CN106742052B - A kind of helicopter body slow test suspension - Google Patents
A kind of helicopter body slow test suspension Download PDFInfo
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- CN106742052B CN106742052B CN201611068485.3A CN201611068485A CN106742052B CN 106742052 B CN106742052 B CN 106742052B CN 201611068485 A CN201611068485 A CN 201611068485A CN 106742052 B CN106742052 B CN 106742052B
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- 239000000725 suspension Substances 0.000 title claims abstract description 32
- 230000003068 static effect Effects 0.000 claims description 36
- 238000001514 detection method Methods 0.000 claims description 17
- 238000010521 absorption reaction Methods 0.000 claims description 10
- 230000007246 mechanism Effects 0.000 claims description 6
- 230000008859 change Effects 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 2
- 230000000149 penetrating effect Effects 0.000 claims description 2
- 230000035939 shock Effects 0.000 claims 3
- 230000003247 decreasing effect Effects 0.000 claims 2
- 238000009966 trimming Methods 0.000 claims 1
- 230000008901 benefit Effects 0.000 abstract description 4
- 230000000694 effects Effects 0.000 abstract description 3
- 230000007423 decrease Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 208000012260 Accidental injury Diseases 0.000 description 1
- 230000006978 adaptation Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 239000003638 chemical reducing agent Substances 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 208000014674 injury Diseases 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Abstract
The invention discloses a kind of helicopter body slow test suspensions.The helicopter body slow test suspension includes: test-bed, and the test-bed includes crossbeam, is provided with mounting groove on the crossbeam；Fine position component, the fine position component is arranged on the mounting groove of the crossbeam and the fine position component is provided with diameter bore；Carrier bar, the carrier bar pass through the diameter bore of the fine position component and connect with the fine position component, and one end across the fine position component of the carrier bar with helicopter body to be measured for removably connecting.The helicopter body slow test suspension of the application is provided with fine position component, carrier bar can move in the activity space, when carrying out helicopter body slow test, it is capable of the actual loading situation of helicopter simulating body, has the advantages that test is more accurate compared with the existing technology.
Description
Technical Field
The invention relates to the technical field of static test of a helicopter body, in particular to a suspension assembly for the static test of the helicopter body.
Background
The helicopter body structure is a mounting platform for engine, main speed reducer, rotor system and other helicopter components, and mainly bears the pneumatic external load, inertial load and aerodynamic moment from all the components. In order to determine the strength, rigidity and stability of the helicopter body structure and the failure mode and dangerous parts of the helicopter body structure, a full-scale static test needs to be performed on the helicopter body structure.
When the prior art is used for hoisting in a full-size static test, a helicopter body is usually fixed, particularly, the helicopter body is prevented from moving, and the actual stress condition of the helicopter body cannot be completely simulated.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present invention to provide a helicopter body static test suspension assembly that overcomes or at least mitigates at least one of the above-mentioned disadvantages of the prior art.
In order to achieve the above object, the present invention provides a helicopter body static test suspension assembly, comprising: the test bed comprises a cross beam, wherein the cross beam is provided with a mounting groove; the position fine adjustment component is arranged on the mounting groove of the beam and is provided with a reducing through hole; the bearing rod penetrates through the diameter-variable through hole of the position fine-tuning assembly and is connected with the position fine-tuning assembly, and one end of the bearing rod, which penetrates through the position fine-tuning assembly, is used for being detachably connected with a helicopter body to be tested; the bearing rod is arranged between the part of the reducing through hole and the reducing through hole, a movable space is formed between the part of the reducing through hole and the reducing through hole, and the bearing rod can move in the movable space.
Preferably, the position fine-tuning assembly comprises a concave fixing seat, the concave fixing seat is provided with the reducing through hole, and the reducing through hole comprises a sliding piece adapting part and a movable part; the concave fixed seat is arranged on the cross beam;
the middle part of the convex sliding piece is provided with a sliding piece through hole, and the convex sliding piece is suitable for being placed in the sliding piece adapting part of the reducing through hole and can slide in the sliding piece adapting part; the sliding piece through hole is suitable for the bearing rod to pass through;
and the fixing device is used for connecting the concave fixing seat, the convex sliding piece and the bearing rod.
Preferably, the concave fixing seat is in the axial direction of carrier bar has two terminal surfaces, is called first terminal surface and second terminal surface, the middle part of first terminal surface is sunken to the second terminal surface direction with the mode that the diameter is dwindled gradually and the middle part of second terminal surface is to the first terminal surface direction is sunken with the mode that the diameter is dwindled gradually, thereby both intersect and form reducing through-hole, and the diameter at both intersection positions is minimum, and this position is called the intermediate position, the intermediate position extremely the reducing through-hole part of first terminal surface is slider adaptation portion, the intermediate position extremely the reducing through-hole part of second terminal surface is the movable part.
Preferably, the helicopter body static test suspension assembly further comprises a telescopic adjustment assembly, the telescopic adjustment assembly is arranged between the bearing rod and the helicopter body to be tested, the telescopic adjustment assembly has a locking state and a motion state, and in the motion state, the telescopic adjustment assembly can perform telescopic motion in the axial direction of the bearing rod; in the locking state, the telescopic adjusting assembly is relatively fixed in the axial direction of the bearing rod.
Preferably, the telescopic adjusting assembly comprises a locking mechanism, and a first rod and a second rod which are sleeved with each other, the first rod is provided with an accommodating cavity, and the second rod is arranged in the accommodating cavity and can move telescopically relative to the first rod;
one end of the first rod is detachably connected with the bearing rod, and one end of the second rod is detachably connected with the helicopter body to be tested; the locking mechanism is arranged on the first rod and is provided with a locking position and an opening position, and the telescopic adjusting assembly is in a locking state at the locking position; in the open position, the telescoping adjustment assembly is in motion.
Preferably, the test bench further comprises a first upright and a second upright, one end of the first upright is used for being connected with the base, and the other end of the first upright is used for being connected with one end of the cross beam; one end of the second upright column is used for being connected with the base, and the other end of the second upright column is used for being connected with the other end of the cross beam.
Preferably, the helicopter body static test suspension assembly further comprises a piezoelectric sensor, and the piezoelectric sensor is arranged on the inner wall of the movable part of the reducing through hole.
Preferably, the helicopter body static test suspension assembly further comprises a vibration absorption safety device and a detection device, wherein the detection device is arranged on the bearing rod and is connected with the vibration absorption safety device; the vibration absorption safety device is arranged below the helicopter body to be tested; wherein,
the detection device is used for detecting the force change of the bearing rod and transmitting information to the vibration absorption safety device; the shock-absorbing safety device can operate according to the information transmitted by the detection device, thereby providing a cushioning force for an object falling onto the shock-absorbing safety device.
Preferably, the vibration-absorbing safety device is a safety sponge component, the safety sponge component comprises a safety sponge containing box and a compressed safety sponge arranged in the safety sponge containing box, the safety sponge containing box is provided with an electric control safety sponge box cover, and the electric control safety sponge box cover is connected with the detection device and can be opened or closed according to the information transmitted by the detection device.
Preferably, a gyroscope assembly is arranged in the convex sliding part, and the gyroscope assembly can record the motion track of the convex sliding part.
The application discloses helicopter organism static test suspends subassembly in midair is provided with position fine setting subassembly, and the carrier bar can the activity space internal motion when carrying out helicopter organism static test, can simulate the actual atress condition of helicopter organism, has experimental more accurate advantage for prior art.
Drawings
FIG. 1 is a schematic structural view of a static test suspension assembly of a helicopter body according to an embodiment of the present invention.
FIG. 2 is a schematic structural view of a portion of a position fine adjustment assembly in the static test suspension assembly of the helicopter body shown in FIG. 1.
Reference numerals
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, but do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the scope of the present invention.
FIG. 1 is a schematic structural view of a static test suspension assembly of a helicopter body according to an embodiment of the present invention. FIG. 2 is a schematic structural view of a portion of a position fine adjustment assembly in the static test suspension assembly of the helicopter body shown in FIG. 1.
The helicopter body static test suspension assembly shown in fig. 1 is characterized by comprising a test bench 1, a position fine adjustment assembly 2 and a bearing rod 3, wherein the test bench 1 comprises a cross beam 11, and an installation groove is formed in the cross beam 11; the position fine adjustment component 2 is arranged on the mounting groove of the beam 11, and the position fine adjustment component 2 is provided with a reducing through hole 21; the bearing rod 3 penetrates through the reducing through hole 21 of the position fine adjustment assembly 2 and is connected with the position fine adjustment assembly 2, and one end, penetrating through the position fine adjustment assembly 2, of the bearing rod 3 is detachably connected with the helicopter body 4 to be tested; the bearing rod is arranged between the part of the reducing through hole and the reducing through hole, a movable space is formed, and the bearing rod can move in the movable space.
The application discloses helicopter organism static test suspends subassembly in midair is provided with position fine setting subassembly, and the carrier bar can the activity space internal motion when carrying out helicopter organism static test, can simulate the actual atress condition of helicopter organism, has experimental more accurate advantage for prior art.
Referring to fig. 1, in the present embodiment, the fine position adjustment assembly 2 includes a concave fixing seat 22, a convex sliding member 23 and a fixing device 24, the concave fixing seat 22 is provided with a reducing through hole 21, and the reducing through hole 21 includes a sliding member adapting portion 211 and a movable portion 212; the concave fixed seat 22 is arranged on the cross beam 11; the middle part of the convex sliding piece 23 is provided with a sliding piece through hole, and the convex sliding piece 23 is suitable for being placed in the sliding piece adapting part 211 of the reducing through hole 21 and can slide in the sliding piece adapting part 211; said slider through hole being adapted to pass the carrier bar 3; the fixing device 24 is used for connecting the female fixing seat 22, the male sliding member 23 and the carrying rod 3. With this structure, through the cooperation of the concave fixed seat 22, the convex sliding part 23 and the fixing device 24, the position fine adjustment assembly can move along with the bearing rod when a static test is carried out, so that the real airplane movement condition can be simulated.
Referring to fig. 1, in this embodiment, the concave fixing seat 22 has two end faces in the axial direction of the carrier bar 3, which are called a first end face and a second end face, the middle portion of the first end face is recessed toward the second end face in a manner that the diameter gradually decreases, the middle portion of the second end face is recessed toward the first end face in a manner that the diameter gradually decreases, the two end faces meet to form a reducing through hole, the diameter of the reducing through hole at the meeting position of the two end faces is the smallest, the position is called an intermediate position, the reducing through hole portion from the intermediate position to the first end face is a sliding piece adapting portion, and the reducing through hole portion from the intermediate position to the second end. By adopting the structure, the position with the minimum diameter is directly used as the boundary of the adapting part of the sliding piece and the movable part, thereby preventing the convex sliding piece from entering the movable part in the moving process in the actual use process and also preventing the problem of insufficient strength of the boundary of the movable part and the adapting part of the sliding piece.
Referring to fig. 1, in this embodiment, the helicopter body static test suspension assembly further includes a telescopic adjustment assembly 5, the telescopic adjustment assembly is disposed between the carrier bar and the helicopter body to be tested, and the telescopic adjustment assembly has a locking state and a moving state in which the telescopic adjustment assembly can move telescopically in the axial direction of the carrier bar; in the locking state, the telescopic adjusting component is relatively fixed in the axial direction of the bearing rod. By adopting the structure, a user can adjust the position relation between the bearing rod and the helicopter body to be tested according to actual needs.
In this embodiment, the telescopic adjustment assembly includes a locking mechanism, and a first rod and a second rod sleeved with each other, the first rod has an accommodating cavity, and the second rod is disposed in the accommodating cavity and can move telescopically relative to the first rod; one end of the first rod is detachably connected with the bearing rod, and one end of the second rod is detachably connected with the helicopter body to be tested; the locking mechanism is arranged on the first rod and is provided with a locking position and an opening position, and the telescopic adjusting assembly is in a locking state at the locking position; in the open position, the telescoping adjustment assembly is in motion.
In this embodiment, the test bench further includes a first upright 6 and a second upright 7, one end of the first upright 6 is used for connecting with the base, and the other end of the first upright 6 is used for connecting with one end of the cross beam; one end of the second upright post 7 is used for being connected with the base, and the other end of the second upright post 7 is used for being connected with the other end of the cross beam.
In this embodiment, the helicopter body static test suspension assembly further comprises a piezoelectric sensor (not shown in the figure), and the piezoelectric sensor is arranged on the inner wall of the movable part of the reducing through hole. The piezoelectric sensor is arranged to monitor the movement condition of the helicopter body to be tested in the test in real time through the contact between the bearing rod and the inner wall of the movable part.
In this embodiment, the helicopter body static test suspension assembly further comprises a vibration absorption safety device and a detection device, wherein the detection device is arranged on the bearing rod and is connected with the vibration absorption safety device; the vibration absorption safety device is arranged below the helicopter body to be tested; the detection device is used for detecting the force change of the bearing rod and transmitting information to the vibration absorption safety device; the shock-absorbing safety device can work according to the information transmitted by the detection device, thereby providing a cushioning force for an object falling onto the shock-absorbing safety device. Because the helicopter body that awaits measuring hangs the setting, consequently, in order to prevent that the helicopter body that awaits measuring from falling accidental injury user or damage, set up and inhale the safety device that shakes and be used for buffering the power way that the helicopter body that awaits measuring falls, detect the weight on the carrier bar through detection device and start this safety device that shakes.
In this embodiment, inhale the safety device that shakes and be safe sponge subassembly (not shown in the figure), safe sponge subassembly includes that safe sponge holds the case and sets up the compression safety sponge in safe sponge holds the case, and safe sponge holds the case and has automatically controlled safe sponge case lid, and automatically controlled safe sponge case lid is connected with detection device to can open or close according to the information that detection device transmitted. The safety sponge component is adopted, and due to the characteristics of the safety sponge, the helicopter body to be detected can be prevented from being damaged to the greatest extent.
In this embodiment, a gyroscope assembly (not shown in the drawings) is provided in the male slider, and the gyroscope assembly can record the motion track of the male slider.
Finally, it should be pointed out that: the above examples are only for illustrating the technical solutions of the present invention, and are not limited thereto. Although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A helicopter body static test suspension assembly, characterized by that, helicopter body static test suspension assembly includes:
the test bed (1), the test bed (1) comprises a cross beam (11), and an installation groove is formed in the cross beam (11);
the position fine adjustment component (2), the position fine adjustment component (2) is arranged on the mounting groove of the cross beam (11), and the position fine adjustment component (2) is provided with a reducing through hole (21);
the bearing rod (3) penetrates through the reducing through hole (21) of the position fine adjustment assembly (2) and is connected with the position fine adjustment assembly (2), and one end, penetrating through the position fine adjustment assembly (2), of the bearing rod (3) is detachably connected with the helicopter body (4) to be tested; the bearing rod is arranged between the part of the reducing through hole and the reducing through hole, a movable space is formed between the part of the reducing through hole and the reducing through hole, and the bearing rod can move in the movable space.
2. A helicopter body static test suspension assembly as defined in claim 1 wherein said position trimming assembly (2) comprises:
the concave fixing seat (22), the reducing through hole (21) is arranged on the concave fixing seat (22), and the reducing through hole (21) comprises a sliding piece adapting part (211) and a movable part (212); the concave fixed seat (22) is arranged on the cross beam (11);
the convex sliding piece (23), the middle of the convex sliding piece (23) is provided with a sliding piece through hole, the convex sliding piece (23) is suitable for being placed in the sliding piece adapting part (211) of the reducing through hole (21) and can slide in the sliding piece adapting part (211); the slider through hole is adapted to pass the carrier bar (3);
-fixing means (24), said fixing means (24) being intended to connect said female fixing seat (22), male slider (23) and said carrying bar (3).
3. The helicopter body static test suspension assembly of claim 2, characterized in that the concave fixing seat (22) has two end faces in the axial direction of the carrier bar (3), which are called a first end face and a second end face, the middle of the first end face is recessed toward the second end face in a manner of gradually decreasing the diameter, the middle of the second end face is recessed toward the first end face in a manner of gradually decreasing the diameter, the two end faces meet to form the reducing through hole, the diameter at the meeting position of the two end faces is the smallest, which is called an intermediate position, the reducing through hole part from the intermediate position to the first end face is the sliding part adapting part, and the reducing through hole part from the intermediate position to the second end face is the movable part.
4. A helicopter body static test suspension assembly as defined in claim 3 and further comprising a telescoping adjustment assembly (5) disposed between said carrier bar and said helicopter body under test, said telescoping adjustment assembly having a locked state and a moving state in which said telescoping adjustment assembly is capable of telescoping movement in the axial direction of said carrier bar; in the locking state, the telescopic adjusting assembly is relatively fixed in the axial direction of the bearing rod.
5. A helicopter body static test suspension assembly as defined in claim 4 wherein said telescoping adjustment assembly includes a locking mechanism and first and second telescoping rods, said first rod having a receiving cavity and said second rod being disposed within said receiving cavity and being capable of telescoping movement relative to said first rod;
one end of the first rod is detachably connected with the bearing rod, and one end of the second rod is detachably connected with the helicopter body to be tested; the locking mechanism is arranged on the first rod and is provided with a locking position and an opening position, and the telescopic adjusting assembly is in a locking state at the locking position; in the open position, the telescoping adjustment assembly is in motion.
6. A helicopter body static test suspension assembly as defined in claim 5 wherein said test stand further comprises a first upright (6) and a second upright (7), said first upright (6) having one end for connection to a base and said first upright (6) having another end for connection to one end of said cross member; one end of the second upright post (7) is used for being connected with the base, and the other end of the second upright post (7) is used for being connected with the other end of the cross beam.
7. A helicopter body static test suspension assembly as defined in claim 6 wherein said helicopter body static test suspension assembly further includes a piezoelectric sensor disposed on an inner wall of said movable portion of said reducing through bore.
8. A helicopter body static test suspension assembly as defined in claim 7 wherein said helicopter body static test suspension assembly further includes a shock absorbing safety device and a sensing device, said sensing device being disposed on said load bar and connected to said shock absorbing safety device; the vibration absorption safety device is arranged below the helicopter body to be tested; wherein,
the detection device is used for detecting the force change of the bearing rod and transmitting information to the vibration absorption safety device; the shock-absorbing safety device can operate according to the information transmitted by the detection device, thereby providing a cushioning force for an object falling onto the shock-absorbing safety device.
9. The helicopter body static test suspension assembly of claim 8 wherein the shock absorbing safety device is a safety sponge assembly comprising a safety sponge containing box and a compressed safety sponge disposed within the safety sponge containing box, the safety sponge containing box having an electrically controlled safety sponge box cover connected to the detection device and capable of being opened or closed based on information communicated by the detection device.
10. A helicopter body static test suspension assembly as defined in claim 9 wherein a gyroscope assembly is disposed within said male slider, said gyroscope assembly being capable of recording the trajectory of movement of said male slider.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611068485.3A CN106742052B (en) | 2016-11-29 | 2016-11-29 | A kind of helicopter body slow test suspension |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611068485.3A CN106742052B (en) | 2016-11-29 | 2016-11-29 | A kind of helicopter body slow test suspension |
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| CN106742052A CN106742052A (en) | 2017-05-31 |
| CN106742052B true CN106742052B (en) | 2019-01-22 |
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| CN201611068485.3A Active CN106742052B (en) | 2016-11-29 | 2016-11-29 | A kind of helicopter body slow test suspension |
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Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN107813259B (en) * | 2017-11-02 | 2024-07-12 | 中国航发哈尔滨东安发动机有限公司 | Helicopter tail shaft bearing position adjusting device |
| CN108163228B (en) * | 2017-12-03 | 2021-03-23 | 中国直升机设计研究所 | Whole-helicopter flexible suspension test device |
| CN108945513B (en) * | 2018-04-19 | 2021-08-03 | 哈尔滨飞机工业集团有限责任公司 | Movable helicopter mooring hovering test device |
| CN110346098A (en) * | 2019-07-05 | 2019-10-18 | 傅明尧 | A kind of wing slow test hanging apparatus |
| CN110793744B (en) * | 2019-12-02 | 2021-04-13 | 中国空气动力研究与发展中心 | Wind tunnel test model suspension joint |
| CN112722325B (en) * | 2021-02-26 | 2022-07-29 | 芜湖创联航空装备产业研究院有限公司 | Static test device and method for fixed-wing unmanned aerial vehicle body |
| CN114476147B (en) * | 2021-12-31 | 2022-11-01 | 北京空间机电研究所 | Spacecraft cabin multi-point hoisting static test loading device and method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3465846A (en) * | 1967-07-10 | 1969-09-09 | Koor Ind & Crafts Co Ltd | Installation for approaching portions of an airplane |
| US5359542A (en) * | 1991-12-20 | 1994-10-25 | The Boeing Company | Variable parameter collision avoidance system for aircraft work platforms |
| DE4420502C2 (en) * | 1994-06-13 | 1997-10-02 | Mero Raumstruktur Gmbh & Co | Docking device, in particular for the maintenance and overhaul of aircraft |
| CN102147342A (en) * | 2010-06-12 | 2011-08-10 | 北京航空航天大学 | Static test system for min-aircraft structure |
| CN103487277B (en) * | 2013-10-11 | 2015-11-04 | 沈阳航空航天大学 | A kind of multifunctional universal test-bed for light aerocraft slow test |
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