Telescopic spaceflight cable suitable for transformable aircraft

Abstract

The invention discloses a telescopic spaceflight cable suitable for a transformable aircraft, which is formed by sequentially coating an inner layer, a central layer and an outer layer from inside to outside, and the inner layer and the outer layer synchronously and elastically stretch out and draw back. The inner layer is an elastic support body, the central layer is a wire roll body formed by winding a plurality of specially-made wires according to a specific rule, the outer layer is composed of a heat-proof protective sleeve, the heat-proof protective sleeve is composed of a plurality of sections of ripples, and the specially-made wires adopt a composite material multi-layer shielding structure, so that the anti-electromagnetic interference capability of the wire is improved while the flexibility of the wire is ensured. The cable can meet the use requirements of a deformable aircraft cable for being telescopic, small in size, low in weight, resistant to electromagnetic interference and resistant to high temperature.

Description

Technical Field

[0001] The invention relates to the field of aerospace equipment, in particular to a retractable aerospace cable. Background Art

[0002] Deformable aircraft is a hot topic in the current field of aerospace research. Its advantage is that the aircraft can achieve cross-domain flight by changing the shape of the wing surface during flight. During the deformation of the aircraft wing surface, some cables on the device will also shrink and change with the deformation of the wing surface. This requires the cable to have a certain shrinkage performance, be able to adapt to the high temperature environment brought by ultra-high-speed flight, and meet the electromagnetic shielding capabilities required for aerospace cables.

[0003] After investigation, the existing cable retraction solutions are mainly divided into two categories: active retraction and passive retraction:

[0004] Active retractable cable solutions, such as Chinese patent CN217535069U, are named as a retractable cable for submersible pumps, which consists of a water pump body, a cable, a retracting chamber, a coil spring and a clamp. The equipment needs to be equipped with a separate recovery mechanism, has a large structure and a slow retraction speed. Therefore, this cable retraction solution is not suitable for use in aircraft space.

[0005] Passive telescopic cable solutions, such as Chinese patent CN110136869A, named telescopic cable and its manufacturing method, are composed of conductors, insulation layers, outer coverings, etc. The insulation material is a special heat-shrinkable elastomer. The conductors covered with the insulating elastic material are axially unidirectionally spirally wound into a spiral structure, thereby realizing the elastic telescopic ability of the cable. This solution cannot adapt to high temperature environments, the cable does not have electromagnetic shielding capabilities, the outermost layer has no restrained protective layer, and the overall free divergence of the cable during telescopic process makes it very easy to interfere with other mechanisms, causing contraction jams or cable structure damage. Summary of the invention

[0006] In view of the above problems, an object of the present invention is to provide a retractable aerospace cable suitable for a deformable aircraft, which meets the requirements of the deformable aircraft cable for being retractable, small in size, low in weight, anti-electromagnetic interference and high temperature resistant.

[0007] The technical solution of the present invention is as follows:

[0008] A retractable aerospace cable suitable for a deformable aircraft adopts an inner layer, a central layer and an outer layer structure, which are coated from the inside to the outside in sequence. The inner layer is an elastic support body, which is composed of multiple elastic units in series. As the core support element of the cable, it mainly plays the role of wire support and elastic energy storage and release; the central layer is a wire coil formed by winding multiple special wires according to specific rules, in which the special wire adopts a composite material multi-layer shielding structure, which can play a good electromagnetic shielding role; the outer layer is composed of a heat-proof protective sleeve, which is composed of multiple sections of corrugation and has good retractable performance. The silicon-based heat-proof material can protect the internal wire from high temperature impact.

[0009] The elastic support body of the present invention is composed of a plurality of elastic units connected in series, and each two elastic units are welded and fixed by four rivets. A single elastic unit is composed of four elastic sheets cross-welded and fixed on a cross plate. The bending radius of the elastic sheet is defined as r, and the length range of the elastic unit is 2r to 8r.

[0010] The wire coil described in the present invention is formed into a spiral body by winding a plurality of special wires in a left-handed or right-handed manner in a certain diameter. The plurality of special wires described in the present invention refers to a combination of four or more wires in pairs. The present invention bundles the spiral cross sections of the special wires at the connection parts between the elastic units. The advantage of this bundling method is that it reduces the bundling area and releases the curling space while improving the firmness of the bundling. In the present invention, the rotation radius of a single special wire around the central axis is r, and the pitch range is 2r to 8r. The rotation radius and pitch of the special wire depend on the telescopic requirements of the cable.

[0011] The single special wire described in the present invention is composed of a metal wire core, an inner insulating layer, an inner shielding layer, a conductive layer, an outer shielding layer and an outer insulating layer. In the present invention, the metal wire core is the conductive element of the cable, which is a conductive wire core made of copper, aluminum and other alloy materials; the inner insulating layer and the outer insulating layer are made of polyurethane, which plays a role of protection and insulation; the inner shielding and the outer shielding are dense shielding cloths woven from yarns such as silver, nickel, and copper, which play a double-layer electromagnetic shielding role of the cable; the conductive layer between the inner shielding layer and the outer shielding layer is made of polyaniline, which can connect the inner shielding layer and the outer shielding layer to enhance the electromagnetic shielding effect while ensuring good flexibility.

[0012] The heat-resistant protective sleeve of the present invention is composed of a multi-section corrugated structure, with thick corrugated sections at both ends of the cable and a thin corrugated section in the middle. The material of the heat-resistant protective sleeve is formed by a silicon-based heat-resistant coating and aramid fiber layers, and has good heat-resistant and heat-insulating properties.

[0013] Compared with the prior art, the retractable aerospace cable suitable for a deformable aircraft proposed by the present invention has the following characteristics:

[0014] (1) The present invention adopts a three-layer superimposed structure of an inner layer - an elastic support body, a central layer - a wire coil body and an outer layer - a heat-proof protective sleeve. The inner and outer layers are elastically expanded and contracted synchronously, and no additional driving elements are required, thereby saving a large amount of installation space and weight.

[0015] (2) The cable diameter of the present invention can be selected within the range of 10 mm to 150 mm, and the expansion ratio can be up to 50% or more.

[0016] (3) The conductor of the present invention adopts a composite material multilayer shielding structure, which ensures the flexibility of the conductor while improving the conductor's anti-electromagnetic interference capability.

[0017] (4) The outer layer of the cable proposed in the present invention adopts a corrugated tube structure composed of a composite silicon-based heat-resistant composition. The expansion and contraction amount at different positions is planned by presetting the corrugation width, which can avoid damage caused by local concentrated force and can withstand the impact of a high temperature environment of 500°C to 800°C. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a simplified diagram of the cable structure;

[0019] Figure 2 It is a simplified diagram of the elastic support structure;

[0020] Figure 3 It is a simplified diagram of the elastic unit structure;

[0021] Figure 4 It is the elastic support body parameter definition diagram;

[0022] Figure 5 It is a simplified diagram of the conductor coil structure;

[0023] Figure 6 It is the definition diagram of the wire rotation direction;

[0024] Figure 7 It is the wire parameter definition diagram;

[0025] Figure 8 It is a single wire structure diagram;

[0026] Fig. 9 It is the structure diagram of the heat protection cover;

[0027] Fig.10 It is the parameter definition diagram of the heat protection cover.

[0028] Among them: 1- elastic support body 2- conductor coil 3- heat protection sleeve 4- elastic unit 5- rivet 6- cross plate 7- elastic sheet 8- special conductor 9- metal wire core 10- inner insulation layer 11- inner shielding layer 12- conductive layer 13- outer shielding layer 14- outer insulation layer DETAILED DESCRIPTION

[0029] In order to enable those skilled in the art to better understand the scheme of the present invention, the technical scheme in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work should fall within the scope of protection of the present invention.

[0030] This embodiment provides a retractable aerospace cable suitable for a deformable aircraft, which is composed of an inner layer, a center layer and an outer layer structure, which are coated sequentially from the inside to the outside. Figure 1 As shown. The inner layer is an elastic support body 1, which is composed of multiple elastic units in series. As the core support element of the cable, it mainly plays the role of conductor support and elastic energy storage and release; the central layer is a conductor coil 2 formed by winding multiple special conductors according to specific rules, in which the special conductor adopts a composite material multi-layer shielding structure, which can play a good electromagnetic shielding role; the outer layer is composed of a heat-proof protective sleeve 3, which is composed of multiple sections of corrugation and has good elasticity. The silicon-based heat-proof material can protect the internal conductor from high temperature impact.

[0031] Specifically, the elastic support body 1 is composed of a plurality of elastic units 4 connected in series, and each two elastic units 4 are welded and fixedly connected by four rivets 5. Figure 2 The structure of a single elastic unit 4 is shown in Figure 3 As shown, four elastic sheets 7 are cross-fixed and welded on a cross plate 6. The bending radius of the elastic sheet 7 is defined as r, and the length range of the elastic unit 4 is 2r to 8r. The parameter definition is shown in Figure 4 shown.

[0032] The wire coil 2 of the present invention is formed by winding a plurality of special wires 8 in a left-handed or right-handed manner in a cross-winding manner according to a certain diameter to form a spiral body. Figure 5 The multiple special wires 8 described in the present invention refer to a combination of four or more wires in pairs. For the convenience of explanation, the present invention takes four wires as an example. The definition of left-handed and right-handed special wires 8 described in the present invention is shown in Figure 6 As shown, the spiral cross section of the special wire 8 is bundled at the connection between the elastic units 4. The advantage of this bundling method is that it reduces the bundling area and releases the curling space while improving the firmness of the bundling. In the present invention, the rotation radius of a single special wire 8 around the central axis is r, and the pitch range is 2r to 8r. The parameter definition is shown in Figure 7 The rotation radius and pitch of the special conductor 8 depend on the expansion and contraction requirements of the cable.

[0033] The single special wire 8 of the present invention is composed of a metal wire core 9, an inner insulating layer 10, an inner shielding layer 11, a conductive layer 12, an outer shielding layer 13 and an outer insulating layer 14. Figure 8 As shown. In the present invention, the metal core 9 is the conductive element of the cable, which is a conductive core made of copper, aluminum and other alloy materials; the inner insulating layer 10 and the outer insulating layer 14 are made of polyurethane, which plays a role of protection and insulation; the inner shielding layer 11 and the outer shielding layer 13 are dense shielding cloths woven from yarns such as silver, nickel, and copper, which play a double-layer electromagnetic shielding role of the cable; the conductive layer 12 between the inner shielding layer 11 and the outer shielding layer 13 is made of polyaniline, which can connect the inner shielding layer 11 and the outer shielding layer 13 to enhance the electromagnetic shielding effect while ensuring good flexibility.

[0034] The heat protection sleeve 3 of the present invention is composed of a multi-section corrugated structure, with thick corrugated sections at both ends of the cable and a thin corrugated section in the middle. Figure 8 As shown. The total length of the heat protection sleeve 3 is defined as L, and the range of L can be between 0.5 meters and 5 meters. The diameter of the heat protection sleeve 3 is defined as D, and D>2r. The length of the thick corrugated section is defined as L1, and L1=0.15~0.5L. The radial height of the thick corrugated section is defined as t1, and t1=0.2~0.5D. The width of a single corrugation of the thick corrugated section is defined as s1, and s1=0.1~0.3D. The thickness of the thick corrugated section is defined as p1, and p1=3 mm~20 mm. The length of the thin corrugated section is defined as L2, and L2=0.1~0.6L. The radial height of the thin corrugated section is defined as t2, and t2=0.15~0.3D. The width of a single corrugation of the thin corrugated section is defined as s1, and s1=0.1~0.2D. The thickness of the thin corrugated section is defined as p1, and p1=2 mm~15 mm. The material of the heat-proof protective sleeve 3 is formed by a composite stack of silicon-based heat-proof coating and aramid fiber layers, and has good heat-proof and heat-insulating properties.

[0035] The above description of the disclosed embodiments enables one skilled in the art to implement or use the present invention. Various modifications to these embodiments will be apparent to one skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the scope of the present invention. Therefore, the present invention will not be limited to the embodiments shown herein, but rather to the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A retractable aerospace cable suitable for a deformable aircraft, characterized in that: It adopts the structure of inner layer, central layer and outer layer, which are wrapped from inside to outside in sequence, and the inner and outer layers are elastically expanded and contracted synchronously; the inner layer is an elastic support body, which is composed of multiple elastic units in series; the central layer is a wire coil formed by winding multiple special wires, in which the special wires adopt a composite material multi-layer shielding structure; the outer layer is composed of a heat-proof protective sleeve.

2. The retractable aerospace cable suitable for a deformable aircraft according to claim 1, characterized in that: The elastic unit is composed of four elastic sheets which are cross-fixed and welded on a cross plate, and every two elastic units are welded and fixedly connected by four rivets.

3. The retractable aerospace cable suitable for a deformable aircraft according to claim 1, characterized in that: The special wire comprises, from inside to outside, a metal wire core, an inner insulating layer, an inner shielding layer, a conductive layer, an outer shielding layer and an outer insulating layer.

4. The retractable aerospace cable suitable for a deformable aircraft according to claim 3, characterized in that: The inner shielding layer and the outer shielding layer are dense shielding cloths woven from silver, nickel and copper yarns.

5. The retractable aerospace cable suitable for a deformable aircraft according to claim 3, characterized in that: The material of the conductive layer between the inner shielding layer and the outer shielding layer is polyaniline.

6. The retractable aerospace cable suitable for a deformable aircraft according to claim 1, characterized in that: The wire coil is a spiral body formed by winding four or more special wires in a left-handed and right-handed manner in a certain diameter, and the spiral cross sections of the special wires are bundled at the connection parts between the elastic units.

7. The retractable aerospace cable suitable for a deformable aircraft according to claim 1, characterized in that: The heat-proof protective sleeve is composed of a multi-section corrugated structure, with thick corrugated sections at both ends of the cable and a thin corrugated section in the middle.

8. The retractable aerospace cable suitable for a deformable aircraft according to claim 1, characterized in that: The material of the heat-proof protective sleeve is formed by the composite superposition of silicon-based heat-proof coating and aramid fiber layers, and has good heat-proof and heat-insulating properties.

9. The retractable aerospace cable suitable for a deformable aircraft according to claim 7, characterized in that: The thickness of the thick corrugated section is 3 mm to 20 mm, and the thickness of the thin corrugated section is 2 mm to 15 mm.

10. The retractable aerospace cable suitable for a deformable aircraft according to claim 7, characterized in that: The expansion and contraction amount at different positions can be planned by presetting the corrugation width.

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