Rotary member fly-off stop block

Abstract

The utility model relates to mechanical engineering technical field discloses a kind of rotary piece hangs and flies stop slider, to stop rotary piece in the hanging and flying process of rotary body power aircraft before launch. The utility model discloses stop slider includes: the base for being fixed with rotary piece;The both sides of base are provided with the vertical stop pawl, the inside of two stop pawls is equipped with the sliding groove matched with the outer flange of airborne guide rail, and the upper connecting surface between the sliding groove between two is the gap of zero contact with each other between guide rail lower surface.

Description

Technical Field

[0001] This utility model relates to the field of mechanical engineering technology, and in particular to a rotating component hanger stop slider. Background Technology

[0002] Rotating components are widely used in the design of propulsive aircraft. During flight, they can rotate 360 ​​degrees using airflow, significantly improving flight stability and reducing the impact of engine thrust eccentricity, aerodynamic asymmetry, and mass eccentricity on flight trajectory dispersion. However, due to the flexibility of these components, they can sometimes rotate freely during launch, affecting launch safety and the overall launch status of the propulsive aircraft. Therefore, a stop block for these rotating components needs to be designed to ensure their immobilization before launch. Utility Model Content

[0003] The purpose of this utility model is to disclose a rotating component suspension slider to stop the rotating component during the suspension process of a spinning integrated powered aircraft before launch.

[0004] To achieve the above objectives, the rotating component stop slider disclosed in this utility model includes:

[0005] A base for fixing to rotating parts;

[0006] The base has upright stop pawls on both sides. The inner side of each stop pawl has a sliding groove that matches the outer flange of the airborne guide rail. The upper connecting surface between the two sliding grooves and the lower surface of the guide rail are in a gap with zero contact between them.

[0007] Preferably, the present invention is C-shaped and has a symmetrical structure.

[0008] Optionally, the base has a threaded hole and is fixed to the rotating part with screws, and the lower surface is an arc surface with the same radius as the rotating part.

[0009] Preferably, the traction part connected to the rotating component is provided with at least one limiting slider that mates with the inner flange of the guide rail. Further, the guide rail is a linear guide rail, and the symmetry plane of each limiting slider is the same as the symmetry plane of each stop slider; and / or the roughness of each sliding groove in contact with the linear guide rail and the contact surface of each limiting slider is consistent.

[0010] Optionally, the base of this utility model is fixed on the recessed connecting part between two adjacent blades of the rotating part, and the interior of the connecting part is equipped with a bearing coaxial with the traction part.

[0011] This utility model has the following beneficial effects:

[0012] Under the constraint of the stop slider, the spin-type powered aircraft is in a fixed connection with the guide rail during the pre-launch flight process, and the degree of freedom of the rotating parts is constrained. After launch, when the spin-type powered aircraft disengages from the guide rail, the stop slider disengages from the guide rail at the same time, releasing the rotational degree of freedom of the rotating parts. This allows the rotating parts to rotate freely relative to the spin-type powered aircraft, thereby increasing the stability of the spin-type powered aircraft during flight.

[0013] This invention achieves on-orbit constraint of the rotating component during flight by cooperating with the stop slider and the guide rail. It features a simple structure, high safety and reliability, and good stability. Furthermore, when the base of this invention is fixed to the recessed connection between adjacent blades of the rotating component, it does not increase the external envelope of the propulsive aircraft.

[0014] Meanwhile, the upper connecting surface between the two sliding grooves of the stop slider of this utility model has a gap with zero contact between it and the lower surface of the guide rail, which greatly reduces the contact area and frictional resistance during the derailment process, and ensures the smoothness of the spin-type powered aircraft in the process of separating from the guide rail.

[0015] The present invention will now be described in further detail with reference to the accompanying drawings. Attached Figure Description

[0016] The accompanying drawings, which form part of this application, are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention.

[0017] Figure 1 This is a schematic diagram of the connection between the stop slider and the rotating component disclosed in the embodiment of this utility model.

[0018] Figure 2 yes Figure 1 A 3D view of the stopped slider.

[0019] Figure 3 yes Figure 1 Schematic diagram of the connection between the stop slider and the guide rail section. Detailed Implementation

[0020] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered by the claims.

[0021] Example 1

[0022] This embodiment discloses a stop slider, referring to... Figures 1 to 3 The mapping relationship between each digital index and component is as follows: 1. Stop slider; 2. Rotating component; 3. Stop pawl; 4. Base; 5. Slide rail groove; 6. Guide rail; 7. Limit slider.

[0023] In this embodiment, the stop slider 1 is C-shaped and consists of stop pawls 3 on both sides, a base 4, and a slide rail groove 5. The upper surface of the base 4 is a plane with a height of 1.5mm, so that it is 8mm away from the guide rail 6 when assembled. The lower surface of the base 4 is an arc surface with the same radius as the cylindrical section of the outer surface of the rotating part 2. Several through holes are provided on the base 4, which are fixedly connected to the rotating part 2 by screws. Vertical stop pawls 3 are provided on both sides of the base 4. The slide rail groove 5 has a height of 4.6mm and the stop pawls 3 are symmetrically distributed relative to the base 4. The slide rail groove 5 is provided on the inner side of the stop pawls 3. The slide rail groove 5 is 3.7mm wide and fits tightly with the outer flange of the guide rail 6. The surface roughness of the slide rail groove 5 is the same as that of the outer flange of the guide rail 6. The upper connecting surface between the two sliding grooves 3 and the lower surface of the guide rail 6 are in zero contact with each other.

[0024] In this embodiment, the stop slider 1 is installed on the recessed connecting part between two adjacent blades of the rotating part 2, and the rotating body powered aircraft (which can be divided into two parts, the front traction part and the rear rotating part 2, for ease of description) with the rotating part 2 installed is connected to the guide rail 6. At the same time, the stop slider 1 and the guide rail 6 are connected through the slide rail groove 5.

[0025] The working principle of this embodiment is as follows: Under the constraint of the stop slider 1, the spin-type powered aircraft and the guide rail 6 are in a fixed connection state. The rotating component 2 is connected to the guide rail 6 through the stop slider 1. Since the rotating component 2 is mounted on the spin-type powered aircraft, all six degrees of freedom of the rotating component 2 are simultaneously constrained. After launch, when the spin-type powered aircraft detaches from the guide rail 6, the stop slider 1 also detaches from the guide rail 6, releasing the rotational degrees of freedom of the rotating component 2. This allows the rotating component 2 to rotate freely relative to the spin-type powered aircraft, thereby increasing the stability of the spin-type powered aircraft during flight. To ensure stability during the flight process, preferably, the guide rail 6 is a linear guide rail. The traction part of the spin-type powered aircraft is provided with at least one limiting slider 7 that cooperates with the inner flange of the guide rail. The symmetry plane of each limiting slider 7 is the same as the symmetry plane of each stop slider 1, and the roughness of each sliding groove 3 and the contact surface of each limiting slider 7 that contacts the linear guide rail is consistent.

[0026] In summary, this utility model embodiment achieves on-orbit constraint of the rotating component 2 during the take-off process through the cooperation of the stop slider 1 and the guide rail 6. The structure is simple, safe and reliable, and has good stability. It does not increase the outer envelope of the spinning-integrated powered aircraft. The take-off stop of the rotating component 2 can be achieved simply by adding the stop slider 1 to the rotating component 2 of the spinning-integrated powered aircraft.

[0027] Meanwhile, the upper connecting surface between the two sliding grooves 3 of the stop slider of this utility model and the lower surface of the guide rail are in a gap with zero contact with each other, which greatly reduces the contact area and frictional resistance during the derailment process, and ensures the smoothness of the spin-type powered aircraft in the process of separating from the guide rail 6.

[0028] The above description is merely a preferred embodiment of this utility model and is not intended to limit the utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A rotating component with a stop slider, characterized in that, include: A base for fixing to rotating parts; The base has upright stop pawls on both sides. The inner side of each stop pawl has a sliding groove that matches the outer flange of the airborne guide rail. The upper connecting surface between the two sliding grooves and the lower surface of the guide rail are in a gap with zero contact between them.

2. The rotating component stop slider according to claim 1, characterized in that, The overall shape is C-shaped and has a symmetrical structure.

3. The rotating component stop slider according to claim 1, characterized in that, The base has threaded holes and is fixed to the rotating part with screws. The lower surface is an arc surface with the same radius as the rotating part.

4. The rotating component stop slider according to any one of claims 1 to 3, characterized in that, The traction part connected to the rotating component is provided with at least one limiting slider that mates with the inner flange of the guide rail.

5. The rotating component stop slider according to claim 4, characterized in that, The guide rail is a linear guide rail, and the symmetry plane of each limit slider is the same as the symmetry plane of each stop slider.

6. The rotating component stop slider according to claim 5, characterized in that, The surface roughness of the contact surfaces of each sliding groove and each limiting slider that contacts the linear guide rail is consistent.

7. The rotating component stop slider according to claim 6, characterized in that, The base is fixed to the recessed connecting part between two adjacent blades of the rotating component, and the interior of the connecting part is equipped with a bearing coaxial with the traction part.

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