CN215155762U - A rear launch fulcrum structure for retractable drone body - Google Patents
A rear launch fulcrum structure for retractable drone body Download PDFInfo
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- CN215155762U CN215155762U CN202023090802.6U CN202023090802U CN215155762U CN 215155762 U CN215155762 U CN 215155762U CN 202023090802 U CN202023090802 U CN 202023090802U CN 215155762 U CN215155762 U CN 215155762U
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- 230000005540 biological transmission Effects 0.000 abstract description 31
- 230000008878 coupling Effects 0.000 abstract description 5
- 238000010168 coupling process Methods 0.000 abstract description 5
- 238000005859 coupling reaction Methods 0.000 abstract description 5
- 230000009471 action Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000000149 penetrating effect Effects 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 238000005034 decoration Methods 0.000 description 2
- 230000003014 reinforcing effect Effects 0.000 description 2
- 125000006850 spacer group Chemical group 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
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Abstract
The utility model discloses a rear-emitting fulcrum structure of a retractable unmanned aerial vehicle body, which comprises a chute positioned at the rear end of an unmanned aerial vehicle emitting frame and a rear-emitting fulcrum coupled at the bottom of the rear end of the unmanned aerial vehicle; the sliding groove is arranged along the launching direction of the unmanned aerial vehicle; one end of the rear transmitting fulcrum is coupled to the bottom of the rear end of the unmanned aerial vehicle and can rotate around the coupling point; the other end of the rear emission fulcrum is movably arranged in the sliding groove, can slide along the direction of the sliding groove, slides out from the front end of the sliding groove and is separated from the sliding groove; the middle part of back transmission fulcrum is connected with unmanned aerial vehicle's rear end bottom through an elastic component, when back transmission fulcrum from spout front end roll-off, through this elastic component pulling transmission fulcrum around the axle contact rotation, withdraws in the unmanned aerial vehicle organism.
Description
Technical Field
The utility model belongs to the unmanned aerial vehicle field, concretely relates to back transmission fulcrum structure of retractable unmanned aerial vehicle organism.
Background
At present, a front fixed type launching fulcrum and a rear fixed type launching fulcrum are generally adopted for an engine body interface matched with an unmanned aerial vehicle launching device, and the front fixed type launching fulcrum and the rear fixed type launching fulcrum are exposed on the outer surface of an engine body of the unmanned aerial vehicle, so that the pneumatic appearance of the unmanned aerial vehicle is influenced; when the unmanned aerial vehicle flies at a high speed, the air resistance is increased, and the flying speed and the maneuvering capability are reduced; fixed transmission fulcrum also can increase the radar scattering cross-section of aircraft, reduces the stealthy characteristic of aircraft, is caught by monitoring facilities such as radar at the flight in-process easily.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: the utility model aims to solve the technical problem that not enough to prior art provides a back transmission fulcrum structure of recoverable unmanned aerial vehicle organism, and after unmanned aerial vehicle transmission, inside this back transmission fulcrum can withdraw the organism to reduce flight resistance, strengthen stealthy characteristic.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
a rear-launching fulcrum structure of a retractable unmanned aerial vehicle body comprises a chute positioned at the rear end of an unmanned aerial vehicle launching rack and a rear-launching fulcrum coupled to the bottom of the rear end of the unmanned aerial vehicle;
the sliding groove is arranged along the launching direction of the unmanned aerial vehicle;
one end of the rear transmitting fulcrum is coupled to the bottom of the rear end of the unmanned aerial vehicle and can rotate around the coupling point; the other end of the rear emission fulcrum is movably arranged in the sliding groove, can slide along the direction of the sliding groove, slides out from the front end of the sliding groove and is separated from the sliding groove;
the middle part of back transmission fulcrum is connected with unmanned aerial vehicle's rear end bottom through an elastic component, when back transmission fulcrum from spout front end roll-off, through this elastic component pulling transmission fulcrum around the axle contact rotation, withdraws in the unmanned aerial vehicle organism.
Specifically, the axle joint of back transmission fulcrum is located the fixing base of unmanned aerial vehicle rear end bottom, and the pivot coupling of back transmission fulcrum through running through this axle joint is on the fixing base.
Specifically, the one end and the back transmission fulcrum middle part of elastic component are connected, and the other end is connected on the strengthening frame of unmanned aerial vehicle rear end bottom.
Specifically, the elastic component be extension spring or torsional spring, when the tip of transmission fulcrum was located the spout, the elastic component was in tensile state, when the tip of transmission fulcrum was followed the spout front end roll-off, retracted elasticity through this elastic component and pulled the transmission fulcrum and rotate around the axle contact, withdraw in the unmanned aerial vehicle organism.
Furthermore, the bottom of the fixing seat and the middle upper part of the rear emission fulcrum are correspondingly provided with through holes, and the rear emission fulcrum is limited in the fixing seat by penetrating through the corresponding through holes through a limiting pin, so that the rear emission fulcrum is prevented from being retracted into the machine body under the elastic force of a spring.
Further, the through-hole is correspondingly seted up to the top of spout and back transmission fulcrum middle and lower part, runs through this corresponding through-hole through a definite power round pin, will launch the fulcrum restriction in the spout after, prevents that the engine from starting the back, and unmanned aerial vehicle slides forward under engine thrust.
Has the advantages that:
the utility model discloses back transmission fulcrum structure is different from fixed transmission fulcrum, and this back transmission fulcrum's fixing utilizes spacer pin, decides power round pin and launching cradle combined action to realize. At the moment of launching of the unmanned aerial vehicle, the limiting pin and the fixed force pin are both sheared under the thrust action of the boosting rocket, and the rear launching fulcrum is retracted into the engine body under the action of the tension force of the tension spring (or the torsion force of the tension spring). The problem of unmanned aerial vehicle flight back transmission fulcrum expose at the organism outside is solved, avoid influencing unmanned aerial vehicle's aerodynamic configuration and stealthy performance. The launching fulcrum has a simple and reliable structure, can be pulled out quickly during use, can automatically withdraw the body after launching is finished, and has higher practical value.
Drawings
These and/or other advantages of the present invention will become more apparent from the following detailed description of the present invention when taken in conjunction with the accompanying drawings and the following detailed description.
Fig. 1 is an erection state diagram of the unmanned aerial vehicle using the rear-launch fulcrum structure on the launch tower.
Fig. 2 is an erection state diagram of the rear-firing fulcrum structure.
Fig. 3 is a release state diagram of the rear emission fulcrum structure.
Wherein each reference numeral represents: 1, unmanned plane; 2 front emitting fulcrum assembly; 3 rocket booster; 4, a rear emission fulcrum assembly; 5, a launching rack; 6, a chute; 7, launching a fulcrum; 8, a machine body cabin cover; 9 reinforcing the frame; 10 a tension spring; 11 a rotating shaft; 12, fixing a base; 13, a limiting pin; 14 fixed force pins.
Detailed Description
The invention will be better understood from the following examples.
The drawings in the specification show the structure, ratio, size, etc. only for the purpose of matching with the content disclosed in the specification, so as to be known and read by those skilled in the art, and not for the purpose of limiting the present invention, so the present invention does not have the essential meaning in the art, and any structure modification, ratio relationship change or size adjustment should still fall within the scope covered by the technical content disclosed in the present invention without affecting the function and achievable purpose of the present invention. Meanwhile, the terms "upper", "lower", "front", "rear", "middle", and the like used in the present specification are for the sake of clarity only, and are not intended to limit the scope of the present invention, and changes or adjustments of the relative relationship thereof are also considered to be the scope of the present invention without substantial changes in the technical content.
As shown in fig. 1, an unmanned aerial vehicle 1 is fixed on a launcher 5 through two front launch fulcrum assemblies 2 and one rear launch fulcrum assembly 4 (i.e., a rear launch fulcrum structure protected by the present invention), and after the rocket booster 3 is launched off the launcher, the two front launch fulcrum assemblies 2 retract into the interior of the body under the action of a built-in tension spring; the rear firing fulcrum assembly 4 is retracted into the fuselage interior.
As shown in fig. 2, the rear-launch fulcrum structure includes a chute 6 located at the rear end of the launcher of the unmanned aerial vehicle, and a rear-launch fulcrum 7 coupled to the bottom of the rear end of the unmanned aerial vehicle. The sliding groove 6 is arranged along the launching direction of the unmanned aerial vehicle; one end of the rear emission fulcrum 7 is coupled to the bottom of the rear end of the unmanned aerial vehicle and can rotate around the coupling point; the other end of the rear emission fulcrum 7 is movably arranged in the sliding groove 6, can slide along the direction of the sliding groove 6, slides out from the front end of the sliding groove 6 and is separated from the sliding groove 6; the middle part of back transmission fulcrum 7 is connected with unmanned aerial vehicle's rear end bottom through an elastic component 10, when back transmission fulcrum 7 from 6 front ends roll-off of spout, through the rotation of this elastic component 10 pulling transmission fulcrum 7 around the axle contact, withdraws in the unmanned aerial vehicle organism.
The axle connection point of back transmission fulcrum 7 is located the fixing base 12 of unmanned aerial vehicle rear end bottom, and back transmission fulcrum 7 is through the pivot 11 coupling that runs through this axle connection point on fixing base 12. One end of the elastic piece 10 is connected with the middle part of the rear emission fulcrum 7, and the other end of the elastic piece is connected to the reinforcing frame 9 at the bottom of the rear end of the unmanned aerial vehicle. Elastic component 10 is extension spring or torsional spring, and when the tip of transmission fulcrum 7 was located spout 6, elastic component 10 was in tensile state, when the tip of transmission fulcrum 7 was followed spout 6 front end roll-off, retracted elasticity through this elastic component 10 and pulled transmission fulcrum 7 and rotate around the axle contact, withdrawed in the unmanned aerial vehicle organism. Through holes are correspondingly formed in the bottom of the fixed seat 12 and the middle upper part of the rear emission fulcrum 7, and the rear emission fulcrum 7 is limited in the fixed seat 12 through a limiting pin 13 penetrating through the corresponding through hole. Through holes are correspondingly formed in the top of the sliding groove 6 and the middle lower part of the rear launching fulcrum 7, and the rear launching fulcrum 7 is limited in the sliding groove 6 through a certain force pin 14 penetrating through the corresponding through holes.
Unmanned aerial vehicle back-launch fulcrum 7 places in the spout 6 of launcher, and extension spring elastic component 10 on the back-launch fulcrum 7 is connected with organism strengthening frame 9 to be in tensile state (if for the torsional spring that revolutes the rotation of axes, then this torsional spring is in the torsional state), carry on spacingly to back-launch fulcrum 7 through spacer pin 13 and fixed force round pin 14. The limiting pin 13 is used for limiting the rear emission fulcrum in the fixed seat 12 and preventing the rear emission fulcrum from being retracted into the machine body under the elastic force of the spring; the fixed force pin 14 is used for limiting the launching fulcrum in a sliding groove of the launching rack, and the unmanned aerial vehicle is prevented from sliding forwards under the thrust of an engine after the engine is started.
As shown in fig. 3, at the moment of launching of the unmanned aerial vehicle, the limit pin 13 and the fixed force pin 14 are both cut off under the action of the rocket booster, and under the combined action of the thrust and the spring force (tension spring or torsion spring) of the booster rocket, the rear launching fulcrum 7 moves out of the chute 6, and then rotates around the rotating shaft 11 to retract into the body (an opening is reserved on the body hatch cover 8 for retracting the rear launching fulcrum into the body).
The utility model provides a thinking and method of the back transmission fulcrum structure of recoverable unmanned aerial vehicle organism, the method and the way that specifically realize this technical scheme are many, above only the utility model discloses a preferred embodiment should point out, to the ordinary technical personnel of this technical field, is not deviating from the utility model discloses under the prerequisite of principle, can also make a plurality of improvements and moist decorations, these improve and moist decorations should also regard as the utility model discloses a protection scope. All the components not specified in the present embodiment can be realized by the prior art.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023090802.6U CN215155762U (en) | 2020-12-21 | 2020-12-21 | A rear launch fulcrum structure for retractable drone body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023090802.6U CN215155762U (en) | 2020-12-21 | 2020-12-21 | A rear launch fulcrum structure for retractable drone body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215155762U true CN215155762U (en) | 2021-12-14 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023090802.6U Active CN215155762U (en) | 2020-12-21 | 2020-12-21 | A rear launch fulcrum structure for retractable drone body |
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| Country | Link |
|---|---|
| CN (1) | CN215155762U (en) |
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2020
- 2020-12-21 CN CN202023090802.6U patent/CN215155762U/en active Active
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| GR01 | Patent grant | ||
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| CP03 | Change of name, title or address |
Address after: No.2, Huangpu Road, Xuanwu District, Nanjing, Jiangsu Province, 210016 Patentee after: China Rongtong Group 60th Research Institute Country or region after: China Address before: No. 2 Huangpu Road, Xuanwu District, Nanjing City, Jiangsu Province Patentee before: NO.60 INSTITUTE OF THE HEADQUARTERS OF GENERAL STAFF OF PLA Country or region before: China |
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| CP03 | Change of name, title or address |