

Abstract

The invention discloses a multi-angle airfoil pneumatic structure which comprises a multi-angle upper mounting plate, a front pneumatic plate, side sealing plates and reinforcing ribs. The pneumatic structures are welded to the left and right sides of the rocket sled supporting structure. The reinforcing ribs are welded to the rocket sled body chassis and used for improving the overall rigidity of the pneumatic structure. The multi-angle upper mounting plate, the front pneumatic plate and the side sealing plate are welded together and form a closed structure with the rocket sled body chassis, and the reinforcing ribs are surrounded in the closed structure; the front pneumatic plate is a windward side of the pneumatic structure, is flush with the stand column end of the rocket sled body and is used for providing resistance for the sled body. The sweepback angle formed by the windward side of the pneumatic structure and the multi-angle upper mounting plate is obtained when the maximum resistance of the pneumatic structure is solved by taking the maximum in-orbit operation speed of the rocket sled body required by the test outline as input. According to the invention, the pneumatic resistance of the skid body is changed through the angle of the pneumatic structure, so that the recovery type test of the same skid body under different working conditions can be completed.

Description

Technical Field

[0001] The invention belongs to the technical field of range testing, and in particular relates to a multi-angle airfoil aerodynamic structure. Background Art

[0002] The rocket sled is a ground test system that uses rocket engines as power and slides at high speed along a specially built slide rail. It mainly simulates the speed, acceleration, aerodynamic environment and other conditions in the development process of weapon systems, and is used for the functional assessment of missiles, aircraft, aerospace vehicles, etc. As my country's weapon systems develop towards high speed and intelligence, the requirements for weapon system functional assessment are becoming higher and higher. As a special weapon system test method, the rocket sled test is basically not limited by the volume and weight of the test piece. From full-size aircraft or missile parts (except large transport aircraft, bombers and large missiles) to small components such as electrical appliances, they can all be tested through the rocket sled.

[0003] In various rocket sled recovery tests, verifying the on-orbit running characteristics of the test object is one of the important indicators of rocket sled recovery test assessment. This type of test requires that the test object is fixed on the sled during the operation of the sled, and after the test object is loaded to a certain speed, the friction between the shoe and the rail and the aerodynamic resistance are used to recover the sled through free sliding.

[0004] With the development of weapons and equipment towards high speed, supersonic cruise missiles, supersonic drones and other weapons and equipment have higher and higher requirements for ground dynamic assessment of flight environment. Under such conditions, the recovery test of supersonic rocket sleds will increase the difficulty of the test due to insufficient safe glide distance on the track, and cannot meet the needs of safe and reliable recovery of the test object. Usually, the sled body is weighted to shorten the glide time on the track, which not only increases the mass of the sled body, but also increases the test cost. Therefore, it is urgent to design an effective aerodynamic structure to meet the test requirements and shorten the glide distance of the sled body on the track. During the high-speed operation of the rocket sled on the track, the aerodynamic resistance will affect the running speed of the entire sled body. Now an aerodynamic structure is designed. By changing the sweep angle of the windward surface of the aerodynamic device, while meeting the maximum speed requirements during the test, the aerodynamic resistance of the sled body can effectively shorten the glide distance of the sled body on the track, and ensure that the sled body can stop quickly at the allowable glide distance on the track during high-speed operation, so as to achieve the purpose of recovering the test object. Summary of the invention

[0005] In order to overcome the deficiencies of the prior art, the present invention provides a multi-angle wing-shaped aerodynamic structure, including a multi-angle upper mounting plate, a front aerodynamic plate, a side sealing plate and a reinforcing rib; the aerodynamic structure is welded on the left and right sides of the rocket skid support structure; the reinforcing rib is welded to the rocket skid chassis to improve the overall rigidity of the aerodynamic structure; the multi-angle upper mounting plate, the front aerodynamic plate and the side sealing plate are welded together to form a closed structure with the rocket skid chassis to enclose the reinforcing rib inside the closed structure; the front aerodynamic plate is the windward surface of the aerodynamic structure, which is flush with the column end of the rocket skid to provide resistance for the skid; the angle of the swept back angle formed by the windward surface of the aerodynamic structure and the multi-angle upper mounting plate is obtained by taking the maximum speed of the rocket skid on-orbit as the input required by the test outline, and solving the maximum resistance of the aerodynamic structure. The present invention changes the aerodynamic resistance of the skid through the angle of the aerodynamic structure, so that the recovery type test under different working conditions under the same skid can be completed.

[0006] The technical solution adopted by the present invention to solve the technical problem is as follows:

[0007] A multi-angle airfoil aerodynamic structure, comprising a multi-angle upper mounting plate, a front aerodynamic plate, a side sealing plate and reinforcing ribs;

[0008] The pneumatic structure is welded to the left and right sides of the rocket skid support structure;

[0009] The reinforcing ribs are welded to the chassis of the rocket skid body to improve the overall rigidity of the aerodynamic structure;

[0010] The multi-angle upper mounting plate, the front pneumatic plate, and the side sealing plate are welded together to form a closed structure with the rocket skid chassis, and the reinforcing ribs are enclosed inside the closed structure;

[0011] The front aerodynamic plate is the windward surface of the aerodynamic structure, is flush with the column end of the rocket skid body, and is used to provide resistance for the rocket skid body;

[0012] The sweep angle formed by the windward surface of the aerodynamic structure and the multi-angle upper mounting plate is obtained by taking the maximum speed of the rocket sled body on orbit as input as required by the test outline, and solving the problem when the aerodynamic structure resistance is maximum.

[0013] Preferably, the pneumatic structure is BS 700 steel plate with a thickness of 6 mm.

[0014] Preferably, the reinforcement ribs of the pneumatic structure are BS 700 steel plates with a thickness of 6 mm.

[0015] Preferably, the front pneumatic plate is BS 700 steel plate with a thickness of 6 mm.

[0016] The beneficial effects of the present invention are as follows:

[0017] 1) The multi-angle airfoil aerodynamic structure designed in the present invention changes the aerodynamic resistance of the sled through the angle of the aerodynamic structure, thereby being able to complete recovery type tests under different working conditions on the same sled.

[0018] 2) Establish a mathematical model of the sweep angle of the windward surface of the aerodynamic structure and the aerodynamic structure resistance, solve the sweep angle, and adjust the aerodynamic resistance of the skid by changing the sweep angle, which is not available in previous designs.

[0019] 3) The multi-degree adjustable airfoil aerodynamic structure designed in the present invention provides the required resistance of the skid body by adjusting the angle device of the aerodynamic structure, which greatly reduces the test cost compared with the previous counterweight method.

[0020] 4) The airfoil aerodynamic structure designed in the present invention can not only provide the required resistance for the sled, but also provide sufficient lateral support strength to ensure the reliability of lateral fixation of the test object. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 It is a schematic diagram of the pneumatic structure of the present invention;

[0022] Figure 2 It is a schematic diagram of the pneumatic structure of the present invention (excluding the multi-angle upper mounting plate on the right side and the multi-angle upper mounting plate on the left side);

[0023] Figure 3 It is an overall schematic diagram of the pneumatic structure of the present invention installed on a rocket skid.

[0024] Description of the drawings: 1-right-side multi-angle upper mounting plate; 2-left-side multi-angle upper mounting plate; 3-right-side sealing plate; 4-right-side reinforcing rib; 5-left-side sealing plate; 6-left-side reinforcing rib; 7-left-front aerodynamic plate; 8-right-front aerodynamic plate; α, β-windward surface sweep angles. DETAILED DESCRIPTION

[0025] The present invention is further described below in conjunction with the accompanying drawings and embodiments.

[0026] The present invention is aimed at the free sliding stage of the existing supersonic dual-track recovery rocket sled test, which has a long on-track running distance and cannot ensure the safe recovery of the sled. An airfoil aerodynamic structure is designed. While meeting its own strength requirements, the aerodynamic structure provides aerodynamic resistance for the sled, thereby reducing the free sliding distance of the sled on the track, thereby achieving reliable and safe recovery of the test object.

[0027] According to the test outline requirements, the present invention uses ANSYS topology optimization calculation, takes the maximum speed requirement of the skid on-track as input, and the maximum resistance that the aerodynamic structure can provide as the design target, and then solves the windward sweep angle of the skid. By changing the windward sweep angle of the skid, the maximum speed requirement of the skid on-track required by the outline is met, while providing the maximum aerodynamic resistance of the skid as much as possible, shortening the gliding distance.

[0028] The present invention is described in detail below:

[0029] like Figure 1 and Figure 2 As shown, the present invention is a multi-angle airfoil aerodynamic structure used for supersonic rocket sled recovery tests. In the test, the aerodynamic resistance of the sled is adjusted by changing the angle of the aerodynamic structure, thereby increasing the reliability of the sled's safe on-orbit recovery, thereby achieving the purpose of verifying the on-orbit operating characteristics of the test object.

[0030] The multi-angle airfoil aerodynamic structure is installed on both sides of the test object, and is mainly composed of a multi-angle upper mounting plate, a front aerodynamic plate, a side sealing plate, and reinforcing ribs. A mathematical model of the windward sweep angle of the aerodynamic structure and the aerodynamic structure resistance is established. The maximum speed of the sled on track required by the outline is used as input to solve the angle of the sweep angle when the aerodynamic structure resistance is maximum. The same sled can meet the outline requirements while ensuring safe and reliable recovery by changing the windward sweep angle.

[0031] The pneumatic structure is a BS 700 steel plate with a thickness of 6 mm, which is welded on the left and right sides of the product support structure. The purpose is to reduce the lateral swing force of the product during the operation of the sled and make the sled operation environment more stable.

[0032] The reinforcement ribs of the pneumatic structure are BS 700 steel plates with a thickness of 6 mm, which are welded between the multi-angle upper mounting plate and the side sealing plate to improve the overall rigidity of the pneumatic structure.

[0033] The front aerodynamic plate is a BS 700 steel plate with a thickness of 6 mm. It is the windward surface area of ​​the aerodynamic structure and is designed to be flush with the column end of the sled body to provide the greatest possible resistance to the sled body.

[0034] When the pneumatic structure is installed, the internal reinforcement ribs are first welded to the skid chassis, and then the multi-angle upper mounting plate, the front pneumatic plate, and the side sealing plate are welded, so as to ensure the reliability of the overall structure of the skid.

[0035] Example:

[0036] Figure 3It is a rocket sled test platform equipped with a multi-angle wing-shaped aerodynamic structure recovery type, which mainly tests the separation running trajectory of the front end of the test object at different speeds. In this case, the mass of the test object is 350kg, and it is required to complete the head shield ejection test of the test object at a speed of 800m / s±50m / s and 950m / s±50m / s, mainly to test the trajectory of the whole process of the test object shield ejection and the non-destructive recovery of the test object.

[0037] The rocket sled system is designed to be propulsive as a whole sled. At the speeds of 800m / s±50m / s and 950m / s±50m / s required by the outline, the optimal solution for the sweep angle is 53.5° and 42.6°. The test object is installed at the front end of the sled, and three D-type engines are installed at the rear end. The multi-angle wing-shaped aerodynamic structure is welded on the left and right sides of the sled, and the reinforcement ribs are welded to the sled chassis to ensure the connection strength of the sled. By changing the angle of the multi-angle upper mounting plate, the recovery test of the test object at different speeds can be completed on the same rocket sled test platform.

[0038] During the test, the rocket engine is ignited at the launch point, and the sled moves forward under the thrust of the engine. After reaching the predetermined speed, the test product completes the specified action through the ground power supply device. After the engine is completed, the sled passes through the wing-shaped aerodynamic structure and slides on the track under the action of aerodynamic resistance and friction resistance until it stops, completing the on-orbit recovery, ending the entire test process and achieving the assessment purpose.

Claims

1. A multi-angle airfoil aerodynamic structure, characterized in that: It includes a multi-angle upper mounting plate, a front pneumatic plate, a side sealing plate and reinforcing ribs; The pneumatic structure is welded to the left and right sides of the rocket skid support structure; The reinforcing ribs are welded to the chassis of the rocket skid body to improve the overall rigidity of the aerodynamic structure; The multi-angle upper mounting plate, the front pneumatic plate, and the side sealing plate are welded together to form a closed structure with the rocket skid chassis, and the reinforcing ribs are enclosed inside the closed structure; The front aerodynamic plate is the windward surface of the aerodynamic structure, is flush with the column end of the rocket skid body, and is used to provide resistance for the rocket skid body; The sweep angle formed by the windward surface of the aerodynamic structure and the multi-angle upper mounting plate is obtained by taking the maximum speed of the rocket sled body on orbit as input as required by the test outline, and solving the problem when the aerodynamic structure resistance is maximum.

2. A multi-angle airfoil aerodynamic structure according to claim 1, characterized in that: The pneumatic structure is made of BS700 steel plate with a thickness of 6 mm.

3. The multi-angle airfoil aerodynamic structure according to claim 1, characterized in that: The reinforcement ribs of the pneumatic structure are BS 700 steel plates with a thickness of 6 mm.

4. The multi-angle airfoil aerodynamic structure according to claim 1, characterized in that: The front pneumatic plate is a BS700 steel plate with a thickness of 6 mm.

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