CN114056598B - Helicopter fuselage upper platform test device - Google Patents
Helicopter fuselage upper platform test device Download PDFInfo
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- CN114056598B CN114056598B CN202111381910.5A CN202111381910A CN114056598B CN 114056598 B CN114056598 B CN 114056598B CN 202111381910 A CN202111381910 A CN 202111381910A CN 114056598 B CN114056598 B CN 114056598B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a helicopter middle fuselage upper platform test device, which is characterized in that a fuselage butt joint fixing tool is arranged on a ground rail and is used for fixing a middle fuselage of a helicopter; the main speed reducer mounting and loading tool is arranged on the ground rail and is used for mounting a main speed reducer stay bar joint and applying load to the main speed reducer stay bar joint; wherein the main reducer stay bar joint is arranged on the middle machine body; the anti-torsion loading tool is arranged on the machine body butt joint tool and the main speed reducer mounting loading tool and is used for applying load to the main speed reducer anti-torsion joint; wherein the main deceleration anti-torsion connector is arranged on the middle machine body; the invention can simulate the real constraint mode of the butt joint frames at the two ends of the middle machine body, simultaneously apply the main stay bar load and the anti-torsion joint load to the upper platform of the middle machine body, and truly check the static strength and the fatigue strength of the upper platform of the middle machine body and the supporting frame beams thereof.
Description
Technical Field
The invention belongs to the technical field of helicopter structural strength tests, and particularly relates to a helicopter body upper platform test device.
Background
The upper platform of the middle fuselage of the helicopter is used as a mounting platform of a main speed reducer of a rotor system and an engine, so that not only is the lift force of a rotor under different flight conditions transferred, but also the reactive torque (single-rotor-wing-with-tail-rotor configuration) generated by the rotation of a rotor shaft is transferred, and meanwhile, the aerodynamic load and the inertial load generated by the dead weight and the load of the fuselage in the flight and maneuvering processes are borne, and the stress form is very complex.
In the relative technology, the loads of all the components are split, and are checked through single component or local frame beam tests such as a main stay bar, a main stay joint, an anti-torsion joint and the like, so that the strength and the performance of the mounting platform cannot be completely checked, and complex stress conditions such as load coupling and the like caused by periodic deformation of the mounting platform of different component loads cannot be truly simulated.
Disclosure of Invention
Aiming at the technical problems, the invention provides a device for testing a platform on a helicopter body, which comprises the following components:
the machine body butt joint fixing tool is arranged on the ground rail and is used for fixing the middle machine body of the helicopter;
the main speed reducer mounting and loading tool is arranged on the ground rail and is used for mounting a main speed reducer stay bar joint and applying load to the main speed reducer stay bar joint; wherein the main reducer stay bar joint is arranged on the middle machine body;
the anti-torsion loading tool is arranged on the machine body butt joint tool and the main speed reducer mounting loading tool and is used for applying load to the main speed reducer anti-torsion joint; wherein the main deceleration anti-torsion connector is arranged on the middle machine body.
Preferably, the method further comprises:
the ground rail is arranged on the ground and is used for fixedly mounting the machine body butt joint fixing tool and the main speed reducer mounting and loading tool.
Preferably, the fuselage butt joint fixing tool comprises:
a bearing wall assembly;
the machine body butt joint angle material assembly is connected with the middle machine body;
the adapter plate assembly is arranged on the surface of the bearing wall assembly and is connected with the machine body butt joint angle material assembly.
Preferably, the fuselage butt angle assembly comprises:
a plurality of angle bars arranged on the frame beam of the middle machine body; the angle material is L-shaped, one side of the angle material is connected with the frame beam through rivets, and the other side of the angle material is connected with the adapter plate assembly through bolts.
Preferably, the main reducer mounting and loading tool comprises:
the suspension fixing frame assembly is used for supporting and fixing the main reducer stay bar mounting platform assembly;
the main speed reducer stay bar mounting platform assembly is arranged on the suspension fixing frame assembly and is connected with a main speed reducer stay bar joint;
and the stay bar loading actuator assembly is arranged on the main speed reducer stay bar joint and applies load to the main speed reducer stay bar joint.
Preferably, the suspension fixing frame assembly includes: the upright post is fixedly arranged on the ground rail, and the cross beam is arranged on the upright post.
Preferably, the strut loading actuator assembly includes an actuator mounted at a predetermined angle to the final drive strut mounting platform assembly.
Preferably, the anti-torsion loading tool comprises:
the anti-torsion joint loading assembly is connected with the anti-torsion joint of the main speed reducer;
the loading connecting rod assembly is used for connecting the anti-torsion joint loading assembly and the loading actuator assembly;
and the loading actuator assembly is used for applying load to the anti-torsion joint of the main speed reducer.
The beneficial technical effects of the invention are as follows:
the invention can simulate the real constraint mode of the butt joint frames at the two ends of the middle machine body approximately equivalently, can apply the load of the main reducer stay bar and the load of the anti-torsion joint to the upper platform of the middle machine body at the same time, and can truly check the static strength and the fatigue strength of the upper platform of the middle machine body and the supporting frame beams thereof.
Drawings
FIG. 1 is a front view of the overall installation form provided by an embodiment of the present invention;
FIG. 2 is a top view of the overall installation form provided by an embodiment of the present invention;
FIG. 3 is a general diagram of a tool for fixing a docking machine body according to an embodiment of the present invention;
FIG. 4 is a general diagram of another tool for fixing a docking machine body according to an embodiment of the present invention;
FIG. 5 is a general diagram of a main reducer mounting and loading tool provided by an embodiment of the invention;
FIG. 6 is an overall diagram of an anti-torsion loading tool provided by an embodiment of the invention;
wherein: 1-fuselage butt joint fixed tooling, 1 a-fuselage butt joint angle material assembly, 1 b-adapter plate assembly, 1 c-bearing wall assembly, 2-main reducer installation loading tooling, 2 a-suspension fixed frame assembly, 2 b-main reducer supporting rod installation platform assembly, 2 c-supporting rod loading actuator assembly, 3-torsion-proof loading tooling, 3 a-torsion-proof joint loading assembly, 3 b-loading connecting rod assembly and 3 c-loading actuator assembly.
Detailed Description
The invention adopts special tools to restrain the front frame and the rear frame of the middle machine body and simulate the lift force suspension mode of the rotor system through the frame, adopts special loading tools to apply load to all main reducer joints and anti-torsion joints at the same time, and simulates the actual loading of an upper platform structure. The invention can be used for static force and fatigue test of the upper platform of the helicopter body.
Referring to fig. 1-6, the technical scheme of the present invention is as follows: a helicopter body upper platform test device mainly comprises a helicopter body butt joint fixing tool, a main speed reducer mounting and loading tool and an anti-torsion loading tool, wherein the number of the helicopter body butt joint fixing tools is 2, and the helicopter body butt joint fixing tools can be the same or different according to actual structures.
In this application embodiment, fuselage butt joint fixed frock includes: the machine body butt joint angle material assembly, the adapter plate assembly and the bearing wall assembly. The machine body butt joint angle material is used for connecting a machine body frame beam and an adapter plate assembly, consists of a plurality of angle materials distributed on a middle machine body butt joint frame, is connected to a main bearing frame beam of the machine body, does not cause adverse effect on the bearing force of the original machine body structure, is distributed symmetrically, and cannot generate unbalanced load so as not to cause unexpected damage to the structure; the adapter plate assembly is used for connecting the machine body butt joint angle material and the bearing wall, the distribution of the adapter plate assembly corresponds to the machine body butt joint angle material, the adapter plate assembly can be segmented or integrated, the problems that the rigidity of the bearing wall is overlarge to affect the real loading of a butt joint frame, and strengthening measures such as heat treatment cannot be carried out due to the large size of the bearing wall can be solved, and the installation, the positioning and the replacement of damaged parts are convenient; the bearing wall component is a middle machine body fixing and bearing clamp, the required strength and rigidity are enough, the installation and the fixation are convenient, and the transition plate and the angle adjusting device can be added according to the actual condition of the structure so as to adapt to the requirements of different butt joint angles.
In this application embodiment, final drive installation loading frock includes: and the suspension fixing frame assembly, the main reducer stay bar mounting platform assembly and the stay bar loading actuator assembly. The suspension fixing frame assembly consists of 4 upright posts, 2 cross beams, a plurality of reinforcing channel steel and fixing bolts, and is used for bearing the dead weight of the middle fuselage and the load of a main reducer stay bar, the 2 cross beams are required to have enough strength and rigidity, and the lower surfaces of the cross beams are horizontal so that the upper platform of the middle fuselage is in a horizontal state; the main speed reducer stay bar mounting platform assembly consists of a mounting plate, a main speed reducer stay bar fixing joint and a fastening bolt, and is used for mounting the main speed reducer stay bar joint and connecting with the suspension fixing frame; the supporting rod loading actuator assembly is a special loading actuator, and consists of a loading executing mechanism, a load sensor and a loading connector, and can be additionally provided with a displacement sensor for displacement control or monitoring of loading stroke.
In this application embodiment, anti-torsion loading frock includes: the anti-torsion joint loading assembly, the loading connecting rod assembly and the loading actuator assembly. In order to ensure accurate application of load under the condition of large deformation of the upper platform of the anti-torsion joint, error influence caused by deformation is reduced by prolonging the distance between a load loading point and an actuator fixing point, and all loads are designed to be tensile loads so as to avoid instability caused by compression loading. The anti-torsion joint loading assembly consists of a side loading joint, a course loading device and a tightening nut and is used for applying symmetrical side loads and course loads of the two anti-torsion joints; the loading connecting rod assembly consists of a loading joint and an extension rod, and the connecting part is hinged and used for releasing additional moment generated by component force when the upper platform is deformed; the loading actuator assembly consists of a loading executing mechanism, a loading connecting rod, an actuator fixing device and a load sensor, and can also be additionally provided with a displacement sensor for controlling displacement or monitoring loading stroke.
The key point of the invention is as follows:
the main speed reducer of the main body butt joint fixing assembly is mainly composed of a loading tool 2 and an anti-torsion loading tool 3, wherein the number of the main body butt joint fixing tools is 2, and the main body butt joint fixing tools can be the same or different according to actual structures.
Wherein, fuselage butt joint fixed frock 1 includes: fuselage butt joint angle material subassembly 1a, keysets subassembly 1b, bearing wall subassembly 1c. The machine body butt joint angle material 1a is used for connecting a machine body frame beam and the adapter plate assembly 1b and consists of a plurality of angle materials distributed on a middle machine body butt joint frame, the structure and rigidity of the machine body butt joint angle material assembly 1a can be adjusted according to the actual loading condition of the frame beam, the butt joint angle materials are uniformly distributed on a main bearing frame beam of the machine body, and the bearing force of the original machine body structure is not influenced, so that unbalanced load is not generated to avoid unexpected damage to the structure; the adapter plate assembly 1b is used for connecting the machine body butt joint angle material assembly 1a and the bearing wall assembly 1c, the distribution of the adapter plate assembly corresponds to the machine body butt joint angle material assembly 1a, the adapter plate assembly can be segmented or integrated, the strength and the rigidity of the adapter plate assembly are matched with the actual constraint rigidity of the machine body butt joint frame, the problems that the actual load of the butt joint frame is affected by overlarge rigidity of the bearing wall and strengthening measures such as heat treatment cannot be carried out due to large size of the bearing wall can be solved, and the fixing holes of the connecting bolts can be designed into waist-shaped holes along the lateral direction or the vertical direction so as to meet the degree of freedom release requirements in different directions, and the adapter plate assembly is convenient to install, position and replace damaged parts; the bearing wall component 1c is a middle machine body fixing and bearing clamp, has enough required strength and rigidity, is convenient to install and fix, and can be added with a transition plate and an angle adjusting device according to the actual condition of the structure so as to meet the requirements of different butt joint angles.
Wherein, main reducer installs loading frock 2 includes: a suspension fixed frame assembly 2a, a final drive strut mounting platform assembly 2b, and a strut loading actuator assembly 2c. The suspension fixing frame component 2a consists of 4 upright posts, 2 cross beams, a plurality of reinforcing channel steel and fixing bolts, and is used for bearing the dead weight of the middle fuselage and the supporting rod load of the main reducer, the 2 cross beams are required to have enough strength and rigidity, and the lower surfaces of the cross beams are horizontal so that the upper platform of the middle fuselage is in a horizontal state; the main speed reducer stay bar mounting platform assembly 2b is used for mounting a main speed reducer stay bar joint and is connected with the suspension fixing frame assembly 2a, and the position of the main speed reducer stay bar mounting platform assembly is required to meet the requirement of a loading angle of a main speed reducer stay bar; the supporting rod loading actuator component 2c is a special loading actuator, a displacement sensor can be additionally arranged for displacement control or monitoring of loading stroke, a joint bearing is additionally arranged at the fixed end of the supporting rod loading actuator component to prevent additional bending moment generated during deformation, and the maximum stroke is not more than the maximum deformation of a platform on the middle machine body, so that the limiting protection can be carried out through the displacement sensor.
In the embodiment of the application, the strut loading actuator assembly 2c should be mounted on the final drive strut mounting platform assembly 2b at a predetermined angle; the preset angle may be a true installation angle of the final drive stay.
Wherein, anti-torsion loading frock 3 includes: an anti-twist joint loading assembly 3a, a loading linkage assembly 3b, and a loading actuator assembly 3c. In order to ensure accurate application of load under the condition of large deformation of the upper platform of the anti-torsion joint, error influence caused by deformation is reduced by prolonging the distance between a load loading point and an actuator fixing point, and all loads are designed to be tensile loads so as to avoid instability caused by compression loading. The anti-twist joint loading assembly 3a is used for applying symmetrical side loads and heading loads of two anti-twist joints; the loading connecting rod assembly 3b consists of a loading joint and an extension rod, and the connecting part is hinged and is used for releasing additional moment generated by component force when the upper platform is deformed; the loading actuator assembly 3c may be provided with a displacement sensor for displacement control or monitoring of the loading stroke, and the fixed end thereof is provided with a knuckle bearing for preventing additional bending moment generated during deformation.
The invention can simulate the real constraint mode of the butt joint frames at the two ends of the middle machine body approximately equivalently, can apply the load of the main reducer stay bar and the load of the anti-torsion joint to the upper platform of the middle machine body at the same time, and can truly check the static strength and the fatigue strength of the upper platform of the middle machine body and the supporting frame beams thereof.
In the embodiment of the application, the application provides a helicopter fuselage upper platform test device, by fuselage butt joint fixed frock 1, main reducer installation loading frock 2, prevent torsion loading frock 3 constitute, wherein fuselage butt joint fixed frock has 2, can be the same or different according to actual structure.
The installation steps of the upper platform test device of the middle machine body are as follows: firstly, installing a main mounting loading tool 2, and enabling the lower surface of a cross beam to be basically horizontal by adjusting a suspension fixing frame assembly 2 a; secondly, mounting the middle body test piece on the suspension fixing frame assembly 2a, wherein the stroke of the stay bar loading actuator assembly 2c is adjusted during mounting so as to keep the middle body test piece horizontal, and the stroke of the stay bar loading actuator assembly 2c is in a middle position; then, the machine body butt joint fixing tool 1 is in butt joint with two ends of the middle machine body test piece, the machine body butt joint angle material assembly 1a and the adapter plate assembly 1b are tightly attached, if a gap exists locally, gaskets can be added, all butt joint bolts apply tightening torque according to requirements to ensure uniform stress, and if a waist-shaped groove with release freedom degree exists, the butt joint bolts are positioned in the middle position of the waist-shaped groove; finally, the anti-torsion loading tool 3 is installed, and the connecting line of the loading point and the actuator installation fixed point is kept horizontal when the anti-torsion loading tool is installed, and the loading point is parallel to the course central axis of the fuselage test piece (course load) or vertical to the course central axis of the fuselage test piece (side load).
Claims (5)
1. An on-board helicopter body test apparatus, comprising:
the machine body butt joint fixing tool is arranged on the ground rail and is used for fixing the middle machine body of the helicopter;
the main speed reducer mounting and loading tool is arranged on the ground rail and is used for mounting a main speed reducer stay bar joint and applying load to the main speed reducer stay bar joint; wherein the main reducer stay bar joint is arranged on the middle machine body;
the anti-torsion loading tool is arranged on the machine body butt joint tool and the main speed reducer mounting loading tool and is used for applying load to the main speed reducer anti-torsion joint; wherein the main reducer anti-torsion connector is arranged on the middle machine body;
wherein, fuselage butt joint is fixed frock includes:
a bearing wall assembly;
the machine body butt joint angle material assembly is connected with the middle machine body;
the adapter plate assembly is arranged on the surface of the bearing wall assembly and is connected with the machine body butt joint angle material assembly;
main reducer installation loading frock includes:
the suspension fixing frame assembly is used for supporting and fixing the main stay bar mounting platform assembly;
the main speed reducer stay bar mounting platform assembly is arranged on the suspension fixing frame assembly and is connected with a main speed reducer stay bar joint;
the stay bar loading actuator assembly is arranged on the main speed reducer stay bar joint and is used for applying load to the main speed reducer stay bar joint;
the anti-torsion loading tool comprises:
the anti-torsion joint loading assembly is connected with the anti-torsion joint of the main speed reducer;
the loading connecting rod assembly is used for connecting the anti-torsion joint loading assembly and the loading actuator assembly;
and the loading actuator assembly is used for applying load to the anti-torsion joint of the main speed reducer.
2. The on-board helicopter fuselage platform test apparatus of claim 1, further comprising:
the ground rail is arranged on the ground and is used for fixedly mounting the machine body butt joint fixing tool and the main speed reducer mounting and loading tool.
3. The on-board helicopter fuselage airframe testing device of claim 1, wherein said fuselage butt angle assembly comprises:
a plurality of angle bars arranged on the frame beam of the middle machine body; the angle material is L-shaped, one side of the angle material is connected with the frame beam through rivets, and the other side of the angle material is connected with the adapter plate assembly through bolts.
4. The on-board helicopter fuselage platform test apparatus of claim 1, wherein the suspension mounting frame assembly comprises: the upright post is fixedly arranged on the ground rail, and the cross beam is arranged on the upright post.
5. The on-fuselage platform test device of claim 1, wherein the strut loading actuator assembly comprises an actuator mounted on the final drive strut mounting platform assembly at a predetermined angle.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111381910.5A CN114056598B (en) | 2021-11-19 | 2021-11-19 | Helicopter fuselage upper platform test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381910.5A CN114056598B (en) | 2021-11-19 | 2021-11-19 | Helicopter fuselage upper platform test device |
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| CN114056598A CN114056598A (en) | 2022-02-18 |
| CN114056598B true CN114056598B (en) | 2023-04-28 |
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| CN113109170A (en) * | 2021-04-20 | 2021-07-13 | 中国直升机设计研究所 | Composite material long beam strength test device |
| CN113335560A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Complicated load box section or barrel section testing device and method |
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| DE102008020125B3 (en) * | 2008-04-21 | 2009-10-08 | Airbus Deutschland Gmbh | Device for testing load of fuselage barrel in air travel and space travel, comprises two pressure bulkheads for pressure tight locking of fuselage barrel at their front sides |
| CN104807694A (en) * | 2015-05-04 | 2015-07-29 | 中国飞机强度研究所 | Fuselage panel combined load test device |
| CN108238282A (en) * | 2017-12-04 | 2018-07-03 | 中国飞机强度研究所 | A kind of center wing box test method |
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| CN113335560A (en) * | 2021-06-04 | 2021-09-03 | 中国飞机强度研究所 | Complicated load box section or barrel section testing device and method |
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| CN114056598A (en) | 2022-02-18 |
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