Helicopter full-scale static test restraint device

Abstract

The present application belongs to helicopter full machine static test technology, and relates to a helicopter full machine static test restraint device. The method comprises the following steps: a Z-direction restraint assembly, an X-direction restraint assembly, a Y-direction restraint assembly, a mounting plate and a load loading device. The Z-direction restraint assembly is arranged on the mounting surface of the mounting plate, is connected with the landing gear mounting point of the test machine, and is used for restraining the translational, pitching and rolling degrees of the test machine along the Z-axis. The mounting plate is fixed on the bearing rail. The X-direction restraint assembly is arranged at the rear part of the test machine, is connected with the rear middle mounting point of the landing gear of the test machine, and is used for restraining the translational degree of the test machine along the X-axis. The X-direction restraint assembly is fixed on the bearing rail. The Y-direction restraint assembly is arranged on the left side of the test machine, is connected with the front and rear two tethering points on the left side of the test machine, and is used for restraining the translational and yaw degrees of the test machine along the Y-axis. The Y-direction restraint assembly is fixed on the bearing rail. The load loading device applies the load to the corresponding restraint point of the test machine.

Description

Technical Field

[0001] This invention pertains to helicopter static testing technology and relates to a constraint device for helicopter static testing. Background Technology

[0002] In full-aircraft static testing, the design of the constraint device is a crucial factor in test design, and a correct and reasonable constraint method is essential for obtaining accurate test results. Currently, full-aircraft static testing of helicopters commonly employs suspension constraints. The test aircraft is suspended from a gantry beam via lifting points on a dummy lift system component, and test loads are applied to other locations on the aircraft, with the Z-axis load of the lift system passively applied. Suspension constraints can realistically simulate the load-bearing state of a helicopter under various flight conditions. However, this approach presents challenges, such as difficulty in maintaining the aircraft's attitude and high requirements for multi-point coordinated loading. Imbalanced loads can lead to significant changes in the aircraft's attitude, affecting the accuracy of test data and test safety. Using this constraint method for full-aircraft static testing presents significant challenges in test debugging and carries substantial safety risks due to changes in the aircraft's attitude during the test. Summary of the Invention

[0003] The purpose of this invention is:

[0004] A statically determinate constraint device for full-aircraft static testing of helicopters is provided, which solves the problem of attitude change of the test aircraft during the coordinated loading of suspension constraints, and realizes the functions of passive load monitoring of constraint points and loading of active loads in other directions of constraint points.

[0005] Technical solution:

[0006] A static test constraint device for a helicopter includes: a Z-axis constraint assembly, an X-axis constraint assembly, a Y-axis constraint assembly, a mounting plate, and a load loading device;

[0007] The Z-axis constraint assembly is mounted on the mounting surface of the mounting plate and connected to the landing gear mounting point of the testing machine. It is used to constrain the translational, pitch, and roll degrees of freedom of the testing machine along the Z-axis. The mounting plate is fixed to the load-bearing ground rail.

[0008] The X-axis constraint assembly is located at the rear of the testing machine and is connected to the rear center mounting point of the testing machine's landing gear. It is used to constrain the degree of freedom of the testing machine's translation along the X-axis. The X-axis constraint assembly is fixed to the load-bearing ground rail.

[0009] The Y-axis constraint assembly is located on the left side of the testing machine and is connected to the two tie points on the front and rear sides of the testing machine. It is used to constrain the translational and yaw degrees of freedom of the testing machine along the Y-axis. The Y-axis constraint assembly is fixed on the load-bearing ground rail.

[0010] Both the Y-axis constraint assembly and the X-axis constraint assembly are connected to the two tie points on the left side of the testing machine via adapters. A force sensor is connected in series in the middle, and the screws with left-hand and right-hand internal threads at both ends can be adjusted in length. They are fixed to the load-bearing ground rail by a triangular column.

[0011] The load loading device applies the load to the corresponding constraint points of the testing machine.

[0012] The load loading device includes at least: a constraint point load Fx loading device, a landing gear limit point load Fz and Fy loading devices, a landing gear limit point load Fx loading device, a front constraint point load Fy loading device, and a rear constraint point load Fy loading device.

[0013] The Z-axis constraint components correspond one-to-one with the landing gear mounting points of the testing machine.

[0014] The Z-axis constraint assembly includes: adapter, load-bearing beam, spherical joint, end cap, spherical base, and six-component force sensor;

[0015] The adapter is at the top and connects to the landing gear mounting point of the testing machine; the load-bearing beam is a beam welded from profiles and steel plates; the spherical joint is at the bottom of the load-bearing beam, and after assembly with the end cap and spherical base, the spherical joint can rotate freely along the center of the sphere; the six-component force sensor is at the bottom of the Z-axis constraint assembly and connects to the spherical base and mounting plate.

[0016] The thread at the lower end of the adapter is a right-hand thread, while the thread on the ball joint is a left-hand thread, which allows for adjustment of the length of the Z-axis constraint component.

[0017] The X-axis constraint component and the Y-axis constraint component have the same structure.

[0018] The X-axis constraint assembly includes: adapter, sensor, screw, mounting base, and triangular column;

[0019] The adapter is a set of single and double fork joints, one end of which is connected to the rear center mounting point of the testing machine landing gear, and the other end is connected to the force sensor; the two ends of the screw are left-hand and right-hand internal threads respectively, and the length of the X-direction constraint component can be adjusted by rotating the screw; the mounting base is a welded structure support connected to the triangular column; the triangular column is fixed on the load-bearing ground rail.

[0020] The load-bearing beam is also equipped with a transverse active load loading joint and a Y-direction active load loading joint;

[0021] The active load in the X direction of the constraint points of the testing machine is applied to the transverse active load loading joint through the constraint point load Fx loading device; the active load in the Y direction of the left front and right front constraint points is applied to the Y direction active load loading joint through the front constraint point load Fy loading device; the active load in the Y direction of the rear center constraint point is applied to the transverse active load loading joint through the rear constraint point load Fy loading device.

[0022] Beneficial effects:

[0023] This invention provides a statically determinate constraint device for full-aircraft static testing of helicopters. It effectively solves the problems of aircraft attitude changes during coordinated loading of suspension constraints and the deviation of main suspension loads caused by passive loading of suspension points. The lift system load is actively loaded, and the main suspension load simulation is accurate. No additional attitude control of the aircraft is required during the test, eliminating the risk of attitude changes and improving test safety. Simultaneously, it also enables passive load monitoring of constraint points and active load loading in other directions around the constraint points. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of the present invention (right side view).

[0025] Figure 2 This is a schematic diagram of the overall structure of the present invention (left side view).

[0026] Figure 3 This is a schematic diagram of the Z-direction constraint component 1 of the present invention.

[0027] Figure 4 This is a schematic diagram of the X-direction constraint component 2 of the present invention.

[0028] Among them, 1-Z-direction constraint assembly; 1a-adapter; 1b-bearing beam; 1c-spherical joint; 1d-end cap; 1e-spherical base; 1f-six-component force sensor; 1g-lateral active load loading joint; 1h-Y-direction active load loading joint; 2-X-direction constraint assembly; 2a-adapter; 2b-force sensor; 2c-screw; 2d-mounting base; 2e-triangular column; 3-Y-direction constraint assembly; 4-constraint point load Fx loading device; 5-landing gear limit point load Fz, Fy loading device; 6-landing gear limit point load Fx loading device; 7-mounting plate; 8-front constraint point load Fy loading device; 9-rear constraint point load Fy loading device. Detailed Implementation

[0029] The present invention will now be described in further detail with reference to the accompanying drawings. Figures 1 to 4 .

[0030] A static test constraint device for the entire helicopter, such as Figure 1 As shown, it includes:

[0031] Z-axis constraint components 1 are installed on the mounting surface of mounting plate 7, and there are 3 of them. They are connected to the 3 landing gear mounting points of the testing machine respectively, and are used to constrain the translational, pitch and roll degrees of freedom of the testing machine along the Z-axis. Mounting plate 7 is fixed on the load-bearing ground rail.

[0032] The Z-axis constraint assembly 1 consists of: an adapter 1a at the top, connected to the landing gear mounting point of the testing machine; a load-bearing beam 1b, welded from profiles and steel plates; a spherical joint 1c at the bottom of the load-bearing beam 1b, which, after assembly with the end cap 1d and the spherical base 1e, can rotate freely around the center of the sphere; and a six-component force sensor 1f at the bottom of the Z-axis constraint assembly 1, connected to the spherical base 1e and the mounting plate 7. The thread at the bottom of the adapter 1a is a right-hand thread, and the thread of the spherical joint 1c is a left-hand thread, allowing for adjustment of the length of the Z-axis constraint assembly 1.

[0033] X-axis constraint assembly 2, located at the rear of the testing machine, consists of one unit and is connected to the rear center mounting point of the testing machine's landing gear. It is used to constrain the degree of freedom of the testing machine's translation along the X-axis. X-axis constraint assembly 2 is fixed to the load-bearing ground rail.

[0034] Composition of X-direction constraint component 2: Adapter 2a is a set of single and double fork joints, one end of which is connected to the rear center mounting point of the landing gear of the testing machine, and the other end is connected to the force sensor 2b; the two ends of screw 2c are left-handed and right-handed internal threads respectively, and the length of X-direction constraint component 2 can be adjusted by rotating screw 2c; mounting base 2d is a support of welded structure, connected to triangular column 2e; triangular column 2e is fixed on load-bearing ground rail.

[0035] Y-axis constraint assembly 3, located on the left side of the testing machine, consists of two units, each connected to one of the front and one of the rear mooring points on the left side of the testing machine. These components constrain the machine's translational and yaw degrees of freedom along the Y-axis. The Y-axis constraint assembly 3 is fixed to the load-bearing ground rail.

[0036] The composition of the Y-direction constraint assembly 3 is similar to that of the X-direction constraint assembly 2. It is connected to the two tie points on the left side of the testing machine by an adapter, with a force sensor connected in series in the middle. The screws with left-hand and right-hand internal threads at both ends can be adjusted in length, and are fixed to the load-bearing ground rail by a triangular column.

[0037] The transverse active load loading joint 1g and the Y-direction active load loading joint 1h of the constraint point are machined loading joints, which are respectively installed on the bearing beam 1b and the adapter 1a, enabling the Z-direction constraint component 1 to simultaneously apply active loads in the X and Y directions to the constraint point.

[0038] like Figure 1 , Figure 2 As shown, a static test constraint device for a helicopter includes a Z-axis constraint component 1, an X-axis constraint component 2, and a Y-axis constraint component 3.

[0039] like Figure 3As shown, the Z-axis constraint assembly 1 is composed of a load-bearing beam 1b welded from profiles and steel plates, an adapter 1a, a ball joint 1c, and a six-component force sensor 1f. During testing, the lower end of the Z-axis constraint assembly 1 is installed onto the mounting plate 7 fixed to the load-bearing ground rail, and the upper end is connected to the fuselage landing gear constraint point to provide Z-axis constraint for the testing machine. The thread at the lower end of the adapter 1a is a right-hand thread, and the thread of the ball joint 1c is a left-hand thread, which allows for the adjustment of the length of the Z-axis constraint assembly 1 and can be used to adjust the level of the testing machine during constraint installation. Since the active loads in the X and Y directions of the constraint point are also applied to the Z-axis constraint assembly 1, it is necessary to separate the Z-axis force borne by the Z-axis constraint assembly 1 from the forces in other directions to avoid coupling of measurement results. The six-component force sensor 1f can achieve the above function. The upper and lower ends of the Z-axis constraint assembly 1 each have a hinge point, forming a two-force bar structure, which can ensure the accurate measurement of the Z-axis load at the constraint point.

[0040] like Figure 4 As shown, the X-direction constraint assembly 2 is composed of an adapter 2a, a force sensor 2b, a screw 2c, a mounting base 2d, and a triangular column 2e. During testing, the adapter 2a is connected to the constraint point of the testing machine, and the triangular column 2e is fixed to the load-bearing ground rail. The force sensor 2b of the X-direction constraint assembly has a hinge point at each end, forming a two-force bar structure, which ensures accurate measurement of the X-direction load at the constraint point.

[0041] The composition of the Y-direction constraint assembly 3 is similar to that of the X-direction constraint assembly 2. During testing, it is connected to the two tie points on the left side of the testing machine via an adapter, with a force sensor connected in series in the middle. The screws with left-hand and right-hand internal threads at both ends can be adjusted in length, and are fixed to the load-bearing ground rail by a triangular column. The force sensor of the Y-direction constraint assembly 3 has a hinge point at each end, forming a two-force bar structure, which can ensure accurate measurement of the Y-direction load at the constraint point.

[0042] like Figure 1 , Figure 2 As shown, during the test, the Z-axis translational, pitch, and roll degrees of freedom of the testing machine are restricted by Z-axis constraint component 1; the X-axis translational degree of freedom is restricted by X-axis constraint component 2; and the Y-axis translational and yaw degrees of freedom are restricted by Y-axis constraint component 3. The testing machine has 6 degrees of freedom and 6 constraints, and the constraints of the testing machine are statically determinate.

[0043] The X-direction active load of the test machine constraint point is applied to the lateral active load loading joint 1g through the constraint point load Fx loading device 4; the Y-direction active load of the left front and right front constraint points is applied to the Y-direction active load loading joint 1h through the front constraint point load Fy loading device 8; the Y-direction active load of the rear center constraint point is applied to the lateral active load loading joint 1g through the rear constraint point load Fy loading device 9, which solves the interference problem between the rear center constraint point Y-direction load and the landing gear limit point load Fz, Fy loading device 5, and landing gear limit point load Fx loading device 6.

[0044] This invention provides a statically determinate constraint device for static testing of a helicopter, which can effectively solve the problem of attitude change of the test aircraft during the coordinated loading of suspension constraints. At the same time, it can also realize the functions of passive load monitoring of constraint points and loading of active loads in other directions of constraint points.

Claims

1. A constraint device for static testing of the entire helicopter, characterized in that, include: Z-direction constraint assembly (1), X-direction constraint assembly (2), Y-direction constraint assembly (3), mounting plate (7), load loading device; The Z-axis constraint component (1) is set on the mounting surface of the mounting plate (7) and connected to the landing gear mounting point of the testing machine. It is used to constrain the translation, pitch and roll degrees of freedom of the testing machine along the Z-axis. The mounting plate (7) is fixed on the load-bearing ground rail. The X-axis constraint assembly (2) is located at the rear of the testing machine and is connected to the rear center mounting point of the testing machine's landing gear. It is used to constrain the degree of freedom of the testing machine's translation along the X-axis. The X-axis constraint assembly (2) is fixed on the load-bearing ground rail. The Y-axis constraint component (3) is located on the left side of the testing machine and is connected to the two tie points on the left side of the testing machine. It is used to constrain the translational and yaw degrees of freedom of the testing machine along the Y-axis. The Y-axis constraint component (3) is fixed on the load-bearing ground rail. The Y-direction restraint assembly (3) is connected to the two tie points on the left side of the testing machine using an adapter; the X-direction restraint assembly (2) is connected to the rear middle mounting point of the landing gear of the testing machine using an adapter; the middle series force sensor, with left-hand and right-hand internal threads at both ends, can achieve length adjustment and is fixed on the load-bearing ground rail by a triangular column; The load loading device applies the load to the corresponding constraint points of the testing machine; The load loading device includes at least: constraint point load Fx loading device (4), landing gear limit point load Fz and Fy loading device (5), landing gear limit point load Fx loading device (6), front constraint point load Fy loading device (8), and rear constraint point load Fy loading device (9). Z-direction constraint assembly (1) includes: adapter (1a), load-bearing beam (1b), spherical joint (1c), end cap (1d), spherical base (1e), and six-component force sensor (1f). The adapter (1a) is at the top and is connected to the landing gear mounting point of the testing machine; the load-bearing beam (1b) is a beam welded from profiles and steel plates; the spherical joint (1c) is at the bottom of the load-bearing beam (1b), and after being assembled with the end cap (1d) and the spherical base (1e), the spherical joint (1c) can rotate freely along the center of the sphere; the six-component force sensor (1f) is at the bottom of the Z-direction constraint assembly (1), and is connected to the spherical base (1e) and the mounting plate (7); The X-direction constraint component (2) and the Y-direction constraint component (3) have the same structure; The X-axis constraint assembly (2) includes: an adapter (2a), a sensor (2b), a screw (2c), a mounting base (2d), and a triangular column (2e); The adapter (2a) is a set of single and double fork joints, one end of which is connected to the rear center mounting point of the landing gear of the testing machine, and the other end is connected to the force sensor (2b); the two ends of the screw (2c) are left-hand and right-hand internal threads respectively, and the length of the X-direction constraint component (2) can be adjusted by rotating the screw (2c); the mounting base (2d) is a support of the welded structure, which is connected to the triangular column (2e); the triangular column (2e) is fixed on the load-bearing ground rail; The load-bearing beam (1b) is also provided with a transverse active load loading joint (1g) and a Y-direction active load loading joint (1h). The X-direction active load of the test machine constraint point is applied to the transverse active load loading joint (1g) through the constraint point load Fx loading device (4); the Y-direction active load of the left front and right front constraint points is applied to the Y-direction active load loading joint (1h) through the front constraint point load Fy loading device (8); the Y-direction active load of the rear middle constraint point is applied to the transverse active load loading joint (1g) through the rear constraint point load Fy loading device (9).

2. The apparatus according to claim 1, characterized in that, The Z-direction constraint component (1) corresponds one-to-one with the landing gear mounting point of the testing machine.

3. The apparatus according to claim 2, characterized in that, The thread at the lower end of the adapter (1a) is a right-hand thread, and the thread of the ball joint (1c) is a left-hand thread, which can realize the length adjustment of the Z-direction constraint component (1).

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