Spray pipe servo mechanism environment test load simulation device

Abstract

The invention belongs to the technical field of load simulation, and particularly relates to a nozzle servo mechanism environment test load simulation device, which is used for carrying out load simulation on tested equipment, and the tested equipment comprises a gimbal seat, a nozzle simulation piece installed on the gimbal seat and a servo mechanism used for pushing the nozzle simulation piece to swing. The servo mechanisms comprise a first servo mechanism and a second servo mechanism, and the load simulation device comprises two mechanical load mechanisms which are arranged opposite to the first servo mechanism and the second servo mechanism respectively; the mechanical load mechanism comprises a movable rod hinged to the spray pipe simulation piece and a fixed rod hinged to the ground, and a movable plate, an elastic element and a fixed plate are sequentially arranged between the movable rod and the fixed rod; the servo mechanism pushes the spray pipe simulation piece to swing, and the swing of the spray pipe simulation piece drives the elastic element to stretch or compress. According to the invention, a mechanical load mechanism is adopted, and the device has the advantages of high frequency response and simple wiring during high and low temperature environment simulation.

Description

Technical Field

[0001] The invention belongs to the technical field of load simulation, and in particular relates to a nozzle servo mechanism environmental test load simulation device. Background Art

[0002] During the flight of an aircraft, the vector nozzle needs to perform multiple functions such as propulsion, turning, and attitude adjustment. Generally, a servo mechanism is installed on the aircraft engine nozzle to complete the swing control of the engine nozzle. Two servo mechanisms need to be installed on the engine nozzle. The two servo mechanisms are arranged perpendicular to each other on the side of the engine, so that the nozzle can swing in all axes, and then the pitch and yaw movements of the aircraft are achieved by controlling the nozzle.

[0003] If there are design or control defects in the nozzle, it can easily cause an aircraft accident, so load simulation testing of the nozzle is very important and necessary.

[0004] Most existing simulation devices use a load hydraulic cylinder that is matched with a servo mechanism. The load hydraulic cylinder is connected to a nozzle simulation component. When the servo mechanism loads the nozzle simulation component, the load hydraulic cylinder is used to simulate the load of the nozzle on the servo mechanism. However, the frequency response of the load device in this simulation method is low, and when simulating high and low temperature environment tests, the use of the load hydraulic cylinder to simulate the load of the nozzle on the servo mechanism requires the layout of the load hydraulic cylinder pipeline, which is relatively cumbersome. Summary of the invention

[0005] In order to solve the problems in the above-mentioned background technology, the present invention provides a nozzle servo mechanism environmental test load simulation device, which simulates various torque loads that the servo mechanism is subjected to during the swing of the nozzle through a mechanical load mechanism. Compared with simulating various torque loads that the servo mechanism is subjected to during the swing of the nozzle through a load hydraulic cylinder, the mechanical load mechanism has a high frequency response, and the use of the mechanical load mechanism does not require the layout of the pipeline of the load hydraulic cylinder, thereby simplifying the wiring method.

[0006] The present invention provides a nozzle servo mechanism environmental test load simulation device, which is used for load simulation of a device under test. The device under test comprises a gimbal, a nozzle simulation part installed on the gimbal, and a servo mechanism for driving the nozzle simulation part to swing. The gimbal and the servo mechanism are installed on the ground. The servo mechanism comprises a first servo mechanism and a second servo mechanism. The first servo mechanism and the second servo mechanism are installed on the side of the nozzle simulation part and the first servo mechanism and the second servo mechanism are arranged vertically. The load simulation device comprises:

[0007] A mechanical load mechanism is installed on the ground, and two mechanical load mechanisms are provided and are respectively arranged opposite to the first servo mechanism and the second servo mechanism;

[0008] The mechanical load mechanism comprises a movable rod hinged to the nozzle simulation component and a fixed rod hinged to the ground, and a movable plate, an elastic element and a fixed plate are sequentially arranged between the movable rod and the fixed rod;

[0009] The servo mechanism drives the nozzle simulation part to swing, and the swing of the nozzle simulation part drives the elastic element to stretch or compress, so as to simulate the torque load on the servo mechanism.

[0010] Furthermore, the gimbal, the servo mechanism and the fixed rod are installed on the ground through a base.

[0011] Furthermore, the top end of the first servo mechanism is hinged to the nozzle simulation through a joint bearing, the lower end of the first servo mechanism is hinged to the upper surface of the base through a joint bearing, the top end of the second servo mechanism is hinged to the nozzle simulation through a joint bearing, the lower end of the second servo mechanism is hinged to the upper surface of the base through a joint bearing, the moving rod is hinged to the nozzle simulation through a joint bearing, and the fixed rod is hinged to the upper surface of the base through a joint bearing.

[0012] Furthermore, the first servo mechanism pushes the nozzle simulation component to swing to simulate the movement of the aircraft in the yaw direction, and the second servo mechanism pushes the nozzle simulation component to simulate the movement of the aircraft in the pitch direction, and the yaw direction is perpendicular to the pitch direction.

[0013] Furthermore, a line connecting the rotation center of the spherical bearing connected to the fixed rod and the swing center of the nozzle simulation part is arranged parallel to the horizontal plane.

[0014] Furthermore, the movable rod is slidably sleeved with a connecting plate, a plurality of guide pillars are fixedly connected between the connecting plate and the fixed plate, and the movable plate is slidably plugged into the guide pillars.

[0015] Furthermore, a first bearing is fixedly mounted on the connecting plate, and the moving rod is slidably plugged into the first bearing.

[0016] Furthermore, the movable plate is fixedly mounted with a second bearing corresponding to the guide column, and the guide column is slidably plugged into the second bearing.

[0017] Furthermore, the elastic element is a spring. Compared with the prior art, the beneficial effects of the present invention are:

[0018] (1) The mechanical load mechanism is used to simulate the various torque loads that the servo mechanism pushes the nozzle to swing. Compared with the load hydraulic cylinder, which is used to simulate the various torque loads that the servo mechanism pushes the nozzle to swing, the mechanical load mechanism has a high frequency response. In addition, when conducting environmental test simulations, the mechanical load mechanism does not need to lay out the pipelines of the load hydraulic cylinder, which simplifies the wiring method.

[0019] (2) When the movable plate drives the elastic element to stretch or compress, the movable plate slides relatively along the axis of the guide column. The guide column is used to reduce the possibility of radial deflection of the elastic element during the stretching or compression process, reduce the possibility of radial bending deformation of the elastic element, and improve the accuracy of the force exerted by the elastic element on the nozzle simulation component during the test.

[0020] (3) The line connecting the rotation center B of the joint bearing connected to the fixed rod and the swing center O of the nozzle simulation is arranged parallel to the horizontal plane, which can ensure that when the simulated nozzle swings separately in the pitch and yaw directions, they are not coupled with each other, that is, when the pitch and yaw directions swing separately, their respective movements will not interfere with or affect each other. When the second servo mechanism alone pushes the nozzle simulation to swing to simulate the pitch motion, the mechanical load mechanism in the pitch direction is stretched or compressed, generating a force on the nozzle simulation, while the length of the mechanical load mechanism in the yaw direction does not change, and no force on the nozzle simulation is generated; similarly, when the first servo mechanism alone pushes the nozzle simulation to swing to simulate the yaw motion, the mechanical load mechanism in the yaw direction is stretched or compressed, generating a force on the nozzle simulation, while the length of the mechanical load mechanism in the pitch direction does not change, and no force on the nozzle simulation is generated. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0022] Figure 1 This is a schematic diagram of the structure of an embodiment of the present application;

[0023] Figure 2 is a schematic diagram of a first servo mechanism and a second servo mechanism in this embodiment;

[0024] Figure 3 This is a schematic diagram of the structure of the movable plate in this embodiment;

[0025] Figure 4 This is a schematic diagram showing that the line connecting the rotation center of the bottom joint bearing and the swing center of the nozzle simulation part is parallel to the horizontal plane in this embodiment.

[0026] Explanation of the reference numerals: 1. base; 2. gimbal; 3. nozzle simulation; 4. first servo mechanism; 5. second servo mechanism; 6. mechanical load mechanism; 61. moving rod; 62. movable plate; 621. second bearing; 63. elastic element; 64. fixed plate; 65. fixed rod; 66. connecting plate; 661. first bearing; 67. guide column. DETAILED DESCRIPTION

[0027] The following will be combined with the accompanying drawings in the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work belong to the protection scope of the present invention.

[0028] The following is combined with Figure 1 To Attachment Figure 4 The present invention is described in detail with reference to specific embodiments.

[0029] like Figures 1 to 4 As shown, the present invention provides a nozzle servo mechanism environmental test load simulation device, which is used to perform load simulation on the equipment under test. The equipment under test includes a gimbal 2 installed on the ground, a nozzle simulation part 3 fixedly connected to the upper surface of the gimbal 2, and a servo mechanism for driving the nozzle simulation part 3 to swing. A base 1 is provided between the gimbal 2 and the ground, the gimbal 2 is fixedly connected to the upper surface of the base 1, and the gimbal 2 is installed on the ground through the base 1. The nozzle simulation part 3 can swing around the swing center under the push of the servo mechanism.

[0030] The servo mechanism includes a first servo mechanism 4 and a second servo mechanism 5. The top end of the first servo mechanism 4 is hinged to the nozzle simulation part 3 through a joint bearing, and the bottom end of the first servo mechanism 4 is hinged to the upper surface of the base 1 through a joint bearing. When the first servo mechanism 4 loads the nozzle simulation part 3, the first servo mechanism 4 drives the nozzle simulation part 3 to swing, which is used to simulate the movement of the aircraft in the yaw direction. The first servo mechanism 4 is a hydraulic cylinder in this embodiment, and can also be a servo mechanism that can drive the nozzle simulation part 3 to swing by an electric telescopic rod.

[0031] The top end of the second servo mechanism 5 is hinged to the nozzle simulation part 3 through a joint bearing, and the bottom end of the second servo mechanism 5 is hinged to the upper surface of the base 1 through a joint bearing. When the second servo mechanism 5 loads the nozzle simulation part 3, the second servo mechanism 5 drives the nozzle simulation part 3 to swing, which is used to simulate the movement of the aircraft in the pitch direction. The second servo mechanism 5 is a hydraulic cylinder in this embodiment, and can also be a servo mechanism that can drive the nozzle simulation part 3 to swing by an electric telescopic rod.

[0032] The first servo mechanism 4 pushes the nozzle simulation part 3 to swing to simulate the movement of the aircraft in the yaw direction, and the second servo mechanism 5 pushes the nozzle simulation part 3 to swing to simulate the movement of the aircraft in the pitch direction. The yaw direction is perpendicular to the pitch direction.

[0033] The load simulation device includes two mechanical load mechanisms 6, and the two mechanical load mechanisms 6 are respectively arranged opposite to the first servo mechanism 4 and the second servo mechanism 5, that is, the two mechanical load mechanisms 6 are arranged at 90° in the circumference of the nozzle simulation part 3, and the top end of the mechanical load mechanism 6 is hinged to the nozzle simulation part 3 through a joint bearing, and the bottom end of the mechanical load mechanism 6 is hinged to the upper surface of the base 1 through a joint bearing.

[0034] When the first servo mechanism 4 pushes the nozzle simulation component 3 to swing to simulate the movement of the aircraft in the yaw direction, the nozzle simulation component 3 pulls and presses the mechanical load mechanism 6 opposite to the first servo mechanism 4. The mechanical load mechanism 6 opposite to the first servo mechanism 4 simulates the load of the nozzle simulation component 3 on the first servo mechanism 4 through the reaction force on the nozzle simulation component 3, thereby simulating the various torque loads received by the first servo mechanism 4 during yaw.

[0035] When the second servo mechanism 5 pushes the nozzle simulation component 3 to swing to simulate the movement of the aircraft in the pitch direction, the nozzle simulation component 3 pulls and presses the mechanical load mechanism 6 opposite to the second servo mechanism 5. The mechanical load mechanism 6 opposite to the second servo mechanism 5 simulates the load of the nozzle simulation component 3 on the second servo mechanism 5 through the reaction force on the nozzle simulation component 3, thereby simulating the various torque loads received by the second servo mechanism 5 during pitch.

[0036] The mechanical load mechanism 6 is used to simulate various torque loads in the process of the nozzle swinging driven by the servo mechanism. Compared with the various torque loads in the process of the nozzle swinging driven by the servo mechanism simulated by the load hydraulic cylinder, the mechanical load mechanism 6 has a high frequency response, that is, the mechanical load mechanism 6 can quickly respond to the swinging action of the engine and apply the load; the device under test and the mechanical load mechanism 6 are placed in a high and low temperature environmental test chamber, wherein the device under test includes a base 1, a gimbal 2, a nozzle simulation part 3 and a servo mechanism, and the environmental test chamber can simulate high and low temperature environments, the low temperature can simulate -55°C, and the high temperature can simulate 85°C. The mechanical simulation device does not need to layout complex and cumbersome pipelines, which simplifies the wiring method of the entire device.

[0037] like Figure 3As shown, the mechanical load mechanism 6 includes a movable rod 61 hinged to the top of the nozzle simulation part 3 and a fixed rod 65 hinged to the base 1, and a movable plate 62, an elastic element 63 and a fixed plate 64 are arranged in sequence between the movable rod 61 and the fixed rod 65. The top of the movable rod 61 is hinged to the nozzle simulation part 3 through a joint bearing, and a reinforcing plate is arranged between the bottom of the movable rod 61 and the movable plate 62. The reinforcing plate and the movable rod 61 are integrally formed, and multiple screw holes are provided in the circumference of the reinforcing plate, and multiple screw holes are provided in the circumference of the movable plate 62. The screw holes on the reinforcing plate correspond to the screw holes on the movable plate 62 one by one, and the screws pass through the screw holes on the reinforcing plate and the screw holes on the movable plate 62 to fix the movable rod 61 and the movable plate 62 together; the bottom of the fixed rod 65 is hinged to the base 1 through a joint bearing, and the top of the fixed rod 65 is connected and fixed to the fixed plate 64. The fixing method is similar to the fixing method between the movable rod 61 and the movable plate 62, which will not be repeated here; an elastic element 63 is installed between the movable plate 62 and the fixed plate 64, and the elastic element 63 is a tension and compression bidirectional spring. In order to evenly transmit the elastic force generated by the tension and compression bidirectional spring to the nozzle simulation part 3, the axis of the elastic element 63, the axis of the fixed rod 65 and the axis of the movable rod 61 coincide.

[0038] When the nozzle simulation part 3 swings, the nozzle simulation part 3 drives the elastic element 63 to stretch or compress through the movable rod 61 and the movable plate 62. The reaction force of the elastic element 63 directly facing the first servo mechanism 4 on the nozzle simulation part 3 simulates the moment load on the first servo mechanism 4 during yaw, and the reaction force of the elastic element 63 directly facing the second servo mechanism 5 on the nozzle simulation part 3 simulates the moment load on the second servo mechanism 5 during pitch. The mechanical load method of driving the elastic element 63 to stretch or compress through the movable rod 61 and the movable plate 62 simulates the various moment loads on which the servo mechanism drives the nozzle to swing. Compared with the simulation of the various moment loads on which the servo mechanism drives the nozzle to swing through the load hydraulic cylinder, the mechanical load mechanism 6 has a high frequency response, and the use of the mechanical load mechanism 6 does not require the layout of the pipeline of the load hydraulic cylinder, which simplifies the wiring method.

[0039] The outer periphery of the movable rod 61 is sleeved with a connecting plate 66, and a first bearing 661 is fixedly installed inside the connecting plate 66. A connecting hole is opened inside the connecting plate 66, and the first bearing 661 is arranged in the connecting hole and fixed to the connecting plate 66 by screws. The movable rod 61 and the first bearing 661 are slidably plugged. A plurality of guide posts 67 are fixedly connected between the connecting plate 66 and the fixed plate 64. In this example, there are four guide posts 67. The guide posts 67 penetrate the movable plate 62, and four second bearings 621 are fixedly installed inside the movable plate 62. The fixing method is similar to the fixing method between the first bearing 661 and the connecting plate 66, and will not be repeated here. The second bearing 621 and the guide posts 67 are arranged one by one, and the guide posts 67 and the second bearing 621 are slidably plugged. The axis of the guide posts 67 is parallel to the axis of the elastic element 63, so that the elasticity generated by the tension and compression bidirectional spring is evenly transmitted to the nozzle simulation part 3 to simulate the various torque loads received by the servo mechanism.

[0040] When the movable plate 62 drives the elastic element 63 to stretch or compress, the movable plate 62 slides relatively along the axis of the guide column 67. The guide column 67 is used to reduce the possibility of radial deflection of the elastic element 63 during the stretching or compression process, reduce the possibility of radial bending and deformation of the elastic element 63, and improve the accuracy of the force exerted by the elastic element 63 on the nozzle simulation component 3 during the test.

[0041] During the sliding of the movable rod 61 relative to the connecting plate 66, the movable rod 61 is slidably connected to the first bearing 661, and the first bearing 661 reduces the wear of the connecting plate 66 caused by the movable rod 61 directly contacting and sliding with the connecting plate 66. During the sliding of the movable plate 62 relative to the guide post 67, the guide post 67 is slidably connected to the second bearing 621, and the second bearing 621 reduces the wear of the movable plate 62 caused by the guide post 67 directly contacting and sliding with the movable plate 62.

[0042] The rotation center B of the joint bearing located at the bottom and the line connecting the swing center O of the nozzle simulation part 3 are arranged parallel to the horizontal plane, and the upper surface of the base 1 is parallel to the horizontal plane, that is, the rotation center B of the joint bearing connected to the fixed rod 65 and the line connecting the swing center O of the nozzle simulation part 3 are arranged parallel to the horizontal plane, and the rotation center B of the joint bearing connected to the lower end of the first servo mechanism 4 and the second servo mechanism 5 and the line connecting the swing center O of the nozzle simulation part 3 are arranged parallel to the horizontal plane, which can ensure that when the nozzle swings separately in the pitch and yaw directions, they are not coupled with each other, that is, when the pitch and yaw directions swing separately, their respective movements will not interfere or affect each other.

[0043] When the second servo mechanism 5 alone pushes the nozzle simulation component 3 to swing to simulate the pitch motion, the mechanical load mechanism 6 in the pitch direction is stretched or compressed, generating a force on the nozzle simulation component 3, while the length of the mechanical load mechanism 6 in the yaw direction does not change, and no force on the nozzle simulation component 3 is generated; similarly, when the first servo mechanism 4 alone pushes the nozzle simulation component 3 to swing to simulate the yaw motion, the mechanical load mechanism 6 in the yaw direction is stretched or compressed, generating a force on the nozzle simulation component 3, while the length of the mechanical load mechanism 6 in the pitch direction does not change, and no force on the nozzle simulation component 3 is generated.

[0044] When the nozzle simulation part 3 swings in the yaw direction, the mechanical load mechanism 6 in the pitch direction will not generate any force on the nozzle simulation part 3, thus improving the accuracy of the test data when the yaw direction is simulated alone; when the nozzle simulation part 3 swings in the pitch direction, the mechanical load mechanism 6 in the yaw direction will not generate any force on the nozzle simulation part 3, thus improving the accuracy of the test data when the pitch direction is simulated alone. This is determined by the fact that the line connecting O and B is parallel to the horizontal plane, i.e., the situation of mutual non-coupling.

[0045] Take the simulated pitch action as an example. Figure 4 It is the mechanical load mechanism 6 in the yaw direction. Points A and B swing around the swing center O respectively. When point A swings around point O, point O is the swing center and OA is a fixed length for swinging. When point B swings around point O, point O is the swing center and OB is a fixed length for swinging. When the line connecting O and B is parallel to the horizontal plane, the position of point B does not change during the swinging process. B is a fixed point. The lengths of OA and OB are both fixed values, and their angles are also fixed. Therefore, AB is a fixed length, that is, the length of the mechanical load mechanism 6 in the yaw direction does not change, and the mechanical load mechanism 6 in the yaw direction will not generate tension or pressure. When the line connecting O and B is not parallel to the horizontal plane, point B will make a conical motion with point O as the vertex and OB as the generatrix. If the position of point B changes, the length of AB changes, and the mechanical load mechanism 6 in the yaw direction generates tension or pressure, resulting in the occurrence of coupling phenomenon.

[0046] The implementation principle of the nozzle servo mechanism environmental test load simulation device provided by the present invention is: when the first servo mechanism 4 or the second servo mechanism 5 drives the nozzle simulation part 3 to swing, the nozzle simulation part 3 drives the elastic element 63 to stretch or compress through the moving rod 61 and the movable plate 62, and the reaction force of the elastic element 63 opposite to the first servo mechanism 4 on the nozzle simulation part 3 simulates the torque load received by the first servo mechanism 4 during yaw, and the reaction force of the elastic element 63 opposite to the second servo mechanism 5 on the nozzle simulation part 3 simulates the torque load received by the second servo mechanism 5 during pitch.

[0047] The first servo mechanism 4 pushes the nozzle simulation member 3 to swing to simulate the aircraft moving in the yaw direction, and the second servo mechanism 5 pushes the nozzle simulation member 3 to swing to simulate the aircraft moving in the pitch direction, and the yaw direction is perpendicular to the pitch direction. The line connecting the rotation center B of the joint bearing connected to the fixed rod 65 and the swing center O of the nozzle simulation member 3 is arranged parallel to the horizontal plane, which can ensure that the two directions of pitch and yaw are not coupled to each other when simulating independent swings, that is, when the pitch and yaw directions swing independently, their respective movements will not interfere or affect each other.

[0048] The movable rod 61 and the movable plate 62 drive the elastic element 63 to stretch or compress the mechanical load to simulate the various torque loads that the servo mechanism pushes the nozzle to swing. Compared with the various torque loads that the servo mechanism pushes the nozzle to swing by using a load hydraulic cylinder, the mechanical load mechanism 6 has a high frequency response and the use of the mechanical load mechanism 6 does not require the layout of the pipeline of the load hydraulic cylinder, thereby simplifying the wiring method.

[0049] The present invention is further described above with the aid of specific embodiments. However, it should be understood that the specific description here should not be construed as limiting the essence and scope of the present invention. Various modifications made to the above embodiments by ordinary technicians in the field after reading this specification are all within the scope of protection of the present invention.

Claims

1. A nozzle servo mechanism environmental test load simulation device, used for performing load simulation on a device under test, wherein the device under test comprises a gimbal (2), a nozzle simulation member (3) mounted on the gimbal (2), and a servo mechanism for driving the nozzle simulation member (3) to swing, wherein the gimbal (2) and the servo mechanism are mounted on the ground, wherein the servo mechanism comprises a first servo mechanism (4) and a second servo mechanism (5), wherein the first servo mechanism (4) and the second servo mechanism (5) are mounted on the side of the nozzle simulation member (3) and the first servo mechanism (4) and the second servo mechanism (5) are arranged vertically, and wherein the device comprises: include: A mechanical load mechanism (6) is installed on the ground, wherein two mechanical load mechanisms (6) are provided and are respectively arranged opposite to the first servo mechanism (4) and the second servo mechanism (5); The mechanical load mechanism (6) comprises a movable rod (61) hinged to the nozzle simulation component (3) and a fixed rod (65) hinged to the ground, and a movable plate (62), an elastic element (63) and a fixed plate (64) are sequentially arranged between the movable rod (61) and the fixed rod (65); The servo mechanism drives the nozzle simulation part (3) to swing, and the swing of the nozzle simulation part (3) drives the elastic element (63) to stretch or compress, so as to simulate the torque load received by the servo mechanism.

2. The nozzle servo mechanism environmental test load simulation device according to claim 1, characterized in that: The gimbal (2), servo mechanism and fixed rod (65) are installed on the ground via a base (1).

3. The nozzle servo mechanism environmental test load simulation device according to claim 2, characterized in that: The top end of the first servo mechanism (4) is hinged to the nozzle simulation part (3) through a joint bearing, the lower end of the first servo mechanism (4) is hinged to the upper surface of the base (1) through a joint bearing, the top end of the second servo mechanism (5) is hinged to the nozzle simulation part (3) through a joint bearing, the lower end of the second servo mechanism (5) is hinged to the upper surface of the base (1) through a joint bearing, the moving rod (61) is hinged to the nozzle simulation part (3) through a joint bearing, and the fixed rod (65) is hinged to the upper surface of the base (1) through a joint bearing.

4. The nozzle servo mechanism environmental test load simulation device according to claim 1, characterized in that: The first servo mechanism (4) pushes the nozzle simulation part (3) to swing to simulate the movement of the aircraft in the yaw direction, and the second servo mechanism (5) pushes the nozzle simulation part (3) to simulate the movement of the aircraft in the pitch direction, and the yaw direction and the pitch direction are perpendicular to each other.

5. The nozzle servo mechanism environmental test load simulation device according to claim 3, characterized in that: The line connecting the rotation center of the joint bearing connected to the fixed rod (65) and the swing center of the nozzle simulation part (3) is arranged parallel to the horizontal plane.

6. The nozzle servo mechanism environmental test load simulation device according to claim 1, characterized in that: The movable rod (61) is slidably sleeved with a connecting plate (66), a plurality of guide pillars (67) are fixedly connected between the connecting plate (66) and the fixed plate (64), and the movable plate (62) is slidably plugged with the guide pillars (67).

7. The nozzle servo mechanism environmental test load simulation device according to claim 6, characterized in that: The connecting plate (66) is fixedly mounted with a first bearing (661), and the movable rod (61) is slidably plugged into the first bearing (661).

8. The nozzle servo mechanism environmental test load simulation device according to claim 6, characterized in that: The movable plate (62) is fixedly mounted with a second bearing (621) arranged corresponding to the guide column (67), and the guide column (67) is slidably plugged into the second bearing (621).

9. The nozzle servo mechanism environmental test load simulation device according to claim 1, characterized in that: The elastic element (63) is a spring.

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