A mechanism and method for deploying and retracting aerospace vehicle doors based on cable deployment and retraction.

Abstract

This invention discloses a cable-based hatch deployment and retraction mechanism for aerospace vehicles, comprising a pulley system mounted on one side of the hatch's free edge and a hatch rotation drive device mounted at the hatch's pivot point. The pulley system includes a fixed pulley system mounted on a support structure below the hatch's free edge and a movable pulley system mounted on the hatch's free edge. One end of the cable is fixedly connected to the support structure, and the other end of the cable passes through the pulley system and connects to the cable deployment and retraction drive device. The hatch rotation drive device provides rotational torque in the hatch's opening direction. When the cable deployment and retraction drive device retracts the cable, the hatch rotates to close; when the cable deployment and retraction drive device releases the cable, the hatch rotates to open under the rotational torque. This invention features lightweight, small footprint, simple and reliable structure, and precise opening control.

Description

Technical Field

[0001] This invention belongs to the fields of aerospace and mechanical structure technology, and specifically relates to a mechanism and method for deploying and retracting cabin doors of aerospace vehicles based on cable deployment and retraction. Background Technology

[0002] Deployable and retractable hatches (hereinafter referred to as "hatches") serve as channels for space payloads to enter and exit aerospace vehicles, or as load-bearing structures for equipment such as battery arrays and radiators. During the vehicle's on-orbit operation, they need to be easily and quickly opened, and precisely controlled to remain at any opening angle within the maximum opening angle range to ensure the smooth implementation of relevant space missions. During atmospheric reentry, the hatches need to remain reliably closed to ensure the vehicle maintains a good aerodynamic shape and protect the payloads inside. Therefore, a lightweight, reliable, and precisely controllable hatch deployment and retraction mechanism needs to be designed. Simultaneously, due to the limited space in aerospace vehicles, the scanned space of the hatch deployment and retraction mechanism needs to be minimized. Since the entire vehicle is in a weightless environment in orbit when the hatch deployment and retraction mechanism is operating, the gravity of the hatch structure does not need to be considered; therefore, the load-bearing capacity requirement of the deployment and retraction mechanism is relatively low, only requiring the ability to deploy and retract the hatch structure in the space environment. Traditional four-link deployment and retraction mechanisms with a center-seam lock have a large scanned space, require multiple drive devices, are complex, heavy, have low reliability, and are costly. Summary of the Invention

[0003] The purpose of this invention is to provide a mechanism and method for deploying and retracting aerospace vehicle doors based on cable retraction. This invention features lightweight construction, small footprint, simple and reliable structure, and precise opening control.

[0004] The technical solution of this invention is as follows: A door deployment and retrieval mechanism for aerospace vehicles based on cable retraction and release, comprising a pulley assembly installed on one side of the door's free side and a door rotation drive device installed at the door's pivot point; the pulley assembly includes a fixed pulley assembly installed on a support structure below the door's free side and a movable pulley assembly installed at the door's free side; one end of the support structure is fixedly connected to the cable, and the other end of the cable passes through the pulley assembly and is connected to the cable deployment and retrieval drive device; the door rotation drive device provides rotational torque in the door's opening direction; when the cable deployment and retrieval drive device retracts the cable, the door rotates to close; when the cable deployment and retrieval drive device releases the cable, the door rotates to open under the action of rotational torque.

[0005] In the aforementioned aerospace vehicle door retraction and deployment mechanism based on cable retraction and deployment, the fixed pulley group includes pulley A, pulley B, pulley C, and pulley D. Pulleys B and C are coaxially arranged along the length of the support structure; pulleys A and D are arranged along the length of the support structure, with the axes of pulleys A and D perpendicular to the axes of pulleys B and C, and pulleys B and C located above pulleys A and D respectively.

[0006] In the aforementioned aerospace vehicle hatch retraction mechanism based on cable retraction, the movable pulley group includes pulley E, which is connected to a pulley rotating box. The pulley rotating box is connected to the free side of the hatch via a support lug E. The axis of pulley E is perpendicular to the axes of pulleys B and C, and the axis of support lug E is parallel to the axes of pulleys B and C. The pulley rotating box can rotate around the axis of support lug E. The other end of the cable passes through the pulleys in the pulley group in the following order: pulley D, pulley C, pulley E, pulley B, and pulley A.

[0007] In the aforementioned aerospace vehicle door retraction and extension mechanism based on cable retraction and extension, pulleys A, B, C, and D are respectively fixed to the support structure via support lugs A, B, C, and D.

[0008] In the aforementioned aerospace vehicle door retraction and extension mechanism based on cable retraction and extension, the door rotation drive device is in the form of a passive spring or a rotary actuator.

[0009] In the aforementioned aerospace vehicle door deployment and retraction mechanism based on cable deployment and retraction, there is one or more pulley groups along the length of the support structure, and the other end of the cable passes through each pulley group in sequence and is connected to the cable deployment and retraction drive device.

[0010] In the aforementioned aerospace vehicle door retraction mechanism based on cable retraction, the cable remains taut throughout the door retraction process.

[0011] A method for using a spacecraft door deployment and retrieval mechanism based on cable winding and unwinding, as described above, involves the following steps: when closing the door, a cable winding and unwinding drive device winds up the cable and pulls the door to rotate around a pivot to close it; when opening the door, the cable winding and unwinding drive device releases the cable, and the door rotates open under the action of rotational torque; during the opening / closing process of the door, a pulley system is used to adjust the direction of cable movement and simultaneously bear the cable load.

[0012] The beneficial effects of the present invention are as follows: 1. The present invention designs a lightweight, simple structure, and space-saving cable-based aerospace vehicle door opening and closing mechanism that can meet the requirements of large-angle opening and closing of aerospace vehicle doors and can achieve precise control of any opening angle.

[0013] 2. Compared with traditional four-bar linkage and other types of rotary drive mechanisms, the hatch rotary drive device of the present invention has a simple structure, no motion sweep space, occupies little space, and is suitable for various hatch structures with limited space.

[0014] 3. The entire mechanism of the present invention can achieve precise control over the arbitrary opening angle of the hatch.

[0015] 4. During the hatch opening and closing process, the hatch rotation drive device always exerts a rotational torque on the hatch in the opening direction, and the cable winding and unwinding drive device always provides a reverse constraint on the hatch through the cable. Together, they provide a constraint on the hatch opening angle, which can always maintain the stability of the hatch opening angle and prevent the hatch from vibrating.

[0016] 5. The entire mechanism of this invention has a simple structure, is lightweight, easy to operate, and has high reliability.

[0017] 6. This invention is highly scalable and can be adapted to various deployment and retraction methods, such as single hatch opening and left and right hatch opening opposite each other, with slight modifications.

[0018] 7. The cable winding and unwinding drive device of the present invention only needs to realize the rotation winding and unwinding of the cable. It has a single function, simple structure, can be implemented by selecting a variety of simple motor products, occupies little space, has high reliability, and low cost. Attached Figure Description

[0019] Figure 1 This is a side view of the hatch with the door closed.

[0020] Figure 2 This is a top view with the hatch closed;

[0021] Figure 3 This is an isometric view of the hatch with the door closed.

[0022] Figure 4 This is a side view of the hatch with the door open.

[0023] Figure 5 This is a top view of the hatch with the doors open.

[0024] Figure 6 It is an isometric view of the hatch in the deployed state;

[0025] Figure 7 It is a pulley block and cable winding drive device in the closed state of the hatch;

[0026] Figure 8 It consists of the fixed pulley assembly and cables for the hatch in its open position;

[0027] Figure 9 It refers to the movable pulley assembly and cables in the open state of the hatch;

[0028] Figure 10 It is a door rotation drive device (taking a spring as an example, but it can be other rotary actuators). Detailed Implementation

[0029] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0030] Example 1. See also Figures 1-10 It consists of four parts: cable winding and unwinding drive device 2, pulley block 3, door rotation drive device 5, and cable 7.

[0031] The pulley system 3 consists of two parts: a fixed pulley system 8 and a movable pulley system 9. The fixed pulley system 8 includes four pulleys 11, 12, 16, and 18, which are fixed to the support structure 1 below the free side of the hatch 4 by support lugs 10, 17, 18, and 20, respectively. The movable pulley system 9 consists of pulley 14 and pulley rotating box 13, which are fixed to the free side of the hatch 4 by support lugs 15. When the hatch 4 is closed, the movable pulley system 9 is located above the fixed pulley system 8. During the opening of the hatch 4, the movable pulley system 9 moves with the hatch, and at the same time, the pulley rotating box 13 rotates with the hatch 4 to ensure that the movable pulley system 9 is always aligned with the direction of the cable 7.

[0032] The cable winding and unwinding drive device 2 is installed inside the machine body, located next to the fixed pulley group 8. The cable winding and unwinding device 2 can wind and unwind the cable 7 by rotating.

[0033] The hatch rotation drive device 5 is installed at the pivot of the hatch 4. It can be a passive spring 23 or a rotary actuator or other device that can achieve rotation. The hatch rotation drive device 5 always outputs a rotational torque in the opening direction, causing the hatch 4 to rotate around the pivot 24 in the opening direction.

[0034] Several fixed pulley groups 8 and movable pulley groups 9, along with several door rotation drive devices 5, can be arranged along the length of the hatch 4 as needed. The fixed pulley groups 8 and movable pulley groups 9 change the direction of movement of the cable 7 and bear the load of the cable 7. The entire mechanism controls the length of the cable 7 and the opening angle of the hatch through the cable winding and unwinding drive device 2. During the opening and closing of the hatch 4, the cable 7 is always taut. When the cable 7 is at its shortest length, the hatch 4 is closed; when the cable 7 is at its longest length, the hatch 4 reaches its maximum opening angle.

[0035] Example 2. A cable-based aerospace vehicle door deployment and retraction mechanism, see [link / reference]. Figures 1-10The device includes a pulley assembly 3 installed on one side of the free side of the hatch 4 and a hatch rotation drive device 5 installed at the pivot of the hatch 4. The pulley assembly 3 includes a fixed pulley assembly 8 installed on the support structure 1 below the free side of the hatch 4 and a movable pulley assembly 9 installed on the free side of the hatch 4. The support structure 1 is fixedly connected to one end of the cable 7, and the other end of the cable 7 passes through the pulley assembly 3 and is connected to the cable winding and unwinding drive device 2. The hatch rotation drive device 5 is used to provide rotational torque in the direction of opening the hatch 4. When the cable winding and unwinding drive device 2 winds up the cable, the hatch 4 rotates to close. When the cable winding and unwinding drive device 2 unwinds the cable, the hatch 4 rotates to open under the action of rotational torque.

[0036] The aforementioned fixed pulley group 8 includes pulley A11, pulley B12, pulley C16, and pulley D19. Pulleys B and C are coaxially arranged along the length of the support structure 1; pulleys A and D are arranged along the length of the support structure 1, with the axes of pulleys A and D perpendicular to the axes of pulleys B and C, and pulleys B and C located above pulleys A and D respectively.

[0037] The aforementioned movable pulley group 9 includes pulley E14, which is connected to pulley rotating box 13. Pulley rotating box 13 is connected to the free side of hatch 4 via support lug E15. The axis of pulley E14 is perpendicular to the axes of pulleys B and C, and the axis of support lug E15 is parallel to the axes of pulleys B and C. Pulley rotating box 13 can rotate around the axis of support lug E15. The other end of cable 7 passes through the pulleys in pulley group 3 in the following order: pulley D19, pulley C16, pulley E14, pulley B12, and pulley A11.

[0038] The aforementioned pulleys A11, B12, C16, and D19 are fixed to the support structure 1 by support lugs A10, B18, C17, and D20, respectively.

[0039] The aforementioned hatch rotation drive device 5 is in the form of a passive spring 23, or a rotation actuator. For example... Figure 10 Taking the passive spring 23 as an example, a set of more than one set of supports A21, supports B22 and rotating shaft 24 for connecting the hatch 4 and the fuselage are designed along the length direction on the rotating support structure 6 on the fuselage. The passive spring 23 is then fitted on the rotating shaft 24 to provide rotational torque in the opening direction.

[0040] The aforementioned pulley group 3 has one or more sets along the length of the support structure 1, and the other end of the cable 7 passes through each set of pulley groups 3 in sequence and is connected to the cable winding and unwinding drive device 2.

[0041] The aforementioned cable 7 remains taut throughout the extension and retraction of the hatch 4.

[0042] The aforementioned method of using the cable winding and unwinding mechanism for aerospace vehicle doors involves the following steps: when closing the door 4, the cable winding and unwinding drive device 2 winds up the cable 7, pulling the door 4 to rotate around the pivot and close it; when opening the door 4, the cable winding and unwinding drive device 2 releases the cable, and the door 4 rotates open under the action of rotational torque; during the opening / closing process of the door 4, the pulley block 3 is used to adjust the direction of movement of the cable 7 and at the same time bear the load of the cable 7.

[0043] like Figure 1 and Figure 2 As shown, the cable-based aerospace vehicle door deployment and retrieval mechanism consists of four parts: a cable deployment and retrieval drive device 2, a pulley system 3, a door rotation drive device 5, and a cable 7. Several pulley systems 3 and several door rotation drive devices 5 can be arranged along the length of the door 4 according to actual needs. Figure 5 The diagram shows the configuration of four sets of pulleys; in addition, to increase the space passage for space payloads to enter and exit the spacecraft, pulleys may also be installed at only one or both ends of the hatch.

[0044] like Figure 7 The pulley system 3 consists of two parts: a fixed pulley system 8 and a movable pulley system 9. The fixed pulley system 8 is as follows: Figure 8 It includes four pulleys 11, 12, 16, and 18, which are fixed to the support structure 1 below the free side of the hatch 4 via support lugs 10, 17, 18, and 20 respectively; the movable pulley group 9 is as follows Figure 9 It consists of pulley 14 and pulley box 13, which are combined and fixed to the lower free side of hatch 4 by support lugs 15; when hatch 4 is closed, the movable pulley group 9 is located above the fixed pulley group 8, as shown in the figure. Figure 3 and Figure 7 During the unfolding of hatch 4, the movable pulley assembly 9 moves with the hatch, and simultaneously, the pulley rotating box 13 rotates with hatch 4 to ensure that the movable pulley assembly 9 remains aligned with the direction of cable 7. Figure 6 and Figure 9 .

[0045] The hatch rotation drive device 5 is installed at the hinge of the hatch 4, such as... Figure 1 and Figure 3 Its form can be a passive spring 23, or a rotary actuator or other device that can achieve rotation. The hatch rotation drive device 5 always outputs a rotational torque in the opening direction, causing the hatch 4 to rotate around the pivot 24 in the opening direction. The cable retraction drive device 2 is installed inside the fuselage, located next to the fixed pulley block 8, such as... Figure 8 The cable winding device 2 can wind up and wind up the cable 7 by rotating it.

[0046] Throughout the entire operation of the mechanism, the fixed pulley block 8 and the movable pulley block 9 serve to change the direction of movement of the cable 7 and simultaneously bear the load on the cable 7. The cable winding and unwinding drive device 2 controls the winding and unwinding length of the cable 7 and controls the opening angle of the hatch. When the cable winding and unwinding drive device 2 releases the cable, the hatch 4 unfolds under the action of the rotary drive device 5. When the cable winding and unwinding drive device 2 retracts the cable, the opening angle of the hatch 4 decreases until it closes. During the opening and unwinding process of the hatch 4, the cable 7 remains taut, which can maintain the stability of the opening angle of the hatch 4 and prevent the hatch 4 from vibrating.

[0047] The above description is merely a specific embodiment of the present invention, providing a detailed description of the invention. Parts not covered herein are conventional techniques. However, the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in the present invention should be included within the scope of protection of the present invention. The scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A cable-based aerospace vehicle door deployment and retraction mechanism, characterized in that, It includes a pulley assembly (3) installed on one side of the free side of the hatch (4) and a hatch rotation drive device (5) installed at the pivot of the hatch (4); the pulley assembly (3) includes a fixed pulley assembly (8) installed on the support structure (1) below the free side of the hatch (4) and a movable pulley assembly (9) installed at the free side of the hatch (4); the support structure (1) is fixedly connected to one end of the cable (7), and the other end of the cable (7) passes through the pulley assembly (3) and is connected to the cable winding and unwinding drive device (2); the hatch rotation drive device (5) is used to provide rotational torque in the direction of opening the hatch (4); When the cable winding and unwinding drive device (2) winds up the cable, the hatch (4) rotates and closes. When the cable winding and unwinding drive device (2) unwinds the cable, the hatch (4) rotates and opens under the action of rotational torque.

2. The aerospace vehicle door deployment and retraction mechanism based on cable retraction as described in claim 1, characterized in that, The fixed pulley group (8) includes pulley A (11), pulley B (12), pulley C (16), and pulley D (19). Pulleys B and C are coaxially arranged along the length of the support structure (1). Pulleys A and D are arranged along the length of the support structure (1), and the axes of pulleys A and D are perpendicular to the axes of pulleys B and C. Pulleys B and C are located above pulleys A and D, respectively.

3. The aerospace vehicle door deployment and retraction mechanism based on cable retraction as described in claim 2, characterized in that, The movable pulley group (9) includes pulley E (14), which is connected to pulley rotating box (13). The pulley rotating box (13) is connected to the free side of the hatch (4) via support lug E (15). The axis of pulley E (14) is perpendicular to the axes of pulleys B and C, and the axis of support lug E (15) is parallel to the axes of pulleys B and C. The pulley rotating box (13) can rotate around the axis of support lug E (15). The other end of the cable (7) passes through the pulleys in the pulley group (3) in the following order: pulley D (19), pulley C (16), pulley E (14), pulley B (12), and pulley A (11).

4. The aerospace vehicle door deployment and retraction mechanism based on cable retraction as described in claim 2, characterized in that, The pulleys A (11), B (12), C (16), and D (19) are fixed to the support structure (1) by means of support lugs A (10), B (18), C (17), and D (20), respectively.

5. The aerospace vehicle door deployment and retraction mechanism based on cable retraction as described in claim 1, characterized in that, The door rotation drive (5) is in the form of a passive spring (23) or a rotary actuator.

6. The aerospace vehicle hatch deployment and retraction mechanism based on cable retraction as described in claim 1, characterized in that, The pulley group (3) is provided in more than one group along the length of the support structure (1). The other end of the cable (7) passes through each pulley group (3) in sequence and is connected to the cable winding and unwinding drive device (2).

7. The aerospace vehicle hatch deployment and retraction mechanism based on cable retraction as described in claim 1, characterized in that, The cable (7) remains taut throughout the deployment and retraction process of the hatch (4).

8. A method of using a cable-based aerospace vehicle door deployment and retraction mechanism as described in any one of claims 1-7, characterized in that, When the hatch (4) is closed, the cable winding drive device (2) winds up the cable (7) and pulls the hatch (4) to rotate around the pivot and close it; When the hatch (4) is opened, the cable winding and unwinding drive device (2) rotates and opens the cable unwinding hatch (4) under the action of rotational torque; during the opening / closing process of the hatch (4), the pulley block (3) is used to adjust the direction of movement of the cable (7) and bear the load of the cable (7).

Images