Zero-gravity lifting device for space payload

Abstract

The application provides a zero-gravity lifting device for a space payload, which comprises a supporting unit, a transmission unit, a lifting unit and a detection control unit; the supporting unit is fixed on a satellite-borne equipment fixing frame, the transmission unit, the lifting unit and the detection control unit are all fixed on the supporting unit, and the driving end of the transmission unit and the input display of the detection control unit are arranged on the same plane; the lifting unit has two lifting planes, under the control of the transmission unit, the satellite-borne equipment is lifted by one lifting plane or the lifting function is completed by the other lifting plane when the satellite-borne equipment is turned over 180 degrees with the star ship; the detection control unit detects the lifting weight in real time during the lifting process of the lifting plane, and if the lifting weight exceeds the set value, an alarm is given to avoid the contact surface of the satellite-borne equipment from being damaged by strong pressure.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of aerospace, and particularly relates to a zero-gravity lifting device for spacecraft load. BACKGROUND

[0002] In the field of aerospace, some spaceborne devices are connected with the spacecraft body by vibration isolators to weaken the transmission of vibration during the on-orbit operation of the spaceborne devices. However, the spaceborne devices will experience complex vibration and impact during the ascending process of the satellite. In order to avoid damage to the vibration isolator, the spaceborne devices with shock absorption requirements are required to be fastened to the spacecraft body before launch, and then unlocked before the on-orbit operation, so that the vibration isolator can play a role. The spaceborne devices need to go through the unlocking and locking process many times during the ground transportation, mechanical test, performance test, assembly and other links. Since the gravity needs to be overcome and impact on the spaceborne devices is not allowed, the lifting device is a key device for efficiently and accurately completing the unlocking and locking tasks.

[0003] The existing lifting method mainly uses general equipment, such as a crane lifting and a rope hoisting. The operation space and access channel in the spacecraft are very limited, so the lifting equipment cannot be sent into the spacecraft and cannot support the device on a high-strength plane. The rope hoisting method can be used in single machine devices with special tooling, but the high-altitude hoisting environment cannot be provided in the spacecraft, and the device lifting cannot be realized. SUMMARY

[0004] The technical problem solved by the present application is that the existing lifting method cannot be applied to the narrow space of the spacecraft for high-reliability and safe operation. The purpose of the present application is to provide a zero-gravity lifting device for space load which can be operated in a narrow space, is safe and reliable, is suitable for ground stiffness products, and can provide digital feedback during the operation process.

[0005] The technical solution of the present application is a zero-gravity lifting device for space load, comprising a support unit, a transmission unit, a lifting unit and a detection control unit.

[0006] The support unit is fixed on the fixed frame of the spaceborne device, the transmission unit, the lifting unit and the detection control unit are all fixed on the support unit, and the driving end of the transmission unit and the input display of the detection control unit are arranged on the same plane. The lifting unit has two lifting planes, and under the control of the transmission unit, the spaceborne device is lifted by one lifting plane or the lifting function is completed by the other lifting plane when the spaceborne device is turned over 180° with the spacecraft. The detection control unit detects the lifting weight in real time during the lifting process of the lifting plane, and if the value exceeds the set value, an alarm is given to avoid damage to the contact surface of the spaceborne device by strong pressure.

[0007] Preferably, the support unit is a cantilever structure, comprising a front panel, a front end frame, a cantilever beam, a load-bearing plate; the front end frame is arranged with mounting hole positions around for fixing the entire device to the equipment frame, the inside of the front end frame adopts a hollow structure, the front panel is arranged in the middle of the front end frame, and the load-bearing plate is fixedly connected with the front end frame through two cantilever beams.

[0008] Preferably, the transmission unit comprises a rotating roller, a transmission rod, a shaft coupling, a worm gear reducer and a lead screw nut; the transmission rod is connected with the front end frame through a bearing, and the rotating roller is fixedly connected with the transmission rod; the worm gear reducer is fixed on the load-bearing plate, the input end of the worm gear reducer is coaxial with the transmission rod, a shaft coupling is arranged between the input end and the transmission rod for connection, and the output end of the worm gear reducer is a lead screw structure matched with the lead screw nut.

[0009] Preferably, the lifting unit comprises a linear bearing, a light rod, a main structure plate, a main supporting plate, a secondary structure plate and a secondary supporting plate; the light rod is arranged around the main structure plate and connected with the main structure plate and the secondary structure plate at two ends respectively; the light rod and the linear bearing form a sliding pair, the linear bearing is coaxial with the light rod and fixed with the load-bearing plate, so as to limit the rotation of the lifting unit; the main structure plate is fixedly connected with the lead screw nut and moves up and down along the axis of the light rod together with the lead screw nut; the main supporting plate and the secondary supporting plate are connected with the main structure plate and the secondary structure plate respectively through a plurality of weight sensors.

[0010] Preferably, the number of weight sensors is at least three, which are located on the same circumference and uniformly distributed.

[0011] Preferably, the main supporting plate and the secondary supporting plate are made of the same material as the product to be lifted and are designed as thin plates, which can deform with the lifted product to avoid stress concentration on the contact surface.

[0012] Preferably, the stiffness of the main structure plate and the secondary structure plate ensures that the lifting plane is perpendicular to the fixed plane of the front end frame.

[0013] Preferably, the detection and control unit comprises a mobile power supply, a power switch, a reversing switch, a main display instrument, a secondary display instrument, a weight sensor, a displacement sensor and a concentrator box.

[0014] The power switch, the reversing switch, the main display instrument and the secondary display instrument are arranged at the corresponding hole positions of the front panel; two concentrator boxes are fixedly connected on the cantilever beam and transmit the weight data collected by the weight sensors under the main supporting plate / secondary supporting plate to the main display instrument / secondary display instrument after summation.

[0015] The displacement sensor is fixed with the polished rod and is used for detecting the relative displacement of the main structure plate and the bearing plate; the power switch controls the opening and closing of all electrical equipment; the reversing switch is used for selectively opening the main display instrument or the auxiliary display instrument; the main display instrument displays the weight applied on the main supporting plate in real time, and the instrument beeps when the weight reaches the preset warning value, and the beeping automatically disappears when the weight decreases to below the warning value; the auxiliary display instrument displays the weight applied on the auxiliary supporting plate in real time, and the instrument beeps when the weight reaches the preset warning value, and the beeping automatically disappears when the weight decreases to below the warning value.

[0016] A method for using the zero-gravity lifting device for the spaceborne load, comprising:

[0017] The power switch is turned on, the rotating roller is rotated, and the displacement sensor value is observed at the same time, the lifting unit is moved to a suitable position, and the lifting unit does not interfere with the spaceborne equipment during installation.

[0018] The device is fixed on the spaceborne equipment fixed frame through the four peripheral fixed hole positions on the front end frame, the reversing switch is placed in the main direction, the rotating roller is rotated to make the main supporting plate of the lifting unit close to and contact the top surface of the equipment, and the rotating roller is continuously and slowly rotated to stop when the main display instrument value reaches the weight of the spaceborne equipment.

[0019] The spaceborne equipment is tightly connected with the fixed frame, the rotating roller is reversely rotated, the main supporting plate is separated from the equipment, the device fixing screws are disassembled, the whole device is taken out, and each switch is closed one by one or the lifting unit is moved downwards to contact the bottom surface of the spaceborne equipment, and then the whole device is smoothly moved out along the contact surface.

[0020] Preferably, the rotating rotating roller is observed at the same time, the lifting unit is moved to a suitable position, and the lifting unit does not interfere with the spaceborne equipment during installation.

[0021] When the displacement sensor value is zero, the auxiliary supporting plate of the lifting unit contacts the bottom surface of the spaceborne equipment, and is moved to the front end frame and the fixed frame installation surface.

[0022] The rotating roller is rotated, when the fixed hole position on the front end frame is aligned with the corresponding hole position on the fixed frame, the rotating roller is stopped, the displacement sensor value at this time is recorded, and the displacement sensor value corresponding to the lifting unit moving to a suitable position when the spaceborne equipment is lifted is recorded.

[0023] Compared with the prior art, the beneficial effects of the present application are:

[0024] (1) The supporting plate in the device adopts multi-point support and has a follow-up deformation function, and is suitable for lifting working conditions of ground stiffness products.

[0025] (2) The device measures the lifting condition of the operator by monitoring the contact force with the product in real time and feeding back, and triggers a prompt sound near the set force value, which can alert and prevent over-lifting.

[0026] (3) The lifting device is fixed by the hole of the device itself, and the operation process will not interfere with other devices in the cabin.

[0027] (4) All detection and display function components in the device are powered by a mobile power supply, without the need for external power supply, which is convenient for installation and removal.

[0028] (5) The reversing switch in the device only starts the single direction detection circuit each time to prevent misjudgment of the instrument reading. BRIEF DESCRIPTION OF DRAWINGS

[0029] Figure 1 It is a schematic diagram of the overall structure of the device;

[0030] Figure 2 It is a schematic diagram of the main bearing structure in the application;

[0031] Figure 3 It is a schematic diagram of the transmission unit structure in the application;

[0032] Figure 4 It is a schematic diagram of the detection control unit in the application;

[0033] Figure 5 It is a schematic diagram of the lifting unit structure in the application;

[0034] Figure 6 It is a schematic diagram of the main lifting direction lifting in place state in the application;

[0035] BRIEF DESCRIPTION OF DRAWINGS: 1- support unit, 2- transmission unit, 3- lifting unit, 4- detection control unit, 5- front panel, 6- front end frame, 7- cantilever beam, 8- auxiliary support plate, 9- auxiliary structure plate, 10- light lever, 11- linear bearing, 12- weighing plate, 13- main support plate, 14- main structure plate, 15- rotating roller, 16- transmission rod, 17- coupling, 18- worm and gear reducer, 19- sliding nut, 20- auxiliary display instrument, 21- main display instrument, 22- reversing switch, 23- power switch, 24- junction box, 25- weight sensor, 26- displacement sensor, 27- mobile power supply. DETAILED DESCRIPTION

[0036] The application will be further described below in combination with examples.

[0037] The zero-gravity lifting device for space load of the application is as follows Figure 1As shown, it comprises a support unit 1, a transmission unit 2, a lifting unit 3 and a detection control unit 4. The transmission unit 2, the lifting unit 3 and the detection control unit 4 are all fixed on the support unit 1, and the driving end of the transmission unit 2 and the input end of the detection control unit 4 are arranged on the same plane. The lifting device has two supporting plates, which can be used for front lifting of the spaceborne equipment and still meet the lifting function when the spaceborne equipment is turned over 180° with the spacecraft. The detection control unit 4 detects the lifting weight in real time during the lifting of the supporting plate, and alarms if it exceeds the set value, so as to avoid damage to the contact surface of the spaceborne equipment by strong pressure.

[0038] As shown in a preferred embodiment of the present application, Figure 2 The support unit 1 is a cantilever structure, comprising a front panel 5, a front end frame 6, a cantilever beam 7 and a bearing plate 12. Four mounting hole positions are arranged around the front end frame 6, which is used to fix the whole device to the equipment frame. The inside of the front end frame 6 is in a hollow structure, and the surrounding inclined beams are used for gripping to facilitate the transfer in a small space. The front panel 5 is arranged in the middle of the front end frame 6, and the bearing plate 12 is tightly connected with the front end frame 6 through two cantilever beams 7.

[0039] As shown in a preferred embodiment of the present application, Figure 3 The transmission unit 2 comprises a rotating roller 15, a transmission rod 16, a shaft coupling 17, a worm gear reducer 18 and a lead screw nut 19. The transmission rod 16 is connected with the front end frame 6 through a bearing, and the rotating roller 15 is tightly connected with the transmission rod 16 through a screw. The worm gear reducer 18 is fixed on the bearing plate 12, the input end of which is coaxial with the transmission rod 16, and the two are connected through the shaft coupling 17. The output end is a lead screw structure matched with the lead screw nut 19. The transmission unit 2 converts the rotating movement of the rotating roller into the up-down movement of the lead screw nut 19 in the vertical direction.

[0040] As shown in a preferred embodiment of the present application, Figure 2 , 5As shown, the lifting unit 3 includes a linear bearing 11, a light screw 10, a main structure plate 14, a main supporting plate 13, a secondary structure plate 9 and a secondary supporting plate 8. The main structure plate 14 is fixedly connected with the screw nut 19 and moves up and down with the screw nut 19. The light screw 10 is arranged around the main structure plate 14 and forms a sliding pair with the linear bearing 11, and can move along the axis direction of the light screw 10. The linear bearing 11 is coaxial with the light screw 10 and is fixed with the bearing plate 12, thereby limiting the rotation of the lifting unit 3. The main supporting plate 14 and the secondary supporting plate 9 are designed as thin plates, which can deform when contacting with the lifted object to avoid stress concentration on the contact surface. The main structure plate 14 and the secondary structure plate 9 have high rigidity, which can ensure that the lifting plane and the fixed plane of the front end frame 6 are substantially perpendicular. The main supporting plate 13 and the secondary supporting plate 8 are connected with the main structure plate 14 and the secondary structure plate 9 respectively through three weight sensors 25.

[0041] As shown in a preferred embodiment of the present application, Figure 4 As shown, the detection control unit 4 includes a mobile power supply 27, a power switch 23, a reversing switch 22, a main display instrument 21, a secondary display instrument 20, a weight sensor 25, a displacement sensor 26 and a concentrator box 24. The power switch 23, the reversing switch 22, the main display instrument 21 and the secondary display instrument 20 are arranged at the corresponding hole positions of the front panel 5.

[0042] The concentrator box 24 is arranged at the middle position of the two cantilever beams 7 and is arranged in two layers. The concentrator box 24 is fixedly connected with the two cantilever beams 7 through screws and collects and sums the weight data collected by the three weight sensors 25 of the main supporting plate 13 and the secondary supporting plate 8 respectively, and then transmits the summed data to the main display instrument 21 and the secondary display instrument 20.

[0043] The displacement sensor 26 is fixed with the light rod 10 and can be used to detect the relative displacement between the lifting unit 3 and the bearing plate 12. The power switch 23 controls the opening and closing of all electrical equipment, and the reversing switch 22 is used to selectively open the main display instrument 21 or the secondary display instrument 20. The main display instrument 21 can display the weight applied to the main supporting plate 13 in real time. When the weight value reaches the preset warning value, the instrument beeps to alarm, and when the weight decreases to below the warning value, the beeping automatically disappears. The secondary display instrument 20 can display the weight applied to the secondary supporting plate 8 in real time. When the weight value reaches the preset warning value, the instrument beeps to alarm, and when the weight decreases to below the warning value, the beeping automatically disappears.

[0044] The present application will be described in detail below in conjunction with specific embodiments.

[0045] Embodiment 1:

[0046] When the satellite-borne equipment needs to be lifted and locked in the direction of the main supporting plate, the operation process is as follows:

[0047] (1) Turn on the power switch 23, rotate the rotating roller 15 while observing the displacement sensor 26 value, move the lifting unit 3 to the appropriate position, so that the device does not interfere with the spaceborne equipment during installation;

[0048] For the same spaceborne equipment, the first operation can be the displacement sensor value of the lifting unit's auxiliary support plate contacting the bottom surface of the spaceborne equipment when the displacement sensor value is zero, moving to the front end frame and the fixed frame( Figure 6 middle grid part) installation surface contact; Figure 6

[0049] Rotate the rotating roller, when the front end frame fixed hole position and the fixed frame corresponding hole position are aligned, stop rotating the rotating roller, record the displacement sensor value at this time as the displacement sensor value corresponding to the lifting unit moving to the appropriate position when lifting the current spaceborne equipment. Subsequently, the value can be used to simply complete the installation of the front end frame and the fixed frame.

[0050] (2) Fix the device on the spaceborne equipment fixed frame through the four fixed hole positions on the front end frame 6, set the reversing switch 22 to the main direction, rotate the rotating roller 15 to make the main support plate 13 of the lifting unit close to and contact the top surface of the equipment, continue to slowly rotate the rotating roller 15 to stop when the main display instrument 21 value reaches the weight of the equipment;

[0051] (3) Tighten the connection between the spaceborne equipment and the fixed frame, rotate the rotating roller 15 in the opposite direction, make the main support plate 13 separate from the equipment, remove the device fixing screws, take out the entire device and turn off each switch one by one. The lifting unit 3 can also be moved downward to the point where the auxiliary support plate 8 contacts the bottom surface of the equipment, and then the entire device is smoothly removed along the contact surface.

[0052] Although the present application has been disclosed with the above preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application using the disclosed methods and technical contents without departing from the spirit and scope of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application, which does not deviate from the technical solutions of the present application, belongs to the protection scope of the technical solutions of the present application.

[0053] The part of the present application not described in detail is the common knowledge of those skilled in the art.​

Claims

1. A zero-gravity lifting device for space payloads, characterized by: The support unit, the transmission unit, the lifting unit and the detection control unit are arranged on the satellite-borne equipment fixing frame. The support unit is fixed on the satellite-borne equipment fixing frame, the transmission unit, the lifting unit and the detection control unit are fixed on the support unit, and the driving end of the transmission unit and the input end of the detection control unit are arranged on the same plane. The lifting unit has two lifting planes, and the satellite-borne equipment is lifted by one lifting plane under the control of the transmission unit or is lifted by the other lifting plane when the satellite-borne equipment is turned over 180° with the satellite ship. The detection control unit detects the lifting weight in real time during the lifting process of the lifting plane, and alarms if the weight exceeds the set value, so as to avoid the contact surface of the satellite-borne equipment from being damaged by strong pressure. The support unit is a cantilever structure, including a front panel, a front end frame, a cantilever beam and a bearing plate. The front end frame is arranged with mounting hole positions around the four sides for fixing the whole device to the equipment frame, and the inside of the front end frame is hollow. The front panel is arranged in the middle of the front end frame, and the bearing plate is tightly connected with the front end frame through two cantilever beams. The detection control unit includes a mobile power supply, a power switch, a reversing switch, a main display instrument, a secondary display instrument, a weight sensor, a displacement sensor and a junction box. The power switch, the reversing switch, the main display instrument and the secondary display instrument are arranged on the corresponding hole positions of the front panel.

2. The apparatus of claim 1, wherein: Two junction boxes are fixed on the cantilever beam, and the weight data collected by the weight sensors under the main supporting plate and the secondary supporting plate are summed up and then transmitted to the main display instrument and the secondary display instrument.

3. The apparatus of claim 2, wherein: The displacement sensor is fixed with the light rod and is used for detecting the relative displacement of the main structure plate and the bearing plate.

4. The apparatus of claim 3, wherein: The power switch controls the opening and closing of all electrical equipment, and the reversing switch is used to selectively open the main display instrument or the secondary display instrument. The main display instrument displays the weight applied to the main supporting plate in real time, and the instrument beeps when the weight reaches the preset warning value. The secondary display instrument displays the weight applied to the secondary supporting plate in real time, and the instrument beeps when the weight reaches the preset warning value. The transmission unit includes a rotating roller, a transmission rod, a shaft coupling, a worm gear reducer and a lead screw nut. The transmission rod is connected with the front end frame through a bearing, and the rotating roller is tightly connected with the transmission rod. The worm gear reducer is fixed on the bearing plate, the input end of which is coaxial with the transmission rod, and the shaft coupling is arranged between them for connection, and the output end is a screw structure matched with the lead screw nut. The light rod is arranged around the main structure plate, and the two ends are connected with the main structure plate and the secondary structure plate respectively. The light rod and the linear bearing form a sliding pair, the linear bearing is coaxial with the light rod and is fixed with the bearing plate, thereby limiting the rotation of the lifting unit. The main supporting plate and the secondary supporting plate are connected with the main structure plate and the secondary structure plate through multiple weight sensors respectively. The number of weight sensors is at least three, which are arranged on the same circumference and are uniformly distributed.

5. The apparatus of claim 3, wherein: The main supporting plate and the auxiliary supporting plate are made of the same material as the product to be lifted, and are designed as thin plates, so that they can be deformed when contacting the product to be lifted, thereby avoiding stress concentration on the contact surface.

6. The apparatus of claim 3, wherein: The main structure plate and the auxiliary structure plate have rigidity to ensure that the lifting plane is perpendicular to the front end frame fixing plane.

7. The method of using the zero-gravity lifting device for space payloads of claim 3, wherein The method comprises the following steps: Turn on the power switch, rotate the rotating roller while observing the displacement sensor value, move the lifting unit to the appropriate position, so that the device does not interfere with the spaceborne equipment during installation; Fix the device on the spaceborne equipment fixing frame through the four peripheral fixing hole positions on the front end frame, place the reversing switch in the main direction, rotate the rotating roller to make the main supporting plate of the lifting unit approach and contact the top surface of the equipment, continue to slowly rotate the rotating roller to stop when the main display instrument value reaches the weight of the spaceborne equipment; Tighten the connection between the spaceborne equipment and the fixing frame, rotate the rotating roller in the opposite direction to make the main supporting plate separate from the equipment, disassemble the device fixing screws, take out the entire device, and close each switch one by one or move the lifting unit downward to the position where the auxiliary supporting plate contacts the bottom surface of the spaceborne equipment, and then move the entire device along the contact surface smoothly.

8. The method of claim 7, wherein: The method comprises the following steps: When the displacement sensor value is zero, the auxiliary supporting plate of the lifting unit contacts the bottom surface of the spaceborne equipment, and is moved to the position where the front end frame contacts the fixing frame installation surface; Rotate the rotating roller, and when the fixing hole positions on the front end frame are aligned with the corresponding hole positions on the fixing frame, stop rotating the rotating roller, and record the displacement sensor value at this time as the displacement sensor value corresponding to the appropriate position of the lifting unit when the spaceborne equipment is lifted.

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