A device for simulating thrust vector control characteristics of a rocket engine flexible nozzle

Abstract

The present invention provides a device for simulating the thrust vector control characteristics of a flexible nozzle of a rocket engine, and relates to the technical field of electromechanical system experimental facilities. The device for simulating the thrust vector control characteristics of a flexible nozzle of a rocket engine comprises a connecting flange, a support seat, a nozzle member, and an electromechanical actuator. The connecting flange and the support seat are fixedly connected by bolts. A swing shaft is provided in the middle of the support seat, and a joint radial bearing is sleeved on the outer wall of the swing shaft. A clamping end cover is provided on the outside of the joint radial bearing, and the clamping end cover is fixedly connected to the lower end of the support seat by connecting screws. In the present invention, the inertial load, friction torque load, elastic torque load, and flexible characteristics of the engine nozzle in the process of simulating the thrust vector of the flexible nozzle can be simulated, and simulation experiments can be performed on multiple groups of servo mechanisms, avoiding the situation that traditional ground simulation experiments cannot simulate the operation of multiple groups of equipment to control the nozzle.

Description

Technical Field

[0001] The present invention relates to the technical field of electromechanical system experimental facilities, in particular to a rocket engine flexible nozzle thrust vector control characteristic simulation device. Background Art

[0002] Simulating the thrust vector control characteristics of a rocket engine's flexible nozzle is a key technology for nozzle control. This device is used to simulate the structural characteristics of a rocket engine's flexible nozzle in a ground-based laboratory environment. With the increasing functionality and variety of servo system models, ground-based testing of servo systems has necessitated the development of a device capable of simulating the thrust vector control characteristics of a flexible nozzle.

[0003] Traditional servo load simulators are mostly symmetrical inertia disk devices, allowing only one servo system control linear displacement device to be tested on a servo load simulator. For experiments involving multiple servo systems, traditional simulators cannot fully simulate the operating conditions of the servo system.

[0004] Therefore, those skilled in the art provide a device for simulating thrust vector control characteristics of a flexible nozzle of a rocket engine to solve the problems raised in the above background technology. Summary of the Invention

[0005] (1) Technical problems solved

[0006] In response to the shortcomings of the existing technology, the present invention provides a rocket engine flexible nozzle thrust vector control characteristic simulation device, which can simulate the inertial load, friction torque load, elastic torque load and engine nozzle flexibility characteristics during the flexible nozzle thrust vector simulation process, and solves the problem that traditional servo mechanism load simulators are mostly symmetrical inertia disk devices, and only one set of servo system control linear displacement equipment can be used to perform test experiments on the servo mechanism load simulator. For experiments using multiple sets of servo mechanisms for simulation, the traditional simulator equipment cannot fully simulate the operating conditions of the servo system.

[0007] (2) Technical solution

[0008] To achieve the above objectives, the present invention is implemented through the following technical solutions:

[0009] A device for simulating thrust vector control characteristics of a flexible nozzle of a rocket engine comprises a connecting flange, a support seat, a nozzle member, and an electromechanical actuator. The connecting flange and the support seat are fixedly connected by bolts. A swing shaft is provided in the middle of the support seat. The outer wall of the swing shaft is sleeved with a joint radial bearing. A clamping end cap is provided on the outside of the joint radial bearing. The clamping end cap is fixedly connected to the lower end of the support seat by connecting screws. The outer ring of the joint radial bearing is fixed by the workpiece support seat and the clamping end cap for axial and radial positioning.

[0010] The outer wall of the upper end of the swing shaft is connected to a nozzle member, and a nozzle end cap is provided at the end of the nozzle member. The lower end of the joint centripetal bearing is provided with a shaft sleeve, and the lower end of the shaft sleeve is locked and fixed by a locking nut, and the locking nut is threadedly sleeved on the external thread provided at the lower end of the outer wall of the swing shaft. An elastic member is provided between the lower end of the nozzle member and the upper end of the support seat, and the elastic member is sleeved on the outer wall of the swing shaft;

[0011] Through the above technical solution, the servo driver controls the electromechanical actuator to execute the motion instruction. Under the control of multiple groups of controllers, the motor drives the lower lug, and the linear displacement controls the nozzle part to swing around the swing center of the joint radial bearing 7, simulating the movement of the flexible nozzle part around the swing center. The flexible nozzle part performs pitch and yaw movements and compresses the elastic part to generate an elastic torque load. The elastic part is squeezed and generates thrust on the contact component. The thrust acts on the joint radial bearing. Since the internal contact surface of the bearing is not absolutely smooth, a friction load is generated. In addition, the model and preload of the elastic part can be changed to simulate the characteristics of the thrust vector motion of the flexible nozzle part under a certain range of working conditions.

[0012] Furthermore, the upper end of the support seat is connected to a plurality of upper lugs via a second connecting bolt, the upper end of the upper lug is connected to a rotating wheel of an electromechanical actuator, the upper end of the electromechanical actuator is connected to a rotatably connected lower lug, and the lower lug is connected to the outer side wall of the nozzle member via a first connecting bolt;

[0013] Through the above technical solution, the top of the electromechanical actuator is rotatably connected to the nozzle part through the lower support ear, and the servo driver controls the electromechanical actuator to execute motion instructions. Under the control of multiple groups of controllers, the lower support ear is driven by the motor, and the linear displacement controls the nozzle part to swing around the swing center of the joint radial bearing to simulate the movement of the flexible nozzle part around the swing center.

[0014] Furthermore, a servo driver is provided at the upper end of the electromechanical actuator, and the servo driver and the electromechanical actuator are connected via a connecting cable, and the length of the connecting cable is set as required;

[0015] Through the above technical solution, the electromechanical actuator is controlled by the servo driver to execute motion instructions.

[0016] Furthermore, a first spring washer is provided on the first connecting bolt, and a first flat washer is provided at the lower end of the first spring washer;

[0017] With the above technical solution, the first spring washer and the first flat washer are provided to buffer the connection stress between the first connecting bolt and the nozzle member and the lower support ear, thereby avoiding damage.

[0018] Furthermore, a second spring washer is provided on the second connecting bolt, and a second flat washer is provided at the lower end of the second spring washer;

[0019] Through the above technical solution, the second spring washer and the second flat washer are provided to buffer the connection stress between the second connecting bolt and the connecting flange and the support seat, thereby avoiding damage.

[0020] Furthermore, the connecting flange is a fixed flange at the tail end of the nozzle, and it can be set to other shapes;

[0021] Through the above technical solution, in the ground simulation experiment, the shape of the connecting flange can be set as needed to adapt to different simulation experiments.

[0022] Furthermore, a support base is provided at the lower end of the connecting flange, and the shape of the support base is the same as that of the connecting flange;

[0023] Through the above technical solution, the entire simulation device is stably supported by the support base, making the simulation experiment process more stable and reliable.

[0024] Furthermore, the outer wall of the nozzle member is provided with a position sensor along the pitch and yaw directions, and the position sensor is connected to an external controller;

[0025] Through the above technical solution, the three-dimensional vector swing control process of the nozzle can be measured and verified in three directions through the position sensor.

[0026] (3) Beneficial effects

[0027] The present invention provides a device for simulating thrust vector control characteristics of a rocket engine flexible nozzle. It has the following beneficial effects:

[0028] 1. The present invention provides a device for simulating the thrust vector control characteristics of a rocket engine flexible nozzle. The device adopts multiple sets of electromechanical actuators to provide push and pull forces. The device simulates the motion of the flexible nozzle around the swing center through mechanical structures such as a swing shaft and a spherical bearing. The nozzle component performs pitch and yaw movements to compress the elastic component, which applies a variable thrust to the spherical bearing as a whole, generating an elastic torque load. The thrust acts on the contact spherical surface of the spherical bearing to generate a friction load. By changing the model and preload of the elastic component, the thrust vector motion characteristics of the flexible nozzle under different ranges of the servo system are simulated to meet the needs of different torque loading.

[0029] 2. The present invention provides a device for simulating the thrust vector control characteristics of a rocket engine flexible nozzle, which can simulate the inertial load, friction torque load, elastic torque load and flexibility characteristics of the engine nozzle during the flexible nozzle thrust vector simulation process, and can perform simulation experiments on multiple groups of servo mechanisms, avoiding the situation that traditional ground simulation experiments cannot simulate the operation of multiple groups of equipment to control the nozzle.

[0030] 3. The present invention provides a device for simulating the thrust vector control characteristics of a rocket engine flexible nozzle. The device utilizes more standard components and simplified equipment in its structure, and uses elastic components and nozzle schematics for ground experiments rather than manufacturing flexible nozzles. This avoids the waste of production resources caused by manufacturing actual products in the early stages of design, allows for earlier design feedback, and shortens the cycle and cost of a minimum viable product. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 This is a schematic diagram of the overall connection state of the device of the present invention after installation;

[0032] Figure 2 It is a structural schematic diagram of the simulation device of the present invention;

[0033] Figure 3 A top view of the simulation device of the present invention;

[0034] Figure 4 It is a main cross-sectional view of the simulation device of the present invention;

[0035] Figure 5 It is a half-section view of the simulation device of the present invention.

[0036] Among them, 1. connecting flange; 2. support seat; 3. tightening end cover; 4. swing shaft; 5. bushing; 6. locking nut; 7. joint radial bearing; 8. upper support ear; 9. nozzle part; 10. elastic part; 11. lower support ear; 12. nozzle end cover; 13. servo drive; 14. electromechanical actuator; 15. first connecting bolt; 16. first spring washer; 17. first flat washer; 18. second connecting bolt; 19. second spring washer; 20. second flat washer; 21. connecting screw. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the specific embodiments of the present invention to clearly and completely describe the technical solutions in the specific embodiments of the present invention. Obviously, the specific embodiments described are only part of the specific embodiments of the present invention, rather than all the specific embodiments. Based on the specific embodiments of the present invention, all other specific embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

[0038] like Figure 1-5 As shown, a specific embodiment of the present invention provides a rocket engine flexible nozzle thrust vector control characteristic simulation device, including a connecting flange 1, a support seat 2, a nozzle member 9 and an electromechanical actuator 14. The connecting flange 1 and the support seat 2 are fixedly connected by bolts. A swing shaft 4 is provided in the middle of the support seat 2. The outer wall of the swing shaft 4 is sleeved with a joint radial bearing 7. A clamping end cover 3 is provided on the outside of the joint radial bearing 7. The clamping end cover 3 is fixedly connected to the lower end of the support seat 2 by connecting screws 21. The outer ring of the joint radial bearing 7 is fixed by the workpiece support seat 2 and the clamping end cover 3 for axial and radial positioning.

[0039] The upper outer wall of the swing shaft 4 is connected to a nozzle member 9, and a nozzle end cap 12 is provided at the end of the nozzle member 9. The lower end of the joint centripetal bearing 7 is provided with a shaft sleeve 5. The lower end of the shaft sleeve 5 is locked and fixed by a locking nut 6, and the locking nut 6 is threadedly sleeved on the external thread provided on the lower end of the outer wall of the swing shaft 4. An elastic member 10 is provided between the lower end of the nozzle member 9 and the upper end of the support seat 2, and the elastic member 10 is sleeved on the outer wall of the swing shaft 4;

[0040] The electromechanical actuator 14 is controlled by the servo driver 13 to execute the motion instructions. Under the control of multiple groups of controllers, the lower support ear 11 is driven by the motor, and the linear displacement is controlled to control the nozzle component 9 to swing around the swing center of the joint radial bearing 7, simulating the movement of the flexible nozzle component 9 around the swing center. The flexible nozzle component 9 performs pitch and yaw movements and compresses the elastic component 10, generating an elastic torque load. The elastic component 10 is squeezed and generates thrust on the contact component. The thrust acts on the joint radial bearing 7. Since the internal contact surface of the bearing is not absolutely smooth, a friction load is generated. In addition, the model and preload of the elastic component 10 can be changed to simulate the thrust vector motion characteristics of the flexible nozzle component 9 under a certain range of working conditions.

[0041] The upper end of the support seat 2 is connected to multiple upper lugs 8 through a second connecting bolt 18. The upper end of the upper lug 8 is connected to a rotating wheel with an electromechanical actuator 14. The upper end of the electromechanical actuator 14 is connected to a lower lug 11 that is rotatably connected. The lower lug 11 is connected to the outer wall of the nozzle component 9 through a first connecting bolt 15. The top of the electromechanical actuator 14 is rotatably connected to the nozzle component 9 through the lower lug 11, and the electromechanical actuator 14 is controlled by the servo driver 13 to execute motion instructions. Under the control of multiple groups of controllers, the lower lug 11 is driven by a motor, and the linear displacement controls the nozzle component 9 to swing around the swing center of the joint radial bearing 7 to simulate the movement of the flexible nozzle component 9 around the swing center.

[0042] A servo driver 13 is provided at the upper end of the electromechanical actuator 14 . The servo driver 13 and the electromechanical actuator 14 are connected via a connecting cable, and the length of the connecting cable is set as needed. The servo driver 13 controls the electromechanical actuator 14 to execute motion instructions.

[0043] A first spring washer 16 is provided on the first connecting bolt 15, and a first flat washer 17 is provided at the lower end of the first spring washer 16. The first spring washer 16 and the first flat washer 17 buffer the connection stress between the first connecting bolt 15 and the nozzle member 9 and the lower support ear 11 to avoid damage.

[0044] A second spring washer 19 is provided on the second connecting bolt 18, and a second flat washer 20 is provided at the lower end of the second spring washer 19. The second spring washer 19 and the second flat washer 20 are provided to buffer the connection stress between the second connecting bolt 18 and the connecting flange 1 and the support seat 2 to avoid damage.

[0045] The connecting flange 1 is a fixed flange at the tail end of the nozzle, and it can be set to other shapes. In the ground simulation experiment, the shape of the connecting flange 1 can be set as needed to adapt to different simulation experiments.

[0046] A support base is also provided at the lower end of the connecting flange 1. The shape of the support base is the same as that of the connecting flange 1. The support base stably supports the entire simulation device, making the simulation experiment process more stable and reliable.

[0047] Position sensors are provided on the outer wall of the nozzle member 9 along the pitch and yaw directions. The position sensors are connected to an external controller. The three-dimensional vector swing control process of the nozzle can be measured and verified in three directions through the position sensors.

[0048] Working principle: When the simulation device is in use, the top of the electromechanical actuator 14 is rotatably connected to the nozzle part 9 through the lower support ear 11, and the servo driver 13 controls the electromechanical actuator 14 to execute the motion command. Under the control of multiple groups of controllers, the lower support ear 11 is driven by the motor, and the linear displacement controls the nozzle part 9 to swing around the swing center of the joint centripetal bearing 7, simulating the movement of the flexible nozzle part 9 around the swing center. The flexible nozzle part 9 performs pitch and yaw actions and compresses the elastic part 10, generating an elastic torque load. The elastic part 10 is squeezed and generates thrust on the contact component. The thrust acts on the joint centripetal bearing 7. Since the internal contact surface of the bearing is not absolutely smooth, a friction load is generated. In addition, the model and preload of the elastic part 10 can be changed to simulate the characteristics of the thrust vector motion of the flexible nozzle part 9 under a certain range of working conditions. Position sensors are set in the pitch and yaw directions of the nozzle part 9, and the three-dimensional vector swing control process of the nozzle can be measured and verified in the three-dimensional direction.

[0049] Although specific embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and variations can be made to these specific embodiments without departing from the principles and spirit of the invention, and the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A device for simulating thrust vector control characteristics of a flexible nozzle of a rocket engine, comprising a connecting flange (1), a support seat (2), a nozzle member (9) and an electromechanical actuator (14), characterized in that: The connecting flange (1) and the support seat (2) are fixedly connected by bolts, a swing shaft (4) is provided in the middle of the support seat (2), an outer wall of the swing shaft (4) is provided with a joint radial bearing (7), a clamping end cover (3) is provided on the outside of the joint radial bearing (7), the clamping end cover (3) is fixedly connected to the lower end of the support seat (2) by connecting screws (21), and the outer ring of the joint radial bearing (7) is fixed by the workpiece support seat (2) and the clamping end cover (3) for axial and radial positioning; The upper outer wall of the swing shaft (4) is connected to a nozzle member (9), and the end of the nozzle member (9) is provided with a nozzle end cover (12), the lower end of the joint radial bearing (7) is provided with a shaft sleeve (5), the lower end of the shaft sleeve (5) is locked and fixed by a locking nut (6), and the locking nut (6) is threadedly sleeved on the external thread provided at the lower end of the outer wall of the swing shaft (4), an elastic member (10) is provided between the lower end of the nozzle member (9) and the upper end of the support seat (2), and the elastic member (10) is sleeved on the outer wall of the swing shaft (4); The upper end of the support seat (2) is connected to a plurality of upper lugs (8) via a second connecting bolt (18), the upper end rotating wheel of the upper lug (8) is connected to an electromechanical actuator (14), the upper end of the electromechanical actuator (14) is connected to a lower lug (11) which is rotatably connected, and the lower lug (11) is connected to the outer side wall of the nozzle member (9) via a first connecting bolt (15).

2. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 1, characterized in that: A servo driver (13) is provided at the upper end of the electromechanical actuator (14), and the servo driver (13) and the electromechanical actuator (14) are connected via a connecting cable, and the length of the connecting cable is set as required.

3. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 1, characterized in that: A first spring washer (16) is provided on the first connecting bolt (15), and a first flat washer (17) is provided at the lower end of the first spring washer (16).

4. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 1, characterized in that: A second spring washer (19) is provided on the second connecting bolt (18), and a second flat washer (20) is provided at the lower end of the second spring washer (19).

5. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 1, characterized in that: The connecting flange (1) is a fixed flange at the tail end of the nozzle.

6. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 1, characterized in that: A support base is also provided at the lower end of the connecting flange (1), and the shape of the support base is the same as that of the connecting flange (1).

7. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 1, characterized in that: Position sensors are provided on the outer wall of the nozzle member (9) along the pitch and yaw directions, and the position sensors are connected to an external controller.

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