Asteroid probe satellite lander deployment device

Abstract

This invention relates to the field of space exploration satellite landing equipment manufacturing technology, specifically to a small asteroid exploration satellite lander deployment device with a reasonable structure, reliable operation, and the ability to meet the flexible landing requirements of exploration equipment in complex environments. The device is characterized by having a power component, a transmission conversion mechanism, and two or more sets of deployment auxiliary components between the exploration satellite base and the lifting base. The power component drives the transmission conversion mechanism to deploy or retract the two or more sets of deployment auxiliary components. It also includes two or more airbag support components corresponding to the two or more sets of deployment auxiliary components. As the lifting base descends, the airbags can be deployed, with a maximum deployment angle of 90°, enabling stable landing of the exploration satellite in complex asteroid exploration environments.

Description

Technical fields:

[0001] This invention relates to the field of space exploration satellite landing equipment manufacturing technology, specifically to an asteroid exploration satellite lander deployment device that is structurally sound, reliable in operation, and capable of meeting the flexible landing requirements of exploration equipment in complex environments. Background technology:

[0002] With the exploration of outer space, the research and development of asteroids has increasingly become a new hot topic. According to relevant research, many asteroids exist in near-Earth space, containing abundant resources such as fresh water and metals, which can provide supplies for spacecraft and have enormous research and utilization value. Research on the mechanical systems of asteroid landers is a key technology for asteroid exploration and development. Currently, the main problems encountered in asteroid landings include difficulty in securing the asteroid surface, escape velocity, and impact dust. To address these issues, a reusable landing deployment device that can meet the requirements of flexible landing is urgently needed. Summary of the Invention:

[0003] This invention addresses the gaps in existing technologies and the need for flexible landing by proposing a reusable, structurally sound, reliable, and reusable asteroid exploration satellite lander deployment device.

[0004] This invention achieves its purpose through the following measures:

[0005] A deployment device for an asteroid exploration satellite lander includes a lifting base and a satellite base. The satellite base is located above the lifting base and has an interface for connecting to the main body of the exploration equipment. The device is characterized by having a power component, a transmission conversion mechanism, and two or more deployment auxiliary components between the satellite base and the lifting base. The power component drives the transmission conversion mechanism to deploy or retract the two or more deployment auxiliary components. Each deployment auxiliary component includes a fixed aluminum plate and a supporting rod hinged together. The upper end of the fixed aluminum plate is hinged to the outer edge of the satellite base, and the lower end of the supporting rod is hinged to the outer edge of the lifting base. The device also includes two or more airbag support components corresponding to the two or more deployment auxiliary components. Each airbag support component includes a strip-shaped airbag fixed to the outer side of the fixed aluminum plate and a built-in air pump connected to the airbag.

[0006] In order to improve the stability of the probe satellite base and the lifting base during the unfolding / retraction process, the present invention provides an optical bar fixed on the lifting base and a matching optical bar sleeve on the probe satellite base.

[0007] The power component of this invention uses a servo motor. The transmission conversion mechanism includes a fixed bearing housing, a connecting sleeve, a fastening nut, a deep groove ball bearing, a lead screw, a lead screw nut, a shaft end sleeve, an anti-collision pad, and a fixed sleeve. The fixed bearing housing is bolted to the satellite base. There are two deep groove ball bearings, with their outer rings tightly fitted to the fixed bearing housing. The connecting sleeve is tightly fitted to the inner rings of the two deep groove ball bearings. The fastening nut is threaded to the connecting sleeve to achieve reliable axial positioning. The lead screw nut is bolted to the connecting sleeve. The lead screw and lead screw nut cooperate to achieve transmission conversion. The shaft end sleeve is fixed to the lead screw by a set screw. The anti-collision pad is fixed to the lead screw by a set screw. The fixed sleeve and the shaft end sleeve are axially positioned by a boss structure and bolted to the lifting base.

[0008] The present invention also includes a primary transmission mechanism and a secondary transmission mechanism, wherein the secondary transmission mechanism includes a large pulley, a small pulley and a gear transmission belt, the large pulley is fixedly connected to a connecting sleeve by bolts, the small pulley is fixedly connected to the output shaft of the primary transmission mechanism, and the gear transmission belt cooperates with the large and small pulleys; one end of the primary transmission mechanism is fixedly connected to a base fixed on the probe satellite base by bolts, and the other end is fixedly connected to a servo motor by bolts.

[0009] The present invention comprises four sets of lifting optical bars, which are respectively fixed to the lifting base by bolts and cooperate with the optical bar sleeves fixed to the base of the detection satellite.

[0010] The deployment auxiliary assembly of this invention comprises four sets, each set including three pairs of hinge lugs (upper, middle, and lower), a fixed aluminum plate, and a support connecting rod. The upper hinge lug is fixed to the probe satellite base by bolts, the middle hinge lug is fixed to the fixed aluminum plate by bolts, and the lower hinge lug is fixed to the lifting base by bolts. The fixed aluminum plate is fixed to the support airbag by bolts, the support airbag is connected to the upper hinge lug by a pin, and one end of the support connecting rod is connected to the middle hinge lug by a pin, and the other end is connected to the lifting base by a pin.

[0011] In operation, when the asteroid probe satellite is preparing to land, the built-in air pump first inflates the support airbag, causing it to deploy. Then, the servo motor transmits power to the connecting sleeve of the transmission conversion mechanism via a primary and secondary transmission mechanism. The connecting sleeve drives the lead screw nut to rotate, which in turn drives the lead screw to reciprocate, thus converting the motion mode. The lead screw transmits power to the lifting base, causing it to reciprocate. The lifting optical rod is connected to the lifting base, making its reciprocating motion smoother. The deployment auxiliary component is connected between the probe satellite base and the lifting base. The support airbag is fixed to the aluminum plate of the deployment auxiliary component. As the lifting base descends, the support airbag can deploy, with a maximum deployment angle of 90°, enabling stable landing of the probe satellite in complex asteroid environments. Attached image description:

[0012] Appendix Figure 1 This is a schematic diagram of the structure of the present invention.

[0013] Appendix Figure 2 This is a schematic diagram of the transmission conversion mechanism in this invention.

[0014] Appendix Figure 3 This is a schematic diagram of the structure of the secondary transmission mechanism and power component in this invention.

[0015] Appendix Figure 4 This is a schematic diagram of the structure of the unfolding auxiliary component in this invention.

[0016] Appendix Figure 5 This is a schematic diagram of the present invention in the landing preparation state.

[0017] Appendix Figure 6 This is a schematic diagram of the invention in its unfolded state.

[0018] Reference numerals in the attached diagram: satellite base (1), transmission conversion mechanism (2), fixed bearing seat (2-1), connecting sleeve (2-2), fastening nut (2-3), deep groove ball bearing (2-4), lead screw (2-5), lead screw nut (2-6), shaft end sleeve (2-7), anti-collision pad (2-8), and fixed sleeve (2-9), secondary transmission mechanism (3), large pulley (3-1), small pulley (3-2), gear transmission belt (3-3), primary transmission mechanism (4), servo motor (5), lifting optical bar (6), deployment auxiliary component (7), upper hinge lug (7-1), middle hinge lug (7-2), lower hinge lug (7-3), fixed aluminum plate (7-4), support connecting rod (7-5), lifting base (8), and support airbag (9). Detailed implementation method:

[0019] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0020] Example:

[0021] This example provides a solution as shown in the appendix. Figure 1 The asteroid probe satellite lander deployment device shown includes a probe satellite base (1), a transmission conversion mechanism (2), a secondary transmission mechanism (3), a primary transmission mechanism (4), a servo motor (5), a lifting optical bar (6), a deployment auxiliary component (7), a lifting base (8), and a support airbag (9).

[0022] The probe satellite base (1) is fixed to the asteroid probe satellite with bolts. In this example, a variety of mechanical interfaces are designed on the probe satellite base (1) to facilitate the connection and fixation of the lander deployment mechanism.

[0023] As attached Figure 2 As shown, the transmission conversion mechanism (2) includes a fixed bearing housing (2-1), a connecting sleeve (2-2), a fastening nut (2-3), a deep groove ball bearing (2-4), a lead screw (2-5), a lead screw nut (2-6), a shaft end sleeve (2-7), an anti-collision pad (2-8), and a fixed sleeve (2-9). The fixed bearing housing (2-1) is bolted to the probe satellite base (1). There are two deep groove ball bearings (2-4), and their outer rings are tightly fitted to the fixed bearing housing (2-1). The connecting sleeve (2-2) is tightly fitted to the inner rings of the two deep groove ball bearings (2-4). The nut (2-3) is fastened to the connecting sleeve (2-2) by a threaded pair to achieve reliable axial positioning. The screw nut (2-6) is fastened to the connecting sleeve (2-2) by bolts. The screw (2-5) cooperates with the screw nut (2-6) to realize the conversion of the transmission mode. The shaft end sleeve (2-7) is fixed to the screw (2-5) by a set screw. The anti-collision pad (2-8) is fixed to the screw (2-5) by a set screw. The fixed sleeve (2-9) and the shaft end sleeve (2-8) are axially positioned by a boss structure and fixed to the lifting base (8) by bolts.

[0024] As attached Figure 3 As shown, the secondary transmission mechanism (3) includes a large pulley (3-1), a small pulley (3-2), and a gear transmission belt (3-3). The large pulley (3-1) is fixed to the connecting sleeve (2-2) by bolts. The small pulley (3-2) is fixed to the output shaft of the primary transmission mechanism (4). The gear transmission belt (3-3) cooperates with the large and small pulleys. One end of the primary transmission mechanism (4) is fixed to the base fixed on the probe satellite base (1) by bolts, and the other end is fixed to the servo motor (5) by bolts. There are four sets of lifting optical bars (6), which are fixed to the lifting base (8) by bolts and cooperate with the optical bar sleeve fixed on the probe satellite base (1).

[0025] As attached Figure 4 As shown, the deployment auxiliary component (7) has four sets, each set including three pairs of upper, middle and lower hinge lugs, a fixed aluminum plate (7-4), and a support rod (7-5). The upper hinge lug (7-1) is fixed to the probe satellite base (1) by bolts. The middle hinge lug (7-2) is fixed to the fixed aluminum plate (7-4) by bolts. The lower hinge lug (7-3) is fixed to the lifting base (8) by bolts. The fixed aluminum plate (7-4) is fixed to the support airbag (9) by bolts. The support airbag (9) is connected to the upper hinge lug (7-1) by a pin. One end of the support rod (7-5) is connected to the middle hinge lug (7-2) by a pin, and the other end is connected to the lifting base (8) by a pin.

[0026] The main function of the probe satellite base in this implementation scheme is to connect the deployment mechanism to the probe satellite body and provide support for other components of the deployment mechanism. The transmission conversion mechanism has two main functions: first, to convert rotation into reciprocating motion and realize the lifting and lowering movement of the base; second, to adjust the deployment angle of the deployment auxiliary components so that the flexible lander can adapt to the complex landing scenario of asteroids. The primary and secondary transmission mechanisms reduce speed and increase torque. The servo motor provides power to the entire deployment mechanism. There are four sets of lifting optical bars, which mainly make the movement of the lifting base more stable. The deployment auxiliary mechanism provides support for the support airbag and completes the deployment movement. The lifting base provides support for the auxiliary deployment device and works with the deployment auxiliary components to complete the deployment movement.

[0027] The working process in this example is as follows: When the asteroid probe satellite is preparing to land, the built-in air pump first inflates the support airbag, putting the airbag into the deployed state. Then, the servo motor transmits power to the connecting sleeve of the transmission conversion mechanism through the primary and secondary transmission mechanisms. The connecting sleeve drives the lead screw nut to rotate, which in turn drives the lead screw to reciprocate, realizing the conversion of the motion mode. The lead screw transmits power to the lifting base, driving the lifting base to reciprocate. The lifting optical rod is connected to the lifting base, making the reciprocating motion of the lifting base more stable. The deployment auxiliary component is connected between the probe satellite base and the lifting base. The support airbag is fixed to the aluminum plate of the deployment auxiliary component. As the lifting base descends, the support airbag can be deployed. The maximum deployment angle can reach [value missing], which can realize the stable landing of the probe satellite in the complex environment of the asteroid probe satellite.

Claims

1. A deployment device for an asteroid probe lander, comprising a lifting base and a probe satellite base, wherein the probe satellite base is located above the lifting base and has an interface for connecting to the main body of the probe equipment, characterized in that, Between the probe satellite base and the lifting base, there is a power component, a transmission conversion mechanism, and two or more sets of deployment auxiliary components. The power component drives the transmission conversion mechanism to deploy or retract the two or more sets of deployment auxiliary components. The deployment auxiliary components include a fixed aluminum plate and a support rod that are hinged together. The upper end of the fixed aluminum plate is hinged to the outer edge of the probe satellite base, and the lower end of the support rod is hinged to the outer edge of the lifting base. There are also two or more airbag support components corresponding to the two or more sets of deployment auxiliary components. The airbag support components include a strip-shaped airbag fixed to the outer side of the fixed aluminum plate and a built-in air pump connected to the airbag. The power component uses a servo motor. The transmission conversion mechanism includes a fixed bearing housing, a connecting sleeve, a fastening nut, a deep groove ball bearing, a lead screw, a lead screw nut, a shaft end sleeve, an anti-collision pad, and a fixed sleeve. The fixed bearing housing is bolted to the satellite base. There are two deep groove ball bearings, with their outer rings tightly fitted to the fixed bearing housing. The connecting sleeve is tightly fitted to the inner rings of the two deep groove ball bearings. The fastening nut is threaded to the connecting sleeve to achieve reliable axial positioning. The lead screw nut is bolted to the connecting sleeve. The lead screw and lead screw nut cooperate to achieve transmission conversion. The shaft end sleeve is fixed to the lead screw by a set screw. The anti-collision pad is fixed to the lead screw by a set screw. The fixed sleeve and the shaft end sleeve are axially positioned by a boss structure and are bolted to the lifting base. When the asteroid probe is preparing to land, the built-in air pump first inflates the support airbag. As the lifting base descends, the support airbag can be deployed, with a maximum deployment angle of 90°, enabling the probe to land stably in the complex environment of the asteroid probe.

2. The asteroid exploration satellite lander deployment device according to claim 1, characterized in that, A light bar is fixed on the lifting base, and a matching light bar sleeve is provided on the probe satellite base.

3. The asteroid exploration satellite lander deployment device according to claim 1, characterized in that, It also includes a primary transmission mechanism and a secondary transmission mechanism. The secondary transmission mechanism includes a large pulley, a small pulley, and a gear transmission belt. The large pulley is fixed to the connecting sleeve by bolts, the small pulley is fixed to the output shaft of the primary transmission mechanism, and the gear transmission belt cooperates with the large and small pulleys. One end of the primary transmission mechanism is fixed to the base on the probe satellite base by bolts, and the other end is fixed to the servo motor by bolts.

4. The asteroid exploration satellite lander deployment device according to claim 2, characterized in that, The optical bar has four sets, which are fixed to the lifting base by bolts and cooperate with the optical bar sleeves fixed to the base of the detection satellite.

5. The asteroid exploration satellite lander deployment device according to claim 1, characterized in that, The deployment auxiliary components consist of four sets, each set including three pairs of hinge lugs (upper, middle, and lower), a fixed aluminum plate, and a support connecting rod. The upper hinge lug is bolted to the probe satellite base, the middle hinge lug is bolted to the fixed aluminum plate, and the lower hinge lug is bolted to the lifting base. The fixed aluminum plate is bolted to the support airbag, the support airbag is connected to the upper hinge lug via a pin, and one end of the support connecting rod is connected to the middle hinge lug via a pin, while the other end is connected to the lifting base via a pin.

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