Zero-gravity lifting device for spaceflight load

Abstract

The invention provides a zero-gravity lifting device for a spaceflight load. The zero-gravity lifting device comprises a supporting unit, a transmission unit, a lifting unit and a detection control unit. The supporting unit is fixed to a satellite-borne equipment fixing frame, the transmission unit, the lifting unit and the detection control unit are all fixed to the supporting unit, and the driving end of the transmission unit and the input display of the detection control unit are all arranged on the same plane. The lifting unit is provided with a main lifting plane and an auxiliary lifting plane, and under the control of the transmission unit, the front face of the satellite-borne equipment is lifted through one lifting plane or the lifting function is completed through the other lifting plane when the satellite-borne equipment turns over by 180 degrees along with a satellite ship. The detection control unit detects the lifting weight in real time in the lifting process of the lifting plane, and if the lifting weight exceeds a set value, an alarm is given, so that the contact face of satellite-borne equipment is prevented from being damaged by strong pressure.

Description

Technical Field

[0001] The present invention belongs to the field of aerospace, and in particular relates to a zero-gravity lifting device for spacecraft payload. Background Art

[0002] In the field of aerospace, some satellite-borne equipment uses vibration isolators to connect to the starship body to reduce the transmission of vibration when the satellite-borne equipment is in orbit. However, the satellite-borne equipment will experience complex vibrations and shocks during the uplink process with the satellite. In order to avoid damage to the vibration isolators, satellite-borne equipment with shock absorption requirements is required to be tightly connected to the starship body before launch, and then unlocked before starting up in orbit, so that the vibration isolators can play a role. Satellite-borne equipment needs to go through multiple unlocking and locking processes during ground transportation, mechanical testing, performance testing, and assembly. Since there is gravity that needs to be overcome and does not cause impact on the satellite-borne equipment, the lifting device is a key equipment for completing the unlocking and locking tasks efficiently and accurately.

[0003] Existing lifting methods mainly use general equipment, such as crane lifting and rope lifting. The operating space and access channel size in the spacecraft are very limited, so it is generally impossible to send lifting equipment into the spacecraft and there is no high-strength surface to support the equipment. The rope lifting method can be used in conjunction with special tooling for single-machine equipment, but the spacecraft cannot provide a high-altitude lifting environment and cannot achieve equipment lifting. Summary of the invention

[0004] The technical problem solved by the present invention is: in view of the limitation that the existing lifting methods cannot be applied to high-reliability and safe operations in the narrow space of spacecraft, the purpose of the present invention is to provide a zero-gravity lifting device for aerospace payloads that can operate in a small 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 invention is: a zero-gravity lifting device for aerospace payloads, 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 satellite equipment, and the transmission unit, lifting unit and detection control unit are all fixed on the support unit, and the active 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, a positive and a negative lifting plane. Under the control of the transmission unit, the satellite equipment is lifted positively through one lifting plane, or when the satellite equipment flips 180° with the starship, the lifting function is completed through another lifting plane; the detection control unit detects the lifting weight in real time during the lifting process of the lifting plane, and if it exceeds the set value, an alarm is issued to avoid the contact surface of the satellite equipment being damaged by strong pressure.

[0007] Preferably, the supporting unit is a cantilever structure, including a front panel, a front end frame, a cantilever beam, and a load-bearing plate; mounting holes are arranged around the front end frame for fixing the entire device to the equipment frame, and the interior 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 fastened to the front end frame through two cantilever beams.

[0008] Preferably, the transmission unit includes a rotating roller, a transmission rod, a coupling, a worm gear reducer, and a screw nut; the transmission rod is connected to the front end frame through a bearing, and the rotating roller is tightly connected to the transmission rod; the worm gear reducer is fixed to the load-bearing plate, and its input end is coaxial with the transmission rod, a coupling is set between the two for connection, and its output end is a screw structure that cooperates with the screw nut.

[0009] Preferably, the lifting unit includes a linear bearing, an optical bar, a main structure plate, a main support plate, a secondary structure plate and a secondary support plate; the optical bar is arranged around the main structure plate, and its two ends are respectively connected to the main structure plate and the secondary structure plate; the optical bar and the linear bearing form a sliding pair, the linear bearing is coaxial with the optical bar, and is fixed to the load-bearing plate, thereby limiting the rotation of the lifting unit; the main structure plate is fastened to the lead screw nut, and moves up and down along the axis direction of the optical bar with the lead screw nut; the main support plate and the secondary support plate are respectively connected to the main structure plate and the secondary structure plate through multiple weight sensors.

[0010] Preferably, there are at least three weight sensors, which are located on the same circle and evenly distributed.

[0011] Preferably, the main support plate and the auxiliary support plate are made of the same material as the product to be lifted, and are designed as thin plates, so that they can deform when they come into contact 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 remains perpendicular to the fixing plane of the front end frame.

[0013] Preferably, the detection control unit includes a mobile power supply, a power switch, a reversing switch, a main display instrument, a sub-display instrument, a weight sensor, a displacement sensor, and a junction box;

[0014] The power switch, reversing switch, main display instrument and auxiliary display instrument are arranged at the corresponding opening positions of the front panel; two junction boxes are fixedly connected to the cantilever beam, and the weight data collected by the weight sensor under the main pallet / auxiliary pallet are respectively summarized and transmitted to the main display instrument / auxiliary display instrument;

[0015] The displacement sensor is fixed to the light rod and is used to detect the relative displacement between the main structure plate and the load-bearing plate; the power switch controls the opening and closing of all electrical equipment, and the reversing switch is used to selectively turn on the main display instrument or the auxiliary display instrument; the main display instrument displays the weight applied to the main pallet in real time, and the instrument buzzes when the weight value reaches a preset warning value, and the buzzer automatically disappears when the weight decreases below the warning value; the auxiliary display instrument displays the weight applied to the auxiliary pallet in real time, and the instrument buzzes when the weight value reaches a preset warning value, and the buzzer automatically disappears when the weight decreases below the warning value.

[0016] A method for using the zero-gravity lifting device for aerospace payloads comprises:

[0017] Turn on the power switch, rotate the rotating wheel and observe the displacement sensor value, move the lifting unit to a suitable position so that the lifting unit does not interfere with the satellite-borne equipment during installation;

[0018] Fix the device on the fixed frame of the satellite equipment through the fixing holes around the front frame, set the reversing switch to the main direction, turn the rotating roller to make the main support plate in the lifting unit approach and contact the top surface of the equipment, and continue to slowly turn the rotating roller until the value of the main display instrument reaches the weight of the satellite equipment and then stop rotating;

[0019] Tightly connect the satellite-borne equipment to the fixed frame, rotate the rotating roller in the opposite direction to separate the main pallet from the equipment, remove the device fixing screws, take out the entire device and turn off each switch one by one or move the lifting unit downward until the auxiliary pallet contacts the bottom surface of the satellite-borne equipment, and then move the entire device out smoothly along the contact surface.

[0020] Preferably, the rotating roller and the displacement sensor value are observed at the same time to move the lifting unit to a suitable position so that the lifting unit does not interfere with the satellite-borne equipment during installation of the device, including:

[0021] When the displacement sensor value is zero, the auxiliary support plate of the lifting unit is brought into contact with the bottom surface of the satellite-borne equipment, and moved until the front frame is brought into contact with the mounting surface of the fixed frame;

[0022] Turn the rotating roller. When the fixed hole on the front end frame is aligned with the corresponding hole on the fixed frame, stop turning 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 current satellite equipment is lifted.

[0023] The beneficial effects of the present invention compared with the prior art are:

[0024] (1) The support plate in the device adopts multi-point support and has the function of dynamic deformation, which is suitable for lifting conditions of low-rigidity products;

[0025] (2) The device provides feedback to the operator on the lifting status by monitoring the contact force with the product in real time, and triggers a warning sound near the set force value to warn and prevent over-lifting.

[0026] (3) The lifting device is fixed using the holes on the equipment itself, and the operation process will not interfere with other equipment in the cabin;

[0027] (4) All detection and display functional components in the device are powered by a mobile power supply, no external power supply is required, and it is easy to install and remove;

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

[0029] Figure 1 It is the overall structural diagram of the device;

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

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

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

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

[0034] Figure 6 It is a schematic diagram of the present invention in the lifted state in the main lifting direction;

[0035] Explanation of the reference numerals: 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-optical bar, 11-linear bearing, 12-weighing plate, 13-main support plate, 14-main structure plate, 15-rotating roller, 16-transmission rod, 17-coupling, 18-worm 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 present invention will be further described below in conjunction with the embodiments.

[0037] The invention provides a zero-gravity lifting device for aerospace payloads. Figure 1As shown, it includes 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 active end of the transmission unit 2 and the input display of the detection control unit 4 are arranged in the same plane. The lifting device has two pallets, which can be used for front lifting of satellite-borne equipment and can still meet the lifting function when the satellite-borne equipment flips 180° with the starship. The detection control unit 4 detects the lifting weight in real time during the lifting process of the pallet. If it exceeds the set value, an alarm will be issued to prevent the contact surface of the satellite-borne equipment from being damaged by strong pressure.

[0038] The present invention provides a preferred embodiment, as Figure 2 As shown, the support unit 1 is a cantilever structure, including a front panel 5, a front end frame 6, a cantilever beam 7, and a load-bearing plate 12. Four mounting holes are arranged around the front end frame 6, which are used to fix the entire device to the equipment frame. The interior of the front end frame 6 adopts a hollow structure, and the surrounding inclined beams are used for gripping to facilitate transportation and transfer in a small space. The front panel 5 is arranged in the middle of the front end frame 6, and the load-bearing plate 12 is fastened to the front end frame 6 through two cantilever beams 7.

[0039] The present invention provides a preferred embodiment, as Figure 3 As shown, the transmission unit 2 includes a rotating roller 15, a transmission rod 16, a coupling 17, a worm gear reducer 18, and a lead screw nut 19. The transmission rod 16 is connected to the front end frame 6 through a bearing, and the rotating roller 15 is fastened to the transmission rod 16 by screws. The worm gear reducer 18 is fixed on the load-bearing plate 12, and its input end is coaxial with the transmission rod 16, and a coupling 17 is set between the two for connection, and its output end is a lead screw structure that cooperates with the lead screw nut 19. The transmission unit 2 converts the rotational motion of the rotating roller into the vertical up and down movement of the lead screw nut 19.

[0040] The present invention provides a preferred embodiment, as Figure 2 , 5As shown, the lifting unit 3 includes a linear bearing 11, a light bar 10, a main structure plate 14, a main support plate 13, a secondary structure plate 9 and a secondary support plate 8. The main structure plate 14 is tightly connected to the lead screw nut 19 and moves up and down with the lead screw nut 19. The light bar 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 bar 10. The linear bearing 11 is coaxial with the light bar 10 and fixed to the load-bearing plate 12, thereby limiting the rotation of the lifting unit 3. The main support plate 14 and the secondary support plate 9 are designed as thin plates, which can be deformed when contacting the lifting 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 is basically perpendicular to the fixed plane of the front end frame 6. The main support plate 13 and the secondary support plate 8 are respectively connected to the main structure plate 14 and the secondary structure plate 9 through three weight sensors 25.

[0041] The present invention provides a preferred embodiment, as 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 sub-display instrument 20, a weight sensor 25, a displacement sensor 26, and a junction box 24. The power switch 23, the reversing switch 22, the main display instrument 21, and the sub-display instrument 20 are all arranged at the corresponding opening positions of the front panel 5.

[0042] The junction box 24 is arranged in the middle of the two cantilever beams 7, with two arranged above and below, and is fastened to the two cantilever beams 7 by screws. The weight data collected by the three weight sensors 25 under the main support plate 13 and the auxiliary support plate 8 are summarized and summed and then transmitted to the main display instrument 21 and the auxiliary display instrument 20.

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

[0044] The present invention is described in detail below with reference to specific embodiments.

[0045] Embodiment 1:

[0046] When the onboard equipment needs to be lifted and locked toward the main pallet, the operation process is as follows:

[0047] (1) Turn on the power switch 23, rotate the rotating wheel 15 and observe the value of the displacement sensor 26, and move the lifting unit 3 to a suitable position so that the lifting unit does not interfere with the satellite-borne equipment during installation;

[0048] For the same satellite-borne equipment, when operating for the first time, the auxiliary support plate of the lifting unit can be aligned with the satellite-borne equipment ( Figure 6 The bottom surface of the middle grid part) is in contact with the front frame and the fixed frame ( Figure 6 The middle dotted line part) is in contact with the mounting surface;

[0049] Turn the rotating roller until the fixed holes on the front end frame are aligned with the corresponding holes on the fixed frame, then stop turning 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 current satellite equipment is lifted. This value can be used to easily complete the installation of the front end frame and the fixed frame later.

[0050] (2) Fix the device to the fixed frame of the satellite equipment through the fixing holes around the front frame 6, set the reversing switch 22 to the main direction, rotate the rotating roller 15 to make the main support plate 13 in the lifting unit approach and contact the top surface of the equipment, and continue to slowly rotate the rotating roller 15 until the value of the main display instrument 21 reaches the weight of the equipment and then stop rotating;

[0051] (3) Fasten the satellite-borne equipment to the fixed frame, rotate the rotating roller 15 in the opposite direction to separate the main support plate 13 from the equipment, remove the device fixing screws, take out the entire device and turn off each switch one by one. Alternatively, the lifting unit 3 can be moved downward until the auxiliary support plate 8 contacts the bottom surface of the equipment, and then the entire device can be smoothly moved out along the contact surface.

[0052] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

[0053] Parts not described in detail in the present invention belong to common knowledge of those skilled in the art.

Claims

1. A zero-gravity lifting device for aerospace payloads, characterized in that: It includes a supporting unit, a transmission unit, a lifting unit and a detection control unit; The support unit is fixed on the fixed frame of the satellite equipment, and the transmission unit, lifting unit and detection control unit are all fixed on the support unit, and the active 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, a positive and a negative lifting plane. Under the control of the transmission unit, the satellite equipment is lifted positively through one lifting plane, or when the satellite equipment flips 180° with the starship, the lifting function is completed through another lifting plane; the detection control unit detects the lifting weight in real time during the lifting process of the lifting plane, and if it exceeds the set value, an alarm is issued to avoid the contact surface of the satellite equipment being damaged by strong pressure.

2. The device according to claim 1, characterized in that: The support unit is a cantilever structure, including a front panel, a front end frame, a cantilever beam, and a load-bearing plate; mounting holes are arranged around the front end frame for fixing the entire device to the equipment frame, and the interior 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 fastened to the front end frame through two cantilever beams.

3. The device according to claim 2, characterized in that: The transmission unit includes a rotating roller, a transmission rod, a coupling, a worm gear reducer, and a screw nut; the transmission rod is connected to the front end frame through a bearing, and the rotating roller is tightly connected to the transmission rod; the worm gear reducer is fixed to the load-bearing plate, its input end is coaxial with the transmission rod, a coupling is set between the two for connection, and its output end is a screw structure that cooperates with the screw nut.

4. The device according to claim 3, characterized in that: The lifting unit includes a linear bearing, an optical bar, a main structure plate, a main support plate, a secondary structure plate and a secondary support plate; the optical bar is arranged around the main structure plate, and its two ends are respectively connected to the main structure plate and the secondary structure plate; the optical bar and the linear bearing form a sliding pair, the linear bearing is coaxial with the optical bar, and is fixed to the load-bearing plate, thereby limiting the rotation of the lifting unit; the main structure plate is tightly connected to the lead screw nut, and moves up and down along the axis direction of the optical bar with the lead screw nut; the main support plate and the secondary support plate are respectively connected to the main structure plate and the secondary structure plate through multiple weight sensors.

5. The device according to claim 4, characterized in that: The number of the weight sensors is at least three, and the weight sensors are located on the same circumference and evenly distributed.

6. The device according to claim 4, characterized in that: The main support plate and the auxiliary support plate are made of the same material as the product to be lifted and are designed as thin plates. When they come into contact with the lifted product, they can be deformed to avoid stress concentration on the contact surface.

7. The device according to claim 4, characterized in that: The rigidity of the main structure plate and the auxiliary structure plate ensures that the lifting plane remains perpendicular to the fixing plane of the front end frame.

8. The device according to claim 4, characterized in that: 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, reversing switch, main display instrument and auxiliary display instrument are arranged at corresponding opening positions of the front panel; Two junction boxes are fixedly connected to the cantilever beam, and the weight data collected by the weight sensors under the main pallet / auxiliary pallet are summarized and transmitted to the main display instrument / auxiliary display instrument respectively; The displacement sensor is fixed to the polished rod and is used to detect the relative displacement between the main structure plate and the load-bearing plate; The power switch controls the opening and closing of all electrical devices, and the reversing switch is used to selectively open the main display instrument or the auxiliary display instrument; the main display instrument displays the weight applied to the main pallet in real time, and the instrument buzzes when the weight value reaches the preset warning value, and the buzzer automatically disappears when the weight decreases below the warning value; The secondary display instrument displays the weight applied on the secondary support plate in real time. When the weight value reaches a preset warning value, the instrument buzzes to alarm, and the buzzer automatically disappears when the weight decreases below the warning value.

9. A method for using the zero-gravity lifting device for aerospace payloads as claimed in claim 8, characterized in that include: Turn on the power switch, rotate the rotating wheel and observe the displacement sensor value, move the lifting unit to a suitable position so that the lifting unit does not interfere with the satellite-borne equipment during installation; Fix the device on the fixed frame of the satellite equipment through the fixing holes around the front frame, set the reversing switch to the main direction, turn the rotating roller to make the main support plate in the lifting unit approach and contact the top surface of the equipment, and continue to slowly turn the rotating roller until the value of the main display instrument reaches the weight of the satellite equipment and then stop rotating; Tightly connect the satellite-borne equipment to the fixed frame, rotate the rotating roller in the opposite direction to separate the main pallet from the equipment, remove the device fixing screws, take out the entire device and turn off each switch one by one or move the lifting unit downward until the auxiliary pallet contacts the bottom surface of the satellite-borne equipment, and then move the entire device out smoothly along the contact surface.

10. The method according to claim 9, characterized in that: The rotating roller is rotated while observing the displacement sensor value to move the lifting unit to a suitable position so that the lifting unit does not interfere with the satellite-borne equipment during installation, including: When the displacement sensor value is zero, the auxiliary support plate of the lifting unit contacts the bottom surface of the satellite-borne equipment, and moves until the front frame contacts the mounting surface of the fixed frame; Turn the rotating roller. When the fixed hole on the front end frame is aligned with the corresponding hole on the fixed frame, stop turning 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 current satellite equipment is lifted.

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