Rocket engine flexible nozzle thrust vector control characteristic simulation device

Abstract

The invention provides a rocket engine flexible nozzle thrust vector control characteristic simulation device, and relates to the technical field of electromechanical system experiment facilities. The rocket engine flexible nozzle thrust vector control characteristic simulation device comprises a connecting flange, a supporting seat, a nozzle piece and an electromechanical actuator, the connecting flange and the supporting seat are fixedly connected through a bolt, a swing shaft is arranged in the middle of the supporting seat, the outer wall of the swing shaft is sleeved with a joint radial bearing, and the joint radial bearing is connected with the electromechanical actuator. A pressing end cover is arranged outside the joint radial bearing and fixedly connected to the lower end of the supporting base through a connecting screw. According to the invention, the inertia load, the friction torque load, the elastic torque load and the flexible characteristics of the engine jet pipe in the thrust vector simulation process of the flexible jet pipe can be simulated, and the simulation experiment can be carried out aiming at a plurality of groups of servo mechanisms, so that the condition that the traditional ground simulation experiment cannot simulate the operation of the jet pipe controlled by a plurality of groups of equipment is avoided.

Description

Technical Field

[0001] The 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] The simulation of the thrust vector control characteristics of the rocket engine flexible nozzle is a key technology for nozzle control. The thrust vector control characteristics simulation device is used to simulate the structural characteristics of the rocket engine flexible nozzle in a ground laboratory environment. With the specialization of the servo system mechanism functions and the richness of models, higher adaptability requirements are put forward for the servo system ground test, and thus the flexible nozzle thrust vector control characteristics simulation device is developed.

[0003] Traditional servo load simulators are mostly symmetrical inertia disk devices, and only one set of servo system control line displacement devices can be tested on the servo load simulator. For experiments that use multiple sets of servo mechanisms for simulation, traditional simulator equipment 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 rocket engine flexible nozzle to solve the problems raised in the above-mentioned background technology. Summary of the invention

[0005] 1. Technical issues to be resolved

[0006] In view of the deficiencies in the prior art, the present invention provides a device for simulating thrust vector control characteristics of a rocket engine flexible nozzle, which can simulate the inertial load, friction torque load, elastic torque load and flexible characteristics of the engine nozzle in the flexible nozzle thrust vector simulation process, thereby solving the problem that most traditional servo mechanism load simulators are symmetrical inertia disk devices, and only one set of servo system control line 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] (II) Technical solution

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

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

[0010] The upper outer wall of the swing shaft is connected with a nozzle member, and the end of the nozzle member is provided with a nozzle end cap, the lower end of the joint radial bearing is provided with a sleeve, the lower end of the 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 scheme, 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 support ear to linearly control the nozzle member to swing around the swing center of the joint radial bearing 7, simulating the movement of the flexible nozzle member around the swing center. The flexible nozzle member performs pitch and yaw actions and compresses the elastic member to generate an elastic moment load. The elastic member is squeezed to generate 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 member can be changed to simulate the characteristics of the thrust vector motion of the flexible nozzle member under a certain range of working conditions.

[0012] Further, the upper end of the support seat is connected to a plurality of upper ears through a second connecting bolt, the upper end rotating wheel of the upper ears is connected to an electromechanical actuator, the upper end of the electromechanical actuator is connected to a lower ear rotatably connected, and the lower ear is connected to the outer side wall of the nozzle member through 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 electromechanical actuator is controlled by the servo driver 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 is connected to the electromechanical actuator 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 the motion instruction.

[0016] Further, 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] Through the above technical solution, the connection stress between the first connecting bolt and the nozzle member and the lower support ear is buffered by the provision of the first spring washer and the first flat washer, thereby avoiding damage.

[0018] Further, 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] Further, 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 dimensions through the position sensor.

[0026] (III) Beneficial effects

[0027] The present invention provides a rocket engine flexible nozzle thrust vector control characteristic simulation device, which has the following beneficial effects:

[0028] 1. The present invention provides a device for simulating thrust vector control characteristics of a rocket engine flexible nozzle, which adopts multiple sets of electromechanical actuators to provide push and pull forces, and simulates the movement of a flexible nozzle around a swing center through mechanical structures such as a swing shaft and a joint bearing. The nozzle part performs pitch and yaw actions to compress the elastic part, and the overall thrust is given to the joint radial bearing to generate an elastic torque load. The thrust acts on the contact spherical surface of the joint 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 loadings.

[0029] 2. The present invention provides a device for simulating thrust vector control characteristics of a rocket engine flexible nozzle, 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 can perform simulation experiments on multiple groups of servo mechanisms, thereby 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 thrust vector control characteristics of a rocket engine flexible nozzle. The device uses more standard parts and simplified equipment in structure, and uses elastic components and nozzle schematics to conduct ground experiments instead of manufacturing flexible nozzles, thereby avoiding the waste of production resources caused by manufacturing actual products in the early stage of design, and obtaining design feedback at an earlier stage, thereby shortening the cycle and cost of the 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 schematic diagram of the structure 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. supporting seat; 3. clamping 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, not all of the specific embodiments. Based on the specific embodiments of the present invention, all other specific embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0039] 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 arranged in the middle of the support seat 2, a joint radial bearing 7 is sleeved on the outer wall of the swing shaft 4, a clamping end cover 3 is arranged 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;

[0040] The upper outer wall of the swing shaft 4 is connected with a nozzle member 9, and a nozzle end cap 12 is provided at the end of the nozzle member 9, and a sleeve 5 is provided at the lower end of the joint radial bearing 7, and the lower end of the 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, and 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;

[0041] The electromechanical actuator 14 is controlled by the servo driver 13 to execute the motion instruction. Under the control of multiple groups of controllers, the lower support ear 11 is driven by the motor to linearly control the nozzle member 9 to swing around the swing center of the joint radial bearing 7, simulating the movement of the flexible nozzle member 9 around the swing center. The flexible nozzle member 9 performs pitch and yaw actions and compresses the elastic member 10 to generate an elastic moment load. The elastic member 10 is squeezed to generate 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 member 10 can be changed to simulate the thrust vector motion characteristics of the flexible nozzle member 9 under a certain range of working conditions.

[0042] The upper end of the support seat 2 is connected to multiple upper ears 8 through the second connecting bolt 18, the upper end of the upper ear 8 is connected to the electromechanical actuator 14, the upper end of the electromechanical actuator 14 is connected to the lower ear 11 which is rotatably connected, the lower ear 11 is connected to the outer wall of the nozzle member 9 through the first connecting bolt 15, the top of the electromechanical actuator 14 is rotatably connected to the nozzle member 9 through the lower ear 11, and the electromechanical actuator 14 is controlled by the servo driver 13 to execute the motion instruction. Under the control of multiple groups of controllers, the lower ear 11 is driven by the motor, and the linear displacement controls the nozzle member 9 to swing around the swing center of the joint radial bearing 7 to simulate the movement of the flexible nozzle member 9 around the swing center.

[0043] A servo driver 13 is disposed 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 required. The servo driver 13 controls the electromechanical actuator 14 to execute motion instructions.

[0044] A first spring washer 16 is arranged on the first connecting bolt 15, and a first flat washer 17 is arranged 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.

[0045] A second spring washer 19 is arranged on the second connecting bolt 18, and a second flat washer 20 is arranged at the lower end of the second spring washer 19. The second spring washer 19 and the second flat washer 20 are arranged to buffer the connecting stress between the second connecting bolt 18 and the connecting flange 1 and the supporting seat 2 to avoid damage.

[0046] 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.

[0047] 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. The support base provides stable support for the entire simulation device, making the simulation experiment process more stable and reliable.

[0048] Position sensors are arranged 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-dimensional directions through the position sensors.

[0049] Working principle: When the simulation device is used, the top of the electromechanical actuator 14 is rotatably connected to the nozzle member 9 through the lower support ear 11, and the servo driver 13 controls the electromechanical actuator 14 to execute motion instructions. 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 member 9 to swing around the swing center of the joint radial bearing 7, simulating the movement of the flexible nozzle member 9 around the swing center. The flexible nozzle member 9 performs pitch and yaw actions and compresses the elastic member 10 to generate an elastic moment load. The elastic member 10 is squeezed and thrust is generated 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 member 10 can be changed to simulate the characteristics of the thrust vector motion of the flexible nozzle member 9 under a certain range of working conditions. Position sensors are set in the pitch and yaw directions of the nozzle member 9, and the three-dimensional vector swing control process of the nozzle can be measured and verified in the three-dimensional direction.

[0050] Although specific embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the specific embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A rocket engine flexible nozzle thrust vector control characteristic simulation device, 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 arranged in the middle of the support seat (2), a joint radial bearing (7) is sleeved on the outer wall of the swing shaft (4), a clamping end cover (3) is arranged 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 a nozzle end cover (12) is provided at the end of the nozzle member (9). The lower end of the joint radial bearing (7) is provided with a shaft sleeve (5), and 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 an 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).

2. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 1, characterized in that: 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 rotatably connected to a lower lug (11); and the lower lug (11) is connected to the outer wall of the nozzle member (9) via a first connecting bolt (15).

3. A rocket engine flexible nozzle thrust vector control characteristic simulation device according to claim 2, 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 according to needs.

4. A rocket engine flexible nozzle thrust vector control characteristic simulation device according to claim 2, characterized in that: A first spring washer (16) is arranged on the first connecting bolt (15), and a first flat washer (17) is arranged at the lower end of the first spring washer (16).

5. The device for simulating thrust vector control characteristics of a rocket engine flexible nozzle according to claim 2, characterized in that: A second spring washer (19) is arranged on the second connecting bolt (18), and a second flat washer (20) is arranged at the lower end of the second spring washer (19).

6. 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, and it can be set to other shapes.

7. 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).

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

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