A multi-payload adaptation device and separation and release method for a launch vehicle

Abstract

A multi-payload adaptation device and separation and release method for a launch vehicle, belonging to the field of aerospace vehicle structures, comprising a rocket connection adapter, a bottom layer payload mounting plate, support columns, connection columns and an upper layer mounting plate; the rocket connection adapter is connected to the launch vehicle, and the bottom layer payload mounting plate is connected to the rocket connection adapter; one ends of the support columns and the connection columns are fixedly connected to the bottom layer payload mounting plate, two connection columns are provided, the upper layer mounting plate is hinged to the other ends of the connection columns, the support columns are used for supporting the non-hinged side of the upper layer mounting plate, and a compression and release mechanism is arranged between the support columns and the upper layer mounting plate, and the compression and release mechanism is used for fixing the upper layer mounting plate and the support columns, or releasing the fixation between the upper layer mounting plate and the support columns. Without changing the external shapes of existing common payloads and the rocket-satellite connection mode, the internal space of the fairing of the launch vehicle is fully utilized, the payload launch efficiency is improved, and the payload launch cost is reduced.

Description

Technical Field

[0001] The present invention relates to a multi-payload adaptation device and separation and release method for a launch vehicle, belonging to the field of aerospace vehicle structure and mechanism design. Background Art

[0002] With the continuous improvement of the carrying capacity of launch vehicles, the internal space of the fairing has gradually increased. In order to reduce the payload launch cost and improve the utilization rate of the internal space of the launch vehicle fairing, the launch mission is usually completed by means of multiple satellites in one launch or piggybacking.

[0003] Typical payload layout schemes for multi-payload launches include series layout, parallel layout, central load-bearing cylinder layout, CubeSat structure layout, etc. Each layout scheme is selected according to the payload size, the internal space of the fairing, and the existing technical foundation. The series layout scheme represented by "Starlink" requires special design of the payload shape and relies on the payload itself to provide series connection interfaces; the parallel layout scheme mainly arranges multiple payloads of the same magnitude (size, weight) side by side on the same installation plane, resulting in insufficient utilization of the internal height direction space of the fairing; the central load-bearing cylinder layout scheme designs a central load-bearing cylinder in the middle of the fairing, and the payload is connected to the side wall of the central load-bearing cylinder through a connecting device. This side-hanging connection method will introduce a large lateral overload, and the central load-bearing cylinder itself needs to occupy a large space; the CubeSat structure layout scheme currently mainly attaches the CubeSat to the side wall of the launch vehicle payload adapter, which is mainly applicable to the connection of small payloads.

[0004] For different magnitudes and types of payloads, without changing the payload fixing method, improving the adaptability of the payload adaptation device, making full use of the internal space of the launch vehicle fairing and the carrying capacity, and reducing the launch cost are problems that urgently need to be solved in this technical field. Summary of the Invention

[0005] The technical problem solved by this application is: to overcome the deficiencies of the prior art and provide a multi-payload adaptation device and separation and release method for a launch vehicle, which can make full use of the internal space of the launch vehicle fairing and improve the payload launch efficiency without changing the existing common payload shape and the star-vehicle connection method, thereby reducing the payload launch cost.

[0006] The technical solution provided by this application is as follows:

[0007] A multi-payload adaptation device for a launch vehicle includes a rocket connection adapter, a bottom payload mounting plate, support columns, connecting columns, and an upper mounting plate;

[0008] The rocket connection adapter is connected to the launch vehicle, and the bottom payload mounting plate is connected to the rocket connection adapter; along the axis direction of the launch vehicle, the upper mounting plate is located on one side of the bottom payload mounting plate;

[0009] One end of the support column and the connecting column is fixedly connected to the bottom load mounting plate. Two connecting columns are provided and are located at both ends of the bottom load mounting plate along the diameter direction of the bottom load mounting plate. The upper mounting plate is hinged to the other end of the connecting column, and the hinge axis of the upper mounting plate is perpendicular to the axis of the launch vehicle.

[0010] At least two support columns are provided. The support columns are used to support the non-hinged side of the upper mounting plate. A compression and release mechanism is provided between the support columns and the upper mounting plate. The compression and release mechanism is used to fix the upper mounting plate to the support columns or release the fixation between the upper mounting plate and the support columns.

[0011] The lower load is connected to the bottom load mounting plate, and the upper load is connected to the upper mounting plate.

[0012] The upper mounting plate includes a semi-circular upper load mounting plate A and upper load mounting plate B; the straight sides of the upper load mounting plate A and upper load mounting plate B are opposite and are both hinged to the ends of the two connecting columns.

[0013] The support columns are used to support the non-hinged side of the upper load mounting plate A or upper load mounting plate B. A compression and release mechanism is provided between the support columns and the upper load mounting plate A and / or upper load mounting plate B. The compression and release mechanism is used to fix the upper load mounting plate A and / or upper load mounting plate B to the support columns or release the fixation between the upper load mounting plate A and / or upper load mounting plate B and the support columns.

[0014] Both between the upper load mounting plate A and the support column and between the upper load mounting plate B and the support column are connected by spring hinges; after the compression and release mechanism releases the fixation between the upper mounting plate and the support column, the spring hinges drive the non-hinged ends of the upper load mounting plate A and upper load mounting plate B to rotate 90° in a direction away from the bottom load mounting plate until the upper load mounting plate A and upper load mounting plate B are parallel to the axis of the launch vehicle, and the positions of the upper load mounting plate A and upper load mounting plate B are locked.

[0015] The surface of the bottom load mounting plate facing the upper mounting plate is fixedly connected with a bottom load adapter, and the surface of the upper mounting plate facing away from the bottom load mounting plate is fixedly connected with an upper load adapter.

[0016] The upper load mounting plate A is provided with a first avoidance hole for avoiding the adapter on the upper load mounting plate B during closing, and the upper load mounting plate B is provided with a second avoidance hole for avoiding the adapter on the upper load mounting plate A during closing.

[0017] The bottom load adapter and the upper load adapter are selected from existing load adapters.

[0018] Notches are provided at the relative positions of the straight edges of the upper payload mounting plate A and the upper payload mounting plate B, and the notches together form an intermediate hole.

[0019] A method for separating and releasing multiple payloads of a launch vehicle, based on any one of the above-mentioned launch vehicle multi-payload adaptation devices, includes:

[0020] In the initial launch state, the compression and release mechanism locks the upper mounting plate and the support column, the lower payload is connected to the bottom payload mounting plate, the upper payload is connected to the upper mounting plate, and the fairing is sleeved outside the multi-payload adaptation device and connected to the launch vehicle;

[0021] The fairing is first separated from the launch vehicle. After entering the predetermined orbit, the upper payload is separated and released upward along the axis of the launch vehicle. After the upper payload is separated and released to a safe distance, the compression and release mechanism is activated to disconnect the connection between the upper payload mounting plate A, the upper payload mounting plate B and the support column. Driven by the spring hinge, the upper payload mounting plate A and the upper payload mounting plate B rotate 90° around the spring hinge rotation shaft, and then the positions of the upper payload mounting plate A and the upper payload mounting plate B are locked; after the upper payload mounting plate A and the upper payload mounting plate B are folded and locked in position, the lower payload is separated and released simultaneously in an obliquely upward direction.

[0022] In summary, the present application includes at least the following beneficial technical effects:

[0023] 1) Usually, there is a large amount of remaining space above the fairing. The present invention divides the internal space of the fairing into upper and lower layers, improving the utilization rate of the internal space of the fairing.

[0024] 2) Compared with the traditional side-hanging multiple satellites layout of the central load-bearing cylinder, the present invention cancels the central load-bearing cylinder and distributes the main load-bearing structure around, which can accommodate larger-sized payload installations.

[0025] 3) The present invention fully inherits the existing payload connection method, does not require modification of the payload shape and the satellite-rocket interface, and has strong versatility.

[0026] 4) The payload layout scheme of the present invention makes the main overload direction during the launch process of the launch vehicle still along the original main load-bearing direction of the payload, without introducing additional lateral overload. Description of the Drawings

[0027] Figure 1 It is a schematic diagram of the composition of a launch vehicle multi-payload adaptation device of the present invention;

[0028] Figure 2 It is a schematic diagram of the usage scenario of a launch vehicle multi-payload adaptation device of the present invention;

[0029] Figure 3This is a schematic diagram of the payload separation and release process of a multi-payload adaptation device for a launch vehicle according to the present invention.

[0030] Explanation of reference numerals: rocket connection adapter 1-1, bottom payload mounting plate 1-2, support column 1-3, bottom payload adapter 1-4, upper payload mounting plate A 1-5, upper payload mounting plate B 1-6, compression and release mechanism 1-7, upper payload adapter 1-8, spring hinge 1-9, connection column 1-10;

[0031] Upper payload 3; lower payload 2; first avoidance hole 1-5-1; second avoidance hole 1-6-1. Detailed implementation manners

[0032] To make the objectives, technical solutions and advantages of the present invention clearer, the following will further describe in detail the disclosed implementation manners of the present invention with reference to the accompanying drawings.

[0033] As Figure 1 shown, this embodiment provides a multi-payload adaptation device for a launch vehicle. As Figure 1 shown, the device includes: rocket connection adapter 1-1, bottom payload mounting plate 1-2, support column 1-3, bottom payload adapter 1-4, upper payload mounting plate A 1-5, upper payload mounting plate B 1-6, compression and release mechanism 1-7, upper payload adapter 1-8, spring hinge 1-9 and connection column 1-10.

[0034] The rocket connection adapter 1-1 provides a connection interface for the multi-payload adaptation device and the launch vehicle, is fixedly connected to the launch vehicle, and supports the entire multi-payload adaptation device. The bottom payload mounting plate 1-2 is fixedly connected to the rocket connection adapter 1-1. The bottom payload adapter 1-4 is fixedly connected to the bottom payload mounting plate 1-2 and provides a connection interface for the bottom payload. One end of the support column 1-3 and the connection column 1-10 is fixedly connected to the bottom payload mounting plate 1-2. Two connection columns 1-10 are provided and are located at both ends of the bottom payload mounting plate 1-2 along the diameter direction of the bottom payload mounting plate 1-2. The semi-circular upper payload mounting plate A 1-5 and upper payload mounting plate B 1-6 are hinged to the other end of the connection column 1-10, and the hinge axis is perpendicular to the axis of the launch vehicle. At least two support columns 1-3 are provided. The support column 1-3 is used to support the non-hinged sides of the upper payload mounting plate A 1-5 and the upper payload mounting plate B 1-6. The support column 1-3 and the connection column 1-10 are the longitudinal main load-bearing structures of the entire multi-payload adaptation device. In this embodiment, 2 support columns 1-3 and 2 connection columns 1-10 are evenly distributed around the bottom payload mounting plate 1-2, are fixedly connected to the rocket connection adapter 1-1 at the bottom, and are connected to the upper payload mounting plate A 1-5 and the upper payload mounting plate B 1-6 at the top.

[0035] The upper payload mounting plates A1-5 and B1-6 are both semi-circular. The upper payload mounting plate A1-5 is designed with a first avoidance hole 1-5-1 to avoid the adapter on the upper payload mounting plate B1-6 during closure. The upper payload mounting plate B1-6 is designed with a second avoidance hole 1-6-1 to avoid the adapter on the upper payload mounting plate A1-5 during closure. The straight edges of the upper payload mounting plates A1-5 and B1-6 are connected by 4 spring hinges 1-9, and the rotating shafts of the spring hinges 1-9 are fixedly connected to two opposite support columns 1-3. The crowns of the upper payload mounting plates A1-5 and B1-6 are respectively connected to the tops of the opposite support columns 1-3 through compression and release mechanisms 1-7; the compression and release mechanisms 1-7 can be explosive bolts or electromagnetic release structures. After the compression and release mechanisms 1-7 release the compression points, the spring hinges 1-9 can drive the upper payload mounting plates A1-5 and B1-6 to rotate upward by 90° around the rotating shafts of the spring hinges 1-9, and then lock the positions of the upper payload mounting plates A1-5 and B1-6. The upper payload adapter 1-8 is fixedly connected to the upper payload mounting plates A1-5 and B1-6 to provide a mounting interface for the upper payload.

[0036] The height of the support columns 1-3 can be appropriately adjusted within the internal envelope of the fairing according to the payload requirements to adapt to the installation requirements of different-sized payloads.

[0037] The bottom payload adapter 1-4 and the upper payload adapter 1-8 can select existing payload adapters, so as not to change the connection interface between the existing payload and the launch vehicle, and their quantity and positions can be adjusted according to the payload requirements.

[0038] Notches are provided at the relative positions on the straight-edge sides of the upper payload mounting plates A1-5 and B1-6, and the notches form an intermediate hole together for weight reduction. During installation, observation can be carried out through the intermediate hole, and at the same time, wiring is facilitated through this hole.

[0039] Figure 2 This is a schematic diagram of the usage scenario of a multi-payload adaptation device for a launch vehicle according to the present invention. The upper payload 3 is the main payload, and the lower payloads 2 are 4 carried payloads. In the launch state, the fairing 4 is connected to the launch vehicle and sleeved outside the multi-payload adaptation device, so that the entire multi-payload adaptation device and its payloads are wrapped inside the fairing 4.

[0040] Figure 3This is a schematic diagram of the payload separation and release process of a multi-payload adaptation device for a launch vehicle of the present invention. After the launch vehicle is launched and the influence of the airflow can be ignored, the fairing 4 is separated from the launch vehicle; then, after the multi-payload adaptation device enters the predetermined orbit, the upper payload 3 is separated and released upward along the axis of the launch vehicle. After the upper payload 3 is separated and released to a safe distance, the two clamping and release mechanisms 1-7 are activated to disconnect the connection between the upper payload mounting plate A1-5 and the upper payload mounting plate B1-6 and the support column 1-3. Driven by the 4 spring hinges 1-9, the upper payload mounting plate A1-5 and the upper payload mounting plate B1-6 rotate upward by 90° around the axis of the spring hinge 1-9, and then the positions of the upper payload mounting plate A1-5 and the upper payload mounting plate B1-6 are locked. After the upper payload mounting plate A1-5 and the upper payload mounting plate B1-6 are folded and locked in position, the 4 bottom payloads 3 are separated and released simultaneously in the obliquely upward direction.

[0041] The content not described in detail in the specification of this application belongs to the well-known technology of those skilled in the art.

[0042] The above has described this application in detail in combination with specific implementation manners and exemplary examples, but these descriptions should not be construed as limitations on this application. Those skilled in the art understand that without departing from the spirit and scope of this application, various equivalent substitutions, modifications or improvements can be made to the technical solutions and their implementation manners of this application, and these all fall within the scope of this application. The protection scope of this application is subject to the appended claims.

Claims

1. A multi-payload adaptation device for a launch vehicle, characterized in that: It includes a rocket connection adapter (1-1), a bottom payload mounting plate (1-2), support columns (1-3), connection columns (1-10) and an upper mounting plate. The upper mounting plate includes a semi-circular upper payload mounting plate A (1-5) and an upper payload mounting plate B (1-6); the straight sides of the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) are opposite to each other and are both hinged to the ends of the two connection columns (1-10). The rocket connection adapter (1-1) is connected to the launch vehicle, and the bottom payload mounting plate (1-2) is connected to the rocket connection adapter (1-1); along the axis direction of the launch vehicle, the upper mounting plate is located on one side of the bottom payload mounting plate (1-2); one ends of the support columns (1-3) and the connection columns (1-10) are fixedly connected to the bottom payload mounting plate (1-2). There are two connection columns (1-10), and they are located at both ends of the bottom payload mounting plate (1-2) along the diameter direction of the bottom payload mounting plate (1-2). The upper mounting plate is hinged to the other ends of the connection columns (1-10), and the hinge axis of the upper mounting plate is perpendicular to the axis of the launch vehicle. There are at least two support columns (1-3). The support columns (1-3) are used to support the non-hinged sides of the upper payload mounting plate A (1-5) or the upper payload mounting plate B (1-6). A compression and release mechanism (1-7) is provided between the support columns (1-3) and the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6). The compression and release mechanism (1-7) is used to fix the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) to the support columns (1-3), or to release the fixation between the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) and the support columns (1-3). The lower payload (2) is connected to the bottom payload mounting plate (1-2), and the upper payload (3) is connected to the upper mounting plate.

2. The multi-payload adaptation device for a launch vehicle according to claim 1, characterized in that: Both between the upper payload mounting plate A (1-5) and the connection column (1-10) and between the upper payload mounting plate B (1-6) and the connection column (1-10) are connected by spring hinges (1-9); after the compression and release mechanism (1-7) releases the fixation between the upper mounting plate and the support column (1-3), the spring hinges (1-9) drive the non-hinged ends of the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) to rotate 90° in the direction away from the bottom payload mounting plate (1-2) until the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) are parallel to the axis of the launch vehicle, and the positions of the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) are locked.

3. The multi-payload adaptation device for a launch vehicle according to claim 1, characterized in that: A bottom payload adapter (1-4) is fixedly connected to the surface of the bottom payload mounting plate (1-2) facing the upper mounting plate, and an upper payload adapter (1-8) is fixedly connected to the surface of the upper mounting plate facing away from the bottom payload mounting plate (1-2).

4. The multi-payload adaptation device for a launch vehicle according to claim 3, characterized in that: The upper payload mounting plate A (1-5) is provided with a first avoidance hole (1-5-1) for avoiding the adapter on the upper payload mounting plate B (1-6) during closure. The upper payload mounting plate B (1-6) is provided with a second avoidance hole (1-6-1) for avoiding the adapter on the upper payload mounting plate A (1-5) during closure.

5. The multi-payload adaptation device for a launch vehicle according to claim 3, wherein: The bottom payload adapter (1-4) and the upper payload adapter (1-8) are selected from existing payload adapters.

6. The multi-payload adaptation device for a launch vehicle according to claim 1, wherein: Notches are provided at the relative positions of the straight edges of the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6), and the notches together form an intermediate hole.

7. A method for separating and releasing multiple payloads of a launch vehicle, characterized in that, A multi-payload adaptation device for a launch vehicle according to any one of claims 1-6, comprising: In the initial launch state, the clamping and release mechanism (1-7) locks the upper mounting plate and the support column (1-3). The lower payload (2) is connected to the bottom payload mounting plate (1-2), the upper payload (3) is connected to the upper mounting plate, and the fairing (4) is sleeved outside the multi-payload adaptation device and connected to the launch vehicle. After the fairing (4) is first separated from the launch vehicle and enters the predetermined orbit, the upper payload (3) is separated and released upward along the axis of the launch vehicle. After the upper payload (3) is separated and released to a safe distance, the clamping and release mechanism (1-7) is activated to disconnect the connection between the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) and the support column (1-3). Driven by the spring hinge (1-9), the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) rotate 90° around the axis of the spring hinge (1-9), and then the positions of the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) are locked. After the upper payload mounting plate A (1-5) and the upper payload mounting plate B (1-6) are closed and their positions are locked, the lower payload (2) is separated and released simultaneously in an obliquely upward direction.

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