On-orbit replacement device

Abstract

The invention discloses an on-orbit replacement device, solves the problems that an existing boarding load separation interface is tedious in operation and poor in compatibility, and belongs to the field of mechanical structure design. The device comprises a host satellite connecting part, a first electric connecting part, an unlocking and fixing device, a spring ejection device, a motor part, a boarding load connecting part and a second electric connecting part. During assembly, the first electric connection part is electrically connected with the second electric connection part, the clamping structure of the unlocking and fixing device radially clamps the host satellite connection part, the pressing structure of the unlocking and fixing device axially presses the host satellite connection part, and the elastic end of the spring ejection device generates pre-tightening force and is anchored to the host satellite connection part. During separation, the host satellite connecting part is unlocked through driving of a rotating shaft of the motor part, the clamping structure and the pressing structure, the boarding load is pushed to be far away from the host satellite 1 through the pre-tightening force of the elastic end of the spring ejection device, and meanwhile the first electric connecting part and the second electric connecting part are separated.

Description

TECHNICAL FIELD

[0001] The application relates to a standardized strong-adaptation on-orbit replacement device based on electromechanical thermal integration design, and belongs to the field of mechanical structure design. BACKGROUND

[0002] Under the promotion of space commercialization, low-cost launch and constellation deployment, spacecrafts are changing from one-time use to maintainable and expandable modular systems. The on-orbit replacement unit (ORU) concept realizes a new mode of "taking spare parts to space, and performing on-orbit maintenance or upgrading in time" by making key subsystems into quickly disassembled modules. Compared with overall retirement and re-launch, ORU can significantly prolong the platform life, shorten the task empty window, and provide plug-and-play capability for temporary scientific payloads or market demand changes.

[0003] Existing separation interfaces mostly use one-time mechanisms such as pyrotechnic bolts, clamp rings, etc. Although they have large thrust and rapid action, they have strong impact and electromagnetic radiation and cannot be reset, and have a particularly strong impact on small satellite sensitive devices. In recent years, there have been low-impact solutions such as non-explosive electromagnetic locks, shape memory alloy release devices, and flexible guide cones, but most of them only focus on "mechanical + electrical" coupling, and have problems such as complicated operation, poor compatibility, mechanical-electrical-thermal fragmentation, and high risk of thermal interference. At the same time, the problems of complex structure, high power consumption, and large mass also limit the generalization and rapid iteration application. SUMMARY

[0004] In order to solve the problems of complicated operation, poor compatibility, mechanical-electrical-thermal fragmentation, and high risk of thermal interference of the existing hosted payload separation interface, the application provides a small-sized standardized electromechanical thermal integrated on-orbit replacement device suitable for multiple satellite platforms.

[0005] The on-orbit replacement device of the application comprises a host satellite connecting part, a No. 1 electrical connecting part, an unlocking fixing device, a spring ejection device, a motor part, a hosted payload connecting part, and a No. 2 electrical connecting part.

[0006] The host satellite connecting part is connected to the host satellite and the No. 1 electrical connecting part.

[0007] The unlocking fixing device is opposite to the No. 1 electrical connecting part, and the No. 2 electrical connecting part is arranged on the unlocking fixing device and corresponds to the position of the No. 1 electrical connecting part.

[0008] The unlocking fixing device, the spring ejection device, the motor part, and the hosted payload are fixedly connected to the hosted payload connecting part, the unlocking fixing device is provided with a clamping structure and a pressing structure, and the clamping structure and the pressing structure of the unlocking fixing device are driven by the rotating shaft of the motor part.

[0009] When assembled, the first electrical connection part is connected with the second electrical connection part to realize electrical connection between the host satellite and the hosted payload, the clamping structure radially clamps the host satellite connection part, the pressing structure axially presses the host satellite connection part, the elastic end of the spring ejection device generates a pre-tightening force, and is anchored with the host satellite connection part;

[0010] When disassembled, the clamping structure and the pressing structure are unlocked by driving the rotating shaft of the motor part, the pre-tightening force of the elastic end of the spring ejection device pushes the hosted payload 3 away from the host satellite 1, and the first electrical connection part and the second electrical connection part are separated.

[0011] As a preferred, the unlocking fixing device includes a first unlocking fixing device and a second unlocking fixing device;

[0012] The first unlocking fixing device includes a bearing end cover, an inclined sliding block, a first rolling bearing, a nut, an inclined clamp, a support rod and a plurality of clamping structures;

[0013] The bearing end cover is fixed on the hosted payload connection part;

[0014] The top of the bearing end cover is provided with the second electrical connection part; the inclined sliding block is located below the bearing end cover, the first rolling bearing is embedded in the center of the top of the inclined sliding block, the lower end of the first rolling bearing presses the nut, and the bottom surface of the nut abuts against the inclined clamp;

[0015] The side surface of the inclined sliding block is provided with a plurality of inclined tracks starting from the top and downwardly and outwardly, each inclined track corresponds to a clamping structure, one end of the clamping structure is arranged in the inclined sliding track, when assembled, the other end of the clamping structure radially clamps the host satellite connection part, when the nut moves downwardly and the inclined sliding block moves downwardly, one end of the clamping structure moves inwardly along the inclined track, and the other end of the clamping structure unlocks the host satellite connection part;

[0016] The second unlocking fixing device includes a screw sliding block, a second rolling bearing, a bearing seat and a plurality of pressing structures;

[0017] The screw sliding block is provided with a through hole in the center, the inner thread of the through hole is engaged with the outer thread of the nut, the bearing seat is located below the screw sliding block, a plurality of hinged interfaces are arranged along the circumference of the screw sliding block, a plurality of connection ends corresponding to the hinged interfaces are arranged along the circumference of the bearing seat, each pressing structure includes a first connecting rod, a second connecting rod and a pressing block; one end of the first connecting rod is hinged with one hinged interface, the top of the second connecting rod is provided with two hinged interfaces, one of which is hinged with the other end of the first connecting rod, and the other of which is hinged with one end of the pressing block, when assembled, the other end of the pressing block axially presses the host satellite connection part, the bottom of the second connecting rod is provided with a hinged interface, which is hinged with the connection end at the corresponding position of the bearing seat;

[0018] One end of the support rod is fixedly connected with the bearing end cover, and the other end of the support rod is connected with the bearing seat; the No. 2 rolling bearing is arranged at the center of the bearing seat, and the rotating shaft of the motor part passes through the No. 2 rolling bearing, the inclined surface clamp, the nut and the No. 1 rolling bearing in sequence from bottom to top.

[0019] As preferred, the clamping structure comprises a sliding shaft, a flange sleeve and a pull rod; one end of the sliding shaft moves along an inclined track, the other end of the sliding shaft is connected with one end of the pull rod through the flange sleeve, and the one end of the sliding shaft radially clamps the host satellite connection part.

[0020] As preferred, the spring ejection device comprises a pre-tightening spring, a spring locking shaft, a spring guide shaft, a guide rod, a linear bearing and a washer;

[0021] The bottom end of the guide rod is fixedly connected with the washer, the washer is fixed to the host satellite connection part, and the top end of the guide rod is anchored to the host satellite connection part.

[0022] The guide rod is sleeved with the linear bearing, the outer surface of the linear bearing is covered with the spring guide shaft, the outer surface of the spring guide shaft is further sleeved with the pre-tightening spring, one end of the spring locking shaft is fixedly connected with the host satellite connection part, and the other end of the spring locking shaft is sleeved with the top end of the pre-tightening spring.

[0023] As preferred, the No. 1 electric connection part is a male pin, and the No. 2 electric connection part is a female pin coaxial with the male pin.

[0024] As preferred, the on-orbit replacement device is wrapped with multi-layer thermal insulation material, and a polyimide coating is sprayed on the contact surface of the host satellite and the host load in contact with the on-orbit replacement device.

[0025] As preferred, the host satellite connection part is realized by a flange.

[0026] As preferred, the host satellite connection part is realized by a flange.

[0027] As preferred, the mass of the on-orbit replacement device is not more than 5 kg, and the horizontal size of the on-orbit replacement device is less than 200 mm, and the vertical height is less than 100 mm.

[0028] The beneficial effects of the present application are that energy and data transmission are completed by coaxial pins before separation, and low-impact ejection by pre-pressing spring after electric control unlocking; multi-layer thermal insulation is arranged outside the module, and a polyimide coating is arranged between the host satellite and the host load to isolate heat flow, so that thermal coupling between the ends is not realized. The design is compact and can be repeatedly reset, is suitable for various satellite platforms, and significantly improves the efficiency and reliability of on-orbit maintenance and task replacement. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 It is a whole schematic view of the host satellite and the host load;

[0030] Figure 2 Overall structure diagram of the on-orbit replacement device;

[0031] Figure 3 Partial explosion diagram of the on-orbit replacement device;

[0032] Figure 4 Partial structure diagram of the electrical interface;

[0033] Figure 5 Assembly schematic diagram of the No. 1 unlocking fixing device, the No. 2 unlocking fixing device and the spring ejection device 13;

[0034] Figure 6 Assembly structure schematic diagram of the No. 1 unlocking fixing device and the No. 2 unlocking fixing device;

[0035] Figure 7 Structure diagram of the No. 1 unlocking fixing device;

[0036] Figure 8 Structure diagram of the No. 2 unlocking fixing device;

[0037] Figures 9 to 12 Structure diagram of the spring ejection device;

[0038] Figure 13 Structure diagram of the motor part. DETAILED DESCRIPTION

[0039] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0040] It should be noted that the embodiments in the present application and the features in the embodiments can be combined with each other without conflict.

[0041] The present application will be further described below with reference to the drawings and specific embodiments, but not as a limitation of the present application.

[0042] In order to solve the problems of complicated operation, poor compatibility, mechanical-electrical-thermal cutting and high risk of thermal interference of the existing hosted payload separation interface, the present embodiment provides a small-sized standardized mechanical-electrical-thermal integrated on-orbit replacement device based on spring ejection, like Figure 1As shown, the on-orbit replacement device 4 of the embodiment is arranged between the host satellite 1 and the hosted payload 3, and at the initial moment, the three are collectively placed in the rocket fairing. The host satellite 1 is connected with the solar sail 2, the on-orbit replacement device 4 completes energy and data transmission through the coaxial pin before separation, and is ejected by the pre-pressed spring with low impact after the electric control is unlocked; the module is externally multi-layer heat-insulated, and the heat flow is isolated between the host satellite and the hosted payload 3 by using a polyimide coating to realize thermal decoupling of each end. The design is compact in size, can be reset repeatedly, is suitable for various satellite platforms, and significantly improves the efficiency and reliability of on-orbit maintenance and task replacement. The on-orbit replacement device of the embodiment comprises a host satellite connecting part, a first electric connecting part, an unlocking fixing device, a spring ejection device 13, a motor part, a hosted payload connecting part and a second electric connecting part;

[0043] The host satellite connecting part is connected with the host satellite 1 and the first electric connecting part; specifically, the host satellite can comprise a host satellite connecting flange 7 and a host satellite connecting bolt 5, and the host satellite connecting flange 7 is fixed on the host satellite through the host satellite connecting bolt 5;

[0044] The unlocking fixing device is opposite to the first electric connecting part, and the unlocking fixing device is provided with the second electric connecting part, which is in position correspondence with the first electric connecting part; the first electric connecting part is electrically connected with the host satellite 1, and the second electric connecting part is connected with the hosted payload 3, for providing energy and data transmission; specifically, the first electric connecting part is six male pins 15, the second electric connecting part is a female pin 17 coaxial with the male pins 15, and the male pins 15 are fixed on the host satellite connecting flange 7 through a bottom cover 14; the male pins 15 and the female pin 17 form a coaxial plug, which not only bears 28V / 100W power supply, but also supports RS-485 and Ethernet data link with a packet loss rate of less than or equal to 1%;

[0045] The hosted payload connecting part comprises a hosted payload connecting flange 8 and a hosted payload connecting bolt 6, and the hosted payload connecting flange 8 is fixed on the hosted payload 3 through the hosted payload connecting bolt 6 to form a rigid connection, thereby ensuring continuous force during the launch phase.

[0046] The unlocking fixing device, the spring ejection device 13, the motor part and the hosted payload 3 are fixedly connected with the hosted payload connecting flange 8, the unlocking fixing device is provided with a clamping structure and a pressing structure, and the clamping structure and the pressing structure of the unlocking fixing device are driven by the rotating shaft of the motor part;

[0047] During assembly, the first electric connecting part is connected with the second electric connecting part to realize electrical connection of the host satellite and the hosted payload 3, the clamping structure clamps the host satellite connecting part in the radial direction, the pressing structure axially presses the host satellite connecting part, the spring ejection device 13 generates a pre-tightening force at the elastic end, and is anchored with the host satellite connecting part;

[0048] When the host satellite 1 is separated, the clamping structure and the pressing structure are unlocked by the driving of the rotating shaft of the motor part, the pre-tightening force of the spring ejection device 13 pushes the hosted load 3 away from the host satellite 1, and the first electrical connection part and the second electrical connection part are separated.

[0049] Specifically, the unlocking fixing device includes a first unlocking fixing device 11 and a second unlocking fixing device 12.

[0050] The first unlocking fixing device 11 includes a bearing end cover 16, an inclined sliding block 19, a first rolling bearing 20, a nut 21, an inclined clamp 22, a support rod 25 and a clamping structure.

[0051] The top of the bearing end cover 16 is provided with a female pin 17; the inclined sliding block 19 is located below the bearing end cover 16, the first rolling bearing 20 is embedded in the center of the top of the inclined sliding block 19, the two are connected by a countersunk screw 23, the lower end of the first rolling bearing 20 presses the nut 21, the bottom surface of the nut 21 abuts against the inclined clamp 22, the nut 21 is connected with the inclined clamp 24 by a screw 24, and the bearing end cover 16 is fixedly connected with the support rod 25 by a bolt 18.

[0052] The side surface of the inclined sliding block 19 is provided with a plurality of inclined tracks downwardly and outwardly from the top as a starting point, each inclined track corresponds to one clamping structure, one end of the clamping structure is arranged in the inclined sliding track, and the other end of the clamping structure is used for radially clamping the host satellite connection part during assembly, when the rotating shaft of the motor part rotates, the nut 21 moves downwardly along the threads of the rotating shaft, drives the first unlocking fixing device 11 to move downwardly as a whole, when the inclined sliding block 19 moves downwardly, one end of the clamping structure moves inwardly along the inclined track, the other end of the clamping structure is unlocked to the host satellite connection part, and rigid constraint and guidance are realized.

[0053] Specifically, the clamping structure can include a sliding shaft 26, a flange sleeve 27 and a pull rod 28; one end of the sliding shaft 26 moves along the inclined track, the other end of the sliding shaft 26 is connected with one end of the pull rod 28 through the flange sleeve 27, and one end of the sliding shaft 26 is used for radially clamping the host satellite connection part.

[0054] Specifically, the second unlocking fixture 12 comprises a screw block 29, a second rolling bearing 33, a bearing seat 34 and a plurality of pressing structures, the bearing seat 34 is fixed on the hosting load connecting flange 8, the screw block 29 is provided with a through hole in the center, the inner thread of the through hole is engaged with the outer thread of the nut 21, the bearing seat 34 is located below the screw block 29, a plurality of hinged joints are arranged along the circumference of the screw block 29, a plurality of connecting ends corresponding to the hinged joints are arranged along the circumference of the bearing seat 34, each of the pressing structures comprises a first connecting rod 30, a second connecting rod 31 and a pressing block 32, one end of the first connecting rod 30 is hinged with one of the hinged joints, the top of the second connecting rod 31 is provided with two hinged joints, one of the hinged joints is hinged with the other end of the first connecting rod 30, the other hinged joint is hinged with one end of the pressing block 32, when assembled, the other end of the pressing block 32 is axially pressed against the hosting satellite connecting part, the bottom of the second connecting rod 31 is provided with one hinged joint, the hinged joint is hinged with the connecting end of the corresponding position of the bearing seat 34, the lower end of the second connecting rod 31 is hinged with the bearing seat 34 by a screw 35.

[0055] One end of the support rod 25 is fixedly connected with the bearing end cover 16, the other end of the support rod 25 is connected with the bearing seat 34, the second rolling bearing 33 is arranged at the center of the bearing seat 34, and the movement is stable. The rotating shaft of the motor part passes through the second rolling bearing 33, the inclined surface clamp 22, the nut 21 and the first rolling bearing 20 in sequence from bottom to top.

[0056] When the screw block 29 and the nut 21 move downward together, the first connecting rod 30, the second connecting rod 31 and the pressing block 32 are driven to move relatively, and a four-bar linkage mechanism is formed to realize synchronous unlocking.

[0057] Specifically, the spring ejection device 13 comprises a pre-tightening spring 37, a spring locking shaft 38, a spring guide shaft 40, a guide rod 41, a linear bearing 42 and a grommet 43.

[0058] The bottom end of the guide rod 41 is fixedly connected with the grommet 43, the grommet 43 is fixed on the hosting load connecting flange 8 by the screw 36, and the top end of the guide rod 41 is anchored to the hosting satellite connecting part.

[0059] The guide rod 41 is sleeved with the linear bearing 42, the outer surface of the linear bearing 42 is covered with the spring guide shaft 40, the outer surface of the spring guide shaft 40 is further sleeved with the pre-tightening spring 37, one end of the spring locking shaft 38 is fixedly connected with the hosting satellite connecting part, and the other end of the spring locking shaft 38 is sleeved with the top end of the pre-tightening spring 37.

[0060] When the unlocking mechanism completes the downward stroke and releases the constraint, the pre-tightening spring 37 rapidly releases the stored energy, and the guide rod 41 provides separation momentum for the hosting load 3 through the spring guide shaft 40.

[0061] The motor part includes a main motor 9 and a screw flange 44, a screw 45 and a screw rod 46, the screw rod 46 serving as a rotating shaft of the motor part, the main motor 9 is fixed on the hosting load connecting flange 8 through the screw 45, and is connected with the screw flange 44 through a bolt; the screw flange 44 is fixedly connected with the screw rod 46 at the center, and drives the unlocking mechanism to complete the whole sequence of moving down, unlocking and ejecting, so as to ensure reliable separation on the orbit and controllable impact.

[0062] In addition, in the present embodiment, the on-orbit replacement device is wrapped with multiple layers of thermal insulation materials, and a polyimide coating is sprayed on the contact surface of the hosting satellite and the hosting load in contact with the on-orbit replacement device, forming a thermal insulation barrier without direct heat flow channel between the three, so that the parent satellite and the child satellite still do not affect each other within a large temperature cycle of ±50 ℃; this not only avoids the thermal drift of optical or battery components caused by adjacent replacement modules, but also enables designers to quickly integrate without complex cross-structure thermal analysis.

[0063] The on-orbit replacement device of the present embodiment realizes reliable separation of a 50 kg level hosting load under the constraint of extreme lightness and miniaturization, with a mass not exceeding 5 kg, a horizontal size ≤200 mm and a vertical height ≤100 mm. The compact size means that it can be installed on the cabin wall, slide rail or standard flange of various satellite platforms without changing the overall layout; the lower mass directly reduces the design margin of the rocket trim and attitude control system, thereby releasing more payload or propellant space for the whole satellite, improving mission economy.

[0064] Relying on the electrically controlled double-redundant self-locking and precise pre-pressing spring, the on-orbit replacement device of the present embodiment has a on-orbit separation success rate ≥90%, and can provide a linear velocity of up to 1.1 m / s and an angular velocity below 0.1° / s for the child satellite; at the same time, the parent satellite reverse disturbance is suppressed within 0.5 m / s and 0.05° / s. This “low impact, low coupling” kinetic characteristic significantly reduces the consumption of attitude control fuel and momentum wheel during constellation deployment, enabling the satellite to maintain high margin attitude control capability even when multiple payloads are replaced or the mission package is frequently updated.

[0065] The on-orbit replacement device of the present embodiment completes modal, static force, sinusoidal vibration, random vibration and impact full-spectrum environmental tests at the factory stage, and can directly withstand the 15-20 g level load spectrum of the rocket with the hosting satellite without additional reinforcement support, greatly simplifying the assembly and test process. Its standardized mechanical interface has been verified by three types of mainstream commercial satellites, and can quickly adapt to changes in the inertia characteristics of 300 kg level parent satellites and 50 kg level child satellites, helping operators to realize cross-platform and cross-batch mass on-orbit replacement with one set of hardware, significantly reducing non-repetitive design costs.

[0066] In terms of electromechanical coupling, the coaxial pin supports 28 V / 100 W peak power supply; the dual-channel RS-485 and gigabit Ethernet link ensures that the packet loss rate is ≤1% in a high-vibration environment, providing a stable channel for high-bandwidth image transmission or sensitive data acquisition. When the electrically controlled unlocking triggers separation, the pin and signal port are synchronized to pull off, eliminating the risk of electric arc or transient overvoltage caused by timing errors, significantly improving the safety of the sub-satellite and mother satellite electronic systems.

[0067] The working process of the embodiment includes:

[0068] Step 1: At the final assembly site, align the host satellite 1 bottom docking ring with the host satellite connection flange 7 hole of the on-orbit replacement device 4, insert the host satellite connection bolt 5 and tighten it according to the torque specification, and realize rigid fixation.

[0069] Step 2: Align the mounting surface of the hosted payload 3 with the hosted payload connection flange 8 of the on-orbit replacement device 4, assemble the hosted payload connection bolt 6, and form a complete "sandwich" structure.

[0070] Step 3: Install the electrical interface part 10: insert the male pin 15 into the female pin 17 once, and then lock the electrical interface bottom cover 14 to the host satellite connection flange 7 with bolts, complete the closure of the 28V / 100W power supply and the RS-485 / ethernet signal link.

[0071] Step 4: Spray polyimide coating on the contact surfaces of the host side and the hosted side, and wrap the module body with multiple layers of thermal insulation materials to ensure that the heat flow does not conduct between the three.

[0072] Step 5: Compress the spring 37: pull down the spring lock shaft 38 to the specified stroke to generate a pre-tightening force; confirm that the washer 43, guide rod 41 and screws 36 / 39 are firmly fixed in place.

[0073] Step 6: After completing the self-checking, place the combined body—host satellite 1, on-orbit replacement device 4, hosted payload 3—into the rocket fairing as a whole and enter the launch process.

[0074] Step 7: After entering the orbit, the mission computer issues a "separation preparation" instruction; the motor 9 self-checks normally and the position sensor returns a perfect lock.

[0075] Step 8: Execute the "separation" instruction, the motor 9 starts to rotate, and the torque is transmitted to the screw rod 46 through the screw flange 44, driving the screw rod to rotate continuously.

[0076] Step 9: The screw rod 46 rotates and the nut 21 cannot rotate, so the nut 21 moves axially downward along the thread.

[0077] Step 10, the nut 21 first pushes the No. 1 unlocking fixture 11 down: the rolling bearing 20 reduces friction, the inclined surface slider 19 does not rotate as a whole, and only linear displacement is made.

[0078] Step 11, during the downward movement of the inclined surface slider 19, the inclined surface forces the sliding shaft 26 to slide inward, driving the pull rod 28 to retract, thereby releasing the radial clamping of the pull rod on the host satellite connecting flange 7, and realizing the first mechanical unlocking.

[0079] Step 12, at the same time, the nut 21 is in close contact with the screw block 29, and the No. 2 unlocking fixture 12 is continuously pushed down synchronously.

[0080] Step 13, the screw block 29 pulls the No. 1 connecting rod 30 and the No. 2 connecting rod 31 inward, and the pressing block 32 rotates around its hinge point by a small angle, releasing the pressing of the host satellite connecting flange 7, and realizing the second mechanical unlocking.

[0081] Step 14, the bottom end of the No. 2 connecting rod 31 is hinged to the bearing seat 34 by means of the screw 35, and the rolling bearing 33 in the bearing seat provides low-friction support, ensuring smooth operation of the four-bar linkage mechanism.

[0082] Step 15, the No. 1 unlocking fixture 11 and the No. 2 unlocking fixture 12 are supported by the rolling bearings 20 / 33, and only linearly move downward without rotating with the screw.

[0083] Step 16, when both sets of unlocking fixtures reach the designed lower limit position, the travel switch reports to the controller that "all unlocking is completed", and the screw 46 stops rotating.

[0084] Step 17, at this time, only the axial pre-tightening force of the pre-tightening spring 37 remains between the hosted load 3 and the host satellite 1, without any rigid constraint.

[0085] Step 18, when the unlocking fixture is completely opened, the spring release logic is triggered, the pre-warning spring 37 is quickly stretched along the spring guide shaft 40, and the linear bearing 42 ensures pure axial movement.

[0086] Step 19, the guide rod 41 cooperates with the spacer ring 43 to convert the spring potential energy into a linear velocity of 0~1.1m / s, pushing the hosted load 3 away from the host satellite 1, and the angular velocity is limited to 0.1° / s.

[0087] Step 20, at the moment of separation, the male pin 15 and the female pin 17 are synchronously pulled off, safely cutting off the power supply and data link; the heat insulation layer and the polyimide coating continuously block heat conduction.

[0088] In summary, the present embodiment meets or exceeds the requirements of existing technology in all indicators such as quality, volume, dynamic disturbance, electrical bandwidth, thermal isolation, etc., laying a solid foundation for on-orbit maintenance, task quick replacement and long-term reliable operation in the constellation era.

[0089] While the application has been described with reference to particular embodiments, it is to be understood that the application is not limited to the particulars disclosed. Rather, it is a continuation of the principles and applications of the present application. It is therefore to be understood that numerous modifications, both as to the details and embodiments illustrated and the application, can be made by those skilled in the art without departing from the spirit and scope of the application as defined by the appended claims. It should be understood that all the features described in connection with the various embodiments can be combined in other combinations than those explicitly described. It should also be understood that features described in connection with one embodiment can be combined with features described in connection with other embodiments.

Claims

1. On-orbit replacement device, characterized in that, The host satellite connecting part, the first electrical connecting part, the unlocking fixing device, the spring shooting device, the motor part, the hosted payload connecting part and the second electrical connecting part are connected; The host satellite connecting part is connected with the first electrical connecting part; The unlocking fixing device is opposite to the first electrical connecting part, and the second electrical connecting part is arranged on the unlocking fixing device and corresponds to the position of the first electrical connecting part; The unlocking fixing device, the spring shooting device, the motor part and the hosted payload are fixedly connected with the hosted payload connecting part, the unlocking fixing device is provided with clamping structures and pressing structures, and the clamping structures and the pressing structures are driven by the rotating shaft of the motor part; During assembly, the first electrical connecting part is connected with the second electrical connecting part to realize electrical connection of the host satellite and the hosted payload, the clamping structures are used for radially clamping the host satellite connecting part, the pressing structures are used for axially pressing the host satellite connecting part, the pre-tightening force is generated at the elastic end of the spring shooting device, and the host satellite connecting part is anchored; During separation, the clamping structures and the pressing structures are unlocked for the host satellite connecting part by driving the rotating shaft of the motor part, the pre-tightening force of the elastic end of the spring shooting device pushes the hosted payload away from the host satellite, and the first electrical connecting part and the second electrical connecting part are separated.

2. The on-orbit replacement device of claim 1, wherein The unlocking fixing device comprises a first unlocking fixing device and a second unlocking fixing device; The first unlocking fixing device comprises a bearing end cover, an inclined sliding block, a first rolling bearing, a nut, an inclined clamping hoop, a support rod and a plurality of clamping structures; The bearing end cover is fixed on the hosted payload connecting part; The top of the bearing end cover is provided with the second electrical connecting part; The inclined sliding block is located below the bearing end cover, the first rolling bearing is embedded in the center of the top of the inclined sliding block, the lower end of the first rolling bearing presses the nut, and the bottom surface of the nut abuts against the inclined clamping hoop; The side surface of the inclined sliding block is provided with a plurality of inclined tracks starting from the top and downwardly and outwardly, each inclined track corresponds to one clamping structure, one end of the clamping structure is arranged in the inclined sliding track, and the other end of the clamping structure radially clamps the host satellite connecting part during assembly; when the nut moves downwardly, the inclined sliding block moves downwardly, one end of the clamping structure moves inwardly along the inclined track, and the other end of the clamping structure unlocks the host satellite connecting part; The second unlocking fixing device comprises a screw sliding block, a second rolling bearing, a bearing seat and a plurality of pressing structures; A through hole is formed in the center of the screw sliding block, the internal thread of the through hole is engaged with the external thread of the nut, the bearing seat is located below the screw sliding block, a plurality of hinged interfaces are arranged along the circumference of the screw sliding block, a plurality of connecting ends corresponding to the hinged interfaces are arranged along the circumference of the bearing seat, and each pressing structure comprises a first connecting rod, a second connecting rod and a pressing block. One end of the first connecting rod is hinged to one of the hinge joints, the top of the second connecting rod is provided with two hinge joints, one of which is hinged to the other end of the first connecting rod, and the other is hinged to one end of the pressing block, and the other end of the pressing block is axially pressed against the host satellite connection part when assembled, and the bottom of the second connecting rod is provided with a hinge joint which is hinged to the connecting end of the corresponding position of the bearing seat; One end of the support rod is fixedly connected with the bearing end cover, and the other end of the support rod is fixedly connected with the bearing seat; the second rolling bearing is arranged at the center of the bearing seat, and the rotating shaft of the motor part passes through the second rolling bearing, the inclined surface clamp, the nut and the first rolling bearing in sequence from bottom to top.

3. The on-orbit replacement device of claim 2, wherein, Each of the clamping structures comprises a sliding shaft, a flange sleeve and a pull rod; One end of the sliding shaft moves along the inclined track, and the other end of the sliding shaft connects one end of the pull rod through the flange sleeve, and one end of the sliding shaft radially clamps the host satellite connection part.

4. The on-orbit replacement device of claim 1, wherein The spring ejection device comprises a pre-tightening spring, a spring locking shaft, a spring guide shaft, a guide rod, a linear bearing and a grommet; The bottom end of the guide rod is fixed with the grommet, the grommet is fixed to the host load connection part, and the top end of the guide rod is anchored to the host satellite connection part. The guide rod is sleeved with the linear bearing, and the outer surface of the linear bearing is covered with the spring guide shaft. The outer surface of the spring guide shaft is further sleeved with the pre-tightening spring, one end of the spring locking shaft is fixedly connected with the host satellite connection part, and the other end of the spring locking shaft is sleeved with the top end of the pre-tightening spring.

5. The on-orbit replacement device of claim 1, wherein The first electrical connection part is a male pin, and the second electrical connection part is a female pin coaxial with the male pin.

6. The on-orbit replacement device of claim 1, wherein The on-orbit replacement device is wrapped with multiple layers of thermal insulation materials, and the contact surfaces of the host satellite and the host load in contact with the on-orbit replacement device are sprayed with a polyimide coating.

7. The on-orbit replacement device of claim 1, wherein The host satellite connection part is realized by a flange.

8. The on-orbit replacement device of claim 1, wherein, The host load connection part is realized by a flange.

9. The on-orbit replacement device of claim 1, wherein, The mass of the on-orbit replacement device is not more than 5 kg, and the horizontal size of the on-orbit replacement device is less than 200 mm, and the vertical height is less than 100 mm.

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