Aircraft guide rail type composite launching device

Abstract

The utility model relates to the technical field of aircraft launching, in particular to a guide rail type composite launching device for an aircraft. Comprising a roller guide rail sliding block, a first standard sliding block, a second standard sliding block and a sliding guide rail, the roller guide rail sliding block, the first standard sliding block and the second standard sliding block are sequentially and fixedly connected with an aircraft, and the roller guide rail sliding block is in linear contact with the guide rail and can share the total missile weight borne by the standard sliding block; the multiple faces of the standard sliding block make contact with the guide rail, so that the aircraft can only keep linear sliding acceleration along the guide rail, and it is guaranteed that the aircraft directionally and stably slides on the guide rail in a linear mode. The first standard sliding block and the second standard sliding block are located on the two sides of the gravity center of the aircraft. The roller guide rail sliding block is formed by combining a supporting frame and six rollers, the supporting frame is in an I shape, the middle axial face of the supporting frame serves as the symmetry plane, and the two rows of rollers are distributed at the two ends. According to the utility model, not only are the structure and the installation process simplified, but also the reliability and the safety are enhanced.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft launch, in particular to an aircraft guide rail type composite launch device. Background Art

[0002] Currently, most missiles, small drones, and other aircraft use rail-based launch systems. Two or three identical slider-assisted devices are installed on the aircraft, interlocking with the launcher's rails. This allows the aircraft to accelerate steadily by sliding along the rails, leaving the orbit at a predetermined speed and angle, and ensuring stable flight after leaving the orbit. Compared to the launcher proposed in this article, traditional rail-based launchers are more complex and heavier, often secured to the aircraft via welding or multiple screws.

[0003] When the aircraft is relatively long, if the rail-type launch device contains only two sliders, on the one hand, it will affect the aircraft's deorbit speed; on the other hand, after the aircraft leaves orbit, the center of gravity will move forward, causing the "head-down" torque to increase, resulting in excessive changes in the aircraft's attitude angle after leaving orbit, which will affect its flight stability after leaving orbit.

[0004] The disadvantages of the rail-type launcher in the existing technical solution are as follows: the slider in the launcher itself is heavy and has a complex structure; there are many mating surfaces between the slider and the guide rail in the launcher, which can easily affect the aircraft's deorbit speed; the large size of the slider in the launcher itself also increases aerodynamic resistance, especially during supersonic flight, where the shock wave resistance generated by the slider is very large. Summary of the Invention

[0005] In response to the above-mentioned shortcomings of the existing rail-type launch device, this paper proposes an aircraft rail-type composite launch device to solve the problems of the existing launch device such as its own weight, complex structure, and large aerodynamic resistance.

[0006] In order to solve the above technical problems, one of the purposes of the present utility model is to provide an aircraft guide rail composite launch device, including a roller guide rail slider 1, a standard slider 1 2, a standard slider 2 3 and a sliding guide rail 5. The roller guide rail slider 1, the standard slider 1 2 and the standard slider 2 3 are fixedly connected to the aircraft 4 in sequence, and the roller guide rail slider 1 and the guide rail 5 are in line contact, which can share the full weight of the bullet borne by the standard slider 1 2 and the standard slider 2 3.

[0007] When the aircraft 4 is launched, multiple surfaces of the standard slider 1 2 and the standard slider 2 3 contact the guide rail 5, which is sufficient to ensure that the aircraft 4 can only maintain straight sliding acceleration along the guide rail, ensuring that the aircraft 4 is oriented and stably sliding in a straight line on the guide rail 5.

[0008] Furthermore, the roller guide slider 1, standard slider 1 2 and standard slider 2 3 are fixedly connected to the aircraft 4 by threaded connection, slot connection or traditional welding.

[0009] Furthermore, the standard slider 1 2 and the standard slider 2 3 are located on both sides of the center of gravity of the aircraft 4 .

[0010] Furthermore, the distance between the standard slider 1 2 and the standard slider 2 3 can be extremely small, thereby increasing the derailment speed of the aircraft 4 after the straight-line sliding on the guide rail 5, and reducing the "head-down" torque caused by the center of gravity after the aircraft derails, thereby greatly reducing the attitude angle change of the aircraft 4 after derailment.

[0011] Furthermore, the roller guide rail slider 1 is composed of a support frame and 4 or more even number rollers. The support frame is I-shaped, with the central axis of the support frame as the symmetry plane, and two rows of rollers are distributed at both ends.

[0012] Furthermore, lubricating oil is used between the roller and the support frame.

[0013] Furthermore, the roller guide rail slider 1 is composed of a support frame and 6 rollers, and is matched with the guide rail in the form of rollers, thereby achieving line contact, reducing the matching area, and greatly reducing friction resistance.

[0014] Furthermore, the roller guide rail slider 1 adopts a modular design, which is convenient for installation, disassembly, and maintenance.

[0015] The above one or more technical solutions of the present invention have at least one or more of the following technical effects:

[0016] The roller guide rail slider in the guide rail composite launcher provided by the utility model has the characteristics of small size, light weight, simple structure and easy installation;

[0017] The guide rail composite launch device provided by the utility model has a smaller mating surface between the roller guide rail slider and the guide rail, which has been proven to have almost no effect on the derailment speed of the aircraft.

[0018] The roller guide rail slider in the guide rail type composite launching device provided by the utility model is beneficial to reducing the self-weight, aerodynamic resistance and structural design difficulty of the aircraft.

[0019] The utility model proposes a small and simplified rail-type composite launching device, which replaces the launching device in the existing technical solution, not only simplifying its structure and installation process, but also enhancing its reliability and safety. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 : Schematic diagram of the combination of aircraft and slider;

[0021] Figure 2 : Schematic diagram of the aircraft, slider and guide rail combination;

[0022] Figure 3 : Schematic diagram of the roller guide slider structure;

[0023] Figure 4 : Schematic diagram of a standard slider;

[0024] Figure 5 : Schematic diagram of roller guide slider;

[0025] Among them: 1-roller guide slider, 2-standard slider one, 3-standard slider two, 4-aircraft, 5-sliding guide rail. Specific implementation plan

[0026] The utility model proposes a small and simplified aircraft rail-type composite launching device, which replaces the launching device in the existing technical solution, not only simplifying its structure and installation process, but also enhancing its reliability and safety.

[0027] A composite aircraft rail launch device consisting of a roller guide slider 1, a standard slider 1 2, a standard slider 2 3, etc., is used for orbital launch of aircraft; the roller guide slider is used in combination with multiple standard sliders to optimize their overall matching performance; the connection structure between the roller guide slider 1 and the aircraft 4 includes connection methods such as threaded connection, slot connection, welding, bonding and riveting; the material of the roller guide slider 1 includes steel, aluminum alloy, titanium alloy, carbon fiber and ceramic.

[0028] The following is a clear and complete description of the technical solutions in the embodiments of the present invention in conjunction with the embodiments and drawings of the present invention. Obviously, the embodiments described are only part of the embodiments of the present invention, rather than all the embodiments obtained. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field are within the scope of protection of the present invention.

[0029] like Figure 1 and Figure 2 As shown, the aircraft guide rail type composite launching device proposed in the present invention includes a roller guide rail slider 1, a standard slider 1 2 and a standard slider 2 3 and a sliding guide rail 5.

[0030] The roller guide slider 1, standard slider 1 2, and standard slider 2 3 can be fixedly connected to the aircraft 4 by threaded connection, slot connection, or traditional welding, thus achieving a variety of connection methods. Both threaded connection and slot connection will not damage the main structure of the aircraft.

[0031] Secondly, when the aircraft 4 is launched, multiple surfaces of the standard slider 1 2 and the standard slider 2 3 contact the guide rail 5, which is sufficient to ensure that the aircraft 4 can only maintain straight sliding acceleration along the guide rail, ensuring that the aircraft 4 is oriented and stably sliding in a straight line on the guide rail 5.

[0032] Furthermore, roller guide block 1 achieves line contact with guide rail 5, sharing the full weight of the missile borne by standard block 1 2 and standard block 2 3. Standard block 1 2 and standard block 2 3 are located on either side of the center of gravity of aircraft 4, but the distance between them can be smaller, thereby increasing the speed at which aircraft 4 derails after a straight glide on guide rail 5. This also reduces the "head-down" moment caused by the center of gravity after derailment, thereby significantly reducing the change in the aircraft's attitude angle after derailment. Figure 3 、 Figure 4 Shown is a comparison of details of a roller guide runner block and a standard runner block.

[0033] like Figure 5 As shown, the roller guide block 1 is composed of a support frame and 6 identical rollers. The support frame is an I-shaped frame with the support frame mid-axis surface as the symmetrical surface, and two rows of rollers are distributed at both ends, with 3 rollers in each row. Lubricating oil is used between the rollers and the support frame. The roller guide block 1 adopts a modular design, which is convenient for installation, disassembly, and maintenance. At the same time, the roller form is adopted to cooperate with the guide rail to achieve line contact, reduce the matching area, and greatly reduce frictional resistance. Thereby ensuring the smooth derailment of the aircraft, it is conducive to improving the derailment speed of the aircraft.

[0034] To sum up, compared with previous similar rail-type launch devices, the utility model provides a compact, structurally simplified rail-type composite launch device to achieve the smooth off-orbit launch of the aircraft. It not only simplifies the structure of the rail-type launch device, but also optimizes its functions, which is more conducive to the off-orbit launch of the aircraft, and also enhances its versatility and practicality.

[0035] This utility model adjusts the relative positions of the roller guide blocks and standard blocks in a rail-type composite launcher to accommodate variations in the launcher. By adjusting the number of roller guide blocks and standard blocks in the rail-type composite launcher and replacing standard blocks with non-standard blocks, this simplifies the manufacturing process and increases its versatility. By securing the roller guide blocks and standard blocks in the rail-type composite launcher to the top, side, or other locations of the aircraft, this utility model adapts the launcher to operate in various environments.

[0036] Obviously, those skilled in the art may make various changes and modifications to the embodiments of the present invention without departing from the spirit and scope of the embodiments of the present invention. Thus, if such modifications and variations of the embodiments of the present invention fall within the scope of the claims of the present invention and their equivalents, the present invention is intended to include such modifications and variations.

Claims

1. An aircraft rail-type composite launcher, characterized in that: The invention comprises a roller guide rail slider (1), a standard slider 1 (2), a standard slider 2 (3) and a sliding guide rail (5), wherein the roller guide rail slider (1), the standard slider 1 (2) and the standard slider 2 (3) are fixedly connected to the aircraft (4) in sequence, and the roller guide rail slider (1) and the guide rail (5) are in line contact, and can share the full weight of the projectile borne by the standard slider 1 (2) and the standard slider 2 (3). When the aircraft (4) is launched, multiple surfaces of the standard slider 1 (2) and the standard slider 2 (3) are in contact with the guide rail (5), which is sufficient to enable the aircraft (4) to maintain linear sliding acceleration only along the guide rail, thereby ensuring that the aircraft (4) slides in a directional and stable linear manner on the guide rail (5).

2. The aircraft rail-type composite launcher according to claim 1, characterized in that: The roller guide rail slider (1), standard slider one (2) and standard slider two (3) are fixedly connected to the aircraft (4) by threaded connection, slot connection or traditional welding.

3. The aircraft rail-type composite launcher according to claim 1, characterized in that: The standard slider 1 (2) and the standard slider 2 (3) are located on both sides of the center of gravity of the aircraft (4).

4. The aircraft rail-type composite launcher according to claim 3, characterized in that: The distance between the first standard slider (2) and the second standard slider (3) can be extremely small, thereby increasing the derailment speed of the aircraft (4) after the straight-line sliding on the guide rail (5) is completed, and also reducing the "head-down" moment caused by the center of gravity after the aircraft derails, thereby greatly reducing the attitude angle change of the aircraft (4) after derailing.

5. The aircraft rail-type composite launcher according to claim 1, characterized in that: The roller guide rail slider (1) is composed of a support frame and 4 or more rollers in an even number. The support frame is I-shaped, with the central axis of the support frame as the symmetry plane, and two rows of rollers are distributed at both ends.

6. The aircraft rail-type composite launcher according to claim 5, characterized in that: Lubricating oil is used between the roller and the support frame.

7. The aircraft rail-type composite launcher according to claim 5, characterized in that: The roller guide rail slider (1) is composed of a support frame and six rollers, and is matched with the guide rail in the form of rollers, thereby achieving line contact, reducing the matching area, and greatly reducing friction resistance.

8. The aircraft rail-type composite launcher according to any one of claims 5 to 7, characterized in that: The roller guide rail slider (1) adopts a modular design, which is convenient for installation, disassembly, and maintenance.

9. The aircraft rail-type composite launcher according to claim 1, characterized in that: The roller guide rail slider (1) is made of steel, aluminum alloy, titanium alloy, carbon fiber or ceramic.

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