CN112093063B - Outer airborne equipment mounting frame of helicopter cabin - Google Patents
Outer airborne equipment mounting frame of helicopter cabin Download PDFInfo
- Publication number
- CN112093063B CN112093063B CN202010989004.2A CN202010989004A CN112093063B CN 112093063 B CN112093063 B CN 112093063B CN 202010989004 A CN202010989004 A CN 202010989004A CN 112093063 B CN112093063 B CN 112093063B
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- helicopter
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- horizontal support
- hole
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- 230000003014 reinforcing effect Effects 0.000 claims description 10
- 239000003351 stiffener Substances 0.000 claims description 3
- 210000005069 ears Anatomy 0.000 claims description 2
- 230000000149 penetrating effect Effects 0.000 claims 1
- 238000010276 construction Methods 0.000 abstract description 6
- 230000004048 modification Effects 0.000 abstract 1
- 238000012986 modification Methods 0.000 abstract 1
- 238000009434 installation Methods 0.000 description 12
- 238000004891 communication Methods 0.000 description 8
- 230000005540 biological transmission Effects 0.000 description 5
- 238000013016 damping Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000002955 isolation Methods 0.000 description 2
- 239000003973 paint Substances 0.000 description 2
- 238000010008 shearing Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- 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
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Vibration Prevention Devices (AREA)
- Casings For Electric Apparatus (AREA)
Abstract
The invention provides a mounting frame for equipment on the outer side of a helicopter cabin, which relates to the technical field of equipment matched with an aircraft, and aims to solve the technical problems of high construction difficulty and high modification cost of the mounting frame for the equipment on the outer side of the helicopter cabin in the prior art, and the technical scheme of the invention is as follows: the mounting bracket includes: the fastening component is fixedly connected with the vibration isolator; the horizontal support plate is fixedly connected with the fastening component, the shape of the horizontal support plate is matched with that of the shell of the helicopter, a plurality of groups of through holes are formed in the horizontal support plate, and the positions of the through holes are matched with those of the shell holes; and the hole connecting piece penetrates through the through hole and the shell hole so as to connect the horizontal supporting plate with the helicopter.
Description
Technical Field
The invention relates to the technical field of equipment matched with aircrafts, in particular to an airborne equipment mounting frame outside a helicopter cabin.
Background
Compared with a fixed wing aircraft, the helicopter does not need to build an airport, does not need to use a long airport runway, does not need to spend a great deal of land resources, financial resources and material resources, can vertically take off and land in a small area, and is widely applied to a plurality of fields such as transportation, patrol, travel, rescue and the like.
In some special use cases, external equipment, such as an onboard satellite communication system, needs to be installed outside the cabin of the helicopter, and the external equipment is mainly used for solving the problem of limited high-altitude communication. At present, helicopters for bearing flight tasks in Qinghai-Tibet plateau areas and helicopters for executing offshore flight tasks in China are required to be provided with an onboard satellite communication system based on a Ku wave band, wherein communication equipment (communication equipment on the helicopter) of the onboard section mainly comprises an off-board antenna, an antenna control unit, a power amplifier, a modem and wireless access equipment, and part of equipment is required to be arranged outside an cabin, so that a specially designed mounting frame is required to bear the satellite communication equipment.
The traditional helicopter cabin outer airborne equipment mounting frame is fixed in a mode that holes are needed to be drilled in the bearing position of the helicopter casing, and then the helicopter casing is fixedly mounted through bolts.
Disclosure of Invention
In order to solve the technical problems of high construction difficulty and high refitting cost of an installation frame of airborne equipment outside a helicopter cabin in the prior art, the technical scheme of the invention is as follows:
The invention provides a helicopter cabin external airborne equipment mounting frame, the helicopter comprises: the vibration isolator is used for reducing the vibration of the propeller, and the shell hole is formed in the helicopter shell and the shell screw is positioned in the shell hole. What needs to be specifically stated is: the vibration isolator is an elastic device with certain damping, and the vibration isolator is installed in the transmission path of the vibration source to reduce the transmission of the vibration source, which is called vibration isolation, and is a key device in the manufacturing field of helicopters, and is an elastic element arranged on a helicopter propeller and a cabin and used for reducing and eliminating the vibration force transmitted to the cabin by the propeller; the shell of the helicopter is not an integrally formed structure, and is usually an assembly part, the shell hole is formed in the original mounting hole of the shell of the helicopter, and shell screws are arranged in the shell hole, so that the bulk shell of the helicopter is fixed and assembled. In the invention, the original parts of the helicopter are utilized, and the mounting frame is fixed and assembled under the condition that the helicopter is not modified, and the concrete improvement points are as follows: the fastening component is connected with the original vibration isolator of the helicopter and provides a main supporting point for the mounting frame; the horizontal support plate, one side with fastening component fixed connection, the shape of horizontal support plate with the shell shape phase-match of helicopter, the multiunit through-hole has been seted up to the horizontal support plate, the position phase-match of seting up of through-hole with the position phase-match of casing hole, a plurality of through-holes are connected with the casing hole cooperation back, provide a plurality of main strong points for the mounting bracket. The specific installation steps are as follows: the casing screw is disassembled to expose the casing hole, the horizontal support plate is arranged outside the helicopter in a supporting mode, the position of the through hole is adjusted to be corresponding to that of the original casing hole, the through hole is fixed through a hole connecting piece, and the horizontal support plate is fixedly connected to the vibration isolator through the fastening component, so that the mounting frame is mounted on the helicopter.
Taking EC135P2 helicopter installation cabin outer equipment as an example, the original installation and fixation mode needs to be perforated at the bearing position of the helicopter shell, so that the original structure of the helicopter when leaving the factory is destroyed, the strength of the shell is reduced, and the construction difficulty in the perforation process is high and the refitting cost is high. The invention mainly utilizes the bearing points of the original helicopter and the original components, connects one side of the mounting frame with the vibration isolator, and simultaneously dismounts the shell screws at the corresponding positions, and utilizes the original mounting positions, the shell holes and the hole connecting pieces with proper lengths to further complete the fixation and the assembly of other positions of the mounting frame and the shell. The invention avoids hole matching operation in the traditional installation mode, ensures the shell strength of the helicopter, and has simple refitting construction and low cost.
In one possible design, the fastening assembly includes a staple bolt; the staple bolt is arc structure, the isolator is including setting up in the support shell of outside, and wherein the effect of support shell is when preventing the inside damping element inefficacy, plays a supporting role. The two anchor clamps are connected to the periphery of the supporting shell in a matched mode and are fastened through the bolt and nut assembly.
Taking an EC135P2 helicopter as an example, the inside of a vent hole at the lower side of the propeller is the vibration isolator, the fastening component stretches into the vent hole, and the two hoops are sleeved outside the supporting shell and fastened through the bolt and nut component. It should be noted that the fastening assembly requires removal of the housing or the like before extending into the vent hole to provide operating space for workers and equipment.
Optionally, the anchor ear and the horizontal support plate can be connected through a bolt and nut assembly, and also can be designed to be welded with the horizontal support plate by one anchor ear, and the other anchor ear is connected with the horizontal support plate through the bolt and nut assembly.
In one possible design, the fastening assembly further comprises an engagement block; the connecting block is used for connecting the anchor ear and the horizontal support plate, and the connecting part is fastened through a bolt and nut assembly. In order to further improve fastening assembly's assembly flexibility, simultaneously, make the whole of mounting bracket be detachable structure, make things convenient for the mounting bracket to prefabricate at the mill to be convenient for store and transport, spare part commonality is also stronger.
In one possible design, the horizontal support plate includes an integrally formed straight portion and an on-board device mounting portion, the straight portion being connected to the engagement block. The straight line part is mainly used for matching a vent hole channel of the EC135P2 helicopter and is used for connecting the mounting part of the airborne equipment and the vibration isolator. The onboard equipment mounting portion is a main mounting platform, and the satellite communication equipment is mounted on the main mounting platform.
Optionally, in order to ensure the strength of the straight portion, the width of the straight portion is as adapted as possible to the vent hole, and the width of the straight portion is slightly smaller than the aperture of the vent hole.
In one possible design, the straight portion has a first stiffener on both sides.
Wherein, the first reinforcing rib has two main functions: firstly, in order to improve the self strength of the straight line part, the force for connecting the mounting part of the airborne equipment and the vibration isolator is provided by the straight line part because the mounting part of the airborne equipment and the vibration isolator are at a certain distance, so that the strength of the straight line part needs to be ensured; the first reinforcing rib is of a flanging structure, so that the side face of the straight line part has a certain width, and when the reinforcing rib is arranged in the vent hole, the contact area between the straight line part and the vent hole can be increased, and damage to the paint surface of the vent hole is reduced.
In one possible embodiment, the on-board installation section is provided with a plurality of through slots for installing on-board equipment.
Optionally, the through groove is a waist-shaped groove, a round groove and the like, and has the functions that: firstly, in order to assemble the onboard equipment; secondly, in order to reduce dead weight and production cost.
In one possible design, the method further comprises: and the bottom supporting plate is arranged between the horizontal supporting plate and the helicopter shell. Since the helicopter casing is not a plane, it is necessary to design the bottom support plate to support the horizontal support plate.
Optionally, the bottom support plate may be fixedly connected to the horizontal support plate by a bolt and nut assembly, and is abutted to the helicopter casing; or the bottom support plate is fixedly connected with the horizontal support plate and the helicopter shell through hole connecting pieces, and at the moment, the bottom support plate is coordinated with the shell holes and is detached from shell screws in the shell holes.
In one possible design, the bottom support plate has a second reinforcing rib to further increase the strength of the bottom support plate.
In one possible design, the bore connection is a bolt and nut assembly, a pin or a string. Preferably, a bolt and nut assembly is used, in use, the through holes are aligned with the original housing holes and pass through the bolts from the outside of the helicopter housing to the inside of the helicopter, and then the nuts are screwed and installed inside the helicopter.
In one possible design, the nut is a self-locking nut.
The main stress point of the common threaded fastener is only the contact position of the first thread and the second thread of the nut, and other threads are basically not stressed, so that when the tightening torque is large, the stress is concentrated at the first thread, the first thread is easy to bend and deform in shearing, and only then the second thread surface is stressed and generates locking force. By analogy, the load bearing surfaces are subjected to force transmission one by one, so that the threads are sequentially sheared and worn correspondingly, the shearing and wearing damage of each tooth is serious, the strength of the nuts and the threads is greatly reduced, and finally the sliding threads are caused. The thread of the self-locking nut tightly pushes all the screw thread tips of the screw bolt against the 30-degree wedge-shaped inclined plane due to the unique structure, the load born by each tooth on the screw thread is relatively uniform, and the load can be dispersed to each surface and each point, so that the anti-loosening friction force generated on each part of the thread is similar, and the transverse vibration can be effectively resisted. It has been studied that the first load bearing surface of the self-locking thread bears I7% of the load, while the last load bearing surface also bears 12.5% of the load. Therefore, each thread of the screw thread can bear load uniformly, stress concentration does not exist, loosening or tooth slipping is not easy to occur, and fatigue strength is improved exponentially.
Drawings
FIG. 1 is a schematic view of an embodiment of the invention for providing a device mount on board an external aircraft of a helicopter cabin;
FIG. 2 is a schematic diagram of another view of FIG. 1;
FIG. 3 is a schematic view of a fastening assembly provided in one embodiment of the present invention;
FIG. 4 is a schematic view of a bottom support plate provided in one embodiment of the present invention;
fig. 5 is a schematic view of a fastening assembly provided in another embodiment of the present invention.
Reference numerals: 10. a vibration isolator; 11. a support housing; 20. a fastening assembly; 21. a hoop; 22. a joint block; 30. a horizontal support plate; 31. a straight line portion; 311. a first reinforcing rib; 32. an onboard equipment installation part; 321. a through groove; 33. a through hole; 40. a bottom support plate; 41. a second reinforcing rib; 50. and a hole connector.
Detailed Description
The technical scheme of the invention will be described below with reference to the accompanying drawings. It will be apparent that the described embodiments are only some, but not all, embodiments of the invention.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be either fixedly connected, detachably connected, or integrally connected, for example; can be mechanically connected, electrically connected or can be communicated with each other; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the description of the present invention, it should be understood that the terms "upper," "lower," "side," "inner," "outer," "top," "bottom," and the like indicate or are based on mounting orientations or positional relationships, merely to facilitate describing the present invention and simplify the description, and do not indicate or imply that the devices or elements 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 present invention.
It should be further noted that, in the embodiments of the present invention, the same reference numerals denote the same components or the same parts, and for the same parts in the embodiments of the present invention, reference numerals may be given to only one of the parts or the parts in the drawings, and it should be understood that, for other same parts or parts, the reference numerals are equally applicable.
Hereinafter, the terms "first," "second," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature.
As shown in fig. 1-5, the present invention provides a helicopter cabin external airborne equipment mounting rack, the helicopter comprising: vibration isolator 10 for reducing vibration of the propeller, a casing hole formed in the helicopter casing, and a casing screw positioned in the casing hole. What needs to be specifically stated is: vibration isolator 10 is typically an elastic device with a certain damping, and the vibration isolator 10 is installed in the transmission path of the vibration source to reduce the transmission of the vibration source, which is called "vibration isolation", in the field of helicopter manufacturing, vibration isolator 10 is a key device, and is an elastic element arranged between the helicopter propeller and the nacelle to reduce and eliminate the vibration force transmitted to the nacelle by the propeller; the shell of the helicopter is not an integrally formed structure, and is usually an assembly part, the shell hole is formed in the original mounting hole of the shell of the helicopter, and shell screws are arranged in the shell hole, so that the bulk shell of the helicopter is fixed and assembled. In the invention, the original parts of the helicopter are utilized, and the mounting frame is fixed and assembled under the condition that the helicopter is not modified, and the concrete improvement points are as follows: the fastening component 20 is connected with the original vibration isolator 10 of the helicopter and provides a main supporting point for the mounting frame; one side of the horizontal support plate 30 is fixedly connected with the fastening assembly 20, the shape of the horizontal support plate 30 is matched with the shape of the shell of the helicopter, a plurality of groups of through holes 33 are formed in the horizontal support plate 30, the positions of the through holes 33 are matched with the positions of the shell holes, and a plurality of main support points are provided for the mounting frame after the through holes 33 are matched and connected with the shell holes. The specific installation steps are as follows: the casing screw is disassembled to expose the casing hole, the horizontal support plate 30 is erected outside the helicopter, the position of the adjusting through hole 33 corresponds to that of the original casing hole and is fixed through the hole connecting piece 50, the horizontal support plate 30 is fixedly connected to the vibration isolator 10 through the fastening component 20, and then the installation frame is installed on the helicopter.
Taking EC135P2 helicopter installation cabin outer equipment as an example, the original installation and fixation mode needs to be perforated at the bearing position of the helicopter shell, so that the original structure of the helicopter when leaving the factory is destroyed, the strength of the shell is reduced, and the construction difficulty in the perforation process is high and the refitting cost is high. The invention mainly utilizes the bearing points of the original helicopter and the original components, connects one side of the mounting frame with the vibration isolator 10, and simultaneously removes the shell screws at the corresponding positions, and utilizes the original mounting positions, shell holes and hole connecting pieces 50 with proper lengths to further complete the fixation and assembly of other positions of the mounting frame and the shell. The invention avoids hole matching operation in the traditional installation mode, ensures the shell strength of the helicopter, and has simple refitting construction and low cost.
As shown in fig. 5, in one embodiment, the fastening assembly 20 includes a collar 21; the anchor ear 21 is of an arc-shaped plate structure, and the vibration isolator 10 comprises a supporting housing 11 arranged outside, wherein the supporting housing 11 plays a supporting role in preventing the vibration damping element inside from being failed. Two anchor ears 21 are cooperatively connected to the outer periphery of the support housing 11 and fastened by a bolt-and-nut assembly.
Taking an EC135P2 helicopter as an example, the inside of a vent hole at the lower side of the propeller is the vibration isolator 10, the fastening component 20 stretches into the vent hole, and the two anchor clamps 21 are sleeved outside the supporting shell 11 and are fastened through a bolt and nut component. It should be noted that the fastening assembly 20 requires the chassis and other components to be removed before extending into the vent holes to provide operating space for workers and equipment.
In one embodiment, the anchor ear 21 and the horizontal support plate 30 may be connected by a bolt and nut assembly, or it may be designed that one anchor ear 21 is welded to the horizontal support plate 30, and the other anchor ear 21 is connected to both through a bolt and nut assembly.
As shown in fig. 3, in one embodiment, the fastening assembly 20 further includes an engagement block 22; the joint block 22 is used for connecting the anchor ear 21 and the horizontal support plate 30, and the joint is fastened by a bolt and nut assembly. In order to further improve the assembly flexibility of fastening assembly 20, simultaneously, make the whole of mounting bracket be detachable structure, make things convenient for the mounting bracket to prefabricate at the mill to be convenient for store and transport, spare part commonality is also stronger.
As shown in fig. 1-2, in one embodiment, the horizontal support plate 30 includes an integrally formed straight portion 31 and an on-board device mounting portion 32, the straight portion 31 being connected to the engagement block 22. Straight section 31 is used to interface on-board equipment mounting section 32 with vibration isolator 10 primarily to match the vent aperture of the EC135P2 helicopter. The on-board device mounting section 32 is a main mounting platform, to which the satellite communication device is mounted.
In one embodiment, to ensure the strength of the straight portion 31, the width of the straight portion 31 is as adapted as possible to the vent hole, and the width of the straight portion 31 is slightly smaller than the aperture of the vent hole.
In one embodiment, the linear portion 31 has a first stiffener 311 on both sides. The first reinforcing rib 311 has two main functions: firstly, in order to improve the strength of the straight line portion 31, since the airborne equipment mounting portion 32 has a certain distance from the vibration isolator 10, the force for connecting the two components is provided by the straight line portion 31, so that the strength of the straight line portion 31 needs to be ensured; secondly, the reinforcing rib 311 is of a flanging structure, so that the side surface of the straight line part 31 has a certain width, and when the reinforcing rib is arranged in a vent hole, the contact area between the straight line part 31 and the vent hole can be increased, and the damage to the paint surface of the vent hole is reduced.
In one embodiment, the on-board device mounting portion 32 is provided with a plurality of through slots 321 for mounting on-board devices.
Preferably, the through groove 321 is a waist-shaped groove, a circular groove, etc., which functions: firstly, in order to assemble the onboard equipment; secondly, in order to reduce dead weight and production cost.
As shown in fig. 4, in one embodiment, further includes: a bottom support plate 40 disposed between the horizontal support plate 30 and the helicopter casing. Since the helicopter housing is not a plane, the bottom support plate 40 needs to be designed to support the horizontal support plate 30.
In one embodiment, bottom support plate 40 may be fixedly connected to horizontal support plate 30 by a bolt and nut assembly, abutting the helicopter casing.
In one embodiment, bottom support plate 40 is fixedly connected to horizontal support plate 30 and the helicopter housing by hole connection 50, at which point bottom support plate 40 is coordinated with the housing holes and the housing screws in the housing holes are removed.
In one embodiment, the bottom support plate 40 has second ribs 41 to further increase the strength of the bottom support plate 40.
In one embodiment, the hole connector 50 is a bolt and nut assembly, and in use, the through hole 33 is aligned with the original housing hole and threaded through the bolt from outside the helicopter housing to inside the helicopter, and then the nut is threaded into the inside of the helicopter.
Preferably, the nut is a self-locking nut.
The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (5)
1. An off-board equipment mount for a helicopter cabin, the helicopter comprising: vibration isolator (10) for reducing propeller vibration, set up in the casing hole of helicopter shell and be located the casing screw in the casing hole, its characterized in that, the mounting bracket includes:
the fastening assembly (20) is fixedly connected with the vibration isolator (10);
The horizontal support plate (30) is fixedly connected with the fastening assembly (20), the shape of the horizontal support plate (30) is matched with that of the shell of the helicopter, a plurality of groups of through holes (33) are formed in the horizontal support plate (30), and the opening positions of the through holes (33) are matched with those of the shell holes;
A hole connection member (50) penetrating the through hole (33) and the case hole to connect the horizontal support plate (30) with the helicopter;
The shell screw is disassembled to expose the shell hole, the horizontal support plate (30) is erected outside the helicopter and is connected through the hole connecting piece (50), the fastening component (20) fixedly connects the horizontal support plate (30) to the vibration isolator (10), and then the mounting frame is mounted on the helicopter;
Wherein the fastening assembly (20) comprises a hoop (21); the anchor ear (21) is of an arc-shaped plate structure, the vibration isolator (10) comprises a supporting shell (11) arranged outside, and the two anchor ears (21) are connected to the periphery of the supporting shell (11) in a matched mode and are fastened through a bolt and nut assembly;
The fastening assembly (20) further comprises an engagement block (22); the anchor ear (21) and the horizontal support plate (30) are connected through the connecting blocks (22), and each connecting part is fastened through a bolt and nut assembly;
The horizontal support plate (30) comprises an integrally formed linear part (31) and an airborne equipment mounting part (32), and the linear part (31) is connected with the connecting block (22);
The airborne equipment mounting part (32) is provided with a plurality of through grooves (321) for mounting airborne equipment;
The mounting bracket also includes: a bottom support plate (40) arranged between the horizontal support plate (30) and the housing of the helicopter.
2. The helicopter cabin outer onboard equipment mounting frame according to claim 1, wherein the two sides of the straight line part (31) are provided with first reinforcing ribs (311).
3. The off-board equipment mounting frame of a helicopter according to claim 1, characterized in that said bottom support plate (40) has a second stiffener (41).
4. The off-board equipment mount according to claim 1, wherein the hole connection (50) is a bolt-nut assembly, a pin or a wire.
5. The off-board equipment mount for a helicopter cabin according to any one of claims 1 to 4 wherein said nut is a self-locking nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010989004.2A CN112093063B (en) | 2020-09-18 | 2020-09-18 | Outer airborne equipment mounting frame of helicopter cabin |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010989004.2A CN112093063B (en) | 2020-09-18 | 2020-09-18 | Outer airborne equipment mounting frame of helicopter cabin |
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| CN112093063A CN112093063A (en) | 2020-12-18 |
| CN112093063B true CN112093063B (en) | 2024-05-28 |
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| CN202010989004.2A Active CN112093063B (en) | 2020-09-18 | 2020-09-18 | Outer airborne equipment mounting frame of helicopter cabin |
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| CN106985997A (en) * | 2017-03-15 | 2017-07-28 | 上海交通大学 | A kind of miniature quadrotor of vibration isolation |
| CN207328850U (en) * | 2017-08-29 | 2018-05-08 | 天津航天中为数据系统科技有限公司 | A kind of aircraft photoelectric nacelle hanging structure |
| CN207157561U (en) * | 2017-09-22 | 2018-03-30 | 湖南省库塔科技有限公司 | A kind of carry mechanism for helicopter |
| CN108953953A (en) * | 2018-08-28 | 2018-12-07 | 北京无线电测量研究所 | A kind of limit-type damping mounting rack of airborne electronic equipment cabinet |
| CN213414236U (en) * | 2020-09-18 | 2021-06-11 | 星展测控科技股份有限公司 | Mounting rack for airborne equipment outside helicopter cabin |
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| CN112093063A (en) | 2020-12-18 |
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