Electromagnetic separation mechanism for aircraft and parachute

Abstract

The present application discloses an electromagnetic separation mechanism for an aircraft and a parachute, and relates to the field of aerospace technology. The electromagnetic separation mechanism comprises: a fixing member and a separation member, and two ends of the fixing member and the separation member are respectively provided with universal pull rings; the universal pull ring on the fixing member is connected to the aircraft, and the universal pull ring on the separation member is connected to the parachute hanging rope; a locking assembly, and the locking assembly comprises: an electromagnetic lock and a locking pin used in conjunction; the electromagnetic lock is arranged on the fixing member, and the locking pin is arranged on the separation member; the electromagnetic lock has a power-on state and a power-off state; when the electromagnetic lock is in the power-off state, the electromagnetic lock is locked with the locking pin, so that the fixing member and the separation member are connected, so that the aircraft is connected to the parachute; when the electromagnetic lock is in the power-on state, the electromagnetic lock is unlocked with the locking pin, and under the pulling force of the parachute, the fixing member and the separation member are separated, so that the aircraft is separated from the parachute. The entire mechanism structure is simpler and easy to operate.

Description

Technical Field

[0001] The present application generally relates to the field of aerospace technology, and specifically to an electromagnetic separation mechanism for an aircraft and a parachute. Background Art

[0002] The rapid development of aerospace technology has also put forward higher and higher requirements for the safety and reliability of aircraft. The large number of uncertain factors involved in the deceleration and landing process of the aircraft often make this stage one of the most faulty stages of aerospace missions. At present, the separation of the aircraft and the parachute is usually carried out by pyrotechnics, which makes the entire device more complicated and costly. In addition, after the aircraft lands, since the parachute is not separated from the aircraft, it is easily affected by the wind, dragging and pulling the aircraft to bump and move on the ground, causing damage and loss of equipment on the aircraft. Therefore, we provide an electromagnetic separation mechanism for aircraft and parachute to solve the above problems. Summary of the invention

[0003] In view of the above-mentioned defects or deficiencies in the prior art, it is desired to provide an electromagnetic separation mechanism for an aircraft and a parachute that has high reliability, simple structure and is easy to implement.

[0004] The present application provides an electromagnetic separation mechanism for an aircraft and a parachute, comprising:

[0005] A fixing member and a leaving member, wherein two ends of the fixing member and the leaving member which are far from each other are respectively provided with universal pull rings; the universal pull ring on the fixing member is connected to the aircraft, and the universal pull ring on the leaving member is connected to the parachute hanging rope;

[0006] A locking assembly, the locking assembly comprising: an electromagnetic lock and a locking pin used in conjunction with each other; the electromagnetic lock is arranged on the fixing member, and the locking pin is arranged on the leaving member; the electromagnetic lock has a power-on state and a power-off state;

[0007] When the electromagnetic lock is in a power-off state, the electromagnetic lock is locked with the locking pin, so that the fixing part and the separation part are connected, so that the aircraft is connected to the parachute; when the electromagnetic lock is in a power-on state, the electromagnetic lock is unlocked with the locking pin, and under the pulling force of the parachute, the fixing part and the separation part are separated, so that the aircraft is separated from the parachute.

[0008] The technical solution provided by this application also includes:

[0009] A guide member, the guide member having a mounting section and a guide section connected to each other; the mounting section is connected to the fixing member, the guide section passes through the fixing member and is inserted into the opening of the leaving member; the guide section has an inclined guide slope;

[0010] When the electromagnetic lock is unlocked from the locking pin, under the pulling force of the parachute, the leaving member slides along the guiding inclined surface, so that the leaving member is quickly separated from the fixing member.

[0011] According to the technical solution provided in the present application, the mounting section is connected to the fixing member via mounting screws.

[0012] According to the technical solution provided in the present application, the guide section has a first inclined surface and a first adjustment plate, one end of the first adjustment plate is rotatably connected to the first inclined surface; the side of the first adjustment plate away from the first inclined surface forms the guide inclined surface;

[0013] A first driving member is also provided on the first inclined surface, and a driving end of the first driving member is rotatably connected to a first slider; a first slide rail accommodating the sliding of the first slider is provided on one side of the first adjustment plate close to the first inclined surface;

[0014] The first driving member drives the first sliding block to slide along the first sliding rail, thereby changing the inclination degree of the guiding inclined surface.

[0015] According to the technical solution provided by the present application, the inner wall of the opening of the leaving member has a second inclined surface and a second adjustment plate; one end of the second adjustment plate is rotatably connected to the second inclined surface; the side of the second adjustment plate away from the second inclined surface is in surface contact with the guide inclined surface;

[0016] A second driving member is also provided on the second inclined surface, and a driving end of the second driving member is rotatably connected to a second slider. A second slide rail accommodating the sliding of the second slider is provided on one side of the second adjustment plate close to the second inclined surface;

[0017] The second sliding block is driven to slide along the second sliding rail by the second driving member, so that the second adjustment plate is in surface contact with the guiding inclined surface.

[0018] According to the technical solution provided in the present application, the locking pin has a connecting screw and a locking ball that are connected to each other; the connecting screw is connected to the separation piece, and the locking ball is inserted into the electromagnetic lock; the diameter of the locking ball is larger than the diameter of the connecting screw.

[0019] According to the technical solution provided in the present application, the connecting screw is connected to the separation member through a locking nut.

[0020] It can be seen from the above technical solution that the present application has at least the following beneficial effects:

[0021] The present application discloses an electromagnetic separation mechanism for an aircraft and a parachute, the mechanism comprising: a fixing member and a separation member used in conjunction with each other, wherein two ends of the fixing member and the separation member which are away from each other are respectively provided with universal pull rings, wherein the universal pull ring on the fixing member is connected to the aircraft, and the universal pull ring on the separation member is connected to the parachute hanging rope; the mechanism also comprises: a locking assembly, which comprises an electromagnetic lock and a locking pin used in conjunction with each other; the electromagnetic lock is arranged on the fixing member, and the locking pin is arranged on the separation member; the electromagnetic lock has a power-on state and a power-off state; when the electromagnetic lock is in the power-off state, the electromagnetic lock and the locking pin are locked, so that the fixing member and the separation member are connected, so that the aircraft is connected to the parachute; when the electromagnetic lock is in the power-on state, the electromagnetic lock and the locking pin are unlocked, and under the pulling force of the parachute, the fixing member and the separation member are separated, so that the aircraft is separated from the parachute.

[0022] The present application switches the on and off state of the electromagnetic lock to change the locking and unlocking of the electromagnetic lock and the locking pin, thereby controlling the connection and separation relationship between the fixing part and the separation part, so as to connect and separate the aircraft and the parachute. The entire mechanism structure is simpler and easier to operate. In addition, the electromagnetic lock can be reused, which can also achieve the purpose of cost saving. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Other features, objects and advantages of the present application will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings.

[0024] Figure 1 It is a schematic diagram of the overall structure of the electromagnetic separation mechanism of the aircraft and the parachute.

[0025] Figure 2 A cross-sectional view of the electromagnetic separation mechanism of the aircraft and the parachute.

[0026] Figure 3 Schematic diagram of the structure of the guide.

[0027] Figure 4 It is a structural schematic diagram of the guide section and the leaving piece.

[0028] Numbers in the figure: 1. fixing member; 2. separation member; 3. universal pull ring; 4. electromagnetic lock; 5. locking pin; 6. guide member; 7. mounting screw; 8. locking nut; 9. first driving member; 10. first adjustment plate; 11. first slide rail; 12. second adjustment plate; 13. second driving member; 14. second slide rail. DETAILED DESCRIPTION

[0029] The present application is further described in detail below in conjunction with the accompanying drawings and embodiments. It is to be understood that the specific embodiments described herein are only used to explain the relevant invention, rather than to limit the invention. It is also necessary to explain that, for ease of description, only the parts related to the invention are shown in the accompanying drawings.

[0030] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present application will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0031] In order to make the electromagnetic separation mechanism of the aircraft and the parachute provided in the embodiment of the present application clearer and easier to understand, the mechanism is introduced below with reference to the accompanying drawings. Figure 1 As shown, this figure is a schematic diagram of the overall structure of the electromagnetic separation mechanism of the aircraft and the parachute provided in an embodiment of the present application, and the mechanism includes:

[0032] The fixing part 1 and the leaving part 2 are provided with universal pull rings 3 at two ends of the fixing part 1 and the leaving part 2 that are far away from each other; the universal pull ring 3 on the fixing part 1 is connected to the aircraft, and the universal pull ring 3 on the leaving part 2 is connected to the parachute hanging rope; wherein, the fixing part 1 and the leaving part 2 are the same device, and because the parts connected by the universal pull ring 3 are different, in order to facilitate the distinction, the two devices are given different names using functional expressions. The universal pull ring 3 and the corresponding fixing part 1 or the leaving part 2 can be connected through a connecting shaft, and the universal pull ring 3 can rotate relative to the corresponding connecting shaft to avoid additional tension between the parachute and the aircraft, causing the parachute and the aircraft to get stuck or separate prematurely, affecting the reliability of the mechanism.

[0033] Furthermore, the fixing member 1 and the leaving member 2 may be collinear or non-collinear. Figure 1 As shown, notches are provided on both components, and the two notches are engaged with each other, at which time, the fixing component 1 and the separation component 2 are collinear. If the fixing component 1 and the separation component 2 are directly stacked and connected together, at this time, the fixing component 1 and the separation component 2 are not collinear.

[0034] like Figure 2 As shown, the locking assembly includes: an electromagnetic lock 4 and a locking pin 5 used in conjunction with each other; the electromagnetic lock 4 is arranged on the fixing member 1, and the locking pin 5 is arranged on the separation member 2; the electromagnetic lock 4 has a power-on state and a power-off state; wherein the electromagnetic lock 4 is a conventional component and will not be described in detail here. It should be noted that the electromagnetic lock 4 has a deformable card slot for locking or unlocking with the locking pin 5.

[0035] When the electromagnetic lock 4 is in the power-off state, the electromagnetic lock 4 is locked with the locking pin 5, so that the fixing part 1 and the separation part 2 are connected, so that the aircraft is connected to the parachute; when the electromagnetic lock 4 is in the power-on state, the electromagnetic lock 4 and the locking pin 5 are unlocked, and under the pulling force of the parachute, the fixing part 1 and the separation part 2 are separated, so that the aircraft is separated from the parachute.

[0036] The present application switches the on and off state of the electromagnetic lock 4 to change the locking and unlocking of the electromagnetic lock 4 and the locking pin 5, thereby controlling the connection and separation relationship between the fixing member 1 and the separation member 2, so as to connect and separate the aircraft and the parachute. The entire mechanism structure is simpler and easier to operate. In addition, the electromagnetic lock 4 can be reused, which can also achieve the purpose of cost saving.

[0037] Furthermore, if Figure 2 As shown, the agency also includes:

[0038] The guide member 6 has a mounting section and a guide section connected to each other; wherein, Figure 3 a is the installation section, and b is the guide section. The installation section is connected to the fixing member 1, and the guide section passes through the fixing member 1 and is inserted into the opening of the leaving member 2; the guide section has an inclined guide slope, for example, the guide slope forms a first angle with the extension direction of the installation section, and the opening of the first angle faces away from the fixing member 1; Figure 3 As shown, α is the first angle. Here, the angle range of the first angle is 10° to 15°. Here, the mounting section is connected to the fixing member 1 by mounting screws 7.

[0039] When the electromagnetic lock 4 and the locking pin 5 are unlocked, the leaving member 2 slides along the guide slope under the pulling force of the parachute, so that the leaving member 2 and the fixing member 1 are quickly separated. Figure 3 As shown, the guiding slope is arranged toward the side where the parachute is located, which makes it easier to separate the separation member 2 and the fixing member 1 under the pulling force of the parachute.

[0040] Furthermore, if Figure 4 As shown, the guide section has a first inclined surface and a first adjustment plate 10, one end of the first adjustment plate 10 is rotatably connected to the first inclined surface, and the first adjustment plate 10 can swing relative to the first inclined surface; the side of the first adjustment plate 10 away from the first inclined surface forms a guide inclined surface;

[0041] A first driving member 9 is also provided on the first inclined surface, and a driving end of the first driving member 9 is rotatably connected to a first slider; a first slide rail 11 for accommodating the sliding of the first slider is provided on the side of the first adjustment plate 10 close to the first inclined surface; here, the first driving member 9 is, for example, a small driving cylinder.

[0042] The first driving member 9 drives the first sliding block to slide along the first sliding rail 11, thereby changing the inclination of the guiding inclined surface.

[0043] In addition, the inner wall of the opening of the leaving member 2 has a second inclined surface and a second adjustment plate 12; one end of the second adjustment plate 12 is rotatably connected to the second inclined surface, and the second adjustment plate 12 can swing relative to the second inclined surface; the side of the second adjustment plate 12 away from the second inclined surface is in contact with the guide inclined surface;

[0044] A second driving member 13 is also provided on the second inclined surface, and a driving end of the second driving member 13 is rotatably connected to a second slider. A second slide rail 14 for accommodating the sliding of the second slider is provided on the side of the second adjustment plate 12 close to the second inclined surface; here, the second driving member 13 is, for example, a small driving cylinder.

[0045] The second slide block is driven to slide along the second slide rail 14 by the second driving member 13 so that the second adjustment plate 12 is in surface contact with the guide inclined surface.

[0046] By adjusting the relative position of the first adjustment plate 10 and the first inclined surface, and the relative position of the second adjustment plate 12 and the second inclined surface, the first angle is changed to assist in the quick separation of the separation member 2 and the fixing member 1 .

[0047] Among them, when the axes of the fixing member 1, the leaving member 2 and the two universal pull rings 3 are collinear, there is no need to adjust the angle of the first angle, and the guide member 6 can assist the leaving member 2 to separate quickly from the fixing member 1. When there is at least one device among the axes of the fixing member 1, the leaving member 2 and the two universal pull rings 3 that is not collinear with other devices, the current first angle will increase the friction between the leaving member 2 and the fixing member 1, that is, when separating, it will hinder the separation speed of the leaving member 2 and the fixing member 1, and it is easy for the tension and wind force of the parachute to act on the aircraft, causing the aircraft to collide with the ground. At this time, it is necessary to adjust the first driving member 9 and the second driving member 13 to change the inclination of the guiding slope so that the guide member 6 can have the function of assisting the leaving member 2 and the fixing member 1 to separate quickly. In addition, the entire mechanism can also correspond to the conditions of different aircraft and parachutes, and the scope of application is wider.

[0048] It should be noted that the locking pin 5 has a connecting screw and a locking ball that are connected to each other; the connecting screw is connected to the separation member 2, and the locking ball is inserted into the electromagnetic lock 4; the diameter of the locking ball is larger than the diameter of the connecting screw; the electromagnetic lock 4 and the locking ball can achieve the purpose of locking. Here, the connecting screw is connected to the separation member 2 through a locking nut 8. In addition, the pre-tightening force of the locking nut 8 on the connecting screw is smaller than the electromagnetic force of the electromagnetic lock 4, so that the electromagnetic lock 4 and the locking pin 5 can be separated when the electromagnetic lock 4 is powered on.

[0049] The specific working process of this organization is as follows:

[0050] First, analyze whether the two universal pull rings 3, the fixing part 1 and the leaving part 2 are collinear. If they are collinear, the first angle does not need to be adjusted. If they are not collinear, the angle of the first angle is adjusted. The guide member 6 is inserted through the fixing part 1 and into the opening of the leaving part 2. The guide member 6 is connected to the fixing part 1 by means of mounting screws. The universal pull ring 3 on the fixing part 1 is connected to the aircraft. The universal pull ring 3 on the leaving part 2 is connected to the parachute hanging rope. The electromagnetic lock 4 is powered off, and the electromagnetic lock 4 and the locking pin 5 are locked. At this time, the aircraft and the parachute are in a connected state. When the aircraft and the parachute need to be separated, the electromagnetic lock 4 is powered on, the electromagnetic lock 4 and the locking pin 5 are unlocked, and under the pulling force of the parachute, the guide slope is used to assist the fixing part 1 and the leaving part 2 to separate quickly, so as to achieve the purpose of quickly separating the aircraft and the parachute.

[0051] The above description is only a preferred embodiment of the present application and an explanation of the technical principles used. Those skilled in the art should understand that the scope of the invention involved in the present application is not limited to the technical solution formed by a specific combination of the above technical features, but should also cover other technical solutions formed by any combination of the above technical features or their equivalent features without departing from the inventive concept. For example, the above features are replaced with (but not limited to) technical features with similar functions disclosed in the present application.

Claims

1. An electromagnetic separation mechanism for an aircraft and a parachute, characterized in that: include: A fixing member (1) and a leaving member (2), wherein two ends of the fixing member (1) and the leaving member (2) which are away from each other are respectively provided with universal pull rings (3); the universal pull ring (3) on the fixing member (1) is connected to the aircraft, and the universal pull ring (3) on the leaving member (2) is connected to the parachute hanging rope; A locking assembly, the locking assembly comprising: an electromagnetic lock (4) and a locking pin (5) for use together; the electromagnetic lock (4) is arranged on the fixing member (1), and the locking pin (5) is arranged on the leaving member (2); the electromagnetic lock (4) has a power-on state and a power-off state; When the electromagnetic lock (4) is in a power-off state, the electromagnetic lock (4) and the locking pin (5) are locked, so that the fixing member (1) and the separation member (2) are connected, so that the aircraft is connected to the parachute; when the electromagnetic lock (4) is in a power-on state, the electromagnetic lock (4) and the locking pin (5) are unlocked, and under the pulling force of the parachute, the fixing member (1) and the separation member (2) are separated, so that the aircraft is separated from the parachute; Also includes: A guide member (6), the guide member (6) comprising a mounting section and a guide section connected to each other; the mounting section is connected to the fixing member (1), the guide section passes through the fixing member (1) and is inserted into the opening of the leaving member (2); the guide section has an inclined guide slope; When the electromagnetic lock (4) and the locking pin (5) are unlocked, the leaving member (2) slides along the guiding inclined surface under the pulling force of the parachute, so that the leaving member (2) and the fixing member (1) are quickly separated; The guide section comprises a first inclined surface and a first adjustment plate (10); one end of the first adjustment plate (10) is rotatably connected to the first inclined surface; a side of the first adjustment plate (10) away from the first inclined surface forms the guide inclined surface; A first driving member (9) is also provided on the first inclined surface, and a driving end of the first driving member (9) is rotatably connected to a first sliding block; a first slide rail (11) accommodating the sliding of the first sliding block is provided on a side of the first adjustment plate (10) close to the first inclined surface; The first driving member (9) drives the first sliding block to slide along the first sliding rail (11), thereby changing the inclination of the guiding inclined surface; The inner wall of the opening of the separation member (2) has a second inclined surface and a second adjustment plate (12); one end of the second adjustment plate (12) is rotatably connected to the second inclined surface; and a side of the second adjustment plate (12) away from the second inclined surface is in surface contact with the guide inclined surface; A second driving member (13) is also provided on the second inclined surface, and a driving end of the second driving member (13) is rotatably connected to a second sliding block, and a second slide rail (14) accommodating the sliding of the second sliding block is provided on a side of the second adjustment plate (12) close to the second inclined surface; The second slide block is driven by the second driving member (13) to slide along the second slide rail (14), so that the second adjustment plate (12) is in surface contact with the guide inclined surface.

2. The electromagnetic separation mechanism for an aircraft and a parachute according to claim 1, characterized in that: The mounting section is connected to the fixing member (1) via a mounting screw (7).

3. The electromagnetic separation mechanism for an aircraft and a parachute according to claim 1, characterized in that: The locking pin (5) comprises a connecting screw and a locking ball which are connected to each other; the connecting screw is connected to the separation member (2), and the locking ball is inserted into the electromagnetic lock (4); the diameter of the locking ball is greater than the diameter of the connecting screw.

4. The electromagnetic separation mechanism for an aircraft and a parachute according to claim 3, characterized in that: The connecting screw is connected to the separation member (2) via a locking nut (8).

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