Airship power propulsion system integration test device and method

Abstract

The invention provides an airship power propulsion system integration test device and method. The test device comprises a fixed frame assembly (1), a top sliding frame assembly (2), a middle frame assembly (3), a sensor system (4) and a measurement and control cabinet (5). The two sides of the middle frame assembly (3) are slidably connected with an airship power propulsion system test piece, and the top of the middle frame assembly (3) is hung on the fixed frame assembly (1) through the top sliding frame assembly (2), so that the airship power propulsion system test piece is hung and hoisted at different heights. The measurement and control cabinet (5) is used for controlling an engine of the power propulsion system and collecting data of an engine parameter sensor so as to meet the requirements for integrated installation and multi-working-condition test of the airship power propulsion system.

Description

Technical Field

[0001] This invention relates to the field of aircraft propulsion system integration testing, specifically to an airship propulsion system integration testing apparatus and method. Background Technology

[0002] With the continuous development of the low-altitude economy, airships, as lighter-than-air aircraft capable of vertical takeoff and landing, offer irreplaceable advantages in low-altitude sightseeing tourism due to their high safety and low cost. Airship propulsion systems typically possess vectoring capability, providing thrust vectoring and enabling vertical takeoff and landing.

[0003] The airship propulsion system 200 with vectoring tilt capability is relatively complex and is generally located on the airship pod 100. It includes a power unit 201, a power transmission system 202, a vectoring actuation system 203, a propeller system 204, etc. (See...) Figure 1 and Figure 2 The power plant 201 includes an engine (generally a small-power piston engine), an engine mounting system, an engine control system, an engine intake and exhaust system, an engine ventilation and cooling system, an engine lubrication system, and an engine measurement and display system. The propulsion system is highly complex, requiring integrated installation and a series of tests. These tests include verifying engine operating parameters, single-engine propeller thrust, twin-engine propeller thrust, thrust vectoring function, system vibration and acceleration response, and long-term reliable operation capability. Only after these tests can the system be installed on the airship for onboard testing.

[0004] Existing test setups for aircraft propulsion systems are generally designed for "single engine or electric motor + propeller" systems, and are all fixed on the ground, which cannot simulate the actual suspended installation method on a boat. For example, the device disclosed in publication number CN117699043A for testing electric propulsion single-propeller power systems, the dynamic test platform for electric propulsion systems of tiltable electric aircraft disclosed in publication number CN116046428A, and the test rig for distributed propulsion systems of short takeoff / vertical landing aircraft disclosed in publication number CN111619823A are all system test platform schemes for single engine or electric motor + propeller systems.

[0005] Currently, there is no practical integrated testing and experimental device for airship propulsion systems. Summary of the Invention

[0006] This invention provides an integrated testing apparatus and method for airship propulsion systems to meet the requirements for integrated installation and multi-condition testing of airship propulsion systems.

[0007] The first aspect of the present invention provides an integrated testing device for an airship propulsion system, comprising: a fixed frame assembly 1, a top sliding frame assembly 2, a middle frame assembly 3, a sensor system 4, and a measurement and control cabinet 5; Fixed frame component 1 is a portal-shaped structure that provides basic support for the experiment; The top sliding frame assembly 2 is positioned below the top of the fixed frame assembly 1; a lifting chain 14 is provided on the top sliding frame assembly 2. The airship propulsion system test piece is slidably connected to both sides of the middle frame component 3, and the top is connected to the lifting chain 14 through the locking pin 18, so as to realize the suspension and hoisting of the airship propulsion system test piece at different heights; The top sliding frame assembly 2 and the middle frame assembly 3 are respectively provided with a guide limiting structure 15 and a guide rod 19, which are used to limit the swaying of the airship power propulsion system test piece at the preset suspension and hoisting height; The sensor system 4 includes vibration, temperature, pressure, and flow sensors, which are arranged on the power propulsion system test piece to monitor the system's operating status and are connected to the measurement and control cabinet 5. The control cabinet 5 is used for controlling the engine of the power propulsion system and collecting engine parameter sensor data.

[0008] Optionally, the fixed frame assembly 1 includes: a portal frame 8, a fixed frame 9, and a linear guide rail 10; The fixed frame 9 is located at the center position below the top of the portal frame 8; A linear guide rail 10 is installed below the fixed frame 9; The top sliding frame assembly 2 is mounted on the linear guide rail 10.

[0009] Optionally, the top sliding frame assembly 2 includes: a slider 11, a spiral lifting mechanism 12, and a sliding frame 13; The top of the sliding frame 13 is provided with four sliders 11, which are slidably connected to the linear guide rail 10, so that the top sliding frame assembly 2 can slide relative to the fixed frame assembly 1. A first tension sensor 16 is installed between the sliding frame 13 and the fixed frame 9 to measure the tension of the dual-side propulsion system of the airship. A spiral lifting mechanism 12 is installed on the sliding frame 13. The spiral lifting mechanism 12 is connected to the lifting chain 14 and is used for electric control of the lifting chain 14.

[0010] Optionally, the intermediate frame assembly 3 includes: an intermediate frame 17, a side slider 20, a side guide rail 21, a side sliding frame 22, and a power propulsion system mounting point 23; Side guide rails 21 are provided on both sides of the middle frame 17, and the side sliding frame 22 is slidably mounted on the side guide rails 21 via the side slider 20; The side sliding frame 22 is provided with a power propulsion system mounting point 23 for mounting the airship power propulsion system test piece; A second tension sensor 27 is installed between the side sliding frame 22 and the middle frame 17 to measure the tension of the airship's single-sided power propulsion system.

[0011] Optionally, the bottom of the middle frame 17 is equipped with swivel casters 25.

[0012] Optionally, the intermediate frame 17 is an integral welded structure.

[0013] Optionally, an oil tank 26 is provided at the center of the intermediate frame 17 for supplying oil to the airship propulsion system test piece.

[0014] Optionally, a hand-cranked lifting support leg 24 is provided on the intermediate frame 17; The fixed end of the hand-cranked lifting outrigger 24 is fixedly connected to the intermediate frame 17. By cranking the handle of the hand-cranked lifting outrigger 24, the movable end extends downward toward the fixed end, thereby making the movable end contact the ground.

[0015] Optionally, the guide limiting structure 15 is a V-shaped structure, and the guide rod 19 is rod-shaped.

[0016] A second aspect of the present invention provides an integrated testing method for an airship propulsion system, employing the integrated testing apparatus for an airship propulsion system as described in any one of the first aspects, the method comprising: The airship propulsion system test piece is connected to the intermediate frame assembly 3, and the intermediate frame assembly 3 is connected to the lifting chain 14 by the locking pin 18; Adjust the height of the lifting chain 14 so that the guide rod 19 is locked in the guide limit structure 15, and carry out the start-up test of the power propulsion system in a fixed state; Adjust the height of the lifting chain 14 so that the guide rod 19 is disengaged from the guide limit structure 15, and the intermediate frame assembly 3 is in a suspended state, and carry out the driving test of the power propulsion system in the suspended state.

[0017] The beneficial effects of this invention are as follows: 1) It provides a mobile power propulsion system integration platform, which facilitates the rapid integration and installation of power propulsion systems.

[0018] 2) It provides multiple installation states, allowing tests to be conducted under fixed installation conditions as well as suspended installation conditions; it can conduct tests on single-sided power propulsion systems as well as tests on double-sided power propulsion systems; thus meeting the needs of testing under different conditions. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] Figure 1 This is a diagram showing the location of the airship's propulsion system. Figure 1 ; Figure 2 This is a schematic diagram of the airship's propulsion system. Figure 2 ; Figure 3 This is a schematic diagram of the integrated testing and experimental device for the airship propulsion system of the present invention; Figure 4 This is a schematic diagram of the fixed frame component of the present invention; Figure 5 This is a schematic diagram of the top sliding frame component of the present invention. Figure 1 ; Figure 6 This is a schematic diagram of the top sliding frame component of the present invention. Figure 2 ; Figure 7 This is a schematic diagram of the intermediate framework component of the present invention. Figure 1 ; Figure 8 This is a schematic diagram of the intermediate framework component of the present invention. Figure 2 ; Explanation of reference numerals in the attached figures: 100. Airship pod; 200. Airship propulsion system; 201. Power unit; 202. Power transmission system; 203. Vectoring system; 204. Propeller system; 1. Fixed frame assembly; 2. Top sliding frame assembly; 3. Middle frame assembly; 4. Sensor system; 5. Measurement and control cabinet; 6. Test piece of the left side power propulsion system of the airship; 7. Test piece of the left side power propulsion system of the airship; 8. Portal frame; 9. Fixed frame; 10. Linear guide rail; 11. Slider; 12. Helical lifting mechanism; 13. Sliding frame; 14. Lifting chain; 15. Guide and limit structure; 16. First tension sensor; 17. Middle frame; 18. Locking pin; 19. Guide rod; 20. Side slider; 21. Side guide rail; 22. Side sliding frame; 23. Power propulsion system mounting point; 24. Hand-cranked lifting outrigger; 25. Universal caster; 26. Fuel tank; 27. Second tension sensor. Detailed Implementation

[0021] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0022] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0023] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0024] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0025] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0026] The present invention will be further described in detail below with reference to the embodiments and accompanying drawings, but the embodiments of the present invention are not limited thereto.

[0027] The airship propulsion system is suspended and requires integration and installation in a laboratory before installation, along with verification of its functions, performance, and reliability. The propulsion system is complex and necessitates a convenient integration and installation platform. Furthermore, the airship propulsion system requires diverse testing conditions, including single-engine and dual-engine testing, fixed-installation and suspended-installation testing, monitoring of engine parameters, testing of impact and vibration responses under different conditions, and durability testing. The purpose of this invention is to address and meet the multi-condition testing requirements of the airship propulsion system.

[0028] like Figure 3-8 As shown, this invention provides an integrated testing and experimental device for an airship propulsion system, suitable for twin-engine airships, and is achieved through the following technical solution: The integrated testing and experimental apparatus for the airship propulsion system mainly consists of a fixed frame assembly 1, a top sliding frame assembly 2, a middle frame assembly 3, a sensor system 4, and a control cabinet 5. The fixed frame assembly 1 provides the foundation support for the test; the middle frame assembly 3 provides a convenient integrated installation platform for the airship propulsion system test pieces 6 and 7; the sensor system 4 includes sensors for vibration, temperature, pressure, and flow, which are arranged on the propulsion system test pieces to monitor the system's operating status; and the control cabinet 5 is used for controlling the propulsion system engine and collecting engine parameter sensor data.

[0029] Combination Figure 3 and Figure 4 The fixed frame assembly 1 consists of a portal frame 8, a fixed frame 9, and a linear guide rail 10.

[0030] Combination Figure 5 and Figure 6 The top sliding frame assembly 2 consists of sliders 11, a spiral lifting mechanism 12, a sliding frame 13, a lifting chain 14, and a guide and limiting structure 15. The top sliding frame assembly 2 is connected to the linear guide rails 10 on the fixed frame assembly via four sliders 11, allowing the top sliding frame assembly 2 to slide relative to the fixed frame assembly 1. The spiral lifting mechanism 12 is mounted on the sliding frame 13 and can electrically control the lifting of the lifting chain 14. A first tension sensor 16 is installed between the sliding frame 13 and the fixed frame 9 to measure the tension of the airship's dual-side propulsion system.

[0031] Combination Figure 7 and Figure 8The intermediate frame assembly 3 consists of an intermediate frame 17, locking pins 18, guide rods 19, side sliders 20, side guide rails 21, side sliding frames 22, propulsion system mounting points 23, hand-cranked lifting outriggers 24, swivel casters 25, and an oil supply tank 26. The intermediate frame 17 is an integral welded structure, with its top connected to the lifting chain 14 via locking pins 18. The side guide rails 21 are fixedly mounted on the intermediate frame 17, and the side sliding frames 22 are mounted on the side guide rails 21 via side sliders 20, allowing the side sliding frames 22 to slide relative to the intermediate frame 17. A second tension sensor 27 is installed between the side sliding frames 22 and the intermediate frame 17 to measure the tension of the propulsion system on one side of the airship. Four propulsion system mounting points 23 are provided on the side sliding frames 22 for the installation of the propulsion system. One side sliding frame 22 is arranged on each of the left and right sides of the intermediate frame 17, for the integrated installation of the propulsion systems on the left and right sides of the airship, respectively.

[0032] Specific implementation methods: Integration and installation of the power propulsion system test component: Remove the locking pin 18 between the top sliding frame 13 and the intermediate frame assembly 3, place the intermediate frame assembly 3 on the ground, and the casters 25 on the intermediate frame assembly 3 allow the assembly to be moved to a suitable position to carry out the integration and installation of the power propulsion system. The hand-cranked lifting outrigger 24 can fix and level the intermediate frame assembly 3, facilitating the integration and installation of the power propulsion system on the intermediate frame assembly 3.

[0033] Suspending the power propulsion system to the test device: First, move the intermediate frame assembly 3, which integrates and installs the power propulsion system test piece, to below the fixed frame assembly 1. Raise the intermediate frame assembly 3 by using the hand-cranked lifting outrigger 24. Connect the lifting chain 14 on the intermediate frame assembly 3 and the sliding frame assembly using the locking pin 18. Then, retract the hand-cranked lifting outrigger 24 to achieve the suspension installation of the intermediate frame assembly 3.

[0034] Engine parameter sensor installation and layout: Install engine parameter monitoring sensors, including speed sensors, temperature sensors, pressure sensors, vibration sensors, etc., on the power propulsion system and connect them to the control cabinet 5 through wiring to check and confirm that the communication of each sensor is normal.

[0035] Fixed-state operation test of the propulsion system: The lifting chain 14 is raised and tightened by the screw lifting mechanism 12, causing the guide rod 19 on the intermediate frame assembly to be guided into the guide limiting structure 15. The guide limiting structure 15 can restrict the degrees of freedom of the intermediate frame assembly in the horizontal direction. When the screw lifting mechanism 12 is raised to the top, the vertical degrees of freedom of the intermediate frame assembly 3 are also restricted. At this time, the propulsion system test piece and the intermediate frame assembly 3 are fixedly installed, and the fixed-state start-up test of the propulsion system can be carried out. By operating the control switches and levers on the control cabinet 5, the propulsion system can be started, and the various parameters of the propulsion system can be monitored to ensure they are normal. The tension and vibration characteristics of the propulsion system under engine start-up conditions and various speed conditions can be measured.

[0036] Power propulsion system suspension test: The lifting chain 14 is lowered by a suitable length using the screw lifting mechanism 12, causing the guide rod 19 on the intermediate frame assembly to disengage from the guide limiting structure 15, thus suspending the intermediate frame assembly 3. At this point, the power propulsion system test piece and the intermediate frame assembly 3 are suspended as a whole, allowing for a power propulsion system start-up test in suspension. By operating the control switches and levers on the control cabinet 5, the power propulsion system can be started, and the various parameters of the power propulsion system can be monitored to ensure they are normal. The tension and vibration characteristics of the power propulsion system under engine start-up conditions and at various speeds can be measured. This test allows for the measurement of the vibration response characteristics of the power propulsion system under different suspension lengths, providing a reference for the suspension installation design on airships.

[0037] Single / Dual-sided Power Propulsion System Tensile Test: When it is necessary to carry out the integration test of a single-sided power propulsion system, it is only necessary to install the power propulsion system test piece on the single-sided sliding frame 22 to easily carry out the integration installation test of the single-sided power propulsion system.

[0038] The above detailed embodiments are a description of the present invention. It should not be considered that the specific embodiments of the present invention are limited to these descriptions. For those skilled in the art, several simple deductions and substitutions can be made without departing from the concept of the present invention, and all of these should be considered to fall within the protection scope of the present invention.

Claims

1. An airship power propulsion system integration test apparatus, characterized by, The utility model relates to a test device for airship power propulsion system, which comprises a fixed frame assembly (1), a top sliding frame assembly (2), a middle frame assembly (3), a sensor system (4) and a control cabinet (5). The fixed frame assembly (1) is a door-shaped structure and provides basic support for the test. The top sliding frame assembly (2) is slidably arranged on the top of the fixed frame assembly (1) and is provided with a first tension sensor (16) between the fixed frame assembly (1) and the top sliding frame assembly (2). The middle frame assembly (3) is slidably connected with the airship power propulsion system test piece on both sides and is provided with a second tension sensor (27) between the middle frame assembly (3) and the airship power propulsion system test piece. The top sliding frame assembly (2) and the middle frame assembly (3) are respectively provided with a guide limiting structure (15) and a guide rod (19) for limiting the swing of the airship power propulsion system test piece at a preset suspension height. The sensor system (4) comprises vibration, temperature, pressure and flow sensors and is arranged on the power propulsion system test piece for monitoring the system operation state and connected with the control cabinet (5). The control cabinet (5) is used for controlling the power propulsion system engine and collecting the engine parameter sensor data. The fixed frame assembly (1) comprises a door-shaped frame (8), a fixed frame (9) and a linear guide rail (10).

2. The airship power propulsion system integration test apparatus of claim 1, wherein, The fixed frame (9) is arranged at the center position below the top of the door-shaped frame (8). The linear guide rail (10) is arranged below the fixed frame (9). The top sliding frame assembly (2) is slidably arranged on the linear guide rail (10). The top sliding frame assembly (2) comprises a sliding block (11), a screw lifting mechanism (12) and a sliding frame (13).

3. The airship power propulsion system integration test apparatus of claim 2, wherein, The sliding frame (13) is provided with four sliding blocks (11) on the top and is slidably connected with the linear guide rail (10), so that the top sliding frame assembly (2) can slide relative to the fixed frame assembly (1). The first tension sensor (16) is arranged between the sliding frame (13) and the fixed frame (9) for measuring the tension of the airship power propulsion system. The screw lifting mechanism (12) is installed on the sliding frame (13) and is connected with the lifting chain (14) for electrically controlling the lifting of the lifting chain (14). The middle frame assembly (3) comprises a middle frame (17), a side sliding block (20), a side guide rail (21), a side sliding frame (22) and a power propulsion system mounting point (23).

4. The airship power propulsion system integration test apparatus of claim 3, wherein, The middle frame (17) is provided with the side guide rail (21) on both sides, and the side sliding frame (22) is slidably installed on the side guide rail (21) through the side sliding block (20). The side sliding frame (22) is provided with the power propulsion system mounting point (23) for mounting the airship power propulsion system test piece. The second tension sensor (27) is arranged between the side sliding frame (22) and the middle frame (17) for measuring the tension of the airship power propulsion system. The middle frame (17) is provided with universal casters (25) on the bottom.

5. The airship power propulsion system integration test apparatus of claim 4, wherein, ​ 6. The airship power propulsion system integration test apparatus of claim 4, wherein, The intermediate frame (17) is a whole welded structure.

7. The airship power propulsion system integration test apparatus of claim 4, wherein, An oil tank (26) is arranged at the center of the intermediate frame (17) and used for supplying oil to the test piece of the airship power propulsion system.

8. The airship power propulsion system integration test apparatus of claim 4, wherein, The intermediate frame (17) is provided with a hand-operated lifting support leg (24). The fixed end of the hand-operated lifting support leg (24) is fixedly connected to the intermediate frame (17), and the movable end is driven to extend out of the fixed end by shaking the handle of the hand-operated lifting support leg (24), so that the movable end contacts the ground.

9. The airship power propulsion system integration test apparatus of claim 1, wherein, The guide limiting structure (15) is a V-shaped structure, and the guide rod (19) is a rod-shaped structure.

10. A method of testing an integrated power propulsion system for an airship, comprising: The airship power propulsion system integrated test device is used to perform the method, and the method comprises the following steps: The airship power propulsion system test piece is connected to the intermediate frame assembly (3), and the intermediate frame assembly (3) is connected to the lifting locking chain (14) through the locking pin (18); The height of the lifting locking chain (14) is adjusted, the guide rod (19) is clamped in the guide limiting structure (15), and the power propulsion system start-up test in a fixed state is carried out; The height of the lifting locking chain (14) is adjusted, the guide rod (19) is separated from the guide limiting structure (15), the intermediate frame assembly (3) is in a suspended state, and the power propulsion system start-up test in the suspended state is carried out.

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