Flexible deployable shielded head cover device for a return vehicle

Abstract

The application relates to a flexible deployable protective head cover device for a return spacecraft, belonging to the field of spacecraft reentry, return and landing, and comprising a connecting mounting plate, a locking structure, a protective head cover flexible deployment structure and a package rope cutter; the connecting mounting plate is a horizontally placed disc structure; a ring-shaped groove is concentrically arranged on the upper surface of the connecting mounting plate; the locking structure is uniformly embedded in the groove in the circumferential direction; the protective head cover flexible deployment structure is locked on the upper surface of the connecting mounting plate after being folded, and is located at the ring-shaped groove; the package rope cutter is arranged below the protective head cover flexible deployment structure; the application utilizes the pressure difference between the inside and outside of the structure to maintain the rigidity of the structure, and utilizes the surface flexible thermal protection structure to resist external high-temperature airflow, so as to meet the thermodynamic protection requirement of the shoulder instrument equipment of the return spacecraft.

Description

TECHNICAL FIELD

[0001] The application belongs to the field of spacecraft reentry, return and landing, and relates to a flexible deployable protective nose cover device for a return spacecraft. BACKGROUND

[0002] A return spacecraft needs to undergo multiple orbit changes and circumlunar missions in orbit. In order to reduce the structural mass in orbit and save fuel consumption, the rigid nose cover needs to be thrown away after the spacecraft enters the orbit, which will expose the docking mechanism and other instruments and equipment to the high-temperature gas environment outside, and cannot achieve the reuse requirement of the return spacecraft. SUMMARY

[0003] The technical problem solved by the application is to overcome the shortcomings of the prior art and provide a flexible deployable protective nose cover device for a return spacecraft, which uses the pressure difference between the inside and outside of the structure to maintain the rigidity of the structure, and uses the flexible thermal protection structure on the surface to resist the external high-temperature gas flow, so as to achieve the thermodynamic protection requirement of the instruments and equipment on the shoulder of the return spacecraft.

[0004] The technical solution of the application is as follows:

[0005] A flexible deployable protective nose cover device for a return spacecraft comprises a connecting mounting plate, a locking structure, a protective nose cover flexible deployment structure and a package rope cutter. The connecting mounting plate is a horizontally placed disc structure. A ring-shaped groove is concentrically arranged on the upper surface of the connecting mounting plate. The locking structure is uniformly embedded in the groove in the circumferential direction. The protective nose cover flexible deployment structure is locked on the upper surface of the connecting mounting plate after being folded, and is located at the ring-shaped groove. The package rope cutter is arranged below the protective nose cover flexible deployment structure.

[0006] In the above-mentioned flexible deployable protective nose cover device for a return spacecraft, the working process of the deployable protective nose cover device is as follows:

[0007] The package rope cutter cuts and unlocks the protective nose cover flexible deployment structure. The protective nose cover flexible deployment structure is released and deployed into an inverted disc structure. The locking structure is locked in the middle of the upper surface of the connecting mounting plate.

[0008] In the above-mentioned flexible deployable protective nose cover device for a return spacecraft, the protective nose cover flexible deployment structure comprises a skeleton airbag structure and a flexible skin structure. The skeleton airbag structure is a concentric double-ring structure. The flexible skin structure covers the upper surface of the skeleton airbag structure.

[0009] In the flexible deployable protective head cover device for a return spacecraft, the double-ring skeleton airbag structure is uniformly provided with a locking connection structure at the bottom of the outer ring in the circumferential direction; after the flexible deployment structure of the protective head cover is deployed, the locking connection structure is connected with the locking structure one by one, so that the flexible deployment structure of the protective head cover is locked on the upper surface of the connecting mounting plate.

[0010] In the flexible deployable protective head cover device for a return spacecraft, the double-ring skeleton airbag structure is uniformly provided with a locking connection structure at the bottom of the outer ring in the circumferential direction; after the flexible deployment structure of the protective head cover is deployed, the locking connection structure is connected with the locking structure one by one, so that the flexible deployment structure of the protective head cover is locked on the upper surface of the connecting mounting plate.

[0011] In the flexible deployable protective head cover device for a return spacecraft, the double-ring skeleton airbag structure is uniformly provided with a locking connection structure at the bottom of the outer ring in the circumferential direction; after the flexible deployment structure of the protective head cover is deployed, the locking connection structure is connected with the locking structure one by one, so that the flexible deployment structure of the protective head cover is locked on the upper surface of the connecting mounting plate.

[0012] In the flexible deployable protective head cover device for a return spacecraft, the flexible skin structure is divided into three layers, and from top to bottom, they are an ablation-resistant layer, a multilayer thermal insulation layer and a load-bearing layer.

[0013] In the flexible deployable protective head cover device for a return spacecraft, the ablation-resistant layer is used to withstand the scouring of external high-temperature airflow, so as to realize the mechanical protection of the internal structure, and the material is selected from modified glass fiber cloth, alumina fiber cloth or quartz fiber cloth high-temperature fabric material according to the surface temperature; the multilayer thermal insulation layer is used to insulate the external environmental heat flow, so as to realize the thermal protection of the internal structure, and the material is selected from alumina aerogel thermal insulation felt and silica aerogel thermal insulation felt flexible thermal insulation material according to the thermal insulation performance requirement; the load-bearing layer is used to transfer the external aerodynamic force and fix the ablation-resistant layer and the multilayer thermal insulation layer; the material of the load-bearing layer is selected from aramid fiber, nylon fiber or polyimide fiber high-strength organic fiber according to the stress condition.

[0014] In the flexible deployable protective head cover device for a return spacecraft, the locking structure is used to realize the locking and limiting of the flexible deployment structure of the protective head cover through the fixed shaft rotation of the swing rod.

[0015] In the flexible deployable protective head cover device for a return spacecraft, the number of the package rope cutters is 2-4; the surface of the package rope cutters is covered with a flexible thermal insulation multilayer material, so as to realize the thermal protection in orbit.

[0016] The beneficial effects of the present application compared with the prior art are as follows:

[0017] (1) The application adopts the combined application of the inflatable framework airbag structure and the flexible heat insulation skin structure, forms the flexible deployable protective structure in the orbit deployment, realizes the thermodynamic protection of the shoulder structure of the return type spacecraft, realizes the reuse requirement of the instruments and equipment, and greatly reduces the launch cost of the spacecraft;

[0018] (2) The application is in the folded and packed state during the structure launch, and most of the materials are selected from polymer materials and inorganic heat insulation materials with small density, so that the launch volume and weight are small, and the structure can be stored for a long time and quickly respond;

[0019] (3) The application is a flexible structure, which can adapt to various folding shape, size and other state requirements;

[0020] (4) The application can be popularized to the task requirements of the descending of space cargo products, the hypersonic deceleration of rockets and missiles and the like. BRIEF DESCRIPTION OF DRAWINGS

[0021] Figure 1 is a folded state diagram of the flexible deployment structure of the protective head cover of the application;

[0022] Figure 2 is an expanded state diagram of the flexible deployment structure of the protective head cover of the application;

[0023] Figure 3 is a schematic diagram of the flexible deployment structure of the protective head cover of the application;

[0024] Figure 4 is a layered diagram of the flexible skin structure of the application. DETAILED DESCRIPTION

[0025] The application will be further described below in combination with the embodiments.

[0026] The application provides a flexible deployable protective head cover device for a return type spacecraft, which is launched with the spacecraft and is in a folded and packed state, is inflated and deployed to the position under the driving of an air source in the device before the spacecraft reenters, and is locked at the same time, the structural rigidity is maintained by using the pressure difference between the inside and outside of the structure, and the external high temperature airflow is resisted by using the surface flexible heat protection structure, so that the thermodynamic protection requirement of the shoulder instrument equipment of the return type spacecraft is achieved.

[0027] The flexible deployable protective head cover device for the return type spacecraft, like Figure 1As shown, specifically includes the connection mounting plate 1, locking structure 2, protective head cover flexible deployment structure 3 and package rope cutter 4, wherein the connection mounting plate 1 is horizontally placed disc structure, the upper surface of the connection mounting plate 1 is provided with annular groove concentrically, the locking structure 2 is embedded in the groove uniformly along the circumference, the protective head cover flexible deployment structure 3 is locked on the upper surface of the connection mounting plate 1 after folding, and is located at the annular groove, the package rope cutter 4 is arranged below the protective head cover flexible deployment structure 3.

[0028] The working process of the deployable protective head cover device is as follows:

[0029] The package rope cutter 4 cuts and unlocks the protective head cover flexible deployment structure 3, the protective head cover flexible deployment structure 3 is released and deployed into an inverted disc structure, and is locked in the middle of the upper surface of the connection mounting plate 1 through the locking structure 2, as shown in Figure 2 .

[0030] As shown in Figure 3 , the protective head cover flexible deployment structure 3 includes a skeleton airbag structure 6 and a flexible skin structure 5, wherein the skeleton airbag structure 6 is a concentric double-ring structure, and the flexible skin structure 5 covers the upper surface of the skeleton airbag structure 6.

[0031] The flexible skin structure 5 and the skeleton airbag structure 6 are connected and fixed by buckles and connecting ropes, and are fixed on the connection mounting plate 1 by a fixed pressing sheet 9, the package rope cutter 4 is fixed on the side of the protective head cover flexible deployment structure 3, and the locking structure 2 is uniformly distributed at the groove of the connection mounting plate 1. When the structure works, the package rope cutter 4 is powered to unlock the protective head cover flexible deployment structure 3, then a gas cylinder or a gas generator and other gas source devices supply gas to the skeleton airbag inlet valve 8, and the protective head cover flexible deployment structure 3 is deployed in place under the action of the gas, a pressure difference is established and the shape is maintained, according to the in-place signal, the locking structure 2 is supplied with gas to act, so that the locking structure 2 locks and limits the protective head cover flexible deployment structure 3.

[0032] The double-ring skeleton airbag structure 6 is uniformly provided with a locking connection structure 7 at the bottom of the outer ring in the circumferential direction, the locking connection structure 7 is in one-to-one docking with the locking structure 2 after the protective head cover flexible deployment structure 3 is deployed, so that the protective head cover flexible deployment structure 3 is locked on the upper surface of the connection mounting plate 1.

[0033] The double-ring skeleton airbag structure 6 is provided with a fixed pressing sheet 9 at the bottom of the outer ring, and the folded flexible deployment structure 3 is locked on the connection mounting plate 1 through the fixed pressing sheet 9.

[0034] The double annular skeleton airbag structure 6 is provided with an air inlet valve 8 at the bottom of the outer ring; the air inlet valve 8 is located at the fixed pressing sheet 9; when the package rope cutter 4 unlocks the protective head cover flexible unfolding structure 3, the protective head cover flexible unfolding structure 3 is inflated through the air inlet valve 8, so as to realize the stretching and opening of the protective head cover flexible unfolding structure 3.

[0035] As shown in Figure 4 The flexible skin structure 5 is divided into three layers from top to bottom, which are an ablation-resistant layer 10, a multi-layer heat-insulating layer 11 and a load-bearing layer 12. The ablation-resistant layer 10 is used to withstand the scouring of external high-temperature airflow, and to realize the mechanical protection of the internal structure. The material of the ablation-resistant layer 10 is selected according to the surface temperature, and is a modified glass fiber cloth, an alumina fiber cloth or a quartz fiber cloth high-temperature fabric material. The multi-layer heat-insulating layer 11 is used to insulate the external environmental heat flow, and to realize the thermal protection of the internal structure. The material of the multi-layer heat-insulating layer 11 is selected according to the heat-insulating performance requirement, and is an alumina aerogel heat-insulating felt or a silica aerogel heat-insulating felt flexible heat-insulating material. The load-bearing layer 12 is used to transfer the external aerodynamic force and to fix the ablation-resistant layer 10 and the multi-layer heat-insulating layer 11. The material of the load-bearing layer 12 is selected according to the stress condition, and is an aramid fiber, a polyamide fiber or a polyimide fiber high-strength organic fiber.

[0036] The locking structure 2 itself uses a torsional spring type elastic structure, and realizes the locking and limiting of the protective head cover flexible unfolding structure 3 through the fixed shaft rotation of the swing rod.

[0037] The number of the package rope cutters 4 is 2-4; the surface of the package rope cutters 4 is covered with a flexible heat-insulating multi-layer material, so as to realize the thermal protection in orbit.

[0038] In the present application, the flexible deployment structure 3 of the protective head cover is a flexible deployable protective head cover device main structure, which is used to realize the inflation actuation deployment of the structure, and provides thermodynamic protection for the shoulder instrument equipment of the return type spacecraft. The flexible deployment structure 3 of the protective head cover is composed of a framework airbag structure 6 and a flexible skin structure 5, wherein the framework airbag structure 6 is composed of 2-5 layers of polygonal circular rings, longitudinal support tubes are used to connect between the multiple layers of circular rings, a plurality of locking connection structures 7 with a number of n are uniformly distributed on the bottom circular ring, and the number of edges of the bottom polygonal ring is an integer multiple of n+1; the number of edges of the bottom polygonal ring ranges from 16 to 50, the cross-sectional diameter of the top polygonal circular ring is 0.5-1 times the cross-sectional diameter of the bottom polygonal circular ring, and the longitudinal support tube can be set according to the cross-sectional diameter of the adjacent polygonal circular ring. The material of the framework airbag structure 6 is a fiber coated film material, which can realize airtight and load integrated forming, wherein the fiber can be selected from aramid fiber, nylon fiber, polyimide fiber and other high-strength organic fibers according to the stress condition, and the airtight film can be selected from TPU film, polyimide film, polytetrafluoroethylene film and other airtight organic film materials according to the environmental temperature. The flexible skin structure 5 is composed of an ablation-resistant layer 10, a plurality of thermal insulation layers 11 and a load-bearing layer 12, wherein the ablation-resistant layer 10 is used to withstand the scouring of external high-temperature airflow, and to realize the mechanical protection of the internal structure, and the material thereof can be selected from modified glass fiber cloth, alumina fiber cloth, quartz fiber cloth and other high-temperature resistant fabric materials according to the surface temperature; the plurality of thermal insulation layers 11 are used to insulate the external environmental heat flow, and to realize the thermal protection of the internal structure, and the material thereof can be selected from alumina aerogel insulation felt, silica aerogel insulation felt and other flexible thermal insulation materials according to the thermal insulation performance requirement; the load-bearing layer 12 is used to transfer the external aerodynamic force, to fix the ablation-resistant layer 10 and the plurality of thermal insulation layers 11, and to realize the connection between the flexible skin structure 5 and the framework airbag structure 6, and the material thereof can be selected from aramid fiber, nylon fiber, polyimide fiber and other high-strength organic fibers according to the stress condition.

[0039] The locking structure 2 is used to realize the locking and fixing of the flexible deployment structure 3 of the protective head cover after being deployed in place, and the locking structure 2 is pre-installed on the lower side of the joint plate 1 gap, wherein the gap width can be selected from 20mm to 100mm according to the requirement. When the structure works, the locking structure 2 itself uses the torsional spring type elastic structure, and realizes the locking and limiting of the flexible deployment structure 3 of the protective head cover through the fixed shaft rotation of the swing rod.

[0040] The package rope cutter 4 is used to realize the package release of the flexible deployment structure 3 of the protective head cover, wherein a plurality of cutters are used in parallel to cut a plurality of package ropes respectively, so as to prevent the misdeployment of the flexible deployment structure 3 of the protective head cover. The number of the package rope cutter 4 can be selected from 2-4, and the cutting capacity thereof is determined according to the material strength of the package rope. The surface of the package rope cutter 4 is covered with a flexible thermal insulation multi-layer material, so as to realize the thermal protection in orbit.

[0041] The application adopts the combination of inflatable framework airbag structure and flexible heat insulation skin structure, and through the flexible deployable protective head cover device with small volume, small launch weight and long-term storage, the device is inflated and deployed on the orbit and locked, so that the effective thermodynamic protection of the instrument equipment on the shoulder of the return spacecraft is realized, the repeated use requirement of the instrument equipment is realized, and the spacecraft launch cost is greatly reduced. The application can be popularized to the task requirements of space cargo product descending, rocket missile hypersonic speed deceleration and the like, meets the use requirements of various folding packaging envelopes, greatly improves the task adaptability and replaceability of the structure, and the scheme has the characteristics of innovation, simplicity and high efficiency.

[0042] Although the present application has been disclosed with the above preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents without departing from the spirit and scope of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application without departing from the technical solutions of the present application shall fall within the protection scope of the technical solutions of the present application.

Claims

1. A flexible deployable shielded head cover apparatus for a return vehicle, characterized by: The utility model relates to a kind of deployable protective head cover device, including connecting mounting plate (1), locking structure (2), protective head cover flexible deployment structure (3) and package rope cutter (4);Wherein, connecting mounting plate (1) is horizontally placed disc structure;The upper surface of connecting mounting plate (1) is concentrically provided with annular groove;Locking structure (2) is evenly embedded in the groove along the circumference;Protective head cover flexible deployment structure (3) is locked on the upper surface of connecting mounting plate (1) after folding, and located at annular groove;Package rope cutter (4) is arranged below protective head cover flexible deployment structure (3). The protective head cover flexible deployment structure (3) includes skeleton airbag structure (6) and flexible skin structure (5);Wherein, skeleton airbag structure (6) is concentric double-ring structure;Flexible skin structure (5) covers the upper surface of skeleton airbag structure (6). The double-ring skeleton airbag structure (6) is uniformly provided with locking connection structure (7) at the bottom of outer ring along the circumference;After protective head cover flexible deployment structure (3) is unfolded, locking connection structure (7) is one-to-one with locking structure (2) docking, to realize that protective head cover flexible deployment structure (3) is locked on the upper surface of connecting mounting plate (1). The double-ring skeleton airbag structure (6) is provided with fixed pressing sheet (9) at the bottom of outer ring;Through fixed pressing sheet (9), folded flexible deployment structure (3) is locked on connecting mounting plate (1).

2. A flexible deployable shielded head cover apparatus for a return vehicle as in claim 1, wherein: The working process of the deployable protective head cover device is as follows: Package rope cutter (4) cuts and unlocks protective head cover flexible deployment structure (3);Protective head cover flexible deployment structure (3) releases and unfolds into an inverted disc-shaped structure;Locking structure (2) is locked on the middle part of the upper surface of connecting mounting plate (1).

3. A flexible deployable shielded head cover apparatus for a return vehicle as in claim 2, wherein: The double-ring skeleton airbag structure (6) is provided with air inlet valve (8) at the bottom of outer ring;Air inlet valve (8) is located at fixed pressing sheet (9);When package rope cutter (4) unlocks protective head cover flexible deployment structure (3), air is filled into protective head cover flexible deployment structure (3) through air inlet valve (8), to realize the stretching and opening of protective head cover flexible deployment structure (3).

4. A flexible deployable shielded head cover apparatus for a return vehicle as in claim 3, wherein: The flexible skin structure (5) is divided into three layers, from top to bottom, namely, ablation-resistant layer (10), multi-layer thermal insulation layer (11) and load-bearing layer (12).

5. A flexible deployable shielded head cover apparatus for a return vehicle as in claim 4, wherein: The ablation-resistant layer (10) is used to withstand the scouring of external high-temperature airflow, realize the mechanical protection of the internal structure, and the material is selected according to the surface temperature, such as modified glass fiber cloth, alumina fiber cloth or quartz fiber cloth high-temperature fabric material;The multi-layer thermal insulation layer (11) is used to insulate the external environmental heat flow, and realize the thermal protection of the internal structure, and the material is selected according to the thermal insulation performance requirement, such as alumina aerogel insulation felt and silica aerogel insulation felt flexible thermal insulation material;The load-bearing layer (12) is used to transfer external aerodynamic force and fix the ablation-resistant layer (10) and the multi-layer thermal insulation layer (11);The material of the load-bearing layer (12) is selected according to the stress condition, such as aramid fiber, nylon fiber or polyimide fiber high-strength organic fiber.

6. A flexible deployable shielded head cover apparatus for a return vehicle as in claim 1, wherein: The locking structure (2) itself is a torsional spring type elastic structure, which realizes the locking and limiting of the protective head cover flexible deployment structure (3) through the fixed shaft rotation of the swing rod.

7. A flexible deployable shielded head cover apparatus for a return vehicle as in claim 1, wherein: The number of the package rope cutters (4) is 2-4; the surface of the package rope cutters (4) is covered with flexible heat insulation multi-layer material to realize track heat protection.

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