Helicopter embedded mounting retracting and releasing mechanism, cabin door driving mechanism and mounting system

Abstract

The invention provides a helicopter embedded mounting retracting and releasing mechanism, a cabin door driving mechanism and a mounting system, and belongs to the technical field of helicopter structural design. The helicopter embedded mounting retracting and releasing mechanism comprises a left-flight mounting retracting and releasing mechanism and a right-flight mounting retracting and releasing mechanism; and the left sailing mounting retracting and releasing mechanism and the right sailing mounting retracting and releasing mechanism are connected with the longitudinal wall plate of the mounting cabin, are stacked up and down, and are in central symmetry about the horizontal neutral plane of the fuselage. In the flying process of the helicopter, when the hanging object stretches out, the cabin door driving mechanism drives the hanging cabin door to be opened, and the left-flight hanging retracting and releasing mechanism and the right-flight hanging retracting and releasing mechanism drive the hanging object to stretch out towards the left flight direction and the right flight direction respectively; and when the hanging object finishes the task and is retracted, the left-flight hanging and retracting mechanism and the right-flight hanging and retracting mechanism drive the hanging object to be retracted into the cabin, and the cabin door driving mechanism drives the hanging cabin door to be closed. Under the conditions that a helicopter platform is small in space, large in vibration, fragile in paddle and the like, the folding and unfolding functions of the embedded mounting and the opening and closing functions of the cabin door can be achieved.

Description

Technical Field

[0001] The present invention belongs to the technical field of helicopter structural design, and particularly relates to an in - buried type mounting retracting mechanism, a cabin door driving mechanism and a mounting system for a helicopter. Background Art

[0002] With the increasing demand for high - speed performance of helicopters, the equipment mounting system of new - generation helicopters has gradually developed from the original external - hanging type to the in - buried type. The application of in - buried mounting can effectively reduce drag by simplifying the aerodynamic shape design, and at the same time can also reduce the radar cross - section. The in - buried mounting is widely used in fixed - wing aircraft, but less used in helicopters.

[0003] Compared with fixed - wing aircraft, helicopters have difficulties such as limited space, large vibration, and high requirements for controlling the weight of mechanisms. Therefore, it is more difficult to arrange in - buried mounting; and for helicopters, the influence of the mounted object on the tail rotor needs to be considered. For mounted objects with launch requirements, their deployment positions should be as far away from the tail rotor as possible. Summary of the Invention

[0004] In order to solve the technical problem that it is difficult to arrange in - buried mounting in helicopters in the prior art, based on the special requirements of the helicopter platform, the present invention provides an in - buried type mounting retracting mechanism with high space utilization rate and reliable structure, and a cabin door driving mechanism that is convenient for the maintenance and replacement of mounted objects. The technical solutions are as follows:

[0005] In the first aspect, a helicopter in - buried type mounting retracting mechanism is provided, including: a left - hand mounting retracting mechanism 2 and a right - hand mounting retracting mechanism 5. Both the left - hand mounting retracting mechanism 2 and the right - hand mounting retracting mechanism 5 are connected to the longitudinal wall panel 3 of the mounting cabin, and are stacked vertically and symmetrically about the center of the horizontal neutral plane of the fuselage.

[0006] During the flight of the helicopter, when the mounted object 1 needs to be extended, the cabin door driving mechanism drives the cabin door 4 of the mounting cabin to open, and the left - hand mounting retracting mechanism 2 and the right - hand mounting retracting mechanism 5 respectively drive the mounted object 1 to extend to the left and right; when the mounted object 1 needs to be retracted after completing the task, the left - hand mounting retracting mechanism 2 and the right - hand mounting retracting mechanism 5 drive the mounted object 1 to retract into the cabin, and the cabin door driving mechanism drives the cabin door 4 of the mounting cabin to close.

[0007] Among them, both the left - hand mounting retracting mechanism 2 and the right - hand mounting retracting mechanism 5 include: a driving motor 21, a ball screw 22, a mounting rack 24, a roller 25, a pin lock 26, and a transverse wall panel 27 of the mounting cabin.

[0008] The ball screw 22 is fixedly connected to the hanging bracket 24, and the hanging bracket 24 is fixedly connected to the suspended load 1. The driving motor 21, the roller 25 and the pin lock 26 are fixed to the outside of the longitudinal wall panel 3 of the suspension cabin; there are two transverse wall panels 27 of the suspension cabin, which are respectively located at the front and rear of the hanging bracket 24 in the flight direction, and are fixed to the inside of the longitudinal wall panel 3 of the suspension cabin;

[0009] When the hanging bracket 24 of the suspension and retraction mechanism 2 is retracted and extended, the driving motor 21 outputs a driving force, and then the rotary motion is converted into a linear motion through the ball screw 22, so as to drive the hanging bracket 24 and the suspended load 1 to perform retraction and extension motion along the Y direction, and the Y direction is perpendicular to the helicopter flight direction.

[0010] Wherein, there are two raised slideways on both the front and rear sides of the hanging bracket 24, namely the roller slideway 28 and the load-bearing slideway 29. The roller slideway 28 is a horizontal slideway, and the load-bearing slideway 29 has 3 convex points on the horizontal slideway, namely the front convex point 291 of the load-bearing slideway, the middle convex point 292 of the load-bearing slideway, and the rear convex point 293 of the load-bearing slideway; the front convex point 291 of the load-bearing slideway is located at the front end of the load-bearing slideway 29, the rear convex point 293 of the load-bearing slideway is located at the rear end of the load-bearing slideway 29, and the position of the middle convex point 292 of the load-bearing slideway is determined by the moving distance from the retracted position to the deployed position of the hanging bracket. The distance between the middle convex point 292 of the load-bearing slideway and the front convex point 291 of the load-bearing slideway is equal to the moving distance of the hanging bracket 24 from the retracted position to the deployed position;

[0011] The hanging bracket 24 is provided with a middle lock pin hole 23 and a front lock pin hole 30. When the hanging bracket is retracted, the limit pin in the pin lock 26 is inserted into the front lock pin hole 30. When the hanging bracket is deployed to the final position, the limit pin in the pin lock 26 is inserted into the middle lock pin hole 23;

[0012] The transverse wall panel 27 of the suspension cabin is provided with a roller groove 271 and a load-bearing groove 272. The groove positions of the two transverse wall panels 27 of the suspension cabin are the same. The positions of the roller groove 271 and the load-bearing groove 272 respectively correspond to the roller slideway 28 and the load-bearing slideway 29 on the hanging bracket 24. The roller groove 271 is a horizontal groove, and the load-bearing groove 272 has 3 convex points on the horizontal groove, namely the front convex point 273 of the load-bearing groove, the middle convex point 274 of the load-bearing groove and the rear convex point 275 of the load-bearing groove. The front convex point 273 of the load-bearing groove is located at the front end of the load-bearing groove 27, the rear convex point 275 of the load-bearing groove is located at the rear end of the load-bearing groove 27, and the distance between the middle convex point 274 of the load-bearing groove and the rear convex point 275 of the load-bearing groove is equal to the moving distance of the hanging bracket 24 from the retracted position to the deployed position.

[0013] When the hanger 24 needs to be extended, the motor 21 drives the ball screw 22 to drive the hanger 24 to move in a straight line away from the motor 21. When the hanger 24 reaches the final extended position, the convex point 293 at the rear of the load-bearing slideway is stuck in the convex point 274 in the middle of the load-bearing groove, and the convex point 292 in the middle of the load-bearing slideway is stuck in the convex point 273 at the front of the load-bearing groove. At this time, the load is transmitted through the surface contact of the convex points on the slideway and the groove, and the roller slideway 28 does not participate in bearing the load.

[0014] When the hanger 24 needs to be retracted, the motor 21 drives the ball screw 22 to drive the hanger 24 to move in a straight line approaching the motor 21. When the hanger 24 reaches the fully retracted position, the convex point 291 at the front of the load-bearing slideway is stuck in the convex point 273 at the front of the load-bearing groove, and the convex point 293 at the rear of the load-bearing slideway is stuck in the convex point 275 at the rear of the load-bearing groove. At this time, the load is transmitted through the surface contact of the convex points on the slideway and the groove, and the roller slideway 28 does not participate in bearing the load.

[0015] In a second aspect, a hatch driving mechanism is provided, including: the No. 1 rocker 31, the hydraulic actuator 32, and the No. 2 rocker 34; there are a total of four groups of driving mechanisms, which are respectively arranged on the front and rear sides of the hatch, and the driving mechanisms of the left and right side-mounted hatch 4 are symmetrically arranged; one side of the hydraulic actuator 32 is fixed to the longitudinal wall plate 3 of the mounting compartment, and the other side is connected to the No. 1 rocker 31. Both the No. 1 rocker and the No. 2 rocker are fixed on the cross frame 35 on one side and connected to the side-mounted hatch 4 on the other side; when the side-mounted hatch 4 needs to be opened, the hydraulic actuator 32 extends, converts the linear motion into a rotary motion through the No. 1 rocker 31, and the No. 1 rocker 31 drives the side-mounted hatch 4 and the No. 2 rocker 34 to rotate, and finally drives the side-mounted hatch 4 to flip to the lower side of the lower skin 33 of the fuselage.

[0016] Among them, the length of the No. 1 rocker 31 is longer than that of the No. 2 rocker 34, and longer than the distance between the connection point of the No. 1 rocker 31 and the side-mounted hatch 4 and the connection point of the No. 2 rocker 34 and the side-mounted hatch 4; the No. 2 rocker is longer than the distance between the connection point of the No. 1 rocker 31 and the cross frame 35 and the connection point of the No. 2 rocker 34 and the cross frame 35; the fixed end of the hydraulic actuator 32 is located on the upper side of the longitudinal wall plate 3 of the mounting compartment, and the distance from the connection point of the hydraulic actuator 32 and the No. 1 rocker 31 to the connection point of the No. 1 rocker 31 and the cross frame 35 is about 1 / 5 of the total length of the No. 1 rocker.

[0017] In a third aspect, a mounting system is provided, including a helicopter internal buried mounting retraction mechanism according to any one of the first aspects and the hatch driving mechanism according to the second aspect.

[0018] The beneficial effects of the present invention are at least as follows:

[0019] The present invention provides an in - buried mounting retraction mechanism for a helicopter with high space utilization rate and reliable structure, and a hatch driving mechanism facilitating the maintenance and replacement of the load. It can realize the retraction function of the in - buried mounting and the opening and closing function of the hatch under the conditions of limited space, large vibration and fragile blades on the helicopter platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the overall layout of the mounting retraction mechanism of the present invention;

[0021] Figure 2 It is a schematic diagram of the left - hand mounting retraction mechanism of the present invention;

[0022] Figure 3 It is a schematic diagram of the transverse wall structure of the mounting hatch of the present invention;

[0023] Figure 4 It is a schematic diagram of the extended state of the mounting retraction mechanism of the present invention;

[0024] Figure 5 It is a schematic diagram of the hatch driving mechanism of the present invention;

[0025] Figure 6 It is a schematic diagram of the intermediate position of the hatch expansion of the present invention;

[0026] Figure 7 It is a schematic diagram of the final expanded position of the hatch of the present invention.

[0027] Among them, 1 - load, 2 - left - hand mounting retraction mechanism, 3 - longitudinal wall of the mounting hatch, 4 - hatch of the mounting hatch, 5 - right - hand mounting retraction mechanism, 21 - driving motor, 22 - ball screw, 23 - middle locking pin hole, 24 - mounting bracket, 25 - roller, 26 - pin lock, 27 - transverse wall of the mounting hatch, 271 - roller groove, 272 - load - bearing groove, 273 - front convex point of the load - bearing groove, 274 - middle convex point of the load - bearing groove, 275 - rear convex point of the load - bearing groove, 28 - roller slideway, 29 - load - bearing slideway, 291 - front convex point of the load - bearing slideway, 292 - middle convex point of the load - bearing slideway, 293 - rear convex point of the load - bearing slideway, 30 - front locking pin hole, 31 - rocker 1, 32 - hydraulic actuator, 3 - longitudinal wall of the mounting hatch, 33 - lower skin of the fuselage, 34 - rocker 2, 4 - hatch of the mounting hatch, 35 - cross - frame. DETAILED DESCRIPTION OF THE INVENTION

[0028] To make the objectives, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of them. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts fall within the scope of protection of the present invention.

[0029] The features and illustrative embodiments of various aspects of the present invention will be described in detail below. In the following detailed description, many specific details are set forth in order to provide a thorough understanding of the present invention. However, it will be apparent to those skilled in the art that the present invention may be practiced without some of these specific details. The following description of the embodiments is merely provided to better understand the present invention by showing examples of the present invention. The present invention is in no way limited to any specific arrangements and methods set forth below, but covers any improvements, substitutions, and modifications of structures, methods, and devices without departing from the spirit of the present invention. Well-known structures and technologies are not shown in the drawings and the following description to avoid unnecessarily obscuring the present invention.

[0030] It should be noted that, without conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other, and the various embodiments may refer to and cite each other.

[0031] The present invention will be described in detail below with reference to the accompanying drawings and specific embodiments.

[0032] The present invention makes full use of the internal space of the helicopter and effectively ensures the deployment position of the suspended load on the premise of ensuring the structural strength. Before the suspended load is deployed in the air or before the suspended load is replaced and maintained, the hatch of the embedded suspension cabin needs to be opened. The working performance of the hatch mechanism has a direct impact on flight safety and function realization. According to the functional requirements and ground maintenance needs, the driving form and deployment direction of the hatch are restricted. The driving mechanism designed by the present invention can drive the hatch to flip downward. After deployment, the hatch is located on the lower side of the fuselage, facilitating the quick replacement or maintenance of the suspended load.

[0033] The left-side flight suspension retraction drive 2 and the right-side flight suspension retraction mechanism 5 are stacked vertically, and the left and right side suspension retraction structures are symmetric about the central plane of the fuselage's horizontal neutral axis. The overall layout form and spatial distribution are as Figure 1 shown.

[0034] The following takes the left side of the heading as an example to describe the suspension retraction mechanism 2 in detail. The form of the left-side flight suspension retraction mechanism 2 is as Figure 2As shown in the figure. The mounting retracting and extending mechanism 2 consists of a driving motor 21, a ball screw 22, a mounting bracket 24, rollers 25, a pin lock 26, and mounting cabin transverse wall panels 27. The ball screw 22 is fixedly connected to the mounting bracket 24, and the mounting bracket 24 is fixedly connected to the mounted object 1. The driving motor 21, the rollers 25, and the pin lock 26 are fixed outside the longitudinal wall panel 3 of the mounting cabin. There are two mounting cabin transverse wall panels 27, which are respectively located on the forward side and the rear side of the mounting bracket 24 in the flight direction, and are fixed to the inside of the longitudinal wall panel 3 of the mounting cabin.

[0035] When the mounting bracket 24 of the mounting retracting and extending mechanism retracts and extends, the driving motor 21 outputs a driving force, and then converts the rotary motion into a linear motion through the ball screw 22, thereby driving the mounting bracket 24 and the mounted object 1 to perform retracting and extending motions along the Y direction, and the Y direction is perpendicular to the helicopter flight direction.

[0036] As Figure 2 shown, two raised slideways are machined on both the front and rear sides of the mounting bracket 24, namely the roller slideway 28 and the load-bearing slideway 29. The roller slideway 28 is a horizontal slideway, and three convex points are machined on the horizontal slideway of the load-bearing slideway 29, namely the front convex point 291 of the load-bearing slideway, the middle convex point 292 of the load-bearing slideway, and the rear convex point 293 of the load-bearing slideway. A middle locking pin hole 23 and a front locking pin hole 30 are machined on the mounting bracket 24. When the mounting bracket is retracted, the limit pin in the pin lock 26 is inserted into the front locking pin hole 30. When the mounting bracket is extended to the final position, the limit pin in the pin lock 26 is inserted into the middle locking pin hole 23.

[0037] Roller grooves 271 and load-bearing grooves 272 are machined on the mounting cabin transverse wall panels 27. The groove positions of the two mounting cabin transverse wall panels 2 are the same. Taking the rear side wall panel as an example, its structural form is as Figure 3 shown. The positions of the roller grooves 271 and the load-bearing grooves 272 correspond to the roller slideway 28 and the load-bearing slideway 29 on the mounting bracket 24 respectively. The roller groove 271 is a horizontal groove, and three convex points are machined on the horizontal groove of the load-bearing groove 272, namely the front convex point 273 of the load-bearing groove, the middle convex point 274 of the load-bearing groove, and the rear convex point 275 of the load-bearing groove.

[0038] As Figure 2 and Figure 3 shown, when the mounting bracket 24 is retracted, the front convex point 291 and the rear convex point 293 on the load-bearing slideway 29 of the mounting bracket are stuck between the front convex point 273 and the rear convex point 275 of the load-bearing groove, transmitting the load. After the mounting bracket 24 extends in place, the middle convex point 292 and the rear convex point 293 on the load-bearing slideway 29 of the mounting bracket are stuck between the front convex point 273 and the middle convex point 274 of the load-bearing groove, transmitting the load. The load is transmitted through the contact between the convex point surfaces on the load-bearing slideway 29 of the mounting bracket 24 and the convex point surfaces on the load-bearing groove 272 of the mounting cabin transverse wall panel 27, ensuring that the roller slideway 28 does not participate in load transmission. The form of the mounting retracting and extending mechanism in the extended state of the mounting bracket 24 is as Figure 4as shown

[0039] As Figure 4 As shown, when the pylon 24 is in the extended state, the pylon retraction and extension mechanism 2 has two positions for bearing, front and rear, so that the pylon 24 forms an extended beam structure in the extended state. In the pylon retraction and extension mechanism of the present invention, the fuselage space is fully utilized, the load transfer is reasonable, the extension amount of the pylon 24 can be increased, the position of the suspended load can be ensured to be far from the tail rotor, and the probability of the tail spray hitting the blade during the launch of the suspended load can be reduced.

[0040] A set of link mechanism is driven by a hydraulic actuator to realize the opening and closing of the pylon hatch 4. There are four groups of driving mechanisms, which are respectively arranged on the front and rear sides of the pylon hatch 4. The driving mechanisms of the left and right pylon hatches 4 are symmetrically arranged. A single set of hatch driving mechanism consists of a No. 1 rocker 31, a hydraulic actuator 32, and a No. 2 rocker 34. The structural form is as Figure 5 shown. When the pylon hatch 4 needs to be opened, the hydraulic actuator 32 extends, converts the linear motion into a rotary motion through the No. 1 rocker 31, the No. 1 rocker 31 drives the pylon hatch 4 and the No. 2 rocker 34 to rotate, and finally drives the pylon hatch 4 to flip to the lower side of the lower fuselage skin 33. The intermediate position and the final deployment position of the hatch are respectively as Figure 6 and Figure 7 shown. The hatch flips downward, does not block the actuation path of the pylon retraction and extension mechanism, and when replacing or maintaining the suspended load on the ground, the space around the suspended load is open, improving the replacement efficiency of the suspended load and the maintainability of the suspended load.

[0041] The present invention designs an in - buried pylon retraction and extension mechanism for a helicopter. The whole mechanism has a high space utilization rate and a reliable structural form. It can effectively transfer loads and structurally lock in both the retracted and extended states of the pylon, and fully utilizes the space to ensure that the launch position of the suspended load is as far as possible from the tail rotor, improving the safety of the helicopter. At the same time, the present invention designs a driving mechanism for the hatch. This form of hatch deployment ensures the actuation space of the pylon retraction and extension mechanism, and improves the replacement efficiency of the suspended load and the maintainability of the suspended load.

[0042] The above only expresses the implementation modes of the present invention, and its description is relatively specific and detailed, but it cannot be understood as a limitation to the scope of the patent. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can still be made, and these all belong to the protection scope of the present invention. In addition, the parts not elaborated in the present invention are all conventional technologies.

Claims

1. An internal retractable mounting mechanism for a helicopter, characterized in that Including: The left - hand flight - mounted retracting mechanism (2) and the right - hand flight - mounted retracting mechanism (5). The left - hand flight - mounted retracting mechanism (2) and the right - hand flight - mounted retracting mechanism (5) are both connected to the longitudinal wall panel (3) of the mounting bay, are stacked vertically, and are centrosymmetric about the horizontal neutral plane of the fuselage.

2. The retractable mounting mechanism for internal installation in a helicopter according to claim 1, wherein, Both the left - hand flight - mounted retracting mechanism (2) and the right - hand flight - mounted retracting mechanism (5) include: a driving motor (21), a ball screw (22), a mounting bracket (24), rollers (25), a pin lock (26), and transverse wall panels (27) of the mounting bay. The ball screw (22) is fixedly connected to the mounting bracket (24), and the mounting bracket (24) is fixedly connected to the mounted object (1). The driving motor (21), the rollers (25), and the pin lock (26) are fixed to the outside of the longitudinal wall panel (3) of the mounting bay; there are two transverse wall panels (27) of the mounting bay, which are respectively located at the front and rear of the mounting bracket (24) in the flight direction and are fixed to the inside of the longitudinal wall panel (3) of the mounting bay. When the mounting bracket (24) of the retracting mechanism (2) is retracted or extended, the driving motor (21) outputs a driving force, and then converts the rotary motion into a linear motion through the ball screw (22), so as to drive the mounting bracket (24) and the mounted object (1) to perform retracting and extending motions along the Y - direction, and the Y - direction is perpendicular to the helicopter's flight direction.

3. The retractable mechanism for internal mounting of a helicopter according to claim 2, wherein, There are two raised slideways on both the front and rear sides of the mounting bracket (24), namely the roller slideway (28) and the load - bearing slideway (29). The roller slideway (28) is a horizontal slideway, and there are 3 convex points on the load - bearing slideway (29) on the horizontal slideway, namely the front convex point (291) of the load - bearing slideway, the middle convex point (292) of the load - bearing slideway, and the rear convex point (293) of the load - bearing slideway; the front convex point (291) of the load - bearing slideway is located at the front - most end of the load - bearing slideway (29), the rear convex point (293) of the load - bearing slideway is located at the rear - most end of the load - bearing slideway (29), and the position of the middle convex point (292) of the load - bearing slideway is determined by the moving distance from the retracted position to the deployed position of the mounting bracket. The distance between the middle convex point (292) of the load - bearing slideway and the front convex point (291) of the load - bearing slideway is equal to the moving distance of the mounting bracket (24) from the retracted position to the deployed position. There are a middle locking pin hole (23) and a front locking pin hole (30) on the mounting bracket (24). When the mounting bracket is retracted, the limit pin in the pin lock (26) is inserted into the front locking pin hole (30). When the mounting bracket is deployed to the final position, the limit pin in the pin lock (26) is inserted into the middle locking pin hole (23). The lateral wall panel (27) of the mounting pod is provided with a roller groove (271) and a load-bearing groove (272). The groove positions of the two lateral wall panels (27) of the mounting pod are the same. The positions of the roller groove (271) and the load-bearing groove (272) correspond to the roller slideway (28) and the load-bearing slideway (29) on the hanging rack (24) respectively. The roller groove (271) is a horizontal groove. The load-bearing groove (272) is provided with three convex points on the horizontal groove, namely the front convex point (273) of the load-bearing groove, the middle convex point (274) of the load-bearing groove and the rear convex point (275) of the load-bearing groove. The front convex point (273) of the load-bearing groove is located at the foremost end of the load-bearing groove (27), the rear convex point (275) of the load-bearing groove is located at the rearmost end of the load-bearing groove (27), and the distance between the middle convex point (274) of the load-bearing groove and the rear convex point (275) of the load-bearing groove is equal to the moving distance of the hanging rack (24) from the retracted position to the deployed position.

4. The in-aircraft buried mounting retracting mechanism of a helicopter according to claim 3, characterized in that When the hanging rack (24) needs to be extended, the motor (21) drives the ball screw (22) to drive the hanging rack (24) to perform a linear motion away from the motor (21). When the hanging rack (24) reaches the final extended position, the rear convex point (293) of the load-bearing slideway is stuck in the middle convex point (274) of the load-bearing groove, and the middle convex point (292) of the load-bearing slideway is stuck in the front convex point (273) of the load-bearing groove. At this time, the load is transmitted through the surface contact of the convex points on the slideway and the groove, and the roller slideway (28) does not participate in bearing.

5. The in-aircraft buried mounting retracting mechanism of a helicopter according to claim 3, characterized in that When the hanging rack (24) needs to be retracted, the motor (21) drives the ball screw (22) to drive the hanging rack (24) to perform a linear motion close to the motor (21). When the hanging rack (24) reaches the fully retracted position, the front convex point (291) of the load-bearing slideway is stuck in the front convex point (273) of the load-bearing groove, and the rear convex point (293) of the load-bearing slideway is stuck in the rear convex point (275) of the load-bearing groove. At this time, the load is transmitted through the surface contact of the convex points on the slideway and the groove, and the roller slideway 28 does not participate in bearing.

6. A hatch driving mechanism, characterized in that, Including: The first rocker (31), the hydraulic actuator (32), the second rocker (34); There are a total of four groups of driving mechanisms, which are respectively arranged on the front and rear sides of the cabin door, and the driving mechanisms of the left and right side mounting pod doors (4) are symmetrically arranged; one side of the hydraulic actuator (32) is fixed on the longitudinal wall panel (3) of the mounting pod, and the other side is connected to the first rocker (31). Both the first rocker and the second rocker are fixed on the cross frame (35) on one side and connected to the mounting pod door (4) on the other side; when the mounting pod door (4) needs to be opened, the hydraulic actuator (32) extends, converts the linear motion into a rotary motion through the first rocker (31), the first rocker (31) drives the mounting pod door (4) and the second rocker (34) to rotate, and finally drives the mounting pod door (4) to flip to the lower side of the lower skin (33) of the fuselage.

7. The hatch driving mechanism according to claim 6, wherein, The length of the No. 1 rocker (31) is longer than that of the No. 2 rocker (34), and is longer than the distance between the connection point of the No. 1 rocker (31) and the mounting cabin door (4) and the connection point of the No. 2 rocker (34) and the mounting cabin door (4); the No. 2 rocker is longer than the distance between the connection point of the No. 1 rocker (31) and the cross frame (35) and the connection point of the No. 2 rocker (34) and the cross frame (35); the fixed end of the hydraulic actuator (32) is located on the upper side of the longitudinal wall panel (3) of the mounting cabin, and the distance from the connection point of the hydraulic actuator (32) and the No. 1 rocker (31) to the connection point of the No. 1 rocker (31) and the cross frame (35) is about 1 / 5 of the total length of the No. 1 rocker.

8. A mounting system, characterized in that, Comprising an in - buried mounting retracting mechanism for a helicopter according to any one of claims 1 to 7, and a cabin door driving mechanism according to claim 6 or 7.

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