CN116176840A - Spring lock catch spring-open type separating mechanism for split flying wing layout aircraft - Google Patents
Spring lock catch spring-open type separating mechanism for split flying wing layout aircraft Download PDFInfo
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- CN116176840A CN116176840A CN202310221690.2A CN202310221690A CN116176840A CN 116176840 A CN116176840 A CN 116176840A CN 202310221690 A CN202310221690 A CN 202310221690A CN 116176840 A CN116176840 A CN 116176840A
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- 230000000149 penetrating effect Effects 0.000 claims abstract description 20
- 238000000926 separation method Methods 0.000 claims description 18
- 239000002184 metal Substances 0.000 claims description 14
- 230000000452 restraining effect Effects 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 2
- 238000010586 diagram Methods 0.000 description 5
- 238000009434 installation Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D5/00—Aircraft transported by aircraft, e.g. for release or reberthing during flight
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- 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
- Y02T50/40—Weight reduction
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Abstract
The invention discloses a spring lock catch flick type separating mechanism for a separable flying wing layout aircraft, which comprises a main machine connecting rod, a sub-machine nesting rod and a sub-machine separating mechanism, wherein the sub-machine separating mechanism comprises a limiting block, a guide rail, a central fixed block, a guide rail sliding block, a guide rod, a spring penetrating through the guide rod, one end of the spring is abutted to the limiting block, the other end of the spring is abutted to the central fixed block, and a constraint component for locking the position of the limiting block and compressing the spring, the constraint component releases the limiting constraint on the limiting block, the limiting block moves together with the guide rail sliding block to the outer side of the guide rail under the action of the resilience force of the spring, the limiting block is separated from the tail end of the main machine connecting rod, so that the sub-aircraft moves backwards, the nesting rod of the sub-machine is separated from a nesting actuator cylinder of the main machine connecting rod after moving to a certain distance, and finally the sub-aircraft is separated from the main aircraft. The invention improves the stability and the structural reliability of the combined flight by limiting the relative pitching between the long machine and the sub machine.
Description
Technical Field
The invention relates to a separation mechanism of a main aircraft and a sub aircraft, in particular to a spring lock catch spring-open type separation mechanism for a separable flying wing layout aircraft.
Background
The split type layout is a novel aircraft layout scheme, the advantages of the split type aircraft assembly and the individual advantages of the split type aircraft assembly can be fully exerted, the technology of multi-unmanned aerial vehicle cluster flight control is integrated, the multi-task execution capacity of the aircraft is further improved, and the application of the aircraft is greatly expanded.
The split combination of the aircraft relates to the design of a split combination device and a control device, and a powerful flight control program is needed for supporting. In the process of separating the long aircraft from the sub aircraft, due to complex unsteady airflow interference, physical collision between aircrafts can occur, so that separation safety is affected. Prior application (2022106735928) discloses a split flying wing layout unmanned aerial vehicle wherein, to ensure that the combined aircraft can be stably connected, the number of prior sub-aircraft separation mechanism arrangements is excessive, parts are more and less compact, resulting in excessive mass and reduced payload of the aircraft; in addition, there is still high uncertainty, if the manufacturing precision does not reach the prescribed tolerance, the installation is difficult; the guide rail slide block adopts a non-standard component, and the replacement is difficult after the parts are damaged.
Therefore, there is a need to solve the above-mentioned problems.
Disclosure of Invention
The invention aims to: the invention aims to provide a compression spring lock catch spring-open type separating mechanism for a split flying wing layout aircraft, which can effectively limit the relative pitching between a long aircraft and a sub aircraft.
The technical scheme is as follows: in order to achieve the above purpose, the invention discloses a spring lock catch spring type separating mechanism for a split flying wing layout aircraft, which comprises a main machine connecting rod fixedly connected with a main aircraft, a sub machine nested rod detachably connected with the main machine connecting rod and fixedly connected with a sub aircraft, and a sub machine separating mechanism fixedly connected with the sub aircraft and detachably connected with the main machine connecting rod.
The sub-aircraft separation mechanism comprises limiting blocks which are symmetrically arranged at the tail ends of the main engine connecting rods in a penetrating mode, guide rails which are fixedly connected with the sub-aircraft, a central fixing block which is arranged in the middle of the guide rails in a penetrating mode, guide rail sliding blocks which are fixedly connected with the corresponding limiting blocks and can slide inside and outside the guide rails, guide rods which are symmetrically arranged at two sides of the central fixing block, a spring which is arranged on the guide rods in a penetrating mode, one end of the guide rods is abutted to the limiting blocks, the other end of the guide rods is abutted to the central fixing blocks, and a constraint component which is used for locking the positions of the limiting blocks and compressing the spring, wherein the constraint component releases limiting constraint on the limiting blocks, the limiting blocks move towards the outer sides of the guide rails together under the action of resilience force of the spring, the limiting blocks are separated from the tail ends of the main engine connecting rods, so that the sub-aircraft moves backwards, and after the guide rods are separated from the main engine connecting rods, the sub-aircraft is separated from the main aircraft finally.
The restraining assembly comprises a steering engine fixed on the lower wing surface of the sub-aircraft, a metal rocker arm connected with an output shaft of the steering engine and two bosses located on the metal rocker arm, steering engine connecting holes are formed in the metal rocker arm, the bosses are located on the outer side faces of the limiting blocks respectively and used for clamping the limiting blocks and compressing springs, the steering engine is started to drive the metal rocker arm to rotate, the bosses are separated from the outer side faces of the limiting blocks, and limiting constraint of the limiting blocks is relieved.
Preferably, the main machine connecting rod is symmetrically provided with a front cross rod, a middle cross rod, a rear cross rod and a limit embedded sleeve, wherein the lower wing surface of the main aircraft is provided with a connecting groove for penetrating the front cross rod and the rear cross rod, the rear cross rod of the main machine connecting rod penetrates through the limit block, and the limit embedded sleeve of the main machine connecting rod is in nested connection with the auxiliary machine embedded rod.
Furthermore, the central fixed block is of an inverted concave structure crossing the guide rail, a first positioning hole for connecting the guide rail is formed in the upper surface of a top plate of the central fixed block, a stop part for abutting against the spring is arranged between two side plates at the lower part of the central fixed block, and the guide rods are symmetrically arranged at two sides of the stop part.
Further, a first mounting hole and a second mounting hole used for being fixed on the lower wing surface of the sub-aircraft are arranged at the geometric center of the guide rail, and the first mounting hole of the guide rail is fixedly connected with the first positioning hole of the central fixing block through bolts.
Preferably, the limiting block comprises a baffle plate part used for abutting the spring, a limiting hole formed in the baffle plate part and used for penetrating the host connecting rod, a guide rod connecting hole formed in the baffle plate part and used for penetrating the guide rod, and a connecting part located on the upper part of the baffle plate part and used for being fixed with the guide rail sliding block, wherein a first connecting hole used for connecting the guide rail sliding block is formed in the connecting part.
Furthermore, the guide rail sliding block is provided with a sliding groove matched with the guide rail and a second connecting hole for connecting the limiting block, wherein the second connecting hole is fixedly connected with the first connecting hole of the limiting block through a screw.
Further, the son machine nested rod is a solid cylinder and is positioned in the symmetry plane of the son machine separation mechanism, wherein the lower airfoil surface of the son aircraft is provided with a connecting groove for penetrating the son machine nested rod.
The beneficial effects are that: compared with the prior art, the invention has the following remarkable advantages: firstly, the limit of pitching of a main machine and a sub machine in the sub machine separation process is realized by utilizing the sub machine nested rod, so that the stability of combined flight is further improved; secondly, the sub-aircraft separation mechanism has compact structure, simple structure, high reliability and easy installation, and the effective load of the aircraft is improved; finally, standard parts such as the sliding blocks, the guide rails and the like are adopted in the invention, so that the novel sliding block type sliding block is easy to replace after being damaged, has low manufacturing cost and is convenient to popularize.
Drawings
FIG. 1 is a schematic top view of a combination primary and secondary aircraft of the present invention;
FIG. 2 is a schematic diagram of a connecting rod of a host computer according to the present invention;
FIG. 3 is a schematic diagram of a separation mechanism of a neutron machine according to the present invention;
FIG. 4 is a schematic view of the structure of the guide rail of the present invention;
FIG. 5 is a schematic view of the structure of a rail block according to the present invention;
FIG. 6 is a schematic view of the structure of the central fixing block in the present invention;
FIG. 7 is a schematic view of a stopper according to the present invention;
FIG. 8 is a schematic view of a metallic rocker arm according to the present invention;
FIG. 9 is a schematic diagram showing the connection between the connection rod of the main unit and the separation mechanism of the sub-unit in the present invention;
FIG. 10 is a second schematic diagram of the connection between the connection rod of the main unit and the sub-unit separation mechanism according to the present invention;
FIG. 11 is a schematic diagram of a separation mechanism of a neutron machine according to the present invention.
Detailed Description
The technical scheme of the invention is further described below with reference to the accompanying drawings.
As shown in fig. 1, the spring lock catch flick type separating mechanism for the split flying wing layout aircraft is suitable for separating a main aircraft 3 and a sub aircraft 4, and comprises a main machine connecting rod 1, a sub aircraft separating mechanism 2 and a sub aircraft nesting rod 5, wherein one end of the main machine connecting rod 1 is fixedly connected with a lower wing surface of the main aircraft, the other end of the main machine connecting rod 1 is detachably connected with the sub aircraft separating mechanism 2, and a limiting nesting sleeve 104 of the main machine connecting rod 1 is detachably connected with the sub aircraft nesting rod 5; the sub aircraft nested rod 5 is fixedly connected with the lower airfoil surface of the sub aircraft; the sub-aircraft separation mechanism 2 is fixedly connected with the lower airfoil surface of the sub-aircraft; wherein the main machine connecting rod 1 and the sub machine separating mechanism 2 can be symmetrically arranged in left and right to form 2 groups. And in the flying process, the sub-aircraft separation mechanism 2 and the sub-aircraft nested rod 5 are separated from the main engine connecting rod 1 in sequence, so that the separation of the main aircraft 3 and the sub-aircraft 4 is realized. As shown in fig. 2, the front cross rod 101, the middle cross rod 102, the rear cross rod 103 and the limit embedding sleeve 104 are symmetrically arranged on the main machine connecting rod 1, wherein the lower wing surface of the main aircraft 3 is provided with a connecting groove for penetrating the front cross rod and the rear cross rod, the rear cross rod 103 of the main machine connecting rod 1 is penetrated on the limit block 201 of the sub machine separating mechanism 2, and the limit embedding sleeve 104 of the main machine connecting rod 1 is embedded with the sub machine embedding rod 5.
As shown in fig. 3 and 11, the sub-machine separation mechanism 2 includes a stopper 201, a guide rail 202, a central fixed block 203, a guide rail slider 204, a guide rod 205, a spring 206, and a restraining assembly including a steering engine 207, a metal rocker 208, and a boss 209. As shown in fig. 7, 2 limiting blocks 201 are symmetrically arranged at the tail end of the host connecting rod in a penetrating manner, each limiting block 201 comprises a baffle plate portion 214, limiting holes 215, a guide rod connecting hole 216 and a connecting portion 217, the baffle plate portions 214 and the connecting portions 217 are integrally formed, the baffle plate portions 214 are used for abutting against the springs 206, the limiting holes 215 are formed in the upper portions of the baffle plate portions 214, the limiting holes 215 are used for penetrating the host connecting rod 1, the guide rod connecting holes 216 are formed in the lower portions of the baffle plate portions 214, the guide rod connecting holes 216 are used for penetrating the guide rods 205, the connecting portions 217 are located on the upper portions of the baffle plate portions, the connecting portions 217 are horizontally arranged plates, the connecting portions 217 are used for being fixed with the guide rail sliding blocks 204, first connecting holes 218 used for connecting the guide rail sliding blocks 204 are formed in the connecting portions 217, and the upper surfaces of the connecting portions 217 are attached to the lower surfaces of the guide rail sliding blocks 204. The guide rail slide block 204 is provided with a chute 219 and a second connecting hole 220, the cross section of the guide rail slide block 204 is of a groove type structure, the guide rail 202 is positioned in the chute 219 of the guide rail slide block 204, and the guide rail slide block 204 can slide along the inside and outside of the guide rail 202. As shown in fig. 5, the second connecting hole 220 of the guide rail slider 204 is fixedly connected with the first connecting hole 218 of the stopper 201 through a screw, and the guide rail slider 204 drives the stopper 201 to move along the guide rail 202 when sliding inside and outside the guide rail 202. As shown in fig. 4, the guide rail 202 is provided with a first mounting hole 212 and a second mounting hole 213, the first mounting hole 212 is located at the geometric center of the guide rail 202, and the first mounting hole 212 of the guide rail 202 is fixedly connected with the first positioning hole 210 of the central fixing block 203 through a bolt. The second mounting holes 213 are uniformly distributed on the guide rail 202, and the second mounting holes 213 are fixedly connected with the lower wing surface of the sub-aircraft through bolts and are used for fixing the guide rail 202 on the lower wing surface of the sub-aircraft. As shown in fig. 6, the central fixing block 203 is of an inverted concave structure crossing the guide rail 202, the central fixing block 203 is penetrated in the middle of the guide rail, a first positioning hole 210 for connecting the guide rail is formed on the upper surface of the top plate of the central fixing block 203, the guide rail 202 penetrates through the central fixing block 203, and the first positioning hole 210 of the central fixing block 203 is fixedly connected with a first mounting hole 212 of the guide rail 202 through a bolt. A stop part 211 for abutting against the spring is arranged between two side plates at the lower part of the central fixing block 203, the guide rods 205 are symmetrically arranged at two sides of the stop part 211, the springs 206 are arranged on the guide rods 205 in a penetrating mode, one ends of the springs 206 abut against the limiting blocks, and the other ends of the springs 206 abut against the central fixing block. As shown in fig. 8, the restraint assembly is used for locking the position of the limiting block and compressing the spring, the steering engine 207 is fixed on the lower wing surface of the sub-aircraft, the metal rocker arm 208 is connected with the steering engine output shaft, the metal rocker arm 208 is provided with a steering engine connecting hole 221, two bosses 209 are located on the metal rocker arm, and the bosses 209 are respectively located at the outer side surfaces of the limiting block 201 and are used for clamping the limiting block 201 and compressing the spring. In the initial state, the two bosses 209 respectively and correspondingly abut against the outer sides of the two limiting blocks 201 and compress the springs 206 together with the baffle parts of the limiting blocks, so that the limiting blocks 201 are ensured to be arranged on the host connecting rod 1 in a penetrating way; the steering engine 207 is started to drive the metal rocker arm 208 to rotate, the boss 209 rotates along with the metal rocker arm 208, the boss breaks away from the outer side face of the limiting block 201, limiting constraint of the limiting block 201 is relieved, the limiting block 201 moves towards the outer side of the guide rail 202 together with the guide rail sliding block 204 under the action of resilience force of the spring 206, the limiting block 201 breaks away from the tail end of the main machine connecting rod 1, the sub-aircraft 4 moves backwards, after a certain distance is reached, the sub-aircraft nesting rod 5 breaks away from the limiting nesting sleeve 104 of the main machine connecting rod 1, and the sub-aircraft 4 breaks away from the main aircraft 3, as shown in fig. 9 and 10.
Claims (8)
1. A spring lock catch flick type separating mechanism for a split flying wing layout aircraft is characterized by comprising a main machine connecting rod (1) fixedly connected with a main aircraft (3), a sub machine nesting rod (5) fixedly connected with a sub aircraft (4) and detachably connected with the main machine connecting rod (1) and a sub machine separating mechanism (2) fixedly connected with the sub aircraft (4) and detachably connected with the main machine connecting rod (1),
the sub-aircraft separation mechanism (2) comprises limit blocks (201) which are symmetrically arranged at the tail ends of the main engine connecting rods in a penetrating mode, guide rails (202) which are fixedly connected with the sub-aircraft, a central fixing block (203) which is arranged in the middle of each guide rail in a penetrating mode, guide rail sliding blocks (204) which are fixedly connected with the corresponding limit blocks and can slide inside and outside the guide rails along the guide rails, guide rods (205) which are symmetrically arranged at two sides of the central fixing block, springs (206) which are arranged on the guide rods in a penetrating mode, one ends of the guide rods are abutted to the limit blocks, the other ends of the guide rods are abutted to the central fixing blocks, and constraint components which are used for locking the positions of the limit blocks and compressing the springs, wherein the constraint components are used for releasing limit constraints on the limit blocks, the limit blocks move towards the outer sides of the guide rails together with the guide rail sliding blocks under the action of resilience of the springs, the limit blocks are separated from the tail ends of the main engine connecting rods, so that the sub-aircraft moves backwards, and after the sub-aircraft moves to a certain distance, the sub-aircraft nesting rods are separated from the main engine connecting rods, and finally the sub-aircraft is separated from the main aircraft.
2. The spring latch pop-up release mechanism for a separable flying-wing layout aircraft of claim 1, wherein: the restraining assembly comprises a steering engine (207) fixed on the lower wing surface of the sub-aircraft, a metal rocker arm (208) connected with an output shaft of the steering engine and two bosses (209) positioned on the metal rocker arm, wherein steering engine connecting holes (221) are formed in the metal rocker arm (208), the bosses (209) are respectively positioned at the outer side surfaces of the limiting blocks (201) and used for clamping the limiting blocks (201) and compressing springs, the steering engine (207) is started to drive the metal rocker arm (208) to rotate, and the bosses (209) are separated from the outer side surfaces of the limiting blocks (201) to release limiting constraint of the limiting blocks (201).
3. The spring latch pop-up release mechanism for a separable flying-wing layout aircraft of claim 1, wherein: the utility model discloses a main frame connecting rod, including main frame connecting rod (1), main frame connecting rod (1) is last the symmetry be provided with preceding horizontal pole (101), well horizontal pole (102), back horizontal pole (103) and spacing nested sleeve (104), wherein set up the spread groove that is used for wearing to establish preceding horizontal pole and back horizontal pole on the lower wing face of main frame aircraft (3), main frame connecting rod (1) back horizontal pole (103) wear to establish on stopper (201), spacing nested sleeve (104) and sub-nested pole (5) nested connection of main frame connecting rod (1).
4. The spring latch pop-up release mechanism for a separable flying-wing layout aircraft of claim 1, wherein: the central fixed block (203) is of an inverted concave structure crossing the guide rail (202), a first positioning hole (210) for connecting the guide rail is formed in the upper surface of a top plate of the central fixed block (203), a stop part (211) for abutting against a spring is arranged between two side plates at the lower part of the central fixed block, and guide rods (205) are symmetrically arranged at two sides of the stop part (211).
5. The spring latch pop-up release mechanism for a separable flying-wing layout aircraft as recited in claim 4, wherein: a first mounting hole (212) and a second mounting hole (213) used for being fixed on the lower wing surface of the sub-aircraft are arranged at the geometric center of the guide rail (202), and the first mounting hole (212) of the guide rail is fixedly connected with a first positioning hole (210) of the central fixing block through a bolt.
6. The spring latch pop-up release mechanism for a separable flying-wing layout aircraft of claim 1, wherein: the limiting block (201) comprises a baffle plate part (214) used for abutting the spring, a limiting hole (215) formed in the baffle plate part and used for penetrating the host connecting rod, a guide rod connecting hole (216) formed in the baffle plate part and used for penetrating the guide rod, and a connecting part (217) located on the upper part of the baffle plate part and used for being fixed with the guide rail sliding block, wherein a first connecting hole (218) used for connecting the guide rail sliding block is formed in the connecting part (217).
7. The spring latch pop-up release mechanism for a separable flying-wing layout aircraft as recited in claim 6, wherein: the guide rail sliding block (204) is provided with a sliding groove (219) matched with the guide rail and a second connecting hole (220) for connecting the limiting block, wherein the second connecting hole (220) is fixedly connected with the first connecting hole (218) of the limiting block (201) through a screw.
8. The spring latch pop-up release mechanism for a separable flying-wing layout aircraft of claim 1, wherein: the son machine nested rod (5) is a solid cylinder and is positioned in the symmetry plane of the son machine separation mechanism, wherein a connecting groove for penetrating the son machine nested rod (5) is formed in the lower airfoil surface of the son aircraft (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310221690.2A CN116176840A (en) | 2023-03-09 | 2023-03-09 | Spring lock catch spring-open type separating mechanism for split flying wing layout aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310221690.2A CN116176840A (en) | 2023-03-09 | 2023-03-09 | Spring lock catch spring-open type separating mechanism for split flying wing layout aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116176840A true CN116176840A (en) | 2023-05-30 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310221690.2A Pending CN116176840A (en) | 2023-03-09 | 2023-03-09 | Spring lock catch spring-open type separating mechanism for split flying wing layout aircraft |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116588371A (en) * | 2023-07-11 | 2023-08-15 | 西安君晖航空科技有限公司 | Patrol aircraft separation guiding device and patrol aircraft assembly |
-
2023
- 2023-03-09 CN CN202310221690.2A patent/CN116176840A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116588371A (en) * | 2023-07-11 | 2023-08-15 | 西安君晖航空科技有限公司 | Patrol aircraft separation guiding device and patrol aircraft assembly |
| CN116588371B (en) * | 2023-07-11 | 2023-09-29 | 西安君晖航空科技有限公司 | Patrol aircraft separation guiding device and patrol aircraft assembly |
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