Mother and son star deployment and release device

Abstract

A mother-daughter satellite deployment and release device provided by the present invention comprises: a mother satellite; a deployment assembly including a connecting member and a deployment member, one end of the connecting member is connected to the mother satellite, and the other end is connected to the deployment member; a release assembly connected to the deployment member; wherein, the deployment member includes a second driving mechanism and a scissor link mechanism, and the second driving mechanism controls the movement of the scissor link mechanism through a cooperation mode. By operating the attitude adjustment driving motor to drive the attitude adjustment bevel gear to rotate, and then enabling the attitude adjustment driven bevel gear to drive the daughter satellite substrate to deploy and rotate; the cooperation of the scissor link mechanism and the second driving mechanism enables the daughter satellite substrate to be accommodated to achieve multi-layer storage and compress the accommodation space. The deployed and released daughter satellite substrate can continue to be used as the substrate of the antenna / battery wing, achieving the effect of reasonable resource allocation.

Description

Technical Field

[0001] The present invention relates to the field of aerospace, and more specifically, to a mother-satellite deployment and release device in the field of aerospace. Background Art

[0002] Currently, in the mother-satellite launch mode of multiple satellites in one rocket, after the sub-satellites to be orbited are released, the installation platforms of the sub-satellites mostly remain on the platform of the mother-satellite or are thrown away; if the storage platform of the sub-satellite remains on the platform of the mother-satellite, it will surely affect the maneuverability of the mother-satellite, and if the storage platform of the sub-satellite is thrown away from the mother-satellite, it will surely create more space debris; therefore, it is urgent to solve how to achieve multi-functional reuse of the storage platform of the sub-satellite. At the same time, if the multi-layer / multi-plane accommodation space of the scissor-link mechanism is used, there will be some problems when the sub-satellite substrates on different planes release the sub-satellites. Summary of the Invention

[0003] Aiming at the defects in the prior art, the purpose of the present invention is to provide a mother-satellite deployment and release device. A mother-satellite deployment and release device provided by the present invention includes: a mother-satellite; a deployment assembly, including a connecting member and a deployment member, one end of the connecting member is connected to the mother-satellite, and the other end is connected to the deployment member; a release assembly, which is connected to the deployment member; wherein, the deployment member includes a second driving mechanism and a scissor-link mechanism, and the second driving mechanism controls the movement of the scissor-link mechanism through a cooperation method.

[0004] Preferably, the scissor-link mechanism includes a scissor-link driving rod and a scissor-link driven rod, and the two are hinged; wherein, the second driving mechanism drives the scissor-link driving rod to rotate, thereby driving the scissor-link driven rod to rotate, and the scissor-link mechanism realizes lifting.

[0005] Preferably, the cooperation method adopts a gear cooperation method.

[0006] Preferably, the second driving mechanism includes a deployment driving motor, a deployment driving gear and a deployment driven gear, the deployment driving motor is fixed to the support mechanism, and is connected to the deployment driving gear, the deployment driven gear is fixed to the scissor-link driving rod, and the deployment driving gear meshes with the deployment driven gear;

[0007] Wherein, one end of the scissor-link mechanism is hinged to the support mechanism, and the other end is hinged to the sub-satellite substrate.

[0008] Preferably, the release assembly includes a sub-satellite and a sub-satellite substrate, the sub-satellite is arranged on the sub-satellite substrate, and the sub-satellite substrate is hinged to the deployment member.

[0009] Preferably, the sub - satellite substrate is hinged to at least two of the scissor - link mechanisms, and the two hinge points are respectively arranged on the opposite sides of the sub - satellite substrate.

[0010] Preferably, each scissor - link mechanism is hinged to at least two of the sub - satellite substrates, and the distance between the two sub - satellite substrates is not less than the length of the sub - satellite substrate.

[0011] Preferably, the connecting member includes a link mechanism, a support mechanism and a first driving mechanism. One end of the first driving mechanism is connected to the link mechanism, and the other end is connected to the release assembly. The rotation direction of the release assembly is changed by the first driving mechanism.

[0012] Preferably, the connecting member includes a link mechanism and a support mechanism; the link mechanism includes an out - spreading link, a connecting base and an out - spreading base. One end of the out - spreading link is hinged to the connecting base, and the other end is hinged to the out - spreading base; the support mechanism is connected to the out - spreading base, and the movement of the out - spreading link drives the movement of the support mechanism; wherein, the connecting base is fixedly connected to the mother satellite.

[0013] Preferably, the first driving mechanism includes an attitude - adjustment driving motor, an attitude - adjustment driving bevel gear and an attitude - adjustment driven bevel gear. The attitude - adjustment driving motor is fixed on the out - spreading base and is connected to the attitude - adjustment driving bevel gear, and the attitude - adjustment driven bevel gear is fixed on the out - spreading base; wherein, the attitude - adjustment driving bevel gear meshes with the attitude - adjustment driven bevel gear. When the attitude - adjustment driving motor operates, the attitude - adjustment driving bevel gear and the attitude - adjustment driven bevel gear rotate, and the out - spreading base rotates with the attitude - adjustment driven bevel gear.

[0014] Compared with the prior art, the present invention has the following beneficial effects:

[0015] (1) By operating the attitude - adjustment driving motor in the first driving mechanism to drive the rotation of the attitude - adjustment driving bevel gear, and then enabling the attitude - adjustment driven bevel gear to drive the sub - satellite substrate to perform the functions of unfolding and repositioning.

[0016] (2) Through the cooperation of the scissor - link mechanism and the second driving mechanism, the sub - satellite substrate can be accommodated in multiple layers and the accommodation space can be tightly pressed, so that more space can be provided for the sub - satellite, and it has the effects of good expandability, light weight and reliable unfolding.

[0017] (3) The unfolded and released sub - satellite substrate can be continuously used as the substrate of the antenna / battery wing, achieving the effect of reasonable resource allocation. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] By reading the detailed description of the non - restrictive embodiments with reference to the following drawings, other features of the present invention

[0019] The objectives and advantages will become more apparent:

[0020] Figure 1 is a schematic diagram of the overall structure of the mother and child star deployment and release device of the present invention after deployment;

[0021] Figure 2 is a schematic diagram of the overall structure of the connecting member in the mother and child star deployment and release device of the present invention;

[0022] Figure 3 is a schematic diagram of the structure of the scissor link mechanism in the mother and child star deployment and release device of the present invention ready for deployment;

[0023] Figure 4 is a partially enlarged schematic diagram of a part shown in Figure 3;

[0024] Figure 5 is a partially enlarged schematic diagram of another part shown in Figure 3;

[0025] Figure 6 is a schematic diagram of the overall structure of the deployment assembly in the mother and child star deployment and release device of the present invention;

[0026] Figure 7 is a schematic diagram of the structure of the overall structure of the mother and child star deployment and release device of the present invention in a compressed state;

[0027] Figure 8 is a schematic diagram of the overall structure of the mother and child star deployment and release device of the present invention in a semi-deployed state;

[0028] In the figures:

[0029] 100 - mother star;

[0030] 200 - deployment assembly;

[0031] 210 - connecting member;

[0032] 211 - link mechanism;

[0033] 211a - outrigger link;

[0034] 211a-1 - first link;

[0035] 211a-2 - second link;

[0036] 211b - connection base;

[0037] 211c - outrigger base;

[0038] 212 - support mechanism;

[0039] 213 - first drive mechanism;

[0040] 213a - attitude adjustment drive motor;

[0041] 213b - attitude adjustment drive bevel gear;

[0042] 213c - Position - adjusting driven bevel gear;

[0043] 220 - Deployment member;

[0044] 221 - Second driving mechanism;

[0045] 221a - Deployment driving motor;

[0046] 221b - Deployment driving gear;

[0047] 221c - Deployment driven gear;

[0048] 222 - Scissor - link mechanism;

[0049] 222a - Scissor - link driving rod;

[0050] 222b - Scissor - link driven rod;

[0051] 300 - Release assembly;

[0052] 301 - Daughter satellite;

[0053] 302 - Daughter - satellite substrate; Detailed implementation manners

[0054] The present invention will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0055] Currently, in the mother - daughter satellite launch mode of multiple satellites in one rocket, after the daughter satellite to be orbited is released, the installation platform of the daughter satellite mostly remains on the platform of the mother satellite or is thrown away; if the storage platform of the daughter satellite remains on the platform of the mother satellite, it will surely affect the maneuverability of the mother satellite, and if the storage platform of the daughter satellite is thrown away from the mother satellite, it will surely create more space debris; therefore, how to achieve the multi - functional reuse of the storage platform of the daughter satellite urgently needs to be solved. Based on this, the present invention provides a deployment and release device.

[0056] Embodiment 1

[0057] Referring to FIGS. 1, 6 - 8, in the first embodiment of a mother - daughter satellite deployment and release device provided by the present invention, it includes a mother satellite 100, a deployment assembly 200 and a release assembly 300. Before entering the orbit, the release assembly 300 is in a compressed state through the contraction of the deployment assembly 200. After unlocking in orbit, the deployment and rotation of the release assembly 300 are realized through the deployment assembly 200.

[0058] The release component 300 includes a sub - satellite 301 and a sub - satellite substrate 302. The sub - satellite 301 is disposed on the sub - satellite substrate 302. After it is unlocked in orbit, the sub - satellite 301 can be controlled by the control system to be released from the sub - satellite substrate 302.

[0059] In this embodiment, the deployment component 200 includes a connecting member 210 and a deployment member 220. The deployment member 220 is hinged to the sub - satellite substrate 302, thereby achieving the effect of driving the sub - satellite substrate 302 to rotate by the deployment member 220. After the sub - satellite 301 is completely released from the sub - satellite substrate 302, a new antenna or battery wing is formed by the deployment member 220 and the sub - satellite substrate 302.

[0060] Referring to FIGS. 6 - 8, the deployment member 220 includes a second driving mechanism 221 and a scissor - link mechanism 222. Two effects are achieved through the second driving mechanism 221 and the scissor - link mechanism 222: First, through the scissor - link mechanism 222, the space is contracted, so that more space can accommodate the sub - satellite substrate 302, and thus more space can accommodate the sub - satellite 301. Second, due to the multi - layer / multi - plane accommodation space of the scissor - link mechanism 222, there are some problems when releasing the sub - satellite 301 from the sub - satellite substrate 302 on different planes. For example, as shown in the drawings, the sub - satellite substrate 302 is divided into 3 layers. If the sub - satellites 301 on 3 layers are released simultaneously, the release space for the sub - satellites 301 on the second layer or the third layer will be limited, thus failing to achieve the expected effect and causing waste of resources. In this embodiment, through the cooperation of the second driving mechanism 221 and the scissor - link mechanism 222, the sub - satellite substrates 302 in different layers / planes are rotated to the same plane, so as to better achieve the separation effect between the sub - satellite substrate 302 and the sub - satellite 301.

[0061] The deployment component 200 includes a connecting member 210 and a deployment member 220. The deployment member 220 includes a second driving mechanism 221 and a scissor - link mechanism 222. The sub - satellite substrate 302 is hinged to at least 2 scissor - link mechanisms 222, and the 2 hinge points are respectively disposed on the opposite sides of the sub - satellite substrate 302. For example, one point is disposed in front of the sub - satellite substrate 302, and the other is disposed behind the sub - satellite substrate 302, so as to ensure the connection stability between the sub - satellite substrate 302 and the scissor - link mechanism 222.

[0062] It should be noted that, as shown in the drawings, for further ensuring its stability, the preferred solution in this embodiment is:

[0063] Each sub - satellite substrate 302 is hinged to four scissor - link mechanisms 222. The hinge points are the front and rear of the sub - satellite substrate 302, and two hinge points are set on each of the front and rear. It should be noted that the front and rear mentioned above are in terms of the view in the attached drawing. Taking the X direction in the attached drawing as the positive direction, the corresponding surface pointed by this direction is the front, and the opposite direction is the rear.

[0064] In this embodiment, by hinging the scissor - link mechanism 222 with multiple sub - satellite substrates 302, a multi - layer / multi - plane accommodation space is realized. Therefore, each scissor - link mechanism 222 is hinged to at least two sub - satellite substrates 302, and the spacing between each layer of sub - satellite substrates 302 is not less than the length of the sub - satellite substrate 302. For the sake of easy understanding, the length mentioned here is in terms of the Y direction in the attached drawing.

[0065] Preferably, in this embodiment, two groups of scissor - link mechanisms 222 are provided and symmetrically arranged on both sides of the mother satellite 100.

[0066] It should be noted that the functions realized by the unfolding member 220 are divided into two. One is to realize the function of longitudinal contraction / unfolding, and the other is to realize the function of transverse contraction / unfolding. In specific implementation, in order to unfold the already - contracted scissor - link mechanism 222, it is preferably to first realize the function of longitudinal unfolding and then realize the function of transverse unfolding. That is, first make the scissor - link mechanism 222 change from the scissor state to the straight - rod state along the Y - axis direction shown in the attached drawing and then lock it, and then perform the flat unfolding in the Z - axis direction. After rotating the sub - satellite substrates 302 of different layers to the same plane, lock it again.

[0067] Referring to FIGS. 6 - 8, further, the scissor - link mechanism 222 includes a scissor - link driving rod 222a and a scissor - link driven rod 222b. Through the hinged cooperation of the scissor - link driving rod 222a and the scissor - link driven rod 222b, the effect of space storage is realized.

[0068] The scissor - link mechanism 222 includes a scissor - link driving rod 222a and a scissor - link driven rod 222b, which are hinged to each other. The second driving mechanism 221 includes an unfolding driving motor 221a, an unfolding driving gear 221b, and an unfolding driven gear 221c. The unfolding driving motor 221a is fixed to the support mechanism 212 and is connected to the unfolding driving gear 221b. The unfolding driven gear 221c is fixed to the scissor - link driving rod 222a, and the unfolding driving gear 221b meshes with the unfolding driven gear 221c.

[0069] When the deployment drive motor 221a operates, the deployment drive gear 221b rotates accordingly, and then the deployment driven gear 221c meshing with the deployment drive gear 221b also operates. Since the deployment driven gear 221c is fixedly connected to the scissor linkage drive rod 222a, the scissor linkage drive rod 222a also rotates accordingly, and then the distance between the respective sub-star substrates 302 hinged to the scissor linkage mechanism 222 is realized, achieving the contraction and deployment between the sub-star substrates 302.

[0070] Referring to FIGS. 1-5, in this embodiment, the connecting member 210 includes a linkage mechanism 211, a support mechanism 212, and a first drive mechanism 213. The deployment and rotation of the release assembly 300 are achieved through the cooperation of the first drive mechanism 213 and the support mechanism 212.

[0071] The deployment assembly 200 includes a connecting member 210 and a deployment member 220. One end of the connecting member 210 is connected to the mother star 100, and the other end is connected to the deployment member 220. The connecting member 210 includes a linkage mechanism 211 and a first drive mechanism 213. One end of the linkage mechanism 211 is connected to the mother star 100, and the other end is connected to the deployment member 220. The expansion / contraction of the linkage mechanism 211 is used to achieve the magnification / compression of the overall space of the satellite.

[0072] Preferably, referring to the accompanying drawings, in this embodiment, the linkage mechanism 211 includes an outrigger linkage 211a, a connecting base 211b, and an outrigger base 211c. Among them, the outrigger linkage 211a includes a first link 211a-1 and a second link 211a-2. One end of the first link 211a-1 is hinged to the mother star 100, and the other end is hinged to the second link 211a-2. The other end of the second link 211a-2 is hingedly connected to the outrigger base 211c, and the outrigger base 211c is fixedly connected to the deployment member 220.

[0073] Preferably, the support mechanism 212 is connected to the outrigger base 211c, and the movement of the outrigger linkage 211a drives the movement of the support mechanism 212, and the movement directions are the same.

[0074] It should be noted that the number of links of the linkage mechanism 211 is not limited to the number in the drawings and the above, and all numbers not listed and greater than 1 are within the protection scope of the present invention.

[0075] The first driving mechanism 213 includes a posture adjustment driving motor 213a, a posture adjustment driving bevel gear 213b and a posture adjustment driven bevel gear 213c. The posture adjustment driving motor 213a is fixed to the abduction base 211c and is connected to the posture adjustment driving bevel gear 213b. The posture adjustment driven bevel gear 213c is fixed to the abduction base 211c. At the same time, the posture adjustment driving bevel gear 213b meshes with the posture adjustment driven bevel gear 213c.

[0076] When the posture adjustment driving motor 213a works, it drives the posture adjustment driving bevel gear 213b to rotate. Since the posture adjustment driving bevel gear 213b meshes with the posture adjustment driven bevel gear 213c, the posture adjustment driven bevel gear 213c then rotates accordingly. Also, since the posture adjustment driven bevel gear 213c is fixed to the abduction base 211c, the abduction base 211c changes its angle relative to the horizon as the posture adjustment driven bevel gear 213c rotates. Therefore, the deployment member 220 is controlled by the posture adjustment driving motor 213a to rotate in a plane perpendicular to the abduction base 211c.

[0077] It should be noted that in the schematic diagram provided by the present invention, to prevent the deployment member 220 from hitting the mother star 100 during the rotation process, when the link mechanism 211 is in the deployed state, that is, when the first link 211a-1 and the second link 211a-2 are in a straight line and perpendicular to the deployment member 220, the first driving mechanism 213 can drive and adjust the position of the deployment member 220.

[0078] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A mother-son star deployment and release device, characterized in that, Comprising: Mother star (100); Deployment assembly (200), including a connecting member (210) and a deployment member (220), one end of the connecting member (210) is connected to the mother star (100), and the other end is connected to the deployment member (220); a release assembly (300), which is connected to the deployment member (220); Wherein, the deployment member (220) includes a second drive mechanism (221) and a scissor link mechanism (222), and the second drive mechanism (221) controls the movement of the scissor link mechanism (222) through a cooperation method; the scissor link mechanism (222) includes a scissor linkage drive rod (222a) and a scissor linkage driven rod (222b), and they are hinged and cooperated through the scissor linkage drive rod (222a) and the scissor linkage driven rod (222b); the second drive mechanism (221) includes a deployment drive motor (221a), a deployment drive gear (221b) and a deployment driven gear (221c), the deployment drive motor (221a) is fixed to the support mechanism (212) and is connected to the deployment drive gear (221b), the deployment driven gear (221c) is fixed to the scissor linkage drive rod (222a), and the deployment drive gear (221b) meshes with the deployment driven gear (221c).

2. The mother-son star deployment and release device according to claim 1, characterized in that: The scissor link mechanism (222) includes a scissor linkage drive rod (222a) and a scissor linkage driven rod (222b), and the two are hinged; Wherein, the second drive mechanism (221) drives the scissor linkage drive rod (222a) to rotate, thereby driving the scissor linkage driven rod (222b) to rotate, and the scissor link mechanism (222) realizes lifting.

3. The mother-satellite and son-satellite deployment and release device according to claim 2, wherein: The cooperation method adopts a gear cooperation method.

4. The mother-satellite and son-satellite deployment and release device according to claim 3, wherein: The second drive mechanism (221) includes a deployment drive motor (221a), a deployment drive gear (221b) and a deployment driven gear (221c), the deployment drive motor (221a) is fixed to the support mechanism (212) and is connected to the deployment drive gear (221b), the deployment driven gear (221c) is fixed to the scissor linkage drive rod (222a), and the deployment drive gear (221b) meshes with the deployment driven gear (221c).

5. The mother-son star deployment and release device according to claim 4, characterized in that: The release assembly (300) includes a sub-star (301) and a sub-star substrate (302), the sub-star (301) is arranged on the sub-star substrate (302), the sub-star substrate (302) is hinged to the deployment member (220), wherein, one end of the scissor link mechanism (222) is hinged to the support mechanism (212), and the other end is hinged to the sub-star substrate (302).

6. The mother-satellite and son-satellite deployment and release device according to claim 5, wherein: The sub-star substrate (302) is hinged to at least 2 of the scissor link mechanisms (222), and the two hinge points are respectively arranged on the opposite sides of the sub-star substrate (302).

7. The mother-satellite and son-satellite deployment and release device according to claim 5 or 6, characterized in that: Each scissor link mechanism (222) is hinged to at least 2 of the sub-star substrates (302), and the distance between the two sub-star substrates (302) is not less than the length of the sub-star substrate (302).

8. The mother-satellite and son-satellite deployment and release device according to claim 7, characterized in that: The connecting member (210) includes a link mechanism (211), a support mechanism (212), and a first driving mechanism (213). One end of the first driving mechanism (213) is connected to the link mechanism (211), and the other end is connected to the release assembly (300). The rotation direction of the release assembly (300) is changed by the first driving mechanism (213).

9. The mother-satellite and son-satellite deployment and release device according to claim 8, characterized in that: The connecting member (210) includes a link mechanism (211) and a support mechanism (212); The link mechanism (211) includes an abduction link (211a), a connection base (211b), and an abduction base (211c). One end of the abduction link (211a) is hinged to the connection base (211b), and the other end is hinged to the abduction base (211c); The support mechanism (212) is connected to the abduction base (211c), and the movement of the abduction link (211a) drives the movement of the support mechanism (212); Wherein, the connection base (211b) is fixedly connected to the mother star (100).

10. The mother-satellite and son-satellite deployment and release device according to claim 9, characterized in that: The first driving mechanism (213) includes an attitude adjustment driving motor (213a), an attitude adjustment driving bevel gear (213b), and an attitude adjustment driven bevel gear (213c). The attitude adjustment driving motor (213a) is fixed to the abduction base (211c) and is connected to the attitude adjustment driving bevel gear (213b). The attitude adjustment driven bevel gear (213c) is fixed to the abduction base (211c); Wherein, the attitude adjustment driving bevel gear (213b) meshes with the attitude adjustment driven bevel gear (213c). When the attitude adjustment driving motor (213a) operates, the attitude adjustment driving bevel gear (213b) and the attitude adjustment driven bevel gear (213c) rotate, and the abduction base (211c) rotates with the attitude adjustment driven bevel gear (213c).

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