CN114056598A - Upper platform test device for helicopter body - Google Patents
Upper platform test device for helicopter body Download PDFInfo
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- CN114056598A CN114056598A CN202111381910.5A CN202111381910A CN114056598A CN 114056598 A CN114056598 A CN 114056598A CN 202111381910 A CN202111381910 A CN 202111381910A CN 114056598 A CN114056598 A CN 114056598A
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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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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a test device for an upper platform of a middle body of a helicopter, which comprises a body butt joint fixing tool, a middle body butt joint fixing tool, a positioning tool and a positioning tool, wherein the body butt joint fixing tool is arranged on a ground rail and is used for fixing the middle body of the helicopter; the main speed reducer mounting and loading tool is arranged on a ground rail and used for mounting a main speed reducer strut joint and applying load to the main speed reducer strut joint; the main speed reducer strut 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 reducer installation loading tool and is used for applying load to an anti-torsion joint of the main reducer; the main speed reducing anti-twisting joint is arranged on the middle machine body; the method can simulate the real constraint mode of the butt frames at the two ends of the middle machine body, simultaneously apply the main support reducing rod load and the anti-torsion joint load to the platform on the middle machine body, and truly check the static strength and the fatigue strength of the platform on the middle machine body and the support frame beams thereof.
Description
Technical Field
The invention belongs to the technical field of helicopter structural strength tests, and particularly relates to a helicopter upper platform test device.
Background
The upper platform of the middle body of the helicopter is used as a mounting platform of a main speed reducer and an engine of a rotor system, not only is the lift force of the rotor under different flight working conditions transmitted, but also the reaction torque (single rotor with tail rotor configuration) generated by the rotation of a rotor shaft is transmitted, and meanwhile, the aerodynamic load and the inertial load generated by the self weight and the load of the body in the flight and maneuvering processes are born, and the stress form is very complex.
In the relative technology, the loads of all parts are usually split, and the tests are respectively carried out through single parts such as a main reducing support rod, a main reducing joint, an anti-twisting joint and the like or local frame beams, so that the strength and the performance of the mounting platform can not be completely tested, and the complex stress conditions such as load coupling and the like caused by the periodic deformation of the mounting platform can not be truly simulated.
Disclosure of Invention
In view of the above technical problems, the present invention provides a device for testing an upper platform of a helicopter body, comprising:
the machine body butt joint fixing tool is arranged on the ground rail and used for fixing a middle machine body of the helicopter;
the main speed reducer mounting and loading tool is arranged on a ground rail and used for mounting a main speed reducer strut joint and applying load to the main speed reducer strut joint; the main speed reducer strut 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 reducer installation loading tool and is used for applying load to an anti-torsion joint of the main reducer; wherein, the main speed reduction anti-twist joint is arranged on the middle machine body.
Preferably, the method further comprises the following steps:
and the ground rail is arranged on the ground and used for fixedly mounting the machine body butt joint fixing tool and the main speed reducer mounting and loading tool.
Preferably, the fixed frock of fuselage butt joint includes:
a load-bearing wall assembly;
the machine body butt joint angle bar assembly is connected with the middle machine body;
and the adapter plate assembly is arranged on the surface of the bearing wall assembly and is connected with the machine body butt joint angle bar assembly.
Preferably, the fuselage butt-joint angle bar assembly comprises:
the plurality of angle bars are 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 a rivet, and the other side of the angle material is connected with the adapter plate component through a bolt.
Preferably, the main reducer installation loading tool includes:
the suspension fixing frame assembly is used for supporting and fixing the main speed reducer strut mounting platform assembly;
the main speed reducer strut mounting platform assembly is arranged on the suspension fixing frame assembly and is connected with a main speed reducer strut joint;
and the strut loading actuator assembly is arranged on the main speed reducer strut joint and applies load to the main speed reducer strut joint.
Preferably, the suspended fixed frame assembly comprises: the device comprises a stand column fixedly arranged on the ground rail and a cross beam arranged on the stand column.
Preferably, the strut loading actuator assembly includes an actuator mounted on the final drive strut mounting platform assembly at a preset angle.
Preferably, the torsion-proof loading tool comprises:
the anti-twist joint loading assembly is connected with the anti-twist joint of the main speed reducer;
a loading linkage assembly for connecting the anti-twist joint loading assembly and the loading actuator assembly;
and the loading actuator assembly is used for applying load to the main speed reducer anti-torsion joint.
The invention has the beneficial technical effects that:
the invention can simulate the real constraint mode of the butt frames at two ends of the middle machine body approximately and equivalently, can simultaneously apply the main reducer strut load and the anti-torsion joint load to the upper platform of the middle machine body, and truly examines the static strength and the fatigue strength of the upper platform of the middle machine body and the support frame beams thereof.
Drawings
FIG. 1 is a front view of an overall installation form provided by an embodiment of the present invention;
FIG. 2 is a top view of an overall installation form provided by an embodiment of the present invention;
fig. 3 is a general view of a body docking fixture according to an embodiment of the present invention;
fig. 4 is a general view of another fuselage docking fixture provided in an embodiment of the present invention;
FIG. 5 is a general view of a final drive mounting and loading fixture provided in an embodiment of the present invention;
FIG. 6 is a general view of an anti-twist loading fixture provided in an embodiment of the present invention;
wherein: the device comprises a 1-fuselage butt joint fixing tool, a 1 a-fuselage butt joint angle component, a 1 b-adapter plate component, a 1 c-bearing wall component, a 2-main reducer installation loading tool, a 2 a-suspension fixing frame component, a 2 b-main reducer strut installation platform component, a 2 c-strut loading actuator component, a 3-anti-torsion loading tool, a 3 a-anti-torsion connector loading component, a 3 b-loading connecting rod component and a 3 c-loading actuator component.
Detailed Description
The invention adopts a special tool to restrain the front frame and the rear frame of the middle fuselage, simulates the lift suspension mode of a rotor system through a frame, simultaneously applies loads to all main speed reducer joints and anti-torsion joints by adopting a special loading tool, and simulates the real loading of the 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 solution of the present invention: the utility model provides a fuselage upper mounting plate test device in helicopter, mainly by fuselage butt joint fixing frock, main reducer installation loading frock, prevent turning round loading frock and constitute, wherein the fuselage butt joint fixing frock is equipped with 2, can be the same or different according to actual structure.
In this application embodiment, the fixed frock of fuselage butt joint includes: the fuselage butt joint angle section subassembly, adapter plate subassembly, bearing wall subassembly. The butt joint angle bar of the machine body is used for connecting a frame beam of the machine body and the adapter plate assembly and consists of a plurality of angle bars distributed on a butt joint frame of the middle machine body, the butt joint angle bar 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 evenly and cannot generate unbalanced load so as to avoid causing unexpected damage of the structure; the adapter plate assembly is used for connecting a butt joint angle material of the machine body and a bearing wall, the distribution of the adapter plate assembly corresponds to the butt joint angle material of the machine body, and the adapter plate assembly can be segmented or integrated, so that the problems that the rigidity of the bearing wall is overlarge to influence the real loading of a butt joint frame, and the bearing wall has large size and cannot be subjected to strengthening measures such as heat treatment and the like are solved, and the adapter plate assembly is convenient to install, position and replace damaged parts; the bearing wall component is a middle machine body fixing and bearing clamp, the strength and rigidity are required to be sufficient, the installation and the fixation are convenient, and a transition plate and an angle adjusting device can be added according to the actual condition of the structure to adapt to different butt joint angle requirements.
In this application embodiment, final drive installation loading frock includes: the suspension fixing frame assembly, the main speed reducer strut mounting platform assembly and the strut loading actuator assembly. The suspension fixing frame component consists of 4 upright posts, 2 cross beams, a plurality of reinforcing channel steel and fixing bolts, is used for bearing the dead weight of the middle machine body and the load of a main reducer strut, and requires that the 2 cross beams have enough strength and rigidity, and the lower surfaces of the cross beams are horizontal so that the platform on the middle machine body is in a horizontal state; the main speed reducer strut mounting platform assembly consists of a mounting plate, a main speed reducer strut fixing joint and a fastening bolt, and is used for mounting the main speed reducer strut joint and connecting with the suspension fixing frame; the strut loading actuator assembly is a special loading actuator, consists of a loading executing mechanism, a load sensor and a loading joint, and can be additionally provided with a displacement sensor for displacement control or monitoring of a loading stroke.
In this application embodiment, prevent turning round loading frock includes: the anti-twist connector comprises an anti-twist connector loading assembly, a loading connecting rod assembly and a loading actuator assembly. In order to ensure the accurate application of the load under the condition of large deformation of the upper platform, the distance between a load application point and an actuator fixing point is prolonged to reduce the error influence caused by deformation, and all the loads are designed into tensile loads to avoid instability caused by compression loading. The anti-twist joint loading assembly consists of a lateral loading joint, a course loading device and a fastening nut and is used for applying symmetrical lateral loads and course loads of the two anti-twist 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 deforms; the loading actuator assembly consists of a loading executing mechanism, a loading connecting rod, an actuator fixing device and a load sensor, and a displacement sensor can be additionally arranged for displacement control or monitoring of a loading stroke.
The key points of the invention are as follows:
the main speed reducer installation loading tool 2 and the anti-torsion loading tool 3 mainly comprise a machine body butt joint fixing assembly, wherein the machine body butt joint fixing tools are 2, and the machine body butt joint fixing tools can be the same or different according to actual structures.
Wherein, the fixed frock 1 of fuselage butt joint includes: the device comprises a machine body butt joint angle bar component 1a, an adapter plate component 1b and a bearing wall component 1 c. The butt joint angle bar 1a of the machine body is used for connecting a frame beam of the machine body and a switching plate assembly 1b and consists of a plurality of angle bars distributed on a middle machine body butt joint frame, the structure and the rigidity of the butt joint angle bar assembly 1a of the machine body can be adjusted according to the actual loading condition of the frame beam, the butt joint angle bars are uniformly distributed on main bearing frame beams of the machine body and do not cause adverse effects on the bearing force of the original machine body structure so as to avoid generating unbalanced load to avoid causing unexpected damage of the structure; the adapter plate component 1b is used for connecting the butt joint angle component 1a of the machine body and the bearing wall component 1c, the distribution of the adapter plate component corresponds to the butt joint angle component 1a of the machine body, the adapter plate component can be segmented or integrated, the strength and the rigidity of the adapter plate component are matched with the actual constraint rigidity of a butt joint frame of the machine body, the problems that the rigidity of the bearing wall is overlarge to influence the real loading of the butt joint frame and the bearing wall has large size and cannot be subjected to strengthening measures such as heat treatment and the like can be solved, and the fixing hole of the connecting bolt can be designed into a waist-shaped hole along the lateral direction or the vertical direction to meet the requirement of freedom release in different directions and be convenient for installing, positioning and replacing damaged parts; the bearing wall component 1c is a middle machine body fixing and bearing clamp, the strength and rigidity are required to be sufficient, the installation and the fixation are convenient, and a transition plate and an angle adjusting device can be added according to the actual condition of the structure to meet the requirements of different butt joint angles.
Wherein, final drive installation loading frock 2 includes: a suspended fixed frame assembly 2a, a main reducer strut mounting platform assembly 2b, and a strut loading actuator assembly 2 c. The suspension fixing frame assembly 2a consists of 4 upright posts, 2 cross beams, a plurality of reinforcing channel steel and fixing bolts, is used for bearing the dead weight of the middle machine body and the load of a main reducer strut, and requires that the 2 cross beams have enough strength and rigidity, and the lower surfaces of the cross beams are horizontal so that the platform on the middle machine body is in a horizontal state; the main reducer strut mounting platform assembly 2b is used for mounting a main reducer strut joint and is connected with the suspended fixed frame assembly 2a, and the position of the main reducer strut mounting platform assembly meets the requirement of a main reducer strut loading angle; the strut loading actuator component 2c is a special loading actuator, a displacement sensor can be additionally arranged for displacement control or monitoring of a loading stroke, a joint bearing is additionally arranged at the fixed end of the strut loading actuator component to prevent additional bending moment generated during deformation, the maximum stroke does not exceed the maximum deformation of an upper platform of the middle machine body, and the strut loading actuator component can be limited and protected through the displacement sensor.
In the present embodiment, the strut loading actuator assembly 2c should be mounted on the main retarder strut mounting platform assembly 2b at a predetermined angle; wherein the preset angle may be a real installation angle of the strut of the main reducer.
Wherein, prevent turning round loading frock 3 includes: an anti-twist joint loading assembly 3a, a loading linkage assembly 3b, and a loading actuator assembly 3 c. In order to ensure the accurate application of the load under the condition of large deformation of the upper platform, the distance between a load application point and an actuator fixing point is prolonged to reduce the error influence caused by deformation, and all the loads are designed into tensile loads to avoid instability caused by compression loading. The anti-twist joint loading assembly 3a is used for applying symmetrical lateral loads and heading loads of the two anti-twist joints; the loading connecting rod component 3b 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 deforms; the loading actuator assembly 3c may be additionally provided with a displacement sensor for displacement control or monitoring of the loading stroke, and the fixed end thereof must be additionally provided with a joint bearing to prevent additional bending moment generated during deformation.
The invention can simulate the real constraint mode of the butt frames at two ends of the middle machine body approximately and equivalently, can simultaneously apply the main reducer strut load and the anti-torsion joint load to the upper platform of the middle machine body, and truly examines the static strength and the fatigue strength of the upper platform of the middle machine body and the support frame beams thereof.
In the embodiment of the application, the application provides a test device for an upper platform of a helicopter body, which consists of a fixed tool 1 for butt joint of the helicopter body, a main speed reducer installation loading tool 2 and an anti-torsion loading tool 3, wherein the number of the fixed tool 2 for butt joint of the helicopter body can be the same or different according to actual structures.
This platform test device on fuselage's installation step does: firstly, a main reducer mounting and loading tool 2 is mounted, and the lower surface of the cross beam is basically horizontal by adjusting a suspension fixing frame component 2 a; secondly, mounting the middle fuselage test piece on the suspended fixed frame component 2a, wherein the stroke of the strut loading actuator component 2c is adjusted during mounting so as to keep the middle fuselage test piece horizontal and keep the stroke of the strut loading actuator component 2c at the middle position; then, the machine body butt joint fixing tool 1 is in butt joint with two ends of a middle machine body test piece, a machine body butt joint angle section component 1a and an adapter plate component 1b are tightly attached, if a gap exists locally, a gasket can be added, all butt joint bolts apply tightening torque according to requirements to ensure uniform stress, and if a waist-shaped groove with a release freedom degree exists, the butt joint bolts are located in the middle of the waist-shaped groove; and finally, installing the anti-torsion loading tool 3, wherein a connecting line of a loading point and an installation fixing point of the actuator is kept horizontal during installation, and is parallel to a course central axis of the test piece of the machine body (course load) or vertical to the course central axis of the test piece of the machine body (side load).
Claims (8)
1. The utility model provides a fuselage upper mounting plate test device in helicopter which characterized in that includes:
the machine body butt joint fixing tool is arranged on the ground rail and used for fixing a middle machine body of the helicopter;
the main speed reducer mounting and loading tool is arranged on a ground rail and used for mounting a main speed reducer strut joint and applying load to the main speed reducer strut joint; the main speed reducer strut 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 reducer installation loading tool and is used for applying load to an anti-torsion joint of the main reducer; wherein, the main speed reduction anti-twist joint is arranged on the middle machine body.
2. The upper fuselage platform test rig in a helicopter of claim 1 further comprising:
and the ground rail is arranged on the ground and used for fixedly mounting the machine body butt joint fixing tool and the main speed reducer mounting and loading tool.
3. The upper platform test device of a helicopter body in claim 1, wherein the fixed tooling of fuselage butt joint comprises:
a load-bearing wall assembly;
the machine body butt joint angle bar assembly is connected with the middle machine body;
and the adapter plate assembly is arranged on the surface of the bearing wall assembly and is connected with the machine body butt joint angle bar assembly.
4. A test rig for a helicopter hull top hat as claimed in claim 3, wherein said hull docking angle bar assembly comprises:
the plurality of angle bars are 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 a rivet, and the other side of the angle material is connected with the adapter plate component through a bolt.
5. The upper platform test device of a helicopter body in claim 1, wherein the main reducer mounting and loading tool comprises:
the suspension fixing frame assembly is used for supporting and fixing the main support reducing rod mounting platform assembly;
the main speed reducer strut mounting platform assembly is arranged on the suspension fixing frame assembly and is connected with a main speed reducer strut joint;
and the strut loading actuator assembly is arranged on the main speed reducer strut joint and applies load to the main speed reducer strut joint.
6. A fuselage upper deck test rig in a helicopter as claimed in claim 5, wherein the suspended fixed frame assembly comprises: the device comprises a stand column fixedly arranged on the ground rail and a cross beam arranged on the stand column.
7. A fuselage-on-board test rig in a helicopter as claimed in claim 5 wherein said strut loading actuator assembly includes an actuator mounted on said final drive strut mounting platform assembly at a predetermined angle.
8. The upper platform test device of a helicopter body in claim 1, wherein the torsion-proof loading tool comprises:
the anti-twist joint loading assembly is connected with the anti-twist joint of the main speed reducer;
a loading linkage assembly for connecting the anti-twist joint loading assembly and the loading actuator assembly;
and the loading actuator assembly is used for applying load to the main speed reducer anti-torsion joint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111381910.5A CN114056598B (en) | 2021-11-19 | 2021-11-19 | Helicopter fuselage upper platform test device |
Applications Claiming Priority (1)
| 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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| Publication Number | Publication Date |
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| CN114056598A true CN114056598A (en) | 2022-02-18 |
| CN114056598B CN114056598B (en) | 2023-04-28 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111381910.5A Active CN114056598B (en) | 2021-11-19 | 2021-11-19 | Helicopter fuselage upper platform test device |
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| CN112478192A (en) * | 2020-10-30 | 2021-03-12 | 中国直升机设计研究所 | Full-mechanical static test loading rack of small-load helicopter |
| 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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2021
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| Publication number | Priority date | Publication date | Assignee | Title |
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| US20060101921A1 (en) * | 2004-11-12 | 2006-05-18 | The Boeing Company | E-fixture |
| 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 |
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Also Published As
| Publication number | Publication date |
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| CN114056598B (en) | 2023-04-28 |
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