Device and method for improving the reliability of opening of a rescue parachute of an ejection seat

Abstract

The application relates to a device and method for improving the opening reliability of a rescue parachute of an ejection seat, and relates to the field of air dropping. The device for improving the opening reliability of the rescue parachute of the ejection seat comprises a rescue parachute box and a deceleration parachute box which are installed on the ejection seat and are connected with each other, the deceleration parachute box is configured to be separable from the rescue parachute box, the rescue parachute box is internally provided with a rescue parachute, the deceleration parachute box is internally provided with a connecting belt, a deceleration parachute and a constant force breaking rope, one end of the connecting belt is connected with a parachute rope of the deceleration parachute, the other end of the connecting belt is connected with the top of the rescue parachute box, one end of the constant force breaking rope is connected with the top of a canopy of the deceleration parachute, the other end of the constant force breaking rope is connected with the top of the deceleration parachute box. The device and method for improving the opening reliability of the rescue parachute of the ejection seat solve the bending phenomenon of the parachute rope and the canopy during the high-speed ejection of the ejection seat, avoid the problems of early inflation of the rescue parachute, serious damage and local parachute turning, avoid the safety hazards caused by the interference after the separation of the parachute box and the rescue parachute, and improve the high-speed working reliability of the rescue parachute matched with the ejection seat.

Description

Technical Field

[0001] This application relates to the field of airdrops, and more specifically, to a device and method for improving the reliability of ejection seat parachute deployment. Background Technology

[0002] With the rapid development of aircraft performance, the characteristics of high-speed and high-maneuverability aircraft place increasingly higher demands on ejection escape systems, and also expand the application scope of the life-saving parachutes used in conjunction with rocket ejection seats. Currently, to reduce delay time and improve escape performance under adverse attitude conditions, both domestic and international rocket ejection seats adopt a parachute box-opening method. This means that the life-saving parachute is loaded into the ejection seat's parachute box according to a prescribed method. In emergency ejection, the ejection seat is launched from the parachute box using pyrotechnic power, thereby pulling the life-saving parachute out of the box and inflating it fully under aerodynamic force, carrying the pilot down for a stable descent.

[0003] When the ejection seat uses the parachute box deployment method, because the parachute box (including the life-saving parachute) has a certain mass, it will continue to move forward due to inertia after being launched. Meanwhile, the gradually pulled-out parachute lines will move forward at a speed significantly lower than the speed of the ejection seat and parachute box due to airflow, causing them to gradually bend. This leads to abnormalities in the life-saving parachute's operation, resulting in problems such as premature inflation, severe damage, and partial parachute flipping. At the same time, after the parachute box separates from the life-saving parachute, it will continue to move forward due to inertia, which may cause the parachute box to catch up with the life-saving parachute and interfere with it, reducing the high-speed operational reliability of the life-saving parachute associated with the ejection seat. Summary of the Invention

[0004] The purpose of this application is to provide a device and method for improving the reliability of the deployment of the ejection seat parachute. It solves the problem of the parachute rope and canopy bending during the high-speed ejection process of the ejection seat, avoids problems such as premature inflation of the parachute, severe damage, and partial parachute flipping, avoids the safety hazards caused by interference after the parachute box and the parachute are separated, and improves the high-speed working reliability of the ejection seat-equipped parachute.

[0005] This application is implemented as follows:

[0006] This application provides a device for improving the reliability of ejection seat parachute deployment. It includes a parachute box and a deceleration parachute box installed on the ejection seat and connected to each other. The deceleration parachute box is configured to be detachable from the parachute box. The parachute box contains a parachute. The deceleration parachute box contains a connecting belt, a deceleration parachute, and a constant-force break rope. One end of the connecting belt is connected to the parachute rope of the deceleration parachute, and the other end is connected to the top of the parachute box. One end of the constant-force break rope is connected to the top of the parachute canopy of the deceleration parachute, and the other end is connected to the top of the deceleration parachute box.

[0007] In some alternative implementations, the life-saving parachute box and the deceleration parachute box are connected by a spring or an explosive bolt, which is used to separate the deceleration parachute box from the life-saving parachute box before ejection.

[0008] In some alternative implementations, the tension in the connection between the connecting belt and the deceleration chute exceeds the breaking strength of the rope under constant force.

[0009] This application also provides a method for improving the reliability of ejection seat parachute deployment, which is implemented using the aforementioned device for improving ejection seat parachute deployment reliability, and includes the following steps:

[0010] When the aircraft is flying below a preset speed and ejects the ejection seat, the combustion and explosion mechanism is used to launch the detachably connected parachute box and deceleration parachute box, and pull the parachute out of the parachute box, straighten it, inflate it and fully open it;

[0011] When the aircraft flies above a preset speed and ejects the ejection seat, the life-saving parachute box and the deceleration parachute box are separated and the deceleration parachute box is launched. The connecting belt stretches the deceleration parachute and the constant-force break rope in sequence until the tension on the constant-force break rope exceeds the breaking strength and breaks. The connecting belt pulls the deceleration parachute out of the deceleration parachute box and opens it. The deceleration parachute generates aerodynamic drag in the airflow and acts on the life-saving parachute box. Then, the combustion and explosion mechanism launches the life-saving parachute box, which is pulled by the deceleration parachute and its speed is reduced. The life-saving parachute is then pulled out of the life-saving parachute box, straightened, inflated and fully opened.

[0012] The beneficial effects of this application are as follows: The device for improving the reliability of ejection seat parachute deployment provided by this application includes a parachute box and a deceleration parachute box installed on and connected to the ejection seat. The deceleration parachute box is configured to be detachable from the parachute box. The parachute box contains a parachute, while the deceleration parachute box contains a connecting strap, a deceleration parachute, and a constant-force break rope. One end of the connecting strap is connected to the parachute lines, and the other end is connected to the top of the parachute box. One end of the constant-force break rope is connected to the top of the deceleration parachute canopy, and the other end is connected to the top of the deceleration parachute box. The device and method for improving the reliability of ejection seat parachute deployment provided by this application solves the problem of parachute lines and canopy bending during high-speed ejection, avoiding problems such as premature parachute inflation, severe damage, and partial parachute folding. It ensures that the pilot can orderly pull out, straighten, inflate, and fully deploy the parachute lines, while also avoiding safety hazards caused by interference between the parachute box and the parachute due to inertia after the parachute box separates from the parachute. This effectively improves the high-speed operational reliability of the ejection seat-equipped parachute. Attached Figure Description

[0013] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0014] Figure 1 A schematic diagram of the structure of the device for improving the reliability of the ejection seat parachute deployment provided in this application embodiment, installed on an aircraft during the first state of ejection of the ejection seat;

[0015] Figure 2 A schematic diagram of the structure of the device for improving the reliability of ejection seat parachute deployment provided in this application embodiment, installed on an aircraft during the second state of ejection of the ejection seat;

[0016] Figure 3 A schematic diagram of the structure of the device for improving the reliability of the ejection seat parachute deployment provided in this application embodiment, installed on an aircraft during the third state of ejection of the ejection seat;

[0017] Figure 4 A schematic diagram of the device for improving the reliability of ejection seat parachute deployment provided in this application embodiment;

[0018] Figure 5 This is a schematic diagram of the parachute box and the parachute when separated in the device for improving the reliability of the ejection seat parachute deployment provided in this application embodiment.

[0019] In the diagram: 100, parachute box; 110, parachute; 200, deceleration parachute box; 210, connecting belt; 220, deceleration parachute; 230, tension break rope; 240, explosive bolt; 300, ejection seat; 400, aircraft. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, and not all embodiments. The components of the embodiments of this application described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0021] Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

[0022] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0023] In the description of this application, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the product of this application is in use. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation on this application. In addition, the terms "first," "second," and "third," etc., are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0024] Furthermore, terms such as "horizontal," "vertical," and "sag" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal relative to "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0025] In the description of this application, it should also be noted that, unless otherwise expressly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this application based on the specific circumstances.

[0026] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly below or diagonally below the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0027] The features and performance of the device for improving the reliability of ejection seat parachute deployment according to this application will be further described in detail below with reference to embodiments.

[0028] like Figure 1, Figure 2 , Figure 3 , Figure 4 and Figure 5 As shown, this application provides a device for improving the reliability of ejection seat parachute deployment. It includes a parachute box 100 and a deceleration parachute box 200 installed on the ejection seat 300 of an aircraft 400. The parachute box 100 and the deceleration parachute box 200 are connected by four explosive bolts 240, which are used to separate the deceleration parachute box 200 from the parachute box 100 and then eject it. The parachute box 100 contains a parachute 110, and the deceleration parachute box 200 contains a connecting strap 210, a deceleration parachute 220, and a constant-force breakage rope 230. One end of the connecting strap 210 is connected to the parachute lines of the deceleration parachute 220, and the other end is connected to the top of the parachute box 100. One end of the constant-force breakage rope 230 is connected to the top of the canopy of the deceleration parachute 220, and the other end is connected to the top of the deceleration parachute box 200. The connecting tension between the connecting strap 210 and the deceleration parachute 220 exceeds the breaking strength of the constant-force breakage rope 230.

[0029] This application also provides a method for improving the reliability of ejection seat parachute deployment, which is implemented using the aforementioned device for improving ejection seat parachute deployment reliability, and includes the following steps:

[0030] When the aircraft 400 is flying below the preset speed and ejects the ejection seat, the pyrotechnic mechanism is used to launch the detachably connected parachute box 100 and deceleration parachute box 200, and pulls the parachute 110 out of the parachute box 100, straightens it, inflates it and fully opens it.

[0031] When the aircraft 400 flies at a preset speed and ejects from the ejection seat, the parachute box 100 and the deceleration parachute box 200 are separated and the deceleration parachute box 200 is launched. The connecting belt 210 sequentially stretches the deceleration parachute 220 and the constant force breaking rope 230 until the tension on the constant force breaking rope 230 exceeds its breaking strength and breaks. The connecting belt 210 pulls the deceleration parachute 220 out of the deceleration parachute box 200 and opens it. The deceleration parachute 220 generates aerodynamic drag in the airflow and acts on the parachute box 100. Then, the pyrotechnic mechanism launches the parachute box 100, which is pulled by the deceleration parachute 220 and its speed is reduced. The parachute 110 is then pulled out of the parachute box 100, straightened, inflated, and fully opened.

[0032] The device and method for improving the reliability of ejection seat parachute deployment provided in this application divides the traditional seat parachute box into two independent parachute boxes 100 and a deceleration parachute box 200, and connects the parachute box 100 and the deceleration parachute box 200 into a whole through a separation mechanism. In addition to the parachute 110 being installed in the parachute box 100, a deceleration parachute 220, a connecting strap 210, and a constant-force breakage rope 230 are added to the deceleration parachute box 200. Thus, when the ejection seat 300 is ejected at high speed, the separation mechanism connects the deceleration parachute box 200 with the parachute box. After separation from the ejection seat, the parachute 220 is pre-launched and the deceleration rope 230 is broken. The deceleration parachute 220 is then used to decelerate the parachute, and the connecting strap 210 is used to stretch and open the parachute 110 inside the parachute box 100. This avoids the bending of the parachute rope and canopy caused by the parachute box mode during high-speed ejection, ensuring that the pilot can pull out, straighten, inflate, and fully open the parachute rope in an orderly manner. On the other hand, it also avoids the safety hazard caused by the parachute box continuing to move forward due to inertia after separation from the parachute, thus effectively improving the high-speed working reliability of the ejection seat and the parachute.

[0033] The embodiments described above are some, but not all, of the embodiments of this application. The detailed description of the embodiments of this application is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

Claims

1. A method for improving the reliability of ejection seat parachute deployment, characterized in that, It is achieved using a device to improve the reliability of the ejection seat parachute deployment. The device includes a parachute box and a deceleration parachute box installed on the ejection seat and connected to each other. The deceleration parachute box is configured to be detachable from the parachute box. The parachute box contains a parachute. The deceleration parachute box contains a connecting strap, a deceleration parachute, and a constant-force break rope. One end of the connecting strap is connected to the parachute rope of the deceleration parachute, and the other end is connected to the top of the parachute box. One end of the constant-force break rope is connected to the top of the parachute canopy of the deceleration parachute, and the other end is connected to the top of the deceleration parachute box. The parachute box and the deceleration parachute box are connected by a spring or an explosive bolt. The spring or the explosive bolt is used to separate the deceleration parachute box from the parachute box before ejection. The methods to improve the reliability of ejection seat parachute deployment include the following steps: When the aircraft is flying below a preset speed and ejects the ejection seat, the combustion and explosion mechanism is used to launch the detachably connected parachute box and deceleration parachute box, and pull the parachute out of the parachute box, straighten it, inflate it and fully open it; When the aircraft flies above a preset speed and ejects the ejection seat, the parachute box and the deceleration parachute box are separated, and the deceleration parachute box is launched. The connecting belt stretches the deceleration parachute and the constant-force break rope in sequence until the tension on the constant-force break rope exceeds its breaking strength and breaks. The connecting belt pulls the deceleration parachute out of the deceleration parachute box and opens it. The deceleration parachute generates aerodynamic drag in the airflow and acts on the parachute box. Then, the ignition mechanism launches the parachute box, reducing the speed of the parachute box under the pull of the deceleration parachute. The parachute is then pulled out of the parachute box, straightened, inflated, and fully opened.

2. The method for improving the reliability of ejection seat parachute deployment according to claim 1, characterized in that, The tensile force between the connecting belt and the deceleration chute exceeds the breaking strength of the constant-force rope.

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