Mechanical interface system and method based on separation and locking of host satellite and hosted payload

Abstract

The mechanical interface system and method based on the separation and locking of the host satellite and the hosted payload belongs to the field of mechanical structure design. In order to solve the problems of complex operation, slow response speed, poor compatibility and insufficient safety of the existing hosted payload separation method. The ejection plate interface is fixedly connected to the bottom of the hosted payload assembly, the base is located inside the host satellite, and the ejection plate interface extends into the host satellite and is plugged into the base through a compression power spring device; when both release motors are not started, the spring plate squeezes the locking steel ball between the through hole and the groove of the ejection plate interface to achieve the locking of the hosted payload assembly and the host satellite; when both release motors are started, the spring plate is driven to move upward along the base, so that the annular groove on the inner circumference of the spring plate docks with the through hole, and the locking steel ball enters from the annular groove on the ejection plate interface between the through hole and the annular groove on the spring plate to achieve separation. It is used for separating and locking the host satellite and the hosted payload.

Description

Technical Field

[0001] The invention relates to a mechanical interface system and belongs to the field of mechanical structure design. Background Art

[0002] In the field of space technology, especially in host satellite missions, the management and separation of hosted payloads is crucial. Hosted payloads are typically small devices or modules attached to host satellites that perform specific tasks, such as scientific experiments, data collection, or communication assistance. With the increasing number of host satellites and the increasing complexity of missions, the rapid and safe separation of hosted payloads has become a key requirement.

[0003] In the existing technology, the separation of hosted payloads usually relies on methods such as robotic arms or explosive bolts. Although these methods can achieve separation, they have some obvious defects. First, the operation of the robotic arm requires precise control and complex programming, and its size and weight have a significant impact on the overall design and launch cost of the satellite. Although explosive bolts can achieve rapid separation, their disposable nature and the vibrations generated by the explosion may cause damage to surrounding equipment. In addition, these traditional methods are difficult to respond in time in emergency situations (such as satellite failure or collision threat), and cannot effectively protect hosted payloads.

[0004] In practical applications, the rapid and safe separation of hosted payloads is crucial to the success of satellite missions. For example, if a host satellite experiences an unexpected failure, the ability to quickly and safely detach the hosted payload directly impacts the safety of the hosted payload and the execution of subsequent missions. Furthermore, the diversity of hosted payloads and the inter-satellite interface compatibility issues present challenges that existing technologies cannot adequately address.

[0005] Therefore, existing hosted load separation methods have problems such as complex operation, slow response speed, poor compatibility and insufficient security. Summary of the Invention

[0006] The purpose of the present invention is to solve the problems of complex operation, slow response speed, poor compatibility and insufficient safety in the existing host payload separation method, and proposes a mechanical interface system and method based on the separation and locking of the host satellite and the host payload.

[0007] A mechanical interface system based on the separation and locking of the host satellite and the hosted payload, the system comprising an ejection plate interface, a power spring device, a locking steel ball, a spring plate, a base and two release motors;

[0008] The ejection plate interface is fixedly connected to the bottom of the hosted payload assembly, the base is located inside the host satellite, and the ejection plate interface extends into the host satellite and is plugged into the base through a compression power spring device;

[0009] The base includes a central control pillar and two circular support plates. The two circular support plates are named as the first circular support plate and the second circular support plate. The first circular support plate is fixed to the bottom of the pillar, and the second circular support plate is sleeved on the pillar. The pillar and the two circular support plates are an integrated structure. Through holes are evenly provided on the side wall of the pillar located above the second circular support plate. An annular groove is provided on the outer circumference of the ejection plate interface.

[0010] The spring plate is sleeved on the pillar and supported on the second circular support plate. The tops of the two release motors are in contact with the bottom of the spring plate. When the two release motors are not started, the spring plate squeezes and fixes the locking steel ball between the through hole and the groove of the ejection plate interface, thereby locking the hosted payload assembly and the host satellite; when the two release motors are started, the spring plate is driven to move upward along the base, so that the annular groove on the inner circumference of the spring plate docks with the through hole, and the locking steel ball enters from the annular groove on the ejection plate interface between the through hole and the annular groove on the spring plate, thereby separating the hosted payload assembly from the host satellite.

[0011] Preferably, the system further comprises a power regulating motor;

[0012] A power regulating motor is provided between the base and the power spring device;

[0013] The power regulating motor is used to drive the power spring device to move upward and compress the power spring device.

[0014] Preferably, the system further comprises a laser sensor;

[0015] Laser sensor used to measure the displacement of the power spring device.

[0016] Preferably, the release motor is a push rod motor.

[0017] Preferably, the power regulating motor is a push rod motor.

[0018] Preferably, the power spring device comprises four symmetrically distributed springs, an upper top plate and a lower top plate;

[0019] Four symmetrically distributed springs are fixedly connected between the upper top plate and the lower top plate.

[0020] Preferably, the spring in the power spring device is selected according to the mass of the hosted load component.

[0021] A method for separating and locking a host satellite from a hosted payload is implemented based on a mechanical interface system for separating and locking the host satellite from the hosted payload, and includes the following:

[0022] Locking of host satellite and hosted payload:

[0023] The ejection plate interface extends into the host satellite and is plugged into the base. The locking steel ball is clamped between the through hole on the base and the groove on the ejection plate interface to achieve locking of the hosted payload assembly and the host satellite.

[0024] Separation of host satellite and hosted payload:

[0025] After starting the power adjustment motor, the power adjustment motor pushes the power spring device upward, compressing the power spring device, and then starts the two release motors. The release motor pushes the spring plate upward, so that the annular groove on the inner circumference of the spring plate docks with the through hole on the base, and the locking steel ball enters between the through hole and the annular groove on the spring plate from the annular groove on the ejection plate interface. At this time, the power spring device releases the elastic force to achieve the separation of the hosted payload assembly from the host satellite.

[0026] The beneficial effects of the present invention are:

[0027] The present invention uses an ejection plate interface to connect the hosted payload assembly, a base to connect the host satellite, and a locking steel ball clamped between the ejection plate interface and the base to lock the hosted payload assembly to the host satellite. The locking steel ball leaves the space between the ejection plate interface and the base, separating the hosted payload assembly from the host satellite. The present invention has the advantages of an intelligent modular mechanical locking mechanism design, automatic adaptability and rapid response mechanism, remote control and autonomous separation functions, compact design and high integration, a safe locking mechanism, and compatibility with multiple host satellite interfaces. These advantages bring the following benefits to the system:

[0028] 1. Intelligent modular mechanical locking mechanism design: Enhances system compatibility and flexibility, adapting to hosted payloads of varying sizes, shapes, and weights. It enables rapid and secure separation and locking of hosted payloads from host satellites. Automatically adjusts the locking configuration based on the size, shape, and weight of the hosted payload, ensuring compatibility with a variety of host satellites and efficient and safe operation in a variety of complex mission environments.

[0029] 2. Automatic adaptability and rapid response mechanism: Without manual intervention, separation operations can be quickly performed in emergency situations, improving the safety of payload protection; especially suitable for payload protection and mission execution in emergency situations;

[0030] 3. Remote control and autonomous separation functions: Improve the convenience and reliability of operation and adapt to various mission requirements and complex space environments;

[0031] 4. Compact design and high integration: reduce equipment size and weight, lower launch costs, and improve the overall efficiency of the system;

[0032] 5. Safety locking mechanism: ensures the stability of the load before separation, avoiding potential risks caused by misoperation;

[0033] 6. Compatible with multiple host satellite interfaces: Increase the versatility of the system, adapt to the mission requirements of different types of satellites, and reduce customization needs. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 This is the overall structure diagram of the mechanical interface, where: Figure 1 (a) is a structural diagram of the mechanical interface connected to the hosted load component. Figure 1 (b) A diagram showing the structure of the mechanical interface, hosted payload assembly, and host satellite connected together;

[0035] Figure 2 This is the exploded view of the mechanical interface;

[0036] Figure 3 is the locked state diagram, where Figure 3 (a) is a cross-sectional view in the locked state. Figure 3 (b) is a detailed view of the locking steel ball in the initial state;

[0037] Figure 4 This is a schematic diagram of the power regulating motor function;

[0038] Figure 5 Schematic diagram of the host load separation process based on the mechanical interface system;

[0039] Figure 6 A cross-sectional diagram of the hosted load separation process based on the mechanical interface system. DETAILED DESCRIPTION

[0040] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative efforts shall fall within the scope of protection of the present invention.

[0041] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments may be combined with each other.

[0042] The present invention will be further described below with reference to the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0043] Example 1:

[0044] Combine Figures 1 to 6 This embodiment is described, based on a mechanical interface system for separating and locking a host satellite and a hosted payload, the system includes an ejection plate interface 3, a power spring device 5, a locking steel ball 6, a spring plate 7, a base 8 and two release motors 9;

[0045] The ejection plate interface 3 is fixedly connected to the bottom of the hosted payload assembly 15, and the base 8 is located inside the host satellite 16. The ejection plate interface 3 extends into the host satellite 16 and is inserted into the base 8 through the compression power spring device 5;

[0046] The base 8 includes a central control pillar and two circular support plates, the two circular support plates are divided into a first circular support plate and a second circular support plate; the first circular support plate is fixed to the bottom of the pillar, and the second circular support plate is sleeved on the pillar. The pillar and the two circular support plates are an integral structure, and through holes are evenly provided on the side wall of the pillar located above the second circular support plate; an annular groove is provided on the outer circumferential surface of the ejection plate interface 3;

[0047] The spring plate 7 is sleeved on the pillar and supported on the second circular support plate. The top of the two release motors 9 contacts the bottom of the spring plate 7. When the two release motors 9 are not started, the spring plate 7 squeezes and fixes the locking steel ball 6 between the through hole and the groove of the ejection plate interface 3, thereby locking the hosted payload assembly 15 and the host satellite 16; when the two release motors 9 are started, the spring plate 7 is driven to move upward along the base 8, so that the annular groove on the inner circumference of the spring plate 7 docks with the through hole, and the locking steel ball 6 enters from the annular groove on the ejection plate interface 3 between the through hole and the annular groove on the spring plate 7, thereby separating the hosted payload assembly 15 from the host satellite 16.

[0048] Specifically, the hosted payload assembly 15 includes a hosted payload 1 and an antenna satellite substrate 2 ; the host satellite 16 includes a host satellite top plate 13 and a host satellite side plate 14 .

[0049] like Figure 1 As shown, the host payload 1, the antenna satellite substrate 2 and the ejection plate interface 3 are fixedly connected in the initial state; in the separation state, the three are separated together as a whole. Figure 1 As shown in FIG. 2 b , the lower surface of the ejection plate interface 3 contacts the upper surface of the host satellite top plate 13 , and the threaded cover 4 is fixedly connected to the lower surface of the host satellite top plate 13 .

[0050] In addition, to ensure the normal operation of the hosted payload after separation, multiple subsystems, including electrical interfaces, information transmission interfaces, and thermal protection, are theoretically required between the ejection plate interface 3 and the host satellite. This embodiment focuses on the separation of an in-orbit host satellite and hosted payload, and therefore primarily explains the design and separation methods of the mechanical interface system.

[0051] This design ensures the stability and safety of the host load 1 during the separation process, while realizing automated separation and locking functions through intelligent control.

[0052] Initially, base 8 is fixed to the host satellite. Release motors 9 are mounted on both sides of base 8 and connected to base 8 via fixing bolts 12. Release motors 9 are pushrod motors, with their tops directly connected to spring plates 7, driving them along base 8.

[0053] Initially, the power adjustment motor 10 is mounted in the center of the base 8 and connected to the base 8 via a fixing bolt 12. The power adjustment motor 10 is also a push rod motor, with the top connected to the power spring device 5. The ejection speed is controlled by adjusting the compression of the power spring device 5. A laser sensor 11 is mounted near the power adjustment motor 10 to measure the displacement of the power spring device 5.

[0054] The bottom plate of the power spring assembly 5 is connected to the top of the power adjustment motor 10, while the top plate contacts the bottom of the ejection panel interface 3. The power spring assembly 5 comprises four symmetrically distributed springs. The number, stiffness, compression, and placement of the springs are selected based on practical needs. When compressed, it generates an upward spring force. When unlocked, the spring force pushes the top plate, separating the ejection panel interface 3 and simultaneously separating the hosted payload 1 and the antenna satellite baseplate 2.

[0055] The locking steel ball 6 is located in the middle of the base 8, and a groove is provided on the side of the ejection plate interface 3. In the initial state, the spring plate 7 squeezes and fixes the locking steel ball 6 in the groove between the ejection plate interface 3 and the base 8, and uses the structural rigidity of the steel ball to maintain stability. When the release motor 9 is started, the spring plate 7 moves along the base 8. When the internal groove reaches the specified position, the locking steel ball 6 enters the cavity groove between the spring plate 7 and the base 8, thereby unlocking the ejection plate interface 3. The detailed diagram is shown in the figure below. Figure 3 As shown in 3a and 3b.

[0056] This design ensures the stability and safety of the host load 1 during the separation process, while realizing automated separation and locking functions through intelligent control.

[0057] The following further describes the structure for adjusting the separation speed of the hosted load:

[0058] The system further comprises a power regulating motor 10;

[0059] A power regulating motor 10 is provided between the inner bottom surface of the base 8 and the bottom of the power spring device 5;

[0060] The power regulating motor 10 is used to drive the power spring device 5 to move upwards and compress the power spring device 5 .

[0061] Specifically, after the hosted payload assembly 1 is locked with the host satellite 16, the power adjustment motor 10 is activated, pushing the power spring device 5 upward and compressing the power spring device. This is to adjust the separation speed of the hosted payload, because the greater the spring compression, the greater the spring force. The power spring device is first compressed to store the spring force. When the release motor 9 pushes the spring plate 7 upward along the base 8, the locking steel ball 6 falls. At this time, the spring force of the power spring device directly ejects the hosted payload assembly 1, achieving separation of the hosted payload assembly 1 from the host satellite 16.

[0062] The following further describes the preferred components for measuring the displacement of the power spring device 5:

[0063] The system further comprises a laser sensor 11;

[0064] The laser sensor 11 is used to measure the displacement of the power spring device 5 .

[0065] Specifically, the laser sensor 11 is used to monitor the displacement of the power spring device 5 to ensure that the compression amount and the spring force reach the preset values ​​respectively.

[0066] The preferred components of the release motor 9 are further described below:

[0067] The release motor 9 is a push rod motor.

[0068] The preferred components of the power regulating motor 10 are further described below:

[0069] The power regulating motor 10 is a push rod motor.

[0070] The composition of the power spring device 5 is further described below:

[0071] The power spring device 5 includes four symmetrically distributed springs, an upper top plate and a lower top plate;

[0072] Four symmetrically distributed springs are fixedly connected between the upper top plate and the lower top plate.

[0073] The following further describes the selection method of the power spring device 5:

[0074] The spring in the power spring device 5 is selected according to the mass of the hosted load component 15 .

[0075] Example 2:

[0076] A method for separating and locking a host satellite and a hosted payload is implemented according to the mechanical interface system of embodiment 1. The method includes the following steps:

[0077] Locking of host satellite and hosted payload:

[0078] The ejection plate interface 3 extends into the host satellite 16 and is plugged into the base 8 . The locking steel ball 6 is clamped between the through hole on the base 8 and the groove on the ejection plate interface 3 to achieve locking of the hosted payload assembly 15 and the host satellite 16 .

[0079] Separation of host satellite and hosted payload:

[0080] After starting the power adjustment motor 10, the power adjustment motor 10 pushes the power spring device 5 upward, compresses the power spring device 5, and then starts the two release motors 9. The release motor 9 pushes the spring plate 7 upward, so that the annular groove on the inner circumference of the spring plate 7 docks with the through hole on the base 8, and the locking steel ball 6 enters between the through hole and the annular groove on the spring plate 7 from the annular groove on the ejection plate interface 3. At this time, the power spring device 5 releases the elastic force to achieve the separation of the hosted payload assembly 15 and the host satellite 16.

[0081] Working principle:

[0082] like Figure 1 The following describes how to separate the hosted payload 1 from the host satellite through the mechanical interface system.

[0083] Step 1: Initial preparation:

[0084] Determine the mass, size, and shape of the host payload 1, and adjust the pre-compression and spring stiffness of the power spring device 5 based on these parameters. Assume that the mass of the launch target is m, the stiffness of the spring is k, and the pre-compression is x.

[0085] According to Hooke's law formula F=kx, the spring force F of the spring in the pre-compression state is calculated to ensure that the spring force is sufficient to separate the hosted load 1.

[0086] Step 2: Initial connection:

[0087] The hosted payload 1 is fixedly connected to the ejection plate interface 3 through the antenna satellite base plate 2, and the entirety is fixed to the host satellite top plate 13 of the host satellite.

[0088] Ensure that the locking steel ball 6 is fixed in the groove of the ejection plate interface 3 under the pressure of the spring plate 7, and use the structural rigidity of the steel ball to maintain the stability of the system.

[0089] Step 3: Power adjustment:

[0090] Start the power regulating motor 10, push the bottom plate of the power spring device 5 upward, and compress the spring to the preset position, such as Figure 4 shown.

[0091] The laser sensor 11 is used to monitor the displacement of the power spring device 5 to ensure that the compression reaches the preset value x and the spring force reaches the calculated F.

[0092] Step 4: Check before separation:

[0093] Check the connection status of all electrical interfaces, information transmission interfaces and thermal protection subsystems to ensure that the hosted load 1 can operate normally after separation.

[0094] Through system testing and data feedback, it is confirmed that all preparations have been completed and the separation system is on standby.

[0095] Step 5: Start the release motor:

[0096] The release motor 9 is started to push the spring plate 7 to move along the base 8 so that the groove inside the spring plate 7 reaches a specified position.

[0097] When the spring plate 7 moves to its position, the locking steel ball 6 falls off, releasing the lock on the ejection plate interface 3. Figure 5 、 Figure 6 shown.

[0098] Step 6: Separation process:

[0099] The power spring device 5 releases the spring force, the top plate moves upward, and pushes the ejection plate interface 3 to separate.

[0100] In order to ensure the reliability of all mechanisms of the miniaturized propulsion and launch system during the launch process, it is necessary to analyze the relationship between the compression of the power spring and the propulsion speed, and the stress changes of the locking spring during the launch process. At the same time, it is necessary to analyze the maximum load-bearing capacity of the mechanism during the propulsion and launch process, and study the force on the locking mechanism under power control.

[0101] First, a preliminary thrust requirement analysis is conducted for a 5kg launch target and a launch speed of 1-10m / s. Based on the law of conservation of energy, a preliminary calculation of spring power and stroke can be performed:

[0102]

[0103] Where m is the mass of the launch target, v is the expected velocity, k is the spring stiffness, and x is the pre-compression. Based on the design requirements for miniaturization and lightweight mechanical interface systems, and considering the friction between the ejection plate interface 3 and the base 8, it is recommended to use a power spring with a stiffness greater than 5 N / mm, with 3 to 10 springs, and a push rod motor with a maximum travel of 8 to 100 mm. Detailed launch dynamic analysis parameters are shown in Table 1.

[0104] Table 1 Target propulsion launch power analysis

[0105]

[0106]

[0107] Step 8. Subsequent operations:

[0108] Ensure that the orbit and attitude of the hosted payload 1 are stable after separation to avoid unnecessary rotation or drift.

[0109] Check the normal working status of the electrical interface, information transmission interface and thermal protection subsystem after separation to ensure that the host payload 1 can perform the task independently.

[0110] Although the present invention is described herein with reference to specific embodiments, it should be understood that these embodiments are merely illustrative of the principles and applications of the invention. It should be understood that many modifications may be made to the illustrative embodiments, and that other arrangements may be devised, without departing from the spirit and scope of the invention as defined by the appended claims. It should be understood that the various dependent claims and features described herein may be combined in ways other than those described in the original claims. It should also be understood that features described in conjunction with individual embodiments may be employed in conjunction with other described embodiments.

Claims

1. A mechanical interface system based on the separation and locking of the host satellite and the hosted payload, characterized by: The system comprises an ejection plate interface (3), a power spring device (5), a locking steel ball (6), a spring plate (7), a base (8) and two release motors (9); The ejection plate interface (3) is fixedly connected to the bottom of the host payload assembly (15), the base (8) is located inside the host satellite (16), and the ejection plate interface (3) extends into the host satellite (16) and is plugged into the base (8) through the compression power spring device (5); The base (8) includes a hollow pillar and two annular support plates, the two annular support plates being named a first annular support plate and a second annular support plate respectively; the first annular support plate is fixed to the bottom of the pillar, the second annular support plate is sleeved on the pillar, the pillar and the two annular support plates are an integral structure, through holes are evenly provided on the side wall of the pillar located above the second annular support plate; an annular groove is provided on the outer circumferential surface of the ejection plate interface (3); The spring plate (7) is sleeved on the pillar and supported on the second annular support plate. The tops of the two release motors (9) are in contact with the bottom surface of the spring plate (7). When the two release motors (9) are not started, the spring plate (7) squeezes and fixes the locking steel ball (6) between the through hole and the groove of the ejection plate interface (3), thereby locking the host payload assembly (15) and the host satellite (16); when the two release motors (9) are started, the spring plate (7) is driven to move upward along the base (8), so that the annular groove on the inner circumference of the spring plate (7) is docked with the through hole, and the locking steel ball (6) enters from the annular groove on the ejection plate interface (3) between the through hole and the annular groove on the spring plate (7), thereby separating the host payload assembly (15) from the host satellite (16); The system further includes a power regulating motor (10); A power regulating motor (10) is provided between the base (8) and the power spring device (5); The power regulating motor (10) is used to drive the power spring device (5) to move upwards and compress the power spring device (5).

2. The mechanical interface system based on separation and locking of the host satellite and the hosted payload according to claim 1, characterized in that: The system also includes a laser sensor (11); A laser sensor (11) is used to measure the displacement of the power spring device (5).

3. The mechanical interface system based on separation and locking of the host satellite and the hosted payload according to claim 1, characterized in that: The release motor (9) is a push rod motor.

4. The mechanical interface system based on separation and locking of the host satellite and the hosted payload according to claim 1, characterized in that: The power regulating motor (10) is a push rod motor.

5. The mechanical interface system based on separation and locking of the host satellite and the hosted payload according to claim 1, characterized in that: The power spring device (5) includes four symmetrically distributed springs, an upper top plate and a lower top plate; Four symmetrically distributed springs are fixedly connected between the upper top plate and the lower top plate.

6. The mechanical interface system based on separation and locking of the host satellite and the hosted payload according to claim 5, characterized in that: The spring in the power spring device (5) is selected according to the mass of the hosted load component (15).

7. A method for separating and locking a host satellite and a hosted payload, the method being implemented based on the mechanical interface system for separating and locking a host satellite and a hosted payload according to claim 2, characterized in that: The method includes the following: Locking of host satellite and hosted payload: The ejection plate interface (3) extends into the interior of the host satellite (16) and is plugged into the interior of the base (8), and the locking steel ball (6) is clamped between the through hole on the base (8) and the groove on the ejection plate interface (3), thereby achieving locking of the hosted payload assembly (15) and the host satellite (16); Separation of host satellite and hosted payload: After the power regulating motor (10) is started, the power regulating motor (10) pushes the power spring device (5) upward, compresses the power spring device (5), and then starts the two release motors (9). The release motor (9) pushes the spring plate (7) upward, so that the annular groove on the inner circumference of the spring plate (7) is docked with the through hole on the base (8), and the locking steel ball (6) enters between the through hole and the annular groove on the spring plate (7) from the annular groove on the ejection plate interface (3). At this time, the power spring device (5) releases the elastic force, and the host payload assembly (15) and the host satellite (16) are separated.

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