A driving device

Abstract

An embodiment of the present application discloses a driving device, which is fixed on the inner side wall of the fairing; the driving device has a contracted state and a deployed state; it further includes: a driving plate; at least two telescopic belts fixedly connected to the edge of the driving plate; one end of the telescopic belt far from the driving plate is connected with a driver; the number of drivers is equal to that of the telescopic belts and they correspond one by one; when the driving device is in the deployed state, the driving plate and the telescopic belts enclose an accommodation space for accommodating the satellite, and the top of the satellite abuts against the driving plate; when the satellite needs to be separated from the fairing, the driver drives the driving plate to move towards the end of the driver through the telescopic belt, the driving plate pushes the satellite, and the satellite is pushed out of the fairing, and the driving device is in the contracted state. The driving device provided by the present application does not use pyrotechnics, has high test safety, low cost, simple test operation, and the test effect is basically consistent with the actual separation effect.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and more specifically, this application relates to a driving device. Background Art

[0002] The function of the fairing is to enable the rocket to have a good aerodynamic shape during the ascent in the atmosphere and provide good force and heat conditions for the internal satellite. After the rocket flies out of the atmosphere, the fairing needs to be separated from the upper stage to release the internal satellite. The fairing separation process is a key step affecting the success of satellite launch. Fairing separation is usually divided into split separation and integral separation. The fairing for split separation consists of two symmetrical parts, and the two parts are connected by pyrotechnics distributed on the interface. After the pyrotechnics are detonated, a separation force is provided by a spring to drive the two half-fairings to separate to both sides, realizing fairing separation; after the connection between the integral-separation fairing and the satellite tail is disconnected, a separation force is provided by a spring or a pneumatic device to realize fairing separation. Large rockets generally adopt the split separation method, and some small rockets will adopt the integral separation method. The key to integral separation is to provide the fairing with sufficient longitudinal speed to ensure that it can quickly separate from the satellite by a certain distance.

[0003] However, the integral separation method requires the fairing to have a large longitudinal relative speed in a short time. Therefore, a relatively complex driving mechanism is required, usually driven by a spring and a jet engine. These mechanisms are usually complex in structure, high in cost, and difficult to be reused multiple times. Summary of the Invention

[0004] The purpose of the present invention is to provide a driving device to solve at least one of the above technical problems.

[0005] To achieve at least one of the above purposes, this application adopts the following technical solutions:

[0006] This application provides a driving device, which is fixed on the inner side wall of the fairing;

[0007] The driving device includes a contracted state and an expanded state;

[0008] It further includes: a driving plate;

[0009] At least two telescopic bands fixedly connected to the edge of the driving plate;

[0010] One end of the telescopic band far from the driving plate is connected to a driver; the number of drivers is equal to that of the telescopic bands and they correspond one by one;

[0011] When the driving device is in the expanded state, the driving plate and the telescopic bands enclose an accommodation space for accommodating the satellite, and the top of the satellite abuts against the driving plate;

[0012] When the satellite needs to be separated from the fairing, the driver drives the driving plate to move towards one end of the driver through the telescopic belt. The driving plate pushes the satellite, and the satellite is pushed out of the fairing, and the driving device is in a contracted state.

[0013] Optionally, the driver includes:

[0014] A housing that is fixedly connected to the inner side wall of the fairing and has an inner cavity;

[0015] A driving member fixed in the inner cavity of the housing;

[0016] The driving member is fixedly connected to one end of the telescopic belt away from the driving plate.

[0017] Optionally, a fixed shaft rotatably connected to the housing is included in the inner cavity of the housing;

[0018] One end of the driving member is fixedly connected to the fixed shaft, and the other end is fixedly connected to the telescopic belt.

[0019] Optionally, a through hole is provided at the top of the housing;

[0020] The telescopic belt passes through the through hole and is connected to the driving member.

[0021] Optionally, the driving member is a torsion spring.

[0022] Optionally, the driving plate is formed by connecting a plurality of metal rods;

[0023] The thicknesses of the plurality of metal rods in the extending direction of the telescopic belt are equal.

[0024] Optionally, when the driving device is in the deployed state, the accommodation space formed by the driving plate and the telescopic belt is adapted to the shape of the satellite.

[0025] Optionally, there are four telescopic belts, and they are evenly distributed on the edge of the driving plate.

[0026] Optionally, the telescopic belt is made by processing a metal sheet or a flexible rope.

[0027] The beneficial effects of this application are as follows:

[0028] In view of the problems existing in the current prior art, the present application provides a driving device. When the satellite is in flight, the driving device is in an unfolded state, the telescopic belt is in a stretched state, and the satellite is located in the accommodation space formed by the enclosure of the driving plate and the telescopic belt. When the satellite needs to be separated from the fairing, the controller issues an instruction to disconnect the connection between the satellite and the fairing. At this time, under the drive of the driver, the telescopic belt changes from the stretched state to the contracted state. Since the force of the driving member is relatively large, the telescopic belt will quickly change from the stretched state to the contracted state. At this time, the telescopic belt drives the driving plate to move towards the direction of the driver, and the driving plate pushes the top of the satellite, causing the satellite to generate a longitudinal acceleration relative to the fairing, realizing an integrated longitudinal separation, so that the satellite can be separated from the fairing. The driving device provided by the present application does not use pyrotechnics, has high test safety, low cost, simple test operation, and the test effect is basically the same as the actual separation effect. In actual ground tests, it can be reused multiple times, thus facilitating and truly verifying the separation process between the fairing and the satellite during flight; the reliability of the separation process between the satellite and the fairing is high, and after separation, the driving plate will completely move to one end of the fairing close to the opening, ensuring that the satellite is completely separated from the fairing. The driving device has a small and compact structure, does not occupy too much internal space of the fairing, and enables the internal space of the fairing to be effectively used by the satellite carried. The assembly is simple and safe. The driving device is a pure mechanical structure, does not require power supply and pyrotechnics, etc., uses fewer components, and the assembly is simple and safe. It has strong versatility. The driving device can be used for all integrated longitudinal separation fairings, is not limited by the size of the fairing and the size and weight of the loaded satellite. In addition to the fairing separation process, the driving device can also be applied to the separation processes of other similar cabins. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] The following further elaborates in detail the specific embodiments of the present invention in conjunction with the drawings.

[0030] Figure 1 The structural schematic diagram of the satellite when it has not been separated from the fairing in an embodiment of the present application is shown.

[0031] Figure 2 The structural schematic diagram of the driver of the driving device in an embodiment of the present application is shown.

[0032] Figure 3 The side view of the satellite when it has not been separated from the fairing in an embodiment of the present application is shown.

[0033] Figure 4 The side view of the satellite after it has been separated from the fairing in an embodiment of the present application is shown. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0034] In the following description, for purposes of explanation, in order to provide a thorough understanding of one or more embodiments, numerous specific details are set forth. It is apparent, however, that the embodiments may be practiced without these specific details.

[0035] In the description of the present application, it should be noted that the orientation or positional relationship indicated by terms such as "upper", "lower", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as a limitation to the present application. Unless otherwise clearly specified and defined, the terms "mounted", "connected", and "coupled" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present application can be understood according to specific circumstances.

[0036] It should also be noted that in the description of the present application, relative terms such as first and second are only used to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprising", "including", or any other variant thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or device including a series of elements not only includes those elements but also includes other elements not expressly listed, or further includes elements inherent to such process, method, article, or device. Without further limitation, an element defined by the phrase "comprising a..." does not exclude the existence of additional identical elements in the process, method, article, or device including the said element.

[0037] To solve the problems existing in the prior art, an embodiment of the present application provides a driving device, such as Figures 1-4As shown, the driving device is fixed on the inner side wall of the fairing 1; the driving device has a contracted state and an expanded state; further included are: a driving plate 2; at least two telescopic belts 3 connected to the edge of the driving plate 2, and one end of the telescopic belt 3 away from the driving plate 2 is connected to a driver 4; the number of drivers 4 is equal to that of the telescopic belts 3 and they correspond one by one; when the driving device is in the expanded state, the driving plate 2 and the telescopic belts 3 enclose an accommodation space for accommodating the satellite 10, and the top of the satellite 10 abuts against the driving plate 2; when the satellite 10 needs to be separated from the fairing 1, the driver 4 drives the driving plate 2 to move towards the end of the driver 4 through the telescopic belt 3, the telescopic belt 3 gradually contracts, the driving plate 2 pushes the satellite 10, and the satellite 10 is pushed out of the fairing 1, and the driving device is in the contracted state.

[0038] In the above embodiment of the present application, when the satellite 10 is in flight, the driving device is in the expanded state, the telescopic belt 3 is in the stretched state, and the satellite 10 is located in the accommodation space formed by the enclosure of the driving plate 2 and the telescopic belt 3. When the satellite 10 needs to be separated from the fairing 1, the controller issues an instruction to disconnect the connection between the satellite 10 and the fairing 1. At this time, under the drive of the driver 4, the telescopic belt 3 changes from the stretched state to the contracted state. Since the force of the driving member 42 is relatively large, the telescopic belt 3 will quickly change from the stretched state to the contracted state. At this time, the telescopic belt 3 drives the driving plate 2 to move towards the driver 4, and the driving plate 2 pushes the top of the satellite 10, causing the satellite 10 to generate a longitudinal acceleration relative to the fairing 1, realizing an integrated longitudinal separation, so that the satellite 10 is separated from the fairing 1. The driving device provided by the present application does not use pyrotechnics, has high test safety, low cost, simple test operation, and the test effect is basically the same as the actual separation effect. In actual ground tests, it can be reused multiple times, thus facilitating and truly verifying the separation process between the fairing 1 and the satellite 10 during flight; the separation process between the satellite 10 and the fairing 1 has high reliability. After separation, the driving plate 2 will completely move to one end of the fairing 1 close to the opening 11, ensuring that the satellite 10 is completely separated from the fairing 1. The driving device has a small and compact structure, does not occupy too much internal space of the fairing 1, and enables the internal space of the fairing 1 to be effectively used by the loaded satellite 10. The assembly is simple and safe. The driving device is a pure mechanical structure, does not require power supply and pyrotechnics, etc., uses fewer components, and the assembly is simple and safe. It has strong versatility. The driving device can be used for all integrally longitudinally separable fairings 1, is not limited by the size of the fairing 1 and the size and weight of the loaded satellite 10. In addition to the separation process of the fairing 1, the driving device can also be applied to the separation processes of other similar cabins.

[0039] In a specific embodiment, the driver 4 includes: a housing 41 fixedly connected to the inner side wall of the fairing 1 and having an inner cavity; the housing is located at the bottom opening 11 of the fairing 1, and a driving member 42 is fixed in the inner cavity of the housing 41; the driving member 42 is fixedly connected to the end of the telescopic belt 3 away from the driving plate 2. When the driving device is in the contracted state, the telescopic belt 3 is curled inside the housing 41, and the telescopic belt 3 drives the driving plate 2 to be located near the housing 41, that is, at the bottom opening 11 of the fairing 1; when the driving device is in the deployed state, the telescopic belt 3 unfolds, and the satellite 10 is located in the accommodation cavity 5 formed by the enclosure of the driving plate 2 and the telescopic belt 3. At this time, the driving force of the driving member 42 is the largest. After the connection between the satellite 10 and the fairing 1 is disconnected, the driving member 42 drives the telescopic belt 3 to contract, and the telescopic belt 3 drives the driving plate 2 to generate a longitudinal acceleration, and the driving plate 2 pushes the satellite 10, so that the satellite 10 is separated from the fairing 1.

[0040] When actually installing the satellite 10 in the fairing 1, the driving device in the contracted state is installed at the bottom opening 11 of the fairing 1, and then the fairing 1 is lifted. The driving plate 2 is aligned with the top of the satellite 10 body, and pressure is applied from top to bottom. The telescopic belt 3 is pulled out from the housing 41, and the driving plate 2 moves upward until the satellite 10 completely enters the driving device, that is, completely enters the fairing 1. At this time, the bottom of the fairing 1 contacts the bottom of the satellite 10, and the fairing 1 is fixedly connected to the bottom of the satellite 10 to complete the assembly. At this time, there is a tensile pre-tightening force on the telescopic belt 3.

[0041] In practical applications, if the driving force provided by the driving device provided in this application exceeds the bearing capacity of the satellite 10, an explosive bolt can be used to fix the driving plate 2 in advance. When the connection between the fairing 1 and the satellite 10 is disconnected, the explosive bolt needs to be activated synchronously so that the driving plate 2 can move freely; when the driving force provided by the driving device does not exceed the bearing capacity of the satellite 10, there is no need to use an explosive bolt connection, and the satellite 10 can be installed in the fairing 1 by the above method.

[0042] In a specific embodiment, a fixed shaft 43 rotatably connected to the housing 41 is included in the inner cavity of the housing 41; one end of the driving member 42 is fixedly connected to the fixed shaft 43, and the other end is fixedly connected to the telescopic belt 3. When the telescopic belt 3 changes from the contracted state to the deployed state, the driving member 42 rotates around the fixed shaft 43, and the driving force of the driving member 42 gradually increases until the telescopic belt 3 is completely in the deployed state, and the driving force of the driving member 42 reaches the maximum; when the satellite 10 needs to be separated from the fairing 1, the driving member 42 rotates around the fixed shaft 43 under the action of the driving force, driving the telescopic belt 3 to change from the deployed state to the contracted state, and during the contraction process of the telescopic belt 3, the driving member 42 rotates around the fixed shaft 43 until it is completely retracted.

[0043] In a specific embodiment, a through hole (not shown in the figure) is provided at the top of the housing 41; the telescopic belt 3 passes through the through hole and is connected to the driving member 42. The telescopic belt 3 is retracted into the housing 41 through the through hole to keep the shrink bag in a shrunk state; and is released from the housing 41 to be in an unfolded state.

[0044] In a specific embodiment, the driving member 42 is a torsion spring. Without affecting the use effect of the present invention, the driving member 42 can also be other shaped springs or elastic belts with elasticity. During actual use, the elastic force of the torsion spring can be precisely designed. According to the weight of the specific satellite 10 and the requirement of the separation speed for the launch mission, by the stiffness of the torsion spring, its output stable driving force is controlled to enable the fairing 1 and the satellite 10 to have sufficient separation speed.

[0045] In a specific embodiment, the driving plate 2 is formed by connecting a plurality of metal rods 21; the thicknesses of the plurality of metal rods 21 in the extending direction of the telescopic belt 3 are equal. In this way, the driving plate 2 has an equal thickness, and the plane in contact with the satellite 10 is also in the same plane, improving the stability when the driving plate 2 pushes the satellite 10 and not deviating from the separation direction when separating from the satellite 10. Of course, in actual applications, the driving plate 2 can also be formed by combining a metal frame and a flexible rope or a flexible cloth.

[0046] In a specific embodiment, when the driving device is in an unfolded state, the accommodation space formed by enclosing the driving plate 2 and the telescopic belt 3 is adapted to the shape of the satellite 10. In this way, the fairing 1 can be made according to the shape of the satellite 10, saving materials and costs.

[0047] In a specific embodiment, as Figure 1 shown, preferably four telescopic belts 3 are provided, and the four telescopic belts 3 are evenly distributed on the edge of the driving plate 2. In actual applications, the number of telescopic belts 3 can also be set according to the power of the driving member 42 and the satellite 10.

[0048] The telescopic belt 3 is made by processing a metal sheet or a flexible rope, and of course, it can also be made by processing a flexible rope of materials such as Kevlar.

[0049] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, rather than limitations on the implementation manners of the present invention. For those of ordinary skill in the art, other different forms of changes or modifications can be made based on the above description. It is impossible to list all the implementation manners here. Any obvious changes or modifications derived from the technical solutions of the present invention still fall within the protection scope of the present invention.

Claims

1. A driving device, characterized in that, The driving device is fixed on the inner side wall of the fairing; The driving device includes a contracted state and a deployed state; It further includes: a driving plate; At least two telescopic belts fixedly connected to the edge of the driving plate; One end of the telescopic belt away from the driving plate is connected to a driver; the number of drivers is equal to that of the telescopic belts and they correspond one by one; When the driving device is in the deployed state, the driving plate and the telescopic belt enclose a receiving space for accommodating the satellite, and the top of the satellite abuts against the driving plate; When the satellite needs to be separated from the fairing, the driver drives the driving plate to move towards the end of the driver through the telescopic belt, the driving plate pushes the satellite, and the satellite is pushed out of the fairing, and the driving device is in the contracted state; The driver includes: A housing fixedly connected to the inner side wall of the fairing and having an inner cavity; A driving member fixed in the inner cavity of the housing; The driving member is fixedly connected to the end of the telescopic belt away from the driving plate; the driving member is a torsion spring.

2. The drive device according to claim 1, characterized in that, The inner cavity of the housing includes a fixed shaft rotatably connected to the housing; One end of the driving member is fixedly connected to the fixed shaft, and the other end is fixedly connected to the telescopic belt.

3. The drive device according to claim 1, characterized in that, A through hole is provided at the top of the housing; The telescopic belt passes through the through hole and is connected to the driving member.

4. The drive device according to claim 1, characterized in that, The driving plate is formed by connecting a plurality of metal rods; The thicknesses of the plurality of metal rods in the extending direction of the telescopic belt are equal.

5. The drive device according to claim 1, characterized in that, When the driving device is in the deployed state, the receiving space formed by the driving plate and the telescopic belt is adapted to the shape of the satellite.

6. The drive device according to claim 1, characterized in that There are four telescopic belts, which are evenly distributed on the edge of the driving plate.

7. The drive device according to claim 1, characterized in that, The telescopic belt is made by processing a metal sheet or a flexible rope belt.

Images