A liquid carrier rocket engine semi-physical simulation device with a tank bottom

Abstract

The utility model provides a kind of liquid carrying rocket engine semi-physical simulation device with tank bottom, and the engine semi-physical simulation device includes: engine, servo actuator, engine frame and tank bottom. Among them, the lower part of engine frame is fixedly connected with the top of tank bottom by connecting piece, and the upper part of engine frame is used to fixedly connect engine and servo actuator. One end of servo actuator is rotatably connected with engine frame, and the other end is rotatably connected with the side wall of engine. Tank bottom is connected with semi-physical simulation test bed, and semi-physical simulation test bed is connected with engine, to provide required torque for engine. The engine semi-physical simulation device is low in cost, reliable in simulation test result, can accurately simulate the rigidity and modal characteristics of rocket body under engine working condition, and greatly improves the efficiency and accuracy of simulation test data.

Description

Technical Field

[0001] This utility model relates to the field of launch vehicle testing technology, specifically a hardware-in-the-loop simulation device for a liquid launch vehicle engine with a storage tank bottom. Background Technology

[0002] To fully verify the correctness and reliability of the liquid rocket flight control system and the performance indicators of the servo mechanism, liquid rocket engines need to undergo hardware-in-the-loop (HIL) simulation tests on the ground. Currently, liquid rocket second-stage engines are generally connected to the rocket body via an engine rack. During HIL simulation, the engine rack, servo actuators, and engine assembly are connected to a test bench. For structures where the second-stage engine is connected to the bottom of the propellant tank, the tank bottom is a thin-walled structure, and internal pressure exists during flight. The aforementioned HIL structure cannot accurately reflect the flight stiffness and modal characteristics of the rocket body under internal pressure at the tank bottom. This leads to significant deviations between the simulation data and real-world conditions, potentially resulting in economic losses and delays in rocket launch schedules. Utility Model Content

[0003] The purpose of this invention is to overcome the shortcomings of the prior art and provide a semi-physical simulation device for a liquid launch vehicle engine with a tank bottom, which can realize simulation experiments that are close to the real effect and provide relatively realistic and accurate simulation data.

[0004] This invention provides a hardware-in-the-loop (HIL) simulation device for a liquid-fueled launch vehicle engine with a tank bottom. The HIL includes an engine, a servo actuator, an engine frame, and a tank bottom. The lower part of the engine frame is fixedly connected to the top of the tank bottom via a connector. The upper part of the engine frame is used to fixably connect the engine and the servo actuator. One end of the servo actuator is rotatably connected to the engine frame, and the other end is rotatably connected to the engine sidewall. The tank bottom is connected to a hardware-in-the-loop test bench, which is connected to the engine and provides the torque required for testing the engine.

[0005] Furthermore, an axial loading connector is fixedly installed at the lower part of the thrust chamber of the engine, and the axial loading connector is connected to the axial loader of the hardware-in-the-loop test bench for providing axial loading force to simulate engine thrust; a lateral loading connector is fixedly installed at the upper part of the thrust chamber of the engine, and the lateral loading connector is connected to the lateral loader of the hardware-in-the-loop test bench for providing lateral force to simulate the load force during engine swaying.

[0006] Furthermore, the lower sidewall of the thrust chamber of the engine is symmetrically provided with two axial loading connection seats; the upper sidewall of the thrust chamber of the engine is provided with at least two lateral loading connection seats adjacent to each other; the lateral loading connection seats are located on the opposite side of the position where the servo actuator connects to the engine.

[0007] In this embodiment of the utility model, the engine frame includes a frame and a servo bracket. The frame is an integral hollow conical structure, with its top fixedly connected to the engine constant level seat at the end of the engine and its bottom fixedly connected to the bottom of the storage tank. The two fixed ends of the servo bracket are respectively fixedly connected to the top side wall and the bottom side wall of the frame, and the other end of the servo bracket is used to movably connect to one end of the servo actuator.

[0008] Furthermore, the frame has a connecting flange at the top for connecting to the engine's constant level seat, and a connecting ring at the bottom for connecting to the bottom of the storage tank; the conical sidewall of the frame is composed of multiple main beams evenly distributed around an axis, one end of each main beam is fixedly connected to the connecting flange, and the other end branches out into at least two connecting branches near the connecting ring, each connecting branch being fixedly connected to the connecting ring for transmitting engine thrust.

[0009] Further, the servo bracket includes: a servo mounting base, an auxiliary support rod, an upper connecting base, a main support rod, and a lower connecting base. The upper connecting base is fixedly connected to the top side wall of the frame, and the lower connecting base is fixedly connected to the connecting ring. The upper connecting base has a threaded hole, through which one end of the auxiliary support rod is threadedly connected to the connecting base. The lower connecting base has a threaded hole, through which one end of the main support rod is threadedly connected. The servo mounting base has a threaded hole for threaded connection to the other end of the auxiliary support rod and the other end of the main support rod. The servo mounting base has a connecting lug for rotatably connecting to the end of the servo actuator.

[0010] Furthermore, the servo mounting base is threadedly connected to two of the main support rods; each of the main support rods is correspondingly connected to a lower connecting base.

[0011] In this embodiment of the invention, the tank bottom includes a spun bottom, a frame connecting flange, and a semi-physical simulation docking ring. The top of the spun bottom is fixedly connected to the frame connecting flange, and the bottom of the spun bottom is fixedly connected to the semi-physical simulation docking ring. The frame connecting flange is fixedly connected to the connecting ring, and the semi-physical simulation docking ring is fixedly connected to the semi-physical simulation test bench.

[0012] Furthermore, the bottom of the storage tank also has an oxygen delivery flange and a fuel delivery flange, wherein the oxygen delivery flange and the fuel delivery flange are both fixedly mounted on the flange surface of the frame connecting flange; the flange surface of the frame connecting flange is also provided with an axial loading opening, and the axial loader of the semi-physical simulation test bench passes through the axial loading opening and acts on the axial loading connecting seat to provide axial loading force to the engine.

[0013] Furthermore, the cross-section of the semi-physical simulation docking ring is an L-shaped structure, with its vertical surface overlapping the side surface of the spun bottom, and the two are fixedly connected by rivets.

[0014] As can be seen from the above embodiments, the hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom provided by this utility model has at least the following advantages: The hardware-in-the-loop simulation device is low in cost and provides reliable simulation test results. By increasing the thickness of the tank bottom, the stiffness and modal characteristics of the thickened tank bottom are ensured to be consistent with those of a real pressurized tank bottom. This allows for a realistic and accurate simulation of the rocket body's stiffness and modal characteristics under engine operating conditions, greatly improving the efficiency and accuracy of the simulation test data. Furthermore, the hollowed-out frame structure ensures that the hardware-in-the-loop simulation test platform can be connected to the engine without obstruction, thereby enabling the application of precise simulated thrust.

[0015] It should be understood that the above general description and the following specific embodiments are merely exemplary and illustrative, and do not limit the scope of the present invention. Attached Figure Description

[0016] The accompanying drawings are part of the specification of this utility model and illustrate exemplary embodiments of the utility model. The drawings, together with the description in the specification, are used to illustrate the principles of this utility model.

[0017] Figure 1 A schematic diagram of a semi-physical simulation device for a liquid launch vehicle engine with a storage tank bottom, provided by this utility model.

[0018] Figure 2 A schematic diagram of a semi-physical simulation device for a liquid launch vehicle engine with a storage tank bottom, provided for this utility model.

[0019] Figure 3 A schematic diagram of the engine frame structure of a semi-physical simulation device for a liquid launch vehicle engine with a storage tank bottom, provided for this utility model.

[0020] Figure 4 A schematic diagram of the servo support structure of a semi-physical simulation device for a liquid launch vehicle engine with a storage tank bottom, provided for this utility model.

[0021] Figure 5 A schematic diagram of the tank bottom structure of a semi-physical simulation device for a liquid launch vehicle engine with a tank bottom provided by this utility model.

[0022] Figure 6 This utility model provides a schematic diagram showing the connection between the spun bottom of a liquid launch vehicle engine with a tank bottom and the semi-physical simulation docking ring.

[0023] Explanation of reference numerals in the attached figures:

[0024] 1-Engine, 2-Servo actuator, 3-Engine frame, 4-Storm tank bottom;

[0025] 11-Axial loading connecting seat, 12-Lateral loading connecting seat, 13-Engine constant level seat;

[0026] 31-Rack, 32-Servo bracket;

[0027] 41-Spinning bottom, 42-Oxygen delivery flange, 43-Fuel delivery flange, 44-Frame connection flange, 45-Semi-physical simulation docking ring, 46-Axial loading opening;

[0028] 321-Servo mounting base, 322-Auxiliary support rod, 323-Upper connecting base, 324-Main support rod, 325-Lower connecting base. Detailed Implementation

[0029] Various exemplary embodiments of the present invention are now described in detail. This detailed description should not be considered as a limitation of the present invention, but should be understood as a more detailed description of certain aspects, features and implementations of the present invention.

[0030] Various improvements and variations can be made to the specific embodiments described in this utility model without departing from the scope or spirit of this utility model, which will be obvious to those skilled in the art. Other embodiments derived from this utility model description will also be obvious to those skilled in the art. This application specification and embodiments are merely exemplary.

[0031] This invention provides a semi-physical simulation device for a liquid launch vehicle engine with a storage tank bottom, such as... Figure 1The diagram shows the structure of the engine hardware-in-the-loop simulation device. In a specific embodiment, the engine hardware-in-the-loop simulation device includes: an engine 1, a servo actuator 2, an engine frame 3, and a storage tank bottom 4. The lower part of the engine frame 3 is fixedly connected to the top of the storage tank bottom 4 via a connector, and the upper part of the engine frame 3 is used to fixably connect the engine 1 and the servo actuator 2. One end of the servo actuator 2 is rotatably connected to the engine frame 3, and the other end is rotatably connected to the side wall of the engine 1. In this embodiment, the servo actuator 2 is used to control the swaying of the engine 1.

[0032] The tank bottom 4 is connected to a hardware-in-the-loop test bench, which is connected to the engine 1 to provide the torque required for the test. In this embodiment, the tank bottom 4 is thickened to simulate the bottom of a real thin-walled pressurized tank, ensuring that the structural stiffness and modal characteristics of both remain consistent.

[0033] Furthermore, such as Figure 2 As shown, an axial loading connection seat 11 is fixedly installed at the lower part of the thrust chamber of engine 1. The axial loading connection seat 11 is connected to the axial loader of the hardware-in-the-loop test bench used to provide axial loading force to simulate engine thrust.

[0034] A lateral loading connector 12 is fixedly installed on the upper part of the thrust chamber of engine 1. The lateral loading connector 12 is used to provide lateral force to simulate the load force provided during the engine swaying process. It is a lateral loader of the semi-physical simulation test bench, which can then test the servo actuator 2.

[0035] Furthermore, two axial loading connectors 11 are symmetrically arranged on the lower side wall of the thrust chamber of engine 1. The simulation structure of this embodiment, by symmetrically arranging the axial loading connectors 11, ensures that the torque applied by the axial loader to the simulated engine corresponds, thus maintaining consistency between the main structure of engine 1 and its flight state.

[0036] At least two lateral loading connectors 12 are arranged adjacent to each other on the upper sidewall of the thrust chamber of engine 1. In this embodiment, two lateral loading connectors 12 are provided, and the included angle between the two lateral loading connectors 12 is less than 180 degrees. In addition, on the sidewall of the engine thrust chamber, the lateral loading connectors 12 are located on the opposite side of the position where the servo actuator 2 is connected to the engine 1, and are used to counteract the lateral swaying torque applied to the engine by the lateral loader through the two lateral loading connectors 12.

[0037] In specific embodiments of this utility model, such as Figure 3 As shown, the engine frame 3 includes a frame 31 and a servo bracket 32. The frame 31 is an integral hollow conical structure, with its top fixedly connected to the engine constant level seat 13 at the end of the engine 1, and its bottom fixedly connected to the bottom of the storage tank 4, serving the purpose of transmitting torque.

[0038] The two fixed ends of the servo bracket 32 ​​are fixedly connected to the top side wall and the bottom side wall of the frame 31, respectively, and the other end of the servo bracket is used to movably connect to one end of the servo actuator 2.

[0039] Furthermore, the top of the frame 31 has a connecting flange for connecting to the engine constant level seat 13, and the bottom has a connecting ring for connecting to the bottom of the storage tank 4.

[0040] The conical sidewall of the frame 31 is composed of multiple main beams evenly distributed around the axis. One end of each main beam is fixedly connected to a connecting flange, and the other end branches out into at least two connecting branches near the connecting ring. Each connecting branch is fixedly connected to the connecting ring and is used to transmit engine thrust. In this embodiment, for example, the main beam can branch out into three connecting branches near the connecting ring to distribute the engine thrust transmitted by the main beam, ensuring uniform stress on the connecting ring and the bottom of the storage tank 4. Furthermore, the main beam does not interfere with the axial loader of the hardware-in-the-loop test bench.

[0041] Furthermore, such as Figure 4 As shown, the servo bracket 32 ​​includes: a servo mounting base 321, an auxiliary support rod 322, an upper connecting base 323, a main support rod 324, and a lower connecting base 325. The upper connecting base 323 is fixedly connected to the top side wall of the frame 31, and the lower connecting base 325 is fixedly connected to the connecting ring.

[0042] The upper connecting seat 323 has a threaded hole, which is threadedly connected to the external thread at one end of the auxiliary support rod 322. The lower connecting seat 325 has a threaded hole, which is threadedly connected to the external thread at one end of the main support rod 324. The servo mounting seat 321 has a threaded hole that is threadedly connected to the other end of the auxiliary support rod 322 and the other end of the main support rod 324, thus providing stable support for the servo mounting seat 321. In addition, the servo mounting seat 321 has a connecting lug that is rotatably connected to the end of the servo actuator 2.

[0043] In this embodiment, the servo mounting base 321 is threadedly connected to two main support rods 324, and each main support rod 324 is correspondingly connected to a lower connecting seat 325. The two main support rods 324 are set at an angle, which can achieve a stable support effect. The servo bracket 32 ​​adopts a three-bar support structure, which increases the stress area of ​​the tank bottom and improves the rigidity and stability of the servo bracket.

[0044] In specific embodiments of this utility model, such as Figure 5 As shown, the tank bottom 4 includes a spun bottom 41, a frame connecting flange 44, and a semi-physical simulation docking ring 45. The top of the spun bottom 41 is fixedly connected to the frame connecting flange 44, and the bottom of the spun bottom 41 is fixedly connected to the semi-physical simulation docking ring 45.

[0045] The frame connecting flange 44 is fixedly connected to the connecting ring at the bottom of the frame 31.

[0046] The hardware-in-the-loop docking ring 45 is fixedly connected to the hardware-in-the-loop test bench.

[0047] Furthermore, the bottom of the storage tank 4 also has an oxygen delivery flange 42 and a fuel delivery flange 43. Both the oxygen delivery flange 42 and the fuel delivery flange 43 are fixedly mounted on the flange surface of the frame connecting flange 44.

[0048] An axial loading opening 46 is also provided on the flange surface of the frame connecting flange 44. The axial loading opening 46 ensures that the axial loader of the hardware-in-the-loop test bench can pass through the bottom of the storage tank 4 and connect with the axial loading connecting seat 11 on the engine 1 to provide axial loading force to the engine 1. In this embodiment, two axial loading openings 46 are provided on the flange surface of the frame connecting flange 44, corresponding to the two symmetrically arranged axial loading connecting seats 11 at the bottom of the engine 1.

[0049] In specific embodiments of this utility model, such as Figure 6 As shown, the cross-section of the semi-physical simulation docking ring 45 is an L-shaped structure, and its vertical surface overlaps with the side surface of the spun bottom 41 and is fixedly connected by rivets.

[0050] The above description is merely an illustrative embodiment of this utility model. Any equivalent changes and modifications made by those skilled in the art without departing from the concept and principles of this utility model shall fall within the scope of protection of this utility model.

Claims

1. A hardware-in-the-loop simulation device for a liquid-fueled launch vehicle engine with a tank bottom, characterized in that, The engine hardware-in-the-loop simulation device includes: an engine (1), a servo actuator (2), an engine frame (3), and a storage tank bottom (4), wherein, The lower part of the engine frame (3) is fixedly connected to the top of the tank bottom (4) via a connector, and the upper part of the engine frame (3) is used to fix the engine (1) and the servo actuator (2). One end of the servo actuator (2) is rotatably connected to the engine frame (3), and the other end is rotatably connected to the side wall of the engine (1). The bottom of the storage tank (4) is connected to the hardware-in-the-loop test bench, which is connected to the engine (1) and is used to provide the torque required for the test of the engine (1).

2. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom as described in claim 1, characterized in that, An axial loading connection seat (11) is fixedly installed at the lower part of the thrust chamber of the engine (1). The axial loading connection seat (11) is connected to the axial loader of the hardware-in-the-loop test bench for providing axial loading force to simulate engine thrust. A lateral loading connector (12) is fixedly installed on the upper part of the thrust chamber of the engine (1). The lateral loading connector (12) is connected to the lateral loader of the hardware-in-the-loop test bench, which is used to provide lateral force to simulate the load force during the engine swing process.

3. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom according to claim 2, characterized in that, The engine (1) has two axial loading connecting seats (11) symmetrically arranged on the lower side wall of the thrust chamber. At least two of the lateral loading connection seats (12) are arranged adjacent to each other on the upper side wall of the thrust chamber of the engine (1). The lateral loading connector (12) is located opposite the position where the servo actuator (2) is connected to the engine (1).

4. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a storage tank bottom according to claim 2, characterized in that, The engine frame (3) includes a frame (31) and a servo bracket (32), wherein, The frame (31) is an integral hollow cone structure. The top is fixedly connected to the engine constant level seat (13) at the end of the engine (1), and the bottom is fixedly connected to the bottom end of the storage tank bottom (4). The two fixed ends of the servo bracket (32) are fixedly connected to the top side wall and the bottom side wall of the frame (31) respectively, and the other end of the servo bracket (32) is used to be movably connected to one end of the servo actuator (2).

5. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom according to claim 4, characterized in that, The frame (31) has a connecting flange at the top that connects to the engine constant level seat (13) and a connecting ring at the bottom that connects to the bottom of the storage tank (4); The conical sidewall of the frame (31) is composed of multiple main beams evenly distributed around the axis. One end of the main beam is fixedly connected to the connecting flange, and the other end diverges into at least two connecting branches near the connecting ring. Each connecting branch is fixedly connected to the connecting ring for transmitting engine thrust.

6. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom according to claim 5, characterized in that, The servo bracket (32) includes: a servo mounting base (321), an auxiliary support rod (322), an upper connecting base (323), a main support rod (324), and a lower connecting base (325), wherein, The upper connecting seat (323) is fixedly connected to the top side wall of the frame (31), and the lower connecting seat (325) is fixedly connected to the connecting ring; The upper connecting seat (323) has a threaded hole, and one end of the auxiliary support rod (322) is threadedly connected to the connecting seat (323) through the threaded hole; The lower connecting seat (325) has a threaded hole, and the lower connecting seat (325) is threadedly connected to one end of the main support rod (324) through the threaded hole; The servo mounting base (321) has a threaded hole for threaded connection to the other end of the auxiliary support rod (322) and the other end of the main support rod (324); The servo mount (321) has a connecting lug that is rotatably connected to the end of the servo actuator (2).

7. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom according to claim 6, characterized in that, The servo mounting base (321) is threadedly connected to the two main support rods (324). Each of the main support rods (324) is connected to a corresponding lower connecting seat (325).

8. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom according to claim 5, characterized in that, The tank bottom (4) includes a spun bottom (41), a frame connecting flange (44), and a semi-physical simulation docking ring (45), wherein, The top of the spun bottom (41) is fixedly connected to the frame connecting flange (44), and the bottom of the spun bottom (41) is fixedly connected to the semi-physical simulation docking ring (45). The frame connecting flange (44) is fixedly connected to the connecting ring; The hardware-in-the-loop (45) docking ring is fixedly connected to the hardware-in-the-loop test bench.

9. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a storage tank bottom according to claim 8, characterized in that, The bottom of the storage tank (4) also has an oxygen delivery flange (42) and a fuel delivery flange (43), wherein, Both the oxygen delivery flange (42) and the fuel delivery flange (43) are fixedly mounted on the flange surface of the frame connecting flange (44); An axial loading opening (46) is also provided on the flange surface of the frame connecting flange (44). The axial loader of the semi-physical simulation test bench passes through the axial loading opening (46) and acts on the axial loading connecting seat (11) to provide axial loading force to the engine (1).

10. The hardware-in-the-loop simulation device for a liquid launch vehicle engine with a tank bottom according to claim 8, characterized in that, The cross-section of the semi-physical simulation docking ring (45) is an L-shaped structure, and its vertical surface overlaps with the side surface of the spun bottom (41) and is fixedly connected by rivets.

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