Mechanical catapult-based automatic separation device for payload parachute

Abstract

The application discloses a mechanical-ejection-based automatic parachute separation device, which comprises four parts, i.e., a trigger part, a transmission part, a random direction part and a delay separation part. The trigger part is composed of a landing frame, a connecting rod and a trigger rod; the transmission part is composed of a lever and a metal wire; the random direction part is composed of a lower turntable and an ejection tube; and the delay separation part is composed of the ejection tube, a spring, a trigger, a limiter and an ejection slider. The device adopts a non-directional ejection mechanism, can actively complete the parachute throwing in a random direction within several seconds after landing, and avoids the load of the parachute covering the ground. The parachute ejection device adopts a pure mechanical structure, has high reliability, and can complete a task in a complex electromagnetic environment. No burning, explosion, electric current or friction component is used in the whole parachute ejection device, heat generated by the device is very low, and the device is not easy to be detected in an infrared wave band. The device has a regular shape, and is rigidly connected with a load and a parachute, so that the device is convenient to store in a cabin.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of parachute separation devices, and particularly relates to an object-parachute automatic separation device based on mechanical ejection. BACKGROUND

[0002] In recent years, with the development of aviation technology, airplane air-drop operations are becoming more and more common. Whether in war or in disaster relief, air drop is widely used due to its fast transportation speed, high delivery efficiency, no need for advance road repair, no requirement for the type of goods, and relatively concealed advantages. In airplane air-drop operations, if the air-drop is a person, the jumper often needs to manually cut the parachute rope after landing, and then crawl out from under the parachute. If the air-drop is goods, personnel near the air-drop site need to go to clean up the parachute and receive the goods. In both cases, the parachute cannot be separated from the load in time, which causes inconvenience. In recent years, the popularization of intelligent air-drop robots makes the demand for automatic parachute separation more urgent. Although the existing main parachute separation lock device can achieve separation of the parachute by wind, its application is limited by weather conditions. In the absence of wind, the parachute cover covering the load will seriously hinder the movement of the equipment, and still needs manual intervention.

[0003] At present, parachute separation locks can be divided into mechanical and electronic types, and the mechanical type is further divided into lever type, friction type, spring type and pendulum type. The mechanical principle of the electronic type is similar to that of the mechanical type, but the structure is complex and inconvenient to maintain. In the mechanical type, the lever type mainly uses the displacement difference between the air-dropped object and the separation lock when landing to trigger the release device to release the parachute. The friction type and the spring type have the same principle, and both rely on the change of the parachute rope tension when landing to trigger the release device; the pendulum type relies on the angle of the parachute rope deflection when landing to trigger the release device. The above four mechanical types cannot avoid the parachute covering the air-dropped object in the absence of wind, and are prone to false triggering. SUMMARY

[0004] In order to solve the problems of the existing parachute separation lock that cannot avoid the parachute covering the air-dropped object in the absence of wind and is prone to false triggering, the present application provides a non-directional ejection parachute load separation device.

[0005] To achieve the above-mentioned purpose, the present application aims to provide a parachute ejection separation device after landing.

[0006] An object-parachute automatic separation device based on ejection, which is composed of a trigger part, a conduction part, a random direction part and a delay separation part. The landing frame, the connecting rod and the trigger rod constitute the trigger part, the lever and the double-layer flexible wire constitute the conduction part, the lower turntable and the lower end crossbar of the ejection tube constitute the random direction part, and the ejection tube, except for the lower end crossbar, its internal spring, trigger, stopper and ejection slider constitute the delay separation part.

[0007] The trigger part, the landing frame is horizontally placed at the bottom of the container with the airborne object, and is connected with the container with the airborne object through four connecting rods. The trigger rod is vertically placed at the side of the container with the airborne object, and can slide in the groove on the container with the airborne object. When the landing frame touches the ground, the connecting rod between the landing frame and the bottom of the container with the airborne object will rotate from the nearly vertical state to the horizontal direction due to the instability of the parallelogram structure. The bottom landing frame moves upward relative to the bottom of the container with the airborne object, and contacts the upper trigger rod to push it to slide upward.

[0008] The conducting part, the lever is horizontally fixed on the container with the airborne object, and can rotate within a certain angle. One end of the lever is in contact with the trigger rod, and the other end is connected with the metal wire in the double-layer flexible wire. The double-layer flexible wire is similar to the brake wire of a bicycle. The outer layer is a soft tube made of rubber and metal, which can change shape at will, but the length cannot be compressed or stretched. The inner part is a metal wire. The feature of the double-layer flexible wire is that even if the wire is not straight from the appearance, the internal part can still transmit tension. One end of the metal wire is connected with the lever, and the other end is connected with the stopper to transmit the tension of the lever. The outer layer tube is sleeved on the metal wire, but one end is fixed with the container with the airborne object, and the other end is fixed with the launching tube. When one end of the lever is lifted by the trigger rod, the other end can pull down the metal wire.

[0009] The random direction part, the lower turntable and the lower end cross rod of the launching tube constitute a universal shaft structure, which can make the launching tube tilt in any direction. The connection between the lower turntable and the container with the airborne object provides horizontal rotation freedom, and the connection between the lower turntable and the launching tube provides vertical rotation freedom. After the container with the airborne object lands, if there is no wind, the center of gravity of the entire launching tube is not on the axis because the weight part exists on the launching tube, but the mass distribution of the trigger, stopper, spring and launching slider inside the launching tube is symmetrical relative to the axis of the launching tube. The gravity of the launching tube itself will make it fall to the weight side.

[0010] The delay separation part, after the stopper is pulled down by the metal wire, the trigger can rotate freely. The pre-compressed spring inside the launching tube pushes up the launching slider, and the trigger rotates by chance to release the launching slider. The launching tube is air-tight except the large and small air holes and the opening at the upper end. During the upward movement of the launching slider, air can enter the part below the launching slider inside the launching tube through the small air hole at the bottom of the launching tube. The aperture of the small air hole limits the flow rate of air entering the part below the launching slider inside the launching tube, thereby limiting the upward movement speed of the launching slider along the launching tube, and realizing the delay function. After the launching slider moves through the large air hole, air can flow in from the large air hole. The flow rate of air entering the part below the launching slider inside the launching tube is no longer limited, and the launching slider can be accelerated to pop up upward.

[0011] Compared with the prior art, the present application has the following advantages:

[0012] 1. Avoiding parachute covering airborne object: the present application combines time delay and random direction tilting mechanism to achieve the purpose of avoiding parachute covering airborne object. The present application uses aerodynamic principle to achieve time delay release of spring force; the tilting mechanism uses the time of time delay release of parachute to tilt the launching tube, so that the parachute separates obliquely;

[0013] 2. High reliability: the present application designs the trigger part as a frame shape at the bottom of the airborne object, and together with the safety device, the reliability of the present application is improved. Moving the trigger part to the bottom can directly sense the signal of the airborne object landing, and it is not easy to trigger by mistake. The frame structure of the landing frame is relatively point or line shape, and the trigger range is wider, which can trigger the subsequent mechanism in more terrains and ground materials;

[0014] 3. Pure mechanical structure: the present application uses pure mechanical structure to achieve the function of time delay and non-directional launching, without the need of electricity, with strong battlefield response ability, and can be used at any time; the mechanical parts are relatively simple to maintain compared with electronic or chemical elements, with long service life; without the use of pyrotechnics, it is not easy to be found in infrared band, with high concealment. BRIEF DESCRIPTION OF DRAWINGS

[0015] Figure 1 Figure 1 is a structural schematic diagram of the airborne parachute automatic separation device based on mechanical launching of the present application.

[0016] Figure 2 Figure 2 is a front view of the airborne parachute automatic separation device based on mechanical launching of the present application.

[0017] Figure 3 Figure 3 is a sectional view of the random direction and time delay separation part in the present application. Figure 1

[0018] The figure number is explained as follows:

[0019] 1-Container equipped with airborne object, 2-Landing frame, 3-Connecting rod, 4-Safety catch, 5-Trigger lever, 6-Lever,

[0020] 7-Launching tube, 8-Lower turntable, 9-Large air hole, 10-Parachute, 11-Parachute cord, 12-Launching slider, 13-Trigger, 14-Limiting device, 15-Small air hole, 16-Spring (pre-compression), 17-Dual-layer flexible wire, 18-Counterweight. DETAILED DESCRIPTION

[0021] The technical solutions in the patent embodiment of the present application will be clearly and completely described below in combination with the drawings in the patent embodiment of the present application. Obviously, the described embodiments are not a limitation on the present application. ​

[0022] As Figure 1 , Figure 2 shown, a mechanical ejection-based parachute automatic separation device includes a trigger part, a transmission part, a random direction part, and a delay separation part; the trigger part is composed of a landing frame 2, connecting rods 3, and a trigger lever 5; the transmission part is composed of a lever 6 and a double-layer flexible wire 17; the random direction part is composed of an ejection tube 7, a lower turntable 8, and a counterweight 18 on the ejection tube 7; the delay separation part is composed of the ejection tube 7, an ejection slider 12, a trigger 13, a limiter 14, a spring 16, and large and small air holes 9 and 15 on the ejection tube. The landing frame 2 is connected to a container 1 containing airdropped objects through four connecting rods 3, and the connection part can rotate freely; the trigger lever 5 can slide up and down in a sliding groove outside the container 1 containing airdropped objects; a safety catch 4 is obliquely inserted through the trigger lever 5 and the sliding groove outside the container 1 containing airdropped objects; one end of the lever 6 is in contact with the upper end of the trigger lever 5. The device is generally described as follows: after the safety catch 4 is pulled out, when the landing frame 2 lands, the container 1 containing airdropped objects continues to move downward, due to the instability of the parallelogram, the connecting rod 3 rotates, the distance between the landing frame 2 and the container 1 containing airdropped objects decreases, the landing frame 2 contacts the lower end of the trigger lever 5, which makes the trigger lever 5 slide upward, and the trigger lever 5 lifts the left end of the lever 6.

[0023] As Figure 3As shown, the left end of the lever 6 is lifted and the right end is lowered, and the limit stop 14 is pulled down by the double-layer flexible wire 17 to release the limit of the lower end of the trigger 13; the ejection slide 12 moves upward under the action of the pre-compressed spring 16, and the trigger 13 rotates by inertia to release the ejection slide 12; the ejection tube 7 has good air tightness, and only a small air hole 15 at the lower end is connected with the atmosphere, which limits the flow rate of air entering the ejection tube from the lower end; due to air pressure, the ejection slide 12 can only move slowly upward; when the ejection slide 12 passes through the large air hole 9, the large air hole 9 connects the air inside and outside the ejection tube 7, and air quickly flows into the ejection tube 7 to make the air pressure inside and outside the ejection tube 7 the same, and the ejection slide 12 is accelerated to pop out in the direction of the ejection tube 7 under the action of the pre-compressed spring 16. In windy weather, before the ejection slide 12 moves to the large air hole 9, the parachute 10 moves downward in the downwind direction under the action of wind force, and the ejection tube 7 is pulled downward in the downwind direction by the parachute rope 11; after the ejection slide 12 is ejected, it is separated from the device main body along with the parachute 10. In the windless weather, because the counterweight 18 exists on the ejection tube 7, but the mass distribution of the rest is uniform, the center of gravity of the ejection tube 7 is not on the axis, and the gravity of the ejection tube 7 itself will make it fall to the side of the counterweight 18; at the same time, the delay release part is triggered; after the ejection slide 12 slides through the large air hole 9 and is accelerated to pop out, it hits the parachute 10 from below along a parabolic trajectory, changes the shape of the parachute 10, reduces the windward area and the air resistance, and the ejection slide 12 can take the parachute along a parabolic trajectory to a certain place beside the container 1 containing the airborne object.

[0024] The above is only an embodiment of the present application, and is not a limitation on the protection scope of the present application. Any equivalent structural transformation or direct or indirect application in other related technical fields based on the content of the specification and drawings of the present application is included in the protection scope of the present application.

Claims

1. A mechanical catapult-based payload parachute automatic separation device, characterized by: It is composed of trigger part, conduction part, random direction part and delay separation part; the landing frame, connecting rod and trigger lever constitute the trigger part, the lever and double-layer flexible line constitute the conduction part, the lower turntable and the lower end crossbar of the ejector tube constitute the random direction part, and the rest of the ejector tube except the lower end crossbar and the spring, trigger, limiter and ejector slider inside the tube constitute the delay separation part; In the trigger part, the landing frame is horizontally placed at the bottom of the container with airborne objects, connected with the container with airborne objects through four connecting rods, and the trigger lever is vertically placed at the side of the container with airborne objects, sliding in the groove on the container with airborne objects; In the conduction part, the lever is horizontally fixed on the container with airborne objects, with one end contacting the trigger lever and the other end connected with the metal wire inside the double-layer flexible line; the outer layer of the double-layer flexible line is a soft tube made of rubber and metal, which can change shape arbitrarily but cannot be compressed or stretched in length; the inner part is a metal wire; In the random direction part, the lower turntable and the lower end crossbar of the ejector tube constitute a universal shaft structure, allowing the ejector tube to tilt in any direction; the connection between the lower turntable and the container with airborne objects provides horizontal rotation freedom, and the connection between the lower turntable and the ejector tube provides vertical rotation freedom; In the delay separation part, after the limiter is pulled down by the metal wire, the trigger is free to rotate, the pre-compressed spring inside the ejector tube pushes up the ejector slider, and the trigger rotates naturally, releasing the ejector slider.

2. A mechanical ejection based payload parachute automatic separation device according to claim 1, characterized in that: When the lower landing frame touches the ground, due to the instability of the parallelogram structure, the connecting rod between the landing frame and the bottom of the container with airborne objects will rotate from a nearly vertical state to a horizontal state, and the bottom landing frame will move upwards relative to the bottom of the container with airborne objects, contacting the upper trigger lever and pushing it upwards.

3. The mechanical catapult based payload parachute automatic separation device according to claim 1, wherein: The double-layer flexible line appears to be not straight from the outside, but the internal part still transmits tension; one end of the metal wire is connected with the lever, and the other end is connected with the limiter, transmitting the tension of the lever; although the outer layer of the soft tube is wrapped around the metal wire, one end is fixed to the container with airborne objects, and the other end is fixed to the ejector tube; after one end of the lever is lifted by the trigger lever, the other end pulls down the metal wire.

4. The mechanical catapult based payload parachute automatic separation device according to claim 1, wherein: After the container with airborne objects lands, if there is no wind, due to the existence of the counterweight part on the ejector tube, but the mass distribution of the trigger, limiter, spring and ejector slider inside the ejector tube is symmetrical relative to the axis of the ejector tube, so the center of gravity of the entire ejector tube is not on the axis, and the gravity of the ejector tube itself will make it fall to the side of the counterweight.

5. The mechanical catapult based payload parachute automatic separation device according to claim 1, wherein: During the upward movement of the ejector slider, air enters the lower end of the ejector slider inside the ejector tube through the small air hole at the bottom of the ejector tube; the diameter of the small air hole limits the flow rate of air entering the lower end of the ejector slider inside the ejector tube, thereby limiting the upward movement speed of the ejector slider along the ejector tube, and thus realizing the delay function.

6. A mechanical ejection based payload parachute automatic separation device according to claim 5, characterized in that: After the ejector slider moves through the large air hole, air flows in from the large air hole, and the flow rate of air entering the lower end of the ejector slider inside the ejector tube is no longer limited, and the ejector slider is accelerated upward.

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