CN118220538A - Light-small impact-free repeatable folding and unfolding battery wing mechanism - Google Patents

Light-small impact-free repeatable folding and unfolding battery wing mechanism Download PDF

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Publication number
CN118220538A
CN118220538A CN202410359473.4A CN202410359473A CN118220538A CN 118220538 A CN118220538 A CN 118220538A CN 202410359473 A CN202410359473 A CN 202410359473A CN 118220538 A CN118220538 A CN 118220538A
Authority
CN
China
Prior art keywords
battery
battery plate
free
impact
compensation joint
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
CN202410359473.4A
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Chinese (zh)
Inventor
罗海军
崔琦峰
李红
郭晶
杨悦
刘丙霖
徐峰
曹燕燕
郑宗勇
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Shanghai Aerospace System Engineering Institute
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Shanghai Aerospace System Engineering Institute
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shanghai Aerospace System Engineering Institute filed Critical Shanghai Aerospace System Engineering Institute
Priority to CN202410359473.4A priority Critical patent/CN118220538A/en
Publication of CN118220538A publication Critical patent/CN118220538A/en
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • B64G1/443—Photovoltaic cell arrays
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B64G1/2221—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the manner of deployment
    • B64G1/2222—Folding
    • B64G1/2224—Folding about multiple axes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B64G1/2229—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state characterised by the deployment actuating mechanism
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/50—On board measures aiming to increase energy efficiency

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Photovoltaic Devices (AREA)

Abstract

A light, small-sized and impact-free repeatable folding and unfolding battery wing mechanism comprises a body-mounted battery plate, a +Z driving mechanism, a +Z compensation joint, a-Z driving mechanism, a-Z compensation joint and a pressing device; the body-mounted battery plate is connected with the aircraft cabin; the +Z battery plate is connected with the body-mounted battery plate through the +Z driving mechanism and the +Z compensation joint, and the +Z battery plate can be repeatedly unfolded and folded at any position under the driving of the +Z driving mechanism and the +Z compensation joint; the Z battery plate is connected with the body-mounted battery plate through the Z driving mechanism and the Z compensation joint, and the Z battery plate can be repeatedly unfolded and folded at any position under the driving of the Z driving mechanism and the Z compensation joint; before the first use, the +Z battery plate and the-Z battery plate are in a folded state, and the pressing device is used for locking the +Z battery plate and the-Z battery plate.

Description

Light-small impact-free repeatable folding and unfolding battery wing mechanism
Technical Field
The invention relates to a light and small-sized impact-free repeatable unfolding and folding battery wing mechanism, and belongs to the technical field of solar battery wings of aerospace vehicles.
Background
When a light and small aircraft flies in orbit, other actions such as orbit changing or maneuvering are carried out in a space environment according to the task flow requirements, so that the requirements on rigidity of the aircraft and accessories on the aircraft are higher, and the reaction speed of the aircraft is improved. The battery wing is used as a device for providing electric energy on the aircraft, generally, the unfolding area is larger, the aircraft can only be unfolded once and can not be folded on the track, the rigidity of the aircraft is reduced, meanwhile, when the unfolding failure occurs, the reverse operation can not be performed to solve the failure problem, and the initiating explosive device detonates and unlocks to generate larger impact load. Therefore, a light, small-sized and repeatedly unfolded and folded battery wing mechanism is needed to meet the on-orbit flight requirements of the aircraft.
Disclosure of Invention
The invention aims to solve the technical problems that: the method overcomes the defects of the prior art, solves the problem that the battery wings of the aircraft cannot be repeatedly folded when being unfolded in one track, realizes the function of repeatedly unfolding and folding the battery wings in track so as to meet the task requirements of the aircraft, and improves the diversity of the on-track tasks of the aircraft.
The invention aims at realizing the following technical scheme:
A light, small-sized and impact-free repeatable folding and unfolding battery wing mechanism comprises a body-mounted battery plate, a +Z driving mechanism, a +Z compensation joint, a-Z driving mechanism, a-Z compensation joint and a pressing device;
the body-mounted battery plate is connected with the aircraft cabin;
The +Z battery plate is connected with the body-mounted battery plate through the +Z driving mechanism and the +Z compensation joint, and the +Z battery plate can be repeatedly unfolded and folded at any position under the driving of the +Z driving mechanism and the +Z compensation joint;
The Z battery plate is connected with the body-mounted battery plate through the Z driving mechanism and the Z compensation joint, and the Z battery plate can be repeatedly unfolded and folded at any position under the driving of the Z driving mechanism and the Z compensation joint;
Before the first use, the +Z battery plate and the-Z battery plate are in a folded state, and the pressing device is used for locking the +Z battery plate and the-Z battery plate.
The using method based on the light-small-sized impact-free repeatable folding and unfolding battery wing mechanism comprises the following steps:
Unlocking the pressing device;
the +Z driving mechanism and the +Z compensation joint act, so that the +Z battery plate is unfolded;
-a Z drive mechanism and-a Z compensation articulation to cause the-Z panel to unfold.
Further, the using method further comprises the following steps: in the unfolded state of the device, the device is in a unfolded state,
The +Z driving mechanism and the +Z compensation joint act to fold the +Z battery plate;
-a Z drive mechanism and-a Z compensation articulation to cause the-Z panel to collapse.
Compared with the prior art, the invention has the following beneficial effects:
(1) The invention has the advantages of light weight and small volume, and is suitable for the task requirement of light and small aircrafts on the light weight of battery wings;
(2) The invention is used as a battery wing unfolding mechanism to provide a pasting foundation for the battery piece, and meanwhile, the body-mounted battery plate is used as a cabin cover plate of the aircraft, thereby being beneficial to improving the structural efficiency of the aircraft;
(3) The invention uses the light-small-sized driving mechanism with large driving capability, can realize the repeatable unfolding and folding functions of any position of the battery wings, is suitable for the multi-task flow requirement of the on-orbit multi-unfolding of the aircraft, and can be expanded and applied to other unfolding mechanisms with the repeated unfolding requirement;
(4) The invention adopts a compaction mode for on-orbit unlocking of astronauts, and can avoid impact load influence caused by initiating and unlocking of initiating explosive devices;
(5) The invention adopts the design scheme of small envelop compression points, and can reduce the area of the non-sheet-distributing area relative to the conventional battery plate, so that the sheet-distributing efficiency of the battery plate is maximized.
Drawings
FIG. 1 is a schematic view of a light, compact, impact-free repeatable deployment and retraction battery wing mechanism of the present invention in a deployed state;
FIG. 2 is a schematic view of the light, compact, impact-free repeatable folding and unfolding battery wing mechanism-Z panel of the present invention in a folded state;
FIG. 3 is a schematic view of a light, compact, impact-free repeatable folding and unfolding battery wing mechanism of the present invention in a fully folded state;
FIG. 4 is a schematic view of a battery plate structure according to the present invention;
FIG. 5 is a schematic diagram of a driving mechanism according to the present invention;
FIG. 6 is a schematic diagram of a compensating joint of the present invention;
fig. 7 is a cross-sectional view of the structure of the compressing apparatus of the present invention.
The attached drawings are identified: the device comprises a body-mounted battery plate 1, a +Z battery plate 2, a-Z battery plate 3, a +Z driving mechanism 4, a +Z compensation joint 5, a-Z driving mechanism 6, a-Z compensation joint 7 and a compacting device 8; 1-1 is an insulating film, 1-2 is a multi-layer heat insulation assembly, and 1-3 is an aluminum honeycomb sandwich grid panel structure.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
As shown in fig. 1,5 and 6, the battery wing mechanism capable of repeatedly expanding and contracting without impact is light and small and comprises a body-mounted battery plate 1, +z battery plate 2, -Z battery plate 3, +z driving mechanism 4, +z compensation joint 5, -Z driving mechanism 6, -Z compensation joint 7 and pressing device 8. The +Z battery plate and the-Z battery plate can realize the repeated unfolding and folding functions of any positions under the drive of the driving mechanism and the compensation joint, and adapt to the multi-task orbit and control requirements of the aircraft in a space environment, as shown in fig. 2 and 3.
The body-mounted battery plate 1 is connected with the cabin of the aircraft through screws, and the body-mounted battery plate 1 comprises an insulating film 1-1, a multi-layer heat insulation assembly 1-2 and an aluminum honeycomb sandwich grid panel structure 1-3, as shown in fig. 4; the insulating film 1-1 is stuck on the front surface to provide an insulating environment for the solar cell; the back is coated with a heat control multi-layer heat insulation component 1-2 which is used for controlling the temperature and insulating the cabin; the aluminum honeycomb sandwich grid panel structure 1-3 provides a driving mechanism, a compensation joint and an installation interface of the pressing device 8, and adopts a sandwich type interface form of combining a uniform pin and a U-shaped opening.
The +Z battery plate 2 and the-Z battery plate 3 adopt ultra-thin ultra-light aluminum honeycomb sandwich structures with the thickness reduced by half (11 mm), the weight of products is reduced, and the requirement on the driving moment of a driving mechanism is reduced. A miniaturized and repeatable unfolding and folding high-torque unfolding mechanism is used, and comprises a +Z driving mechanism, a-Z driving mechanism, a +Z compensation joint and a-Z compensation joint.
The pressing device 8 provides a common socket head cap screw interface, so that a astronaut can unlock the battery wing in a pressing state by using a common tool on orbit, and the problem of unlocking impact of an initiating explosive device is avoided, as shown in fig. 7.
The invention is mainly applied to the repeatable folding battery wing, provides a light and small-sized impact-free repeatable folding battery wing mechanism, solves the problem that the conventional battery wing can not be folded when being unfolded once, provides a light and small-sized large-torque repeatable folding mechanism, and provides a technical solution for space mechanisms requiring other repeatable folding and unfolding.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Although the present invention has been described in terms of the preferred embodiments, it is not intended to be limited to the embodiments, and any person skilled in the art can make any possible variations and modifications to the technical solution of the present invention by using the methods and technical matters disclosed above without departing from the spirit and scope of the present invention, so any simple modifications, equivalent variations and modifications to the embodiments described above according to the technical matters of the present invention are within the scope of the technical matters of the present invention.

Claims (9)

1. The light-small impact-free repeatable folding and unfolding battery wing mechanism is characterized by comprising a body-mounted battery plate (1), a +Z battery plate (2), a-Z battery plate (3), a +Z driving mechanism (4), a +Z compensation joint (5), a-Z driving mechanism (6), a-Z compensation joint (7) and a pressing device (8);
The body-mounted battery plate (1) is connected with the cabin of the aircraft;
The +Z battery plate (2) is connected with the body-mounted battery plate (1) through the +Z driving mechanism (4) and the +Z compensation joint (5), and the +Z battery plate (2) can be repeatedly unfolded and folded at any position under the driving of the +Z driving mechanism (4) and the +Z compensation joint (5);
the Z battery plate (3) is connected with the body-mounted battery plate (1) through the Z driving mechanism (6) and the Z compensation joint (7), and the Z battery plate (3) can be repeatedly unfolded and folded at any position under the driving of the Z driving mechanism (6) and the Z compensation joint (7);
before the first use, the +Z battery plate (2) and the-Z battery plate (3) are in a folded state, and the pressing device (8) is used for locking the +Z battery plate (2) and the-Z battery plate (3).
2. The light-weight, compact, impact-free, repeatable extending and retracting battery wing mechanism of claim 1, characterized in that the body-mounted battery panel (1) comprises an insulating film (1-1), a multi-layer insulation assembly (1-2), an aluminum honeycomb sandwich grid panel structure (1-3);
the insulating film (1-1) and the multi-layer heat insulation component (1-2) are respectively positioned at two sides of the aluminum honeycomb sandwich grid panel structure (1-3).
3. The lightweight, compact, impact-free, repeatable deployment and retraction battery wing mechanism of claim 2, characterized in that the aluminum honeycomb sandwich mesh panel structure (1-3) takes the form of a sandwich interface with pins combined with U-shaped ports.
4. The light-weight, small-sized, impact-free and repeatable folding and unfolding battery wing mechanism according to claim 1 is characterized in that the +z battery plate (2) and the-Z battery plate (3) are of ultra-thin ultra-light aluminum honeycomb sandwich structure, and the thickness of the battery wing mechanism is smaller than that of the battery wing mechanism of the battery board (1).
5. The lightweight, compact, impact-free, repeatable deployment and retraction battery wing mechanism of claim 1, wherein the body-mounted battery panel (1) is also used as a cabin cover for an aircraft.
6. The lightweight, compact, impact-free, repeatable deployment and retraction battery wing mechanism of claim 1, wherein the compression means (8) mechanically locks the +z panel (2) and the-Z panel (3).
7. The lightweight, compact, impact-free, repeatable deployment and retraction battery wing mechanism of claim 1 wherein the lightweight, compact, impact-free, repeatable deployment and retraction battery wing mechanism is for use in an aircraft in a space environment.
8. A method of using a lightweight, compact, impact-free, repeatable deployment and retraction battery wing mechanism according to claim 1, comprising:
unlocking the pressing device (8);
The +Z driving mechanism (4) and the +Z compensation joint (5) act, so that the +Z battery plate (2) is unfolded;
-Z drive mechanism (6) and-Z compensation joint (7) act such that-Z panel (3) is unfolded.
9. The method of use of claim 8, further comprising: in the unfolded state of the device, the device is in a unfolded state,
The +Z driving mechanism (4) and the +Z compensation joint (5) act to fold the +Z battery plate (2);
-Z drive mechanism (6) and-Z compensation joint (7) act such that-Z panel (3) is collapsed.
CN202410359473.4A 2024-03-27 2024-03-27 Light-small impact-free repeatable folding and unfolding battery wing mechanism Pending CN118220538A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202410359473.4A CN118220538A (en) 2024-03-27 2024-03-27 Light-small impact-free repeatable folding and unfolding battery wing mechanism

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202410359473.4A CN118220538A (en) 2024-03-27 2024-03-27 Light-small impact-free repeatable folding and unfolding battery wing mechanism

Publications (1)

Publication Number Publication Date
CN118220538A true CN118220538A (en) 2024-06-21

Family

ID=91497542

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202410359473.4A Pending CN118220538A (en) 2024-03-27 2024-03-27 Light-small impact-free repeatable folding and unfolding battery wing mechanism

Country Status (1)

Country Link
CN (1) CN118220538A (en)

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