A device and system for displaying a flag on an extraterrestrial object

Abstract

The embodiment of the present disclosure provides a device and system for displaying a flag on an extraterrestrial object, which can include: a flagpole; an elastic rod, a first end of the elastic rod being fixed to the flagpole, wherein a first side of the flag is fixed to the elastic rod; a fixing assembly, the fixing assembly being used for releasably fixing a second end of the elastic rod in a bent state to the flagpole, wherein when the second end of the elastic rod is released, the elastic rod elastically recovers from the bent state to an unfolded state to display the flag.

Description

Technical Field

[0001] This disclosure relates to the field of aerospace engineering, and more particularly to a device and system for displaying flags on extraterrestrial bodies. Background Technology

[0002] Due to the unique characteristics of the space environment, such as microgravity, high vacuum, extreme temperature differences, and strong radiation, ordinary flags cannot be displayed in space. Therefore, special designs and technologies are required to ensure that flags can be successfully displayed in the space environment.

[0003] Currently, there are two main ways to display flags in space. The first is a fully rolled-up unfolding method. Specifically, the flag is rolled up and stored using a roll mechanism, and then unfolded flat by an unfolding mechanism after reaching the destination. For example, the Chang'e 5 and Tianwen 1 probes used this method, where the flag is unfolded by a roll. However, this unfolding method may leave curling marks on the flag, affecting the waving effect. The second method is a folding unfolding method. Specifically, the flag is stored by folding, and unfolding requires external force (such as manual or mechanical devices) to assist in unfolding. This method is prone to leaving creases on the flag and relies on manual or complex mechanical devices.

[0004] Existing methods of displaying space flags suffer from the following technical problems: Completely rolling or folding the flags to reduce space occupation during launch may leave indelible curling or folding marks, preventing the flags from flattening completely after unfolding and affecting the display effect; due to the lack of airflow in space, traditional flag-waving effects are difficult to achieve because the flags are currently fixed by rigid structures, restricting their free movement and impacting the display effect. In conclusion, while existing space flag display technologies achieve basic display functions, there is still room for improvement, particularly in terms of the flatness and waving effect of the displayed flags. Summary of the Invention

[0005] To address the aforementioned technical problems, this disclosure aims to provide an apparatus and system for displaying flags on extraterrestrial celestial bodies, which can avoid the problem of severe and irremovable curling or folding marks, and can subject the flag to less constraint, thereby achieving a better waving effect under external force.

[0006] The technical solution disclosed herein is implemented as follows:

[0007] In a first aspect, embodiments of this disclosure provide an apparatus for displaying a flag on an extraterrestrial body, the apparatus comprising:

[0008] flagpole;

[0009] An elastic rod, the first end of which is fixed to the flagpole, wherein the first side of the flag is fixed to the elastic rod;

[0010] A fixing assembly for releasably fixing a second end of the resilient rod in a bent state to the flagpole, wherein when the second end of the resilient rod is released, the resilient rod elastically returns from the bent state to the unfolded state to display the flag.

[0011] Secondly, embodiments of this disclosure also provide a system for displaying a flag on an extraterrestrial body, the system comprising:

[0012] The apparatus for displaying flags on extraterrestrial bodies as described in the first aspect;

[0013] A launch vehicle for launching the device to the extraterrestrial body.

[0014] Utilizing the elastic deformation of the flexible rod, the flag occupies little space when stored and unfolds without leaving creases, maintaining its flat and aesthetically pleasing appearance. When unfolded, at least one corner of the flag is free, simulating a fluttering effect in a microgravity environment, enhancing visual impact. The flag unfolds automatically solely through the elastic return of the rod, eliminating the need for complex mechanical devices, reducing weight and cost, while simultaneously improving system reliability. Attached Figure Description

[0015] Figure 1 This is a perspective view of an apparatus for displaying a flag on an extraterrestrial body according to an embodiment of the present disclosure, showing an elastic rod in an extended state;

[0016] Figure 2 This is a perspective view of an apparatus for displaying a flag on an extraterrestrial body according to an embodiment of the present disclosure, wherein the elastic rod is shown in a bent state;

[0017] Figure 3 A perspective view of a fixing assembly of a device for displaying a flag on an extraterrestrial body according to an embodiment of the present disclosure;

[0018] Figure 4 A perspective view of a flag for use with an apparatus for displaying a flag on an extraterrestrial body according to an embodiment of the present disclosure;

[0019] Figure 5 A front view of an apparatus for displaying a flag on an extraterrestrial body according to an embodiment of the present disclosure, with the flag in conjunction with the present invention. Detailed Implementation

[0020] The technical solutions in the embodiments of this disclosure will be clearly and completely described below with reference to the accompanying drawings.

[0021] Due to the unique environment of space, including microgravity, high vacuum, extreme temperature differences, and intense cosmic radiation, traditional flag display methods face significant challenges in space. Existing space flag display technologies primarily employ two methods for storage and unfolding: fully rolled up and folded. However, both methods have significant technical problems, limiting the effectiveness and application range of the flag display. While the fully rolled-up storage method saves space, it often leaves persistent curling marks on the flag, preventing it from fully flattening after unfolding and severely impacting the display effect. Furthermore, in current display methods, the flag is fixed by a rigid structure, restricting its free movement and affecting the display's overall appearance.

[0022] To address the aforementioned problems in existing technologies, this disclosure proposes a novel space flag display device aimed at solving issues related to flag flatness and waving effect. Specifically, see [link to details]. Figure 1 This disclosure provides an apparatus 1 for displaying a flag F on an extraterrestrial body, wherein the flag F is... Figure 1 and Figure 2 The area filled with cross-sectional lines is schematically shown. The device 1 may include a flagpole 10, a resilient rod 20, and a fixing assembly 30. A first end 201 of the resilient rod 20 is fixed to the flagpole 10, and a first side FS1 of the flag F is fixed to the resilient rod 20. Fixing the first side FS1 of the flag F to the resilient rod 20 means that the first side FS1 is fixed in an extended manner and along the resilient rod 20. The fixing assembly 30 is used to releasably fix a second end 202 of the resilient rod 20, which is in a bent state, to the flagpole 10. When the second end 202 of the resilient rod 20 is released, the resilient rod 20 elastically returns from the bent state to the extended state to display the flag F. Figure 2 The image shows the state when the second end 202 is fixed to the flagpole 10, while... Figure 1 The image shows the state after the second end 202 has been released.

[0023] The disclosed device 1 achieves the storage and unfolding of the flag F through the elastic deformation of the elastic rod 20. The flag F can be stored in a small space, making it easy to carry and transport, and it can also be unfolded without leaving creases. This is because the elastic deformation of the elastic rod 20 does not cause a sudden change in the direction of extension, or in other words, the curve formed by the deformation is smooth. Therefore, there will be no sudden change in the direction of extension of the flag F fixed to the elastic rod 20, or in other words, no "sharp" creases will be produced. This ensures that the flag F remains flat, clean, and crease-free after unfolding, greatly improving the display effect. When the elastic rod 20 elastically returns to the unfolded state, for example, for a rectangular flag F, at least one corner is free. This means that in the space environment, even without airflow, the flag F can simulate a fluttering effect under external stimuli (such as the movement of spacecraft or minor touches). This design makes the flag F more vivid and attractive when displayed in space, enhancing the visual impact of the display. The flag F is folded and unfolded solely by relying on the elastic deformation of the elastic rod 20. Due to the elastic recovery characteristic of the elastic rod 20, once the fixing component 30 releases the second end 202 of the elastic rod 20, the elastic rod 20 can reliably return from a bent state to an unfolded state, ensuring the smooth unfolding of the flag F, improving the reliability of the display, and eliminating complex mechanical devices such as additional drive motors and complex linkage mechanisms. The fixing component 30 is used to releasably fix the second end 202 of the elastic rod 20; its structure is simple and easy to operate. This simplified design not only reduces the weight of the device 1 but also lowers manufacturing and maintenance costs. In summary, the technical solution of this disclosure, by cleverly utilizing the elastic characteristics of the elastic rod 20, achieves the effective folding and flat unfolding of the flag F, while ensuring the display effect and simplifying the mechanical structure.

[0024] In some embodiments of this disclosure, see Figure 1 and Figure 2 The device 1 may also include a winding shaft 40, around which the elastic rod 20 is wound such that the segment of the elastic rod 20 between the winding shaft 40 and the flagpole 10 is straight. For example, in Figure 2 As shown, the elastic rod 20 can be wound up in a manner similar to the bending of a measuring tape.

[0025] Device 1, by winding the elastic rod 20 around the winding shaft 40, makes the segment of the elastic rod 20 between the winding shaft 40 and the flagpole 10 straight. This design makes the stored flag F generally flat, as shown in... Figure 2 As shown, this further reduces the space occupied by the stored flag F, saving valuable space resources for the spacecraft. In the stored state, the cooperation between the elastic rod 20 and the winding shaft 40 makes the storage of the flag F more compact, optimizing the storage state and facilitating transportation and installation.

[0026] In some embodiments of this disclosure, see Figure 3 and combined Figure 1 and Figure 2 The fixing component 30 includes:

[0027] The bracket 51 is hinged to the flagpole 10, allowing the bracket 51 to rotate relative to the flagpole 10 about its first end 511.

[0028] Pressure plate 52 is used to press down flag F;

[0029] Spring 53 is connected between bracket 51 and pressure plate 52;

[0030] Connector 54 is used to detachably connect the second end 512 of bracket 51 to flagpole 10, wherein, when the second end 512 of bracket 51 is connected to flagpole 10, the second end 512 presses the second end 202 of elastic rod 20 against flagpole 10, and pressure plate 52 presses the second side FS2 of flag F against flagpole 10 by the elastic restoring force of spring 53. Here, again, the second side FS2 is pressed in such a way that it is extended and extends along flagpole 10, the second side FS2 of flag F is adjacent to the first side FS1 of flag F and is close to the second end 202 of elastic rod 20 in the extending direction of elastic rod 20, as in Figure 1 As shown in the image.

[0031] The design of the fixing component 30, particularly the hinged structure between the bracket 51 and the flagpole 10, allows the pressure plate 52 to apply uniform pressure to the second side FS2 of the flag F under the action of the spring 53. This structure ensures that the flag F is pressed firmly against the flagpole 10 when stored, and the flatness of the pressure plate 52 ensures that the flag F remains flat in the folded state, avoiding wrinkles or damage during storage. Because the spring 53 is used as the source of restoring force, this design not only provides reliable clamping force but also maintains consistent performance over long-term use. The spring 53 is also designed for durability, capable of withstanding repeated use without losing its elasticity, ensuring the flag F remains flat during multiple storage and unfolding processes. Through the above technical solutions, this disclosure ensures that the flag F is both compact and flat when stored, improving the practicality and aesthetics of the device 1.

[0032] See Figure 1 and Figure 2 It is easy to understand that, since the second end 202 of the elastic rod 20 needs to be fixed to the flagpole 10, and the second side FS2 of the flag F also needs to be pressed against the flagpole 10 in an extended manner and extending along the flagpole 10, when the first side FS1 of the flag F is fixed to the front side of the elastic rod 20, the front side here refers to... Figure 1In the case shown, with flag F in front and elastic pole 20 behind, if flagpole 10 is smooth, it may cause wrinkles to appear on the second side FS2 of flag F, or in other words, there may be areas where it cannot directly contact flagpole 10. For this, see some embodiments of this disclosure. Figure 1 The flagpole 10 may have a groove 10R for accommodating the second end 202 of the elastic rod 20. In this way, after the second end 202 is fixed to the flagpole 10, the entire second side FS2 of the flag F can be pressed against the flagpole 10 in an extended manner and along the flagpole 10.

[0033] In some embodiments of this disclosure, the connector 54 can be a hot knife binding wire or a release nut. Figure 3 An example of using a hot knife to tie a wire is shown in the image.

[0034] Using a hot-blade binding wire as a connector 54, a rapid and impact-free unlocking process can be achieved. The core component of the hot-blade binding wire is the hot blade, which, when heated to a high temperature by electricity, can quickly cut the rope or similar structure, enabling the rapid release of flag F. This unlocking method features high temperature and rapid action, making the unlocking process both quick and reliable. Furthermore, the hot-blade binding wire allows for remote control, increasing operational flexibility and safety. The hot-blade binding wire unlocking method has minimal impact (approximately 25g), a load-bearing capacity of up to 3kN, and can be reused more than 8 times, making it suitable for releasing various spatially foldable attachment structures. The release nut, as a connector 54, has advantages such as simple structure, high load-bearing capacity, and reliable operation. The release nut is typically composed of a series of connecting and separating device modules, most of which are pyrotechnic devices with varying functions. The main advantages of release nuts include significantly reduced impact load, from 104g for pyrotechnics to 102g, improving the impact environment of spacecraft; elimination of safety protection issues for gunpowder, avoiding safety measures during the manufacturing, transportation, and storage of gunpowder; absence of harmful gases or fragments generated during gunpowder combustion or explosion, thus not polluting the surrounding environment; and the fact that most can be reused multiple times, facilitating testing and verification, and ensuring the reliability of the release device.

[0035] Additionally, when the connector 54 is a hot-blade wire binding device, the flagpole 10 can be formed with a hot-blade wire binding groove, such as in... Figure 1 The top of the middle flagpole 10 is shown to prevent the hot knife binding wire from slipping relative to the flagpole 10.

[0036] In some embodiments of this disclosure, the elastic rod 20 may be made of carbon fiber material.

[0037] Carbon fiber possesses extremely high tensile strength, more than five times that of steel of the same weight, and its elastic modulus is also higher. This allows carbon fiber, when used as an elastic material, to withstand greater loads and stresses, ensuring stable performance in a variety of applications. Carbon fiber also has a low density, only one-quarter that of steel. This lightweight characteristic allows the use of carbon fiber in elastic rods 20 to reduce the overall structural weight while still providing the required strength and stiffness, making it particularly suitable for aerospace and other fields with stringent weight requirements.

[0038] In some embodiments of this disclosure, see Figure 1 The flagpole 10 may include a pole body 11 and a vertical plate 12, with the vertical plate 12 fixed to the pole body 11 and the first end 201 of the elastic rod 20 fixed to the vertical plate 12.

[0039] In some embodiments of this disclosure, see Figure 4 Flag F can include a white LS cover and a back cover LH, combined with Figure 1 or Figure 2 The white LS sleeve is fitted onto the vertical plate 12, and the back sleeve LH sleeve is fitted onto the elastic rod 20.

[0040] By adding a white LS sleeve and a back cover LH to flag F, in conjunction with the flagpole 10 and the elastic rod 20, the exposed mechanical components supporting flag F are effectively prevented, thus maintaining the cleanliness and aesthetics of the front of flag F. This design ensures that when flag F is displayed, viewers only see flag F itself and do not notice the supporting structure behind it, thereby enhancing the aesthetics of the display. The white LS sleeve and back cover LH design increase the rigidity of the flag F's edges, making it easier to keep the flag F flat. This structural design helps reduce wrinkles that occur during the storage and unfolding of flag F, and even in microgravity environments, flag F can remain relatively flat and is less prone to sagging.

[0041] In some embodiments of this disclosure, see Figure 1 and combined Figure 4 The vertical plate 12 may be formed with sewing holes 10H, which are used to allow the sewing thread to pass through in order to sew the white LS to the vertical plate 12. Here, the white LS is sewn in such a way that it is extended and extends along the flagpole 10.

[0042] By providing sewing holes 10H on the flagpole 10, the white LS sleeve can be secured to the flagpole 10 with stitching. This design effectively prevents the white LS sleeve of flag F from slipping along the flagpole 10, thus preventing wrinkles from forming during storage and display. This securing method ensures that flag F maintains a good display effect in various environments. The sewing holes 10H create a strong connection between the white LS sleeve and the flagpole 10, increasing the stability of the overall structure. This stability not only helps maintain the flatness of flag F but also reduces the risk of deformation and damage to flag F under wind or other external factors.

[0043] In some embodiments of this disclosure, see Figure 5 and combined Figure 4 The elastic rod 20 may have a rope attachment hole 20H, which is used to pass a rope through to attach the end portion of the back sleeve LH away from the flagpole 10 to the elastic rod 20.

[0044] The elastic rod 20 is designed with a rope attachment hole 20H, through which the end of the back sleeve LH is tied to the elastic rod 20. This design reduces the rigid constraint on the flag F, allowing the flag F to move freely within a certain range. At the same time, the tension of the rope prevents the flag F from slacking and sagging, maintaining the flag F's display posture. The rope attachment hole 20H allows the flag F to have better spatial freedom while maintaining its connection. This allows the flag F to produce a fluttering motion under external stimuli (such as wind or vibration), enhancing the dynamic effect of the display while avoiding the stiffness caused by complete fixation.

[0045] In some embodiments of this disclosure, see Figure 5 The number of cord-tying holes 20H can be two, with the first cord-tying hole 20H1 configured to allow the back sleeve LH to be corded at a first position, and the second cord-tying hole 20H2 configured to allow the back sleeve LH to be corded at a second position. The distance D1 between the first position and the end of the back sleeve LH is between 3% and 7% of the length of the back sleeve LH, and the distance D2 between the second position and the end of the back sleeve LH is between 15% and 25% of the length of the back sleeve LH. Preferably, the distance D1 between the first position and the end of the back sleeve LH is 5% of the length of the back sleeve LH, and the distance D2 between the second position and the end of the back sleeve LH is 20% of the length of the back sleeve LH.

[0046] By precisely setting two rope-tying holes 20H, namely the first rope-tying hole 20H1 and the second rope-tying hole 20H2, this disclosure achieves effective fixation and display of the back cover LH of the flag F while minimizing the number of rope-tying components. This design reduces unnecessary ropes and holes, lowers material usage and potential failure points, while ensuring the flatness and display effect of the flag F. The specific positioning of the first rope-tying hole 20H1 and the second rope-tying hole 20H2 allows the back cover LH to be effectively tied at two key points when unfolded. The position where the back cover LH is tied provides the flag F with the optimal balance point and display posture.

[0047] This disclosure also provides a system (not shown in the accompanying drawings) for displaying a flag F on an extraterrestrial body, the system comprising:

[0048] The apparatus 1 for displaying a flag F on an extraterrestrial body according to the foregoing embodiments of this disclosure;

[0049] Launch vehicle, which is used to launch device 1 to an extraterrestrial body.

[0050] It should be noted that the technical solutions described in the embodiments of this disclosure can be combined arbitrarily without conflict.

[0051] The above are merely specific embodiments of this disclosure, but the scope of protection of this disclosure is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this disclosure should be included within the scope of protection of this disclosure. Therefore, the scope of protection of this disclosure should be determined by the scope of the claims.

Claims

1. A device for displaying a flag on an extraterrestrial body, characterized in that, The device includes: flagpole; An elastic rod, the first end of which is fixed to the flagpole, wherein the first side of the flag is fixed to the elastic rod; A fixing assembly is provided for releasably securing the second end of the resilient rod, which is in a bent state, to the flagpole, wherein when the second end of the resilient rod is released, the resilient rod elastically returns from the bent state to an unfolded state to display the flag. The fixing component includes: A bracket, hinged to the flagpole, such that the bracket can rotate relative to the flagpole about its first end; A pressure plate, used to press down the flag; A spring is connected between the bracket and the pressure plate; A connector for detachably connecting the second end of the bracket to the flagpole, wherein when the second end of the bracket is connected to the flagpole, the second end presses the second end of the elastic rod against the flagpole, and the pressure plate presses the second side of the flag against the flagpole by the elastic restoring force of the spring, the second side of the flag being adjacent to the first side of the flag and close to the second end of the elastic rod.

2. The apparatus for displaying a flag on an extraterrestrial body according to claim 1, characterized in that, The device further includes a winding shaft, around which the elastic rod is wound such that the segment of the elastic rod between the winding shaft and the flagpole is straight.

3. The apparatus for displaying a flag on an extraterrestrial body according to claim 1, characterized in that, The connector is a hot-blade binding wire or a release nut.

4. The apparatus for displaying a flag on an extraterrestrial body according to claim 1 or 2, characterized in that, The elastic rod is made of carbon fiber material.

5. The apparatus for displaying a flag on an extraterrestrial body according to claim 1, characterized in that, The flagpole includes a pole body and a vertical plate, the vertical plate being fixed to the pole body, and the first end of the elastic pole being fixed to the vertical plate.

6. The apparatus for displaying a flag on an extraterrestrial body according to claim 5, characterized in that, The flag includes a white cover and a back cover, the white cover being fitted onto the vertical plate and the back cover being fitted onto the elastic rod.

7. The apparatus for displaying a flag on an extraterrestrial body according to claim 6, characterized in that, The elastic rod has a rope-tying hole for passing a rope through to tie the end portion of the back sleeve away from the flagpole to the elastic rod.

8. The apparatus for displaying a flag on an extraterrestrial body according to claim 7, characterized in that, The number of cord-tying holes is two, and the first cord-tying hole is configured such that the back cover is corded at a first position, and the second cord-tying hole is configured such that the back cover is corded at a second position. The distance between the first position and the end of the back cover is between 3% and 7% of the length of the back cover, and the distance between the second position and the end of the back cover is between 15% and 25% of the length of the back cover.

9. A system for displaying a flag on an extraterrestrial body, characterized in that, The system includes: An apparatus for displaying a flag on an extraterrestrial body according to any one of claims 1 to 8; A launch vehicle for launching the device to the extraterrestrial body.

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