CN112027066A - Stable unmanned aerial vehicle landing device - Google Patents
Stable unmanned aerial vehicle landing device Download PDFInfo
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- CN112027066A CN112027066A CN202010969195.6A CN202010969195A CN112027066A CN 112027066 A CN112027066 A CN 112027066A CN 202010969195 A CN202010969195 A CN 202010969195A CN 112027066 A CN112027066 A CN 112027066A
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- aerial vehicle
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/24—Operating mechanisms electric
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides a stable unmanned aerial vehicle landing device which comprises four supporting rod assemblies and a control mechanism. The support rod assembly comprises an electric push rod, a mounting plate, a first containing sleeve, a second containing sleeve and an elastic piece. The electric push rod is in driving connection with the mounting plate, the mounting groove is formed in the mounting plate, the first containing sleeve is provided with a limiting plate, the limiting plate is contained in the mounting groove, the mounting plate is provided with a pressure sensor, and the limiting plate is abutted to the pressure sensor. The first accommodating sleeve is connected with the mounting plate, the first accommodating sleeve is provided with a first accommodating groove, the second accommodating sleeve is provided with a second accommodating groove, and the first accommodating sleeve is connected with the second accommodating sleeve in a sliding mode. One end of the elastic piece is connected with the first containing sleeve, and the other end of the elastic piece is connected with the second containing sleeve. The control mechanism is electrically connected with each electric push rod and each pressure sensor respectively. Above-mentioned steady formula unmanned aerial vehicle descending device has promoted buffering shock attenuation effect, has strengthened the adaptability to ground environment.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a stable unmanned aerial vehicle landing device.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer. Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + industry is applied, and is really just needed by the unmanned aerial vehicle. At present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology. The bottom both sides of VTOL unmanned aerial vehicle are provided with the landing frame, have played the absorbing effect of buffering when unmanned aerial vehicle descends. When unmanned aerial vehicle parks on the ground, the landing frame plays the supporting role to the unmanned aerial vehicle body.
However, present unmanned aerial vehicle landing frame, its buffering shock attenuation effect is not good, is difficult to effectively slow down the impact force that unmanned aerial vehicle descending produced. In addition, the landing frame can not adapt to the ground of different terrains, is low in ground environment adaptability, and when the unmanned aerial vehicle is parked on uneven ground, the vertical state of the body of the unmanned aerial vehicle can not be guaranteed, so that the secondary take-off work of the unmanned aerial vehicle is influenced.
Disclosure of Invention
Based on this, it is necessary to provide a steady formula unmanned aerial vehicle landing device to the not good and lower technical problem of ground environmental suitability of buffering shock attenuation effect.
The utility model provides a steady formula unmanned aerial vehicle descending device, this steady formula unmanned aerial vehicle descending device includes four bracing piece subassemblies and control mechanism. Four bracing piece subassemblies are used for installing around the unmanned aerial vehicle bottom respectively. The support rod assembly comprises an electric push rod, a mounting plate, a first containing sleeve, a second containing sleeve and an elastic piece. Electric putter with the mounting panel drive is connected, the mounting groove has been seted up to the mounting panel, first accommodate the sleeve pipe and be provided with the limiting plate, the limiting plate accept in the mounting groove, the width of limiting plate is greater than the notch width of mounting groove. The mounting panel in be provided with pressure sensor in the mounting groove, the limiting plate with pressure sensor looks butt. The first accommodating sleeve is connected with the mounting plate, the first accommodating sleeve is provided with a first accommodating groove, the second accommodating sleeve is provided with a second accommodating groove, and the first accommodating sleeve is accommodated in the second accommodating groove and is in sliding connection with the second accommodating sleeve. One end of the elastic piece is accommodated in the first accommodating groove and connected with the first accommodating sleeve, and the other end of the elastic piece is accommodated in the second accommodating groove and connected with the second accommodating sleeve. The control mechanism is electrically connected with each electric push rod and each pressure sensor respectively.
In one embodiment, the landing device of the stable unmanned aerial vehicle further comprises two foot rest strips, each foot rest strip is connected with the end portions of the two second containing sleeves respectively, and the two foot rest strips are arranged in parallel.
In one embodiment, the foot rest bar comprises a plurality of sub-chains, the sub-chains are connected in sequence, and two adjacent sub-chains are rotatably connected. The end of each second receiving sleeve is connected with the most terminal subchain.
In one embodiment, the bottom surface of the sub-chain is provided with a plurality of anti-skid convex particles.
In one embodiment, the outer side wall of the first receiving sleeve is provided with a limiting sliding strip, the inner wall of the second receiving groove of the second receiving sleeve is provided with a limiting sliding groove, and the limiting sliding strip is received in the limiting sliding groove and is connected with the second receiving sleeve in a sliding manner.
In one embodiment, the resilient member is a compression spring.
In one embodiment, the first receiving sleeve is provided with a first positioning block at the bottom of the first receiving groove, and the first positioning block is embedded into one end of the elastic element.
In one embodiment, a second positioning block is disposed at the bottom of the second receiving groove of the second receiving sleeve, and the second positioning block is embedded into the other end of the elastic element.
In one embodiment, the support rod assembly further includes a telescopic rod, and two ends of the telescopic rod are respectively connected to the first positioning block and the second positioning block.
In one embodiment, two ends of the elastic member are respectively welded with the first receiving sleeve and the second receiving sleeve.
Above-mentioned steady formula unmanned aerial vehicle descending device supports the unmanned aerial vehicle body through four bracing piece subassemblies, and each bracing piece subassembly realizes buffering shock attenuation, supports the effect that stabilizes. The terminal and ground looks butt of sheathed tube are acceptd to each second to support the unmanned aerial vehicle body, utilize first sleeve pipe and the second of acceping to accept the sleeve pipe and accept and install the elastic component, utilize the elastic deformation performance of elastic component buffering unmanned aerial vehicle to descend the impact that produces. Through the sliding connection relation between the first accommodating sleeve and the second accommodating sleeve, the elastic deformation of the elastic piece is adapted. And elastic pressure information from each elastic piece is acquired by each pressure sensor and is fed back to the control mechanism. After the produced elastic pressure of each elastic component of control mechanism analysis, through the shrink of controlling each electric putter to the length of adjustment bracing piece subassembly, when parking with the guarantee this unmanned aerial vehicle, its body is upright state, and then the work of taking off once more of the unmanned aerial vehicle of being convenient for. This steady formula unmanned aerial vehicle descending device has promoted buffering shock attenuation effect, has strengthened the adaptability to ground environment.
Drawings
Fig. 1 is a schematic structural diagram of a stable unmanned aerial vehicle landing device in one embodiment;
FIG. 2 is a schematic cross-sectional structural view of a support rod assembly of the stabilized UAV landing gear in one embodiment;
fig. 3 is an enlarged schematic structural view of a part M of the landing gear of the stationary drone in the embodiment of fig. 2;
FIG. 4 is a schematic cross-sectional view of a portion of the structure of a stabilized drone landing gear in one embodiment;
FIG. 5 is a schematic diagram of a portion of a stabilized drone landing assembly in accordance with one embodiment;
fig. 6 is a schematic cross-sectional view of a part of the structure of a stabilized unmanned aerial vehicle landing device in another embodiment.
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below. In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein.
In the description of the present invention, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are not to be considered limiting of the invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; they may be directly connected or indirectly connected through intervening media, or they may be connected internally or in any other suitable relationship, unless expressly stated otherwise. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through an intermediate. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.
It will be understood that when an element is referred to as being "secured to" or "disposed on" another element, it can be directly on the other element or intervening elements may also be present. When an element is referred to as being "connected" to another element, it can be directly connected to the other element or intervening elements may also be present. The terms "vertical," "horizontal," "upper," "lower," "left," "right," and the like as used herein are for illustrative purposes only and do not denote a unique embodiment.
Referring to fig. 1 to 6, the present invention provides a landing device 10 for a stationary drone, wherein the landing device 10 includes four support rod assemblies 100 and a control mechanism 200. Four bracing piece subassemblies 100 are used for installing around the unmanned aerial vehicle bottom respectively. The support rod assembly 100 includes an electric putter 110, a mounting plate 120, a first receiving sleeve 130, a second receiving sleeve 140, and an elastic member 150. The electric push rod 110 is in driving connection with the mounting plate 120, the mounting plate 120 is provided with a mounting groove 121, the first accommodating sleeve 130 is provided with a limiting plate 131, the limiting plate 131 is accommodated in the mounting groove 121, and the width of the limiting plate 131 is greater than the width of the notch of the mounting groove 121. The mounting plate 120 is provided with a pressure sensor 122 in the mounting groove 121, and the stopper plate 131 abuts against the pressure sensor 122. The first receiving sleeve 130 is connected to the mounting plate 120, the first receiving sleeve 130 has a first receiving groove 132, the second receiving sleeve 140 has a second receiving groove 141, and the first receiving sleeve 130 is received in the second receiving groove 141 and slidably connected to the second receiving sleeve 140. One end of the elastic member 150 is received in the first receiving groove 132 and connected to the first receiving sleeve 130, and the other end of the elastic member 150 is received in the second receiving groove 141 and connected to the second receiving sleeve 140. The control mechanism 200 is electrically connected to each electric push rod 110 and each pressure sensor 122.
Above-mentioned steady formula unmanned aerial vehicle descending device 10 supports the unmanned aerial vehicle body through four bracing piece subassemblies 100, and each bracing piece subassembly 100 realizes buffering shock attenuation, supports the effect that stabilizes. Each second accepts the terminal and ground looks butt of sleeve pipe 140 to support the unmanned aerial vehicle body, utilize first sleeve pipe 130 and the second of acceping to accept sleeve pipe 140 and accept and install elastic component 150, utilize the elastic deformation performance of elastic component 150 buffering unmanned aerial vehicle to descend the impact that produces. The first receiving sleeve 130 and the second receiving sleeve 140 are slidably connected to each other, so that the elastic member 150 is elastically deformed. The elastic pressure information from each elastic member 150 is acquired by each pressure sensor 122 and fed back to the control mechanism 200. After the control mechanism 200 analyzes the elastic pressure generated by each elastic part 150, the control mechanism controls the contraction of each electric push rod 110, so as to adjust the length of the support rod assembly 100, so as to ensure that the unmanned aerial vehicle is in an upright state when parked, and further facilitate the secondary take-off work of the unmanned aerial vehicle. This steady formula unmanned aerial vehicle descending device 10 has promoted buffering shock attenuation effect, has strengthened the adaptability to ground environment.
The supporting rod assembly 100 has the effects of buffering, damping and supporting stability, and ensures that the body of the unmanned aerial vehicle is in an upright state when the unmanned aerial vehicle is in a parking state. The mounting plate 120 also serves to house and secure the first receiving sleeve 130. The first receiving sleeve 130 and the second receiving sleeve 140 are used together to receive the elastic element 150, the first receiving sleeve 130 is connected with the second receiving sleeve 140 in a sliding manner, and the second receiving sleeve 140 slides along the length direction of the first receiving sleeve 130, that is, along the elastic deformation direction of the elastic element 150. The first receiving sleeve 130 and the second receiving sleeve 140 also protect the elastic member 150, and prevent the elastic member 150 from being damaged. The direct and ground looks butt in bottom that sleeve pipe 140 was acceptd to the second to support unmanned aerial vehicle, guarantee unmanned aerial vehicle's the stability of parking. Elastic component 150 has played the cushioning effect, and in this embodiment, elastic component 150 is compression spring, and the elastic deformation performance of elastic component 150 has cushioned the impact effect that produces when unmanned aerial vehicle descends.
In order to avoid the elastic element 150 from being compressed excessively to cause structural damage, in one embodiment, the length of the first receiving sleeve 130 is smaller than the depth of the second receiving groove 141, and the length of the elastic element 150 at the compression limit is smaller than the depth of the second receiving groove 141. That is, when the first receiving sleeve 130 slides to the limit value in the second receiving groove 141, the length of the first receiving sleeve 130 is smaller than the depth of the second receiving groove 141, the front end of the second receiving sleeve 140 will contact the mounting plate 120, and the first receiving sleeve 130 cannot contact the bottom of the second receiving groove 141. The length of the elastic element 150 at the compression limit is smaller than the depth of the second receiving groove 141, that is, no matter how the first receiving sleeve 130 and the second receiving sleeve 140 slide, the elastic element 150 is not excessively pressed by the first receiving sleeve 130 and the second receiving sleeve 140 to cause the elastic structure to be damaged. Thus, the structural stability of the elastic member 150 is ensured, and the operational stability of the support rod assembly 100 is ensured.
Further, in order to avoid the front end of the second receiving sleeve 140 colliding with the mounting plate 120 to damage the two, in one embodiment, the mounting plate 120 is provided with a buffer ring pad 123, and the buffer ring pad 123 is disposed around the first receiving sleeve 130. The cushion ring 123 is used to receive the impact of the end of the second receiving sleeve 140. Thus, the cushion ring 123 serves as a cushion and protection function, and absorbs the impact and collision of the second receiving sleeve 140 to the mounting plate 120. Thus, the front end of the second accommodating sleeve 140 is prevented from colliding with the mounting plate 120 to damage the two, and the structural safety of the support rod assembly 100 is ensured.
In order to avoid the rotation between the first receiving sleeve 130 and the second receiving sleeve 140 and ensure the installation stability of the elastic element 150, in one embodiment, a limiting sliding bar 133 is disposed on an outer side wall of the first receiving sleeve 130, a limiting sliding groove 142 is disposed on an inner wall of the second receiving groove 141 of the second receiving sleeve 140, and the limiting sliding bar 133 is received in the limiting sliding groove 142 and slidably connected to the second receiving sleeve 140. The limiting sliding groove 142 limits the limiting sliding strip 133, so that the first accommodating sleeve 130 can only slide along the length direction of the limiting sliding groove 142, and the first accommodating sleeve 130 cannot rotate in the second accommodating groove 141. Thus, the first receiving sleeve 130 and the second receiving sleeve 140 are prevented from rotating, and the installation stability of the elastic member 150 is ensured.
In order to improve the stability of the installation of the elastic element 150, in one embodiment, the first receiving sleeve 130 is provided with a first positioning block 134 at the bottom of the first receiving groove 132, and the first positioning block 134 is embedded into one end of the elastic element 150. The first positioning block 134 has a limiting and fixing function for one end of the elastic element 150. Further, the second receiving sleeve 140 is provided with a second positioning block 143 at the bottom of the second receiving groove 141, and the second positioning block 143 is embedded in the other end of the elastic member 150. The second positioning block 143 limits and fixes the other end of the elastic element 150. The first positioning block 134 and the second positioning block 143 together stabilize the elastic element 150. Thus, the mounting stability of the elastic member 150 is improved. Further, in one embodiment, two ends of the elastic member 150 are respectively welded to the first receiving sleeve 130 and the second receiving sleeve 140. Thus, the elastic member 150 cannot be separated from the first receiving sleeve 130 and the second receiving sleeve 140. Thus, the fixing effect of the elastic member 150 is enhanced, and the structural stability of the support rod assembly 100 is improved.
In order to prevent the first receiving sleeve 130 and the second receiving sleeve 140 from being pulled apart, in one embodiment, the supporting rod assembly 100 further includes a telescopic rod 160, and two ends of the telescopic rod 160 are respectively connected to the first positioning block 134 and the second positioning block 143. The telescopic link 160 is a product that is well-established in the market, that is, the telescopic link 160 is extended when both ends thereof are pulled, but the telescopic link 160 cannot be extended further when the limit of the stroke is reached. Thus, the telescopic pulling rod 160 restricts the first receiving sleeve 130 from being continuously separated from the second receiving sleeve 140. Thus, the first receiving sleeve 130 and the second receiving sleeve 140 are prevented from being pulled and separated, and the structural stability of the support rod assembly 100 is ensured.
The electric push rod 110 plays a role of lifting, and the electric push rod 110 extends or contracts, thereby adjusting the length of the support rod assembly 100. The pressure sensor 122 is used for receiving the impact pressure of the first receiving sleeve 130 and feeding back the pressure signal to the control mechanism 200. The mounting groove 121 is used for receiving and fixing the pressure sensor 122. The width of the position limiting plate 131 is greater than the width of the notch of the mounting groove 121, so that the position limiting plate 131 cannot leave the mounting groove 121, that is, the first accommodating sleeve 130 is ensured to be in contact with the pressure sensor 122 at any moment, and the pressure sensor 122 receives the impact pressure from the first accommodating sleeve 130 in real time, that is, the elastic pressure information of the elastic member 150. The control mechanism 200 plays a role of coordinated control, and in the present embodiment, the control mechanism 200 is an electronic control device including a control chip. Under control mechanism 200's overall control, behind the produced elastic pressure of each elastic component 150 of control mechanism 200 analysis, through the shrink of each electric putter 110 of control to the length of adjustment bracing piece subassembly 100, when guaranteeing this unmanned aerial vehicle to park, its body is upright state, and then the work of taking off once more of the unmanned aerial vehicle of being convenient for.
In order to improve the stability of the drone when parked, in one embodiment, the landing device of the stationary drone further includes two foot bars 300, each foot bar 300 is connected to the ends of the two second containing sleeves 140, and the two foot bars 300 are arranged in parallel. Further, in the present embodiment, the foot rest bar 300 includes a plurality of sub-chains 310, the sub-chains 310 are connected in sequence, and two adjacent sub-chains 310 are rotatably connected. The end of each second receiving sleeve 140 is connected to a sub-chain 310 at the very end. The foot rest strip 300 is used for abutting with the ground to promote the stability when the unmanned aerial vehicle parks. Each sub-chain 310 is rotatably connected with each other, so that the bending deformation is realized, the adaptive capacity to different terrains is improved, and the foot rest bar 300 can be tightly attached to the ground of different terrains. The area of contact of foot rest strip 300 and ground is big to unmanned aerial vehicle's parking stability has been promoted, make the side direction cross wind be difficult to blow and rock unmanned aerial vehicle. In order to further improve the anti-slip performance of the sub-chain 310, in one embodiment, the bottom surface of the sub-chain 310 is provided with a plurality of anti-slip protruding particles 311. The friction coefficient of the sub-chain 310 is improved by the arrangement of the anti-slip convex grains 311. So, strengthened the non-skid property of subchain strip 310, promoted the stability when parking unmanned aerial vehicle.
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (10)
1. The utility model provides a steady formula unmanned aerial vehicle landing device which characterized in that includes: four strut assemblies and a control mechanism; the four supporting rod assemblies are respectively used for being installed on the periphery of the bottom of the unmanned aerial vehicle;
the supporting rod assembly comprises an electric push rod, a mounting plate, a first containing sleeve, a second containing sleeve and an elastic piece;
the electric push rod is in driving connection with the mounting plate, the mounting plate is provided with a mounting groove, the first containing sleeve is provided with a limiting plate, the limiting plate is contained in the mounting groove, and the width of the limiting plate is larger than the width of a notch of the mounting groove; the mounting plate is provided with a pressure sensor in the mounting groove, and the limiting plate is abutted to the pressure sensor;
the first accommodating sleeve is connected with the mounting plate, the first accommodating sleeve is provided with a first accommodating groove, the second accommodating sleeve is provided with a second accommodating groove, and the first accommodating sleeve is accommodated in the second accommodating groove and is in sliding connection with the second accommodating sleeve; one end of the elastic piece is accommodated in the first accommodating groove and connected with the first accommodating sleeve, and the other end of the elastic piece is accommodated in the second accommodating groove and connected with the second accommodating sleeve;
the control mechanism is electrically connected with each electric push rod and each pressure sensor respectively.
2. A landing gear for a stationary unmanned aerial vehicle as claimed in claim 1, further comprising two leg bars, each leg bar being connected to two ends of the second receiving sleeve, the two leg bars being arranged in parallel.
3. A landing gear for a stationary unmanned aerial vehicle as claimed in claim 2, wherein the foot rest bar comprises a plurality of sub-chains, the plurality of sub-chains are connected in sequence, and two adjacent sub-chains are rotatably connected; the end of each second receiving sleeve is connected with the most terminal subchain.
4. A stationary unmanned aerial vehicle landing apparatus as in claim 3, wherein the bottom surface of the secondary chain is provided with a plurality of anti-slip raised particles.
5. The landing device of claim 1, wherein the outer side wall of the first receiving sleeve is provided with a limiting slide bar, the inner wall of the second receiving groove of the second receiving sleeve is provided with a limiting sliding groove, and the limiting slide bar is received in the limiting sliding groove and is connected with the second receiving sleeve in a sliding manner.
6. A stationary drone landing gear according to claim 1, wherein the resilient member is a compression spring.
7. A landing gear for a stationary drone according to claim 6, wherein the first housing sleeve has a first locating block at the bottom of the first housing groove, the first locating block being embedded in an end of the elastic member.
8. A landing gear for a stationary drone according to claim 7, wherein the second receiving sleeve has a second locating piece at the bottom of the second receiving slot, the second locating piece being embedded in the other end of the elastic member.
9. The stationary unmanned aerial vehicle landing device of claim 8, wherein the support rod assembly further comprises a telescopic rod, and both ends of the telescopic rod are connected to the first positioning block and the second positioning block, respectively.
10. A stationary drone landing gear according to claim 9, wherein the two ends of the elastic member are welded to the first and second housing sleeves, respectively.
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| CN202010969195.6A CN112027066A (en) | 2020-09-15 | 2020-09-15 | Stable unmanned aerial vehicle landing device |
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